Combustor for gas turbine engine

Abstract

A combustor for a gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically about the longitudinal centerline, the combustor comprising: a front liner section; and an aft liner section disposed downstream of the forward liner section with respect to a direction of flow through the combustor, the forward liner section and the aft liner section at least partially defining a combustion chamber, where the forward liner section and the aft liner section are coupled together at a movable interface.

Description

[0001] This application is a divisional application of the invention patent application with application number: 202210629513.3 filed on June 1, 2022 and invention name: "Burner for a gas turbine engine". Technical Field

[0002] The present disclosure relates generally to gas turbine engines and, more particularly, to combustors for gas turbine engines. Background Art

[0003] A gas turbine engine generally includes a compressor section, a combustion section, and a turbine section. More specifically, the compressor section gradually increases the pressure of the air entering the gas turbine engine and supplies the compressed air to the combustion section. The compressed air and fuel are mixed and burned in the combustion section to generate high-pressure and high-temperature combustion gases. The combustion gases flow through the turbine section before leaving the engine. In this regard, the turbine section converts the energy from the combustion gases into rotational mechanical energy. This mechanical energy is in turn used to rotate one or more shafts that drive the compressor section and / or fan assembly of the gas turbine engine.

[0004] Generally, the combustor section includes an annular combustor. Each combustor includes an inner liner, an outer liner and a plurality of fuel nozzles. Specifically, the inner liner and the outer liner define a combustion chamber therebetween. Therefore, the fuel nozzle supplies a fuel and air mixture to the combustion chamber for combustion therein to generate combustion gases.

[0005] In some configurations, the inner liner and / or the outer liner define a plurality of dilution holes positioned downstream of the fuel nozzle. The dilution holes in turn supply additional air to the combustion chamber to mix with the combustion products from the primary zone of the combustion chamber and quickly complete the combustion process, thereby reducing NO x (Nitrogen oxide) emissions. However, such dilution holes may not provide the desired amount of mixing with the combustion gases.

[0006] Therefore, improved combustors for gas turbine engines would be welcome in the art. Summary of the invention

[0007] Aspects and advantages of the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the present disclosure.

[0008] In one aspect, the present subject matter is directed to a combustor for a gas turbine engine. The gas turbine engine further defines a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a forward liner segment; and an aft liner segment disposed downstream of the forward liner segment relative to a flow direction through the combustor, the forward liner segment and the aft liner segment at least partially defining a combustion chamber, wherein the forward liner segment and the aft liner segment are coupled together at a movable interface.

[0009] In another aspect, the present subject matter is directed to a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a front liner segment; an aft liner segment, the aft liner segment disposed downstream of the front liner segment relative to a flow direction through the combustor, the front liner segment and the aft liner segment at least partially defining a combustion chamber; and an intermediate member, the intermediate member disposed longitudinally between the front liner and the aft liner, the intermediate member being configured to form a movable interface with at least one of the front liner segment and the aft liner segment.

[0010] These and other features, aspects and advantages of the present disclosure will become better understood with reference to the following description and appended claims.The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present disclosure and, together with the description, serve to explain the principles of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] In the specification with reference to the accompanying drawings, a complete and enabling disclosure of the preferred embodiments including the best mode thereof is set forth to those skilled in the art, wherein:

[0012] Figure 1 is a schematic cross-sectional view of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0013] Figure 2 is a cross-sectional side view of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0014] Figure 3 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0015] Figure 4 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0016] Figure 5 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0017] Figure 6 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0018] Figure 7 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0019] Figure 8 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0020] Fig. 9 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0021] Fig.10 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0022] Fig.11 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0023] Fig.12 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0024] Fig.13 According to an exemplary embodiment of the present disclosure, Fig.11 A view of the spade interface of the outer lining as seen from line AA;

[0025] Fig.14 According to an exemplary embodiment of the present disclosure, Fig.11 A view of the spade interface of the outer lining as seen from line AA;

[0026] Fig.15 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0027] Fig.16 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0028] Fig.17 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0029] Fig.18 As seen in box B according to an exemplary embodiment of the present disclosure Fig.17 A magnified view of the outer lining;

[0030] Fig.19 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0031] Fig. 20 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0032] Fig.21 is a cross-sectional view of an outer liner of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0033] Fig. 22 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0034] Fig.23 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0035] Fig.24 is a partial perspective view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0036] Fig.25 is a partial enlarged perspective view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0037] Fig.26 is a partial perspective view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0038] Fig. 27 is a partial enlarged perspective view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0039] Fig.28 is a longitudinal front view of a piston seal according to an exemplary embodiment of the present disclosure;

[0040] Fig.29 is a partial perspective view of a piston seal according to an exemplary embodiment of the present disclosure.

[0041] Fig.30 is a partially cutaway perspective view of a gas turbine engine according to an exemplary embodiment of the present disclosure.

[0042] Fig.31 According to an exemplary embodiment of the present disclosure Fig.30 An enlarged partially cutaway perspective view of a gas turbine engine.

[0043] Fig.32 is a cross-sectional view of a spoke and annular support ring of an intermediate member coupled to an arm of a casing of a gas turbine engine according to an embodiment;

[0044] Fig.33 is a cross-sectional view of a spoke and annular support ring of an intermediate member coupled to an arm of a casing of a gas turbine engine according to an embodiment;

[0045] Fig.34 is a partially cutaway cross-sectional view of an outer liner, an intermediate member, and a support of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0046] Fig.35 is a partially cutaway cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0047] Fig.36 is a perspective view of an intermediate member according to an exemplary embodiment of the present disclosure;

[0048] Fig.37 is a partially cutaway cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0049] Fig.38 is a partially cut-away cross-sectional view of a free-floating intermediate member according to an exemplary embodiment of the present disclosure;

[0050] Fig.39 is a partially cut-away cross-sectional view of a free-floating intermediate member according to an exemplary embodiment of the present disclosure;

[0051] Fig.40 is a partially cut-away cross-sectional view of a free-floating intermediate member according to an exemplary embodiment of the present disclosure;

[0052] Fig.41 is a partially cut-away cross-sectional view of a free-floating intermediate member according to an exemplary embodiment of the present disclosure;

[0053] Fig.42 is a partially cut-away cross-sectional view of a free-floating intermediate member according to an exemplary embodiment of the present disclosure;

[0054] Fig.43 is a partially cut-away cross-sectional view of a free-floating intermediate member according to an exemplary embodiment of the present disclosure;

[0055] Fig.44 is an enlarged cross-sectional view illustrating force transmitted through an intermediate member according to an exemplary embodiment of the present disclosure.

[0056] Fig.45 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0057] Fig.46 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0058] Fig.47 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0059] Fig.48 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0060] Fig.49 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0061] Fig.50 is a cross-sectional view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0062] Fig.51 is a cross-sectional view of an outer liner and fence of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0063] Fig.52 is a cross-sectional view of an outer liner and fence of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0064] Fig.53 is a radial view of an outer liner and fence of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0065] Fig.54 is a partial cross-section of a segment of a fence having a fastener coupling the segment to an outer liner of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0066] Fig.55 is a longitudinal view of a fence including a plurality of segments according to an exemplary embodiment of the present disclosure;

[0067] Fig.56is a side view of a fence including a plurality of segments according to an exemplary embodiment of the present disclosure;

[0068] Fig.57 is a radial view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0069] Fig.58 It is like Fig.57 The lines in CC see Fig.57 a cross-sectional view of an outer lining and an intermediate member;

[0070] Fig.59 It is like Fig.58 The line DD sees Fig.58 a cross-sectional view of a portion of an intermediate member;

[0071] Fig.60 is a partial cross-section of a segment of a fence having a fastener coupling the segment to an outer liner of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0072] Fig.61 is a longitudinal view of a fence including a plurality of segments according to an exemplary embodiment of the present disclosure;

[0073] Fig.62 is a side view of a fence including a plurality of segments according to an exemplary embodiment of the present disclosure;

[0074] Fig.63 is a radial view of an outer liner and an intermediate member of a combustion section of a gas turbine engine according to an exemplary embodiment of the present disclosure;

[0075] Fig.64 It is like Fig.63 The lines in CC see Fig.57 a cross-sectional view of an outer liner and an intermediate member;

[0076] Fig.65 It is like Fig.64 The line DD sees Fig.58 a cross-sectional view of a portion of an intermediate member;

[0077] Fig.66 It is like Fig.63 The lines in CC see Fig.57 a cross-sectional view of an outer liner and an intermediate member;

[0078] Fig.67 It is like Fig.63 The lines in CC see Fig.57 a cross-sectional view of an outer lining and an intermediate member;

[0079] Fig.68 It is like Fig.63 The lines in CC see Fig.57 a cross-sectional view of an outer lining and an intermediate member;

[0080] Fig.69 It is like Fig.63 The lines in CC see Fig.57 a cross-sectional view of an outer lining and an intermediate member;

[0081] Fig.70 is a cross-sectional view of an outer liner and an intermediate member according to an embodiment;

[0082] Fig.71 is a cross-sectional view of an outer liner and an intermediate member according to another embodiment;

[0083] Fig.72 is a cross-sectional view of an outer liner and an intermediate member according to another embodiment;

[0084] Fig.73 It is like Fig.71 A cross-sectional view of the outer lining and the intermediate member as seen through line BB in FIG.

[0085] Fig.74 is a cross-sectional view of an outer liner according to another embodiment;

[0086] Fig.75 is a cross-sectional view of an outer liner and a staged interface for introducing dilution air into a combustion chamber according to another embodiment;

[0087] Fig.76 is a cross-sectional view of an outer liner and a staged interface for introducing dilution air into a combustion chamber according to another embodiment;

[0088] Fig.77 is a cross-sectional view of an outer liner and a staged interface for introducing dilution air into a combustion chamber according to another embodiment;

[0089] Fig.78 is a cross-sectional view of an outer liner and a staged interface for introducing dilution air into a combustion chamber according to another embodiment;

[0090] Fig.79 is a cross-sectional view of an outer liner and a staged interface for introducing dilution air into a combustion chamber according to another embodiment; and

[0091] Fig.80 is a cross-sectional view of an outer liner and a staged interface for introducing dilution air into a combustion chamber according to another embodiment.

[0092] Repeat use of reference characters in the present specification and drawings is intended to represent the same or analogous features or elements of the present disclosure. DETAILED DESCRIPTION

[0093] Reference will now be made in detail to exemplary embodiments of the presently disclosed subject matter, one or more examples of which are illustrated in the accompanying drawings. Each example is provided in an illustrative manner and should not be construed as limiting the present disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made in the present disclosure without departing from the scope or spirit of the present disclosure. For example, a feature shown or described as part of one embodiment may be used together with another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to encompass these modifications and variations that fall within the scope of the appended claims and their equivalents.

[0094] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0095] In addition, the terms "upstream" and "downstream" refer to relative directions relative to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction to which the fluid flows.

[0096] In addition, the terms "low", "high" or their respective comparatives (e.g., lower, higher, where applicable) each refer to a relative speed within the engine, unless otherwise specified. For example, a "low-pressure turbine" operates at a pressure that is substantially lower than a "high-pressure turbine". Alternatively, the above terms may be understood as their highest level, unless otherwise specified. For example, a "low-pressure turbine" may refer to the lowest maximum pressure turbine within a turbine section, and a "high-pressure turbine" may refer to the highest maximum pressure turbine within a turbine section.

[0097] In general, the present subject matter is directed to a combustor for a gas turbine engine. As described in more detail below, the combustor may include a front liner segment and a rear liner segment positioned downstream of the front liner segment. In this regard, the front liner segment and the rear liner segment at least partially define a combustion chamber in which a fuel and air mixture is burned to generate combustion gases. The interface formed between the front liner segment and the rear liner segment may be movable to allow a controlled cooling medium flow path at a dilution slot positioned therebetween. The movable interface may include any non-rigid connection formed between the front liner and the rear liner. For example, the movable interface may include a sliding interface formed between an extension of at least one of the front liner segment or the rear liner segment and another of at least one of the front liner segment or the rear liner segment. As a non-limiting example, the movable interface may be configured to absorb deflections caused, for example, by thermal loading during operation.

[0098] The combustor may include one or more dilution slots positioned between the front liner or the rear liner along the longitudinal centerline of the engine. In an embodiment, the dilution slots may be spaced apart from each other along the circumferential direction of the engine. In one or more embodiments, the dilution slots may be longer in the circumferential direction than in the longitudinal direction (e.g., at least three times longer). Thus, unlike conventional combustors that provide discrete streams of dilution air to the combustion chamber, the dilution slots disclosed herein provide an annular ring of dilution air to the combustion chamber. This annular ring of dilution air, in turn, reduces the formation of hot spots within the combustion chamber, thereby allowing NO x Greater reduction in emissions.

[0099] Additionally, in some embodiments, the burner includes a fence positioned adjacent to the dilution slot. More specifically, the fence can extend into the combustion chamber in a radial direction. Thus, the fence directs dilution air entering the combustion chamber via the dilution slot toward the center of the combustion chamber. Furthermore, the fence increases turbulence within the combustion chamber. In this regard, the fence provides faster and more uniform mixing of the dilution air and the burner gases, thereby further reducing NO x emission.

[0100] Now referring to the accompanying drawings, Figure 1 is a schematic cross-sectional view of one embodiment of a gas turbine engine 10. In the illustrated embodiment, the engine 10 is configured as a high bypass turbofan engine. However, in alternative embodiments, the engine 10 may be configured as a propeller engine, a turbojet engine, a turboprop engine, a turboshaft gas turbine engine, or any other suitable type of gas turbine engine.

[0101] like Figure 1 As shown, the engine 10 defines a longitudinal direction L, a radial direction R, and a circumferential direction C. Generally, the longitudinal direction L extends parallel to a longitudinal centerline 12 of the engine 10 , the radial direction R extends orthogonally outward from the longitudinal centerline 12 , and the circumferential direction C extends generally concentrically about the longitudinal centerline 12 .

[0102] In general, the engine 10 includes a fan 14, a low pressure (LP) spool 16, and a high pressure (HP) spool 18 at least partially enclosed by an annular nacelle 20. More specifically, the fan 14 may include a fan rotor 22 and a plurality of fan blades 24 (one shown) coupled to the fan rotor 22. In this regard, the fan blades 24 are spaced apart from one another in a circumferential direction C and extend outwardly from the fan rotor 22 in a radial direction R. In addition, the LP and HP spools 16, 18 are positioned downstream of the fan 14 along the longitudinal centerline 12 (i.e., in the longitudinal direction L). As shown, the LP spool 16 is rotatably coupled to the fan rotor 22, thereby allowing the LP spool 16 to rotate the fan 14. In addition, a plurality of outlet guide vanes or struts 26 spaced apart from one another in the circumferential direction C extend between a casing 28 surrounding the LP and HP spools 16, 18 and the nacelle 20 in a radial direction R. Thus, the struts 26 support the nacelle 20 relative to the outer shell 28 such that the outer shell 28 and the nacelle 20 define a bypass airflow passage 30 positioned therebetween.

[0103] The casing 28 generally surrounds or encloses the compressor section 32, the combustion section 34, the turbine section 36, and the exhaust section 38 in a serial flow order. For example, in some embodiments, the compressor section 32 may include a low pressure (LP) compressor 40 of the LP spool 16 and a high pressure (HP) compressor 42 of the HP spool 18 positioned downstream of the LP compressor 40 along the longitudinal centerline 12. Each compressor 40, 42 may in turn include one or more rows of stator vanes 44 interdigitated with one or more rows of compressor rotor blades 46. Further, in some embodiments, the turbine section 36 includes a high pressure (HP) turbine 48 of the HP spool 18 and a low pressure (LP) turbine 50 of the LP spool 16 positioned downstream of the HP turbine 48 along the longitudinal centerline 12. Each turbine 48, 50 may in turn include one or more rows of stator vanes 52 interdigitated with one or more rows of turbine rotor blades 54.

[0104] In addition, the LP spool 16 includes a low pressure (LP) shaft 56, and the HP spool 18 includes a high pressure (HP) shaft 58 that is concentrically positioned about the LP shaft 56. In this embodiment, the HP shaft 58 rotatably couples the rotor blades 54 of the HP turbine 48 and the rotor blades 46 of the HP compressor 42, such that rotation of the HP turbine rotor blades 54 rotatably drives the HP compressor rotor blades 46. As shown, the LP shaft 56 is directly coupled to the rotor blades 54 of the LP turbine 50 and the rotor blades 46 of the LP compressor 40. In addition, the LP shaft 56 is coupled to the fan 14 via a gearbox 60. In this regard, rotation of the LP turbine rotor blades 54 rotatably drives the LP compressor rotor blades 46 and the fan blades 24.

[0105] In several embodiments, the engine 10 can generate thrust to propel an aircraft. More specifically, during operation, air 62 enters an inlet portion 64 of the engine 10. The fan 14 supplies a first portion of the air 62 (indicated by arrow 66) to the bypass airflow passage 30, and supplies a second portion of the air 62 (indicated by arrow 68) to the compressor section 32. The second portion 68 of the air 62 first flows through the LP compressor 40, where the rotor blades 46 therein gradually compress the second portion 68 of the air 62. Next, the second portion 68 of the air 62 flows through the HP compressor 42, where the rotor blades 46 therein continue to gradually compress the second portion 68 of the air 62. The compressed second portion 68 of the air 62 is then delivered to the combustion section 34. In the combustion section 34, the second portion 68 of the air 62 is mixed with fuel and combusted to generate high temperature and high pressure combustion gases 70. Thereafter, the combustion gases 70 flow through the HP turbine 48, where the HP turbine rotor blades 54 extract a first portion of kinetic and / or thermal energy therefrom. This energy extraction causes the HP shaft 58 to rotate, thereby driving the HP compressor 42. The combustion gases 70 then flow through the LP turbine 50, where the LP turbine rotor blades 54 extract a second portion of kinetic and / or thermal energy therefrom. This energy extraction causes the LP shaft 56 to rotate, thereby driving the LP compressor 40 and the fan 14 via the gearbox 60. The combustion gases 70 then exit the engine 10 through the exhaust section 38.

[0106] exist Figure 1 The configuration of the above-described gas turbine engine 10 shown in FIG. 1 is provided only to place the present subject matter in an exemplary field of use. Therefore, the present subject matter can be readily adapted to any manner of gas turbine engine configuration, including other types of aviation-based gas turbine engines, marine-based gas turbine engines, and / or land-based / industrial gas turbine engines.

[0107] Figure 2is a cross-sectional view of one embodiment of a combustion section 34 of a gas turbine engine 10. As shown, the combustion section 34 includes an annular combustor 100. The combustor 100, in turn, includes an inner liner 102 and an outer liner 104, with the outer liner 104 being positioned outboard of the inner liner 102 in a radial direction R. In this regard, the inner liner 102 and the outer liner 104 define a combustion chamber 106 therebetween. Each liner 102, 104, in turn, includes a front liner segment 108 and an aft liner segment 110, with the aft liner segment 110 being positioned downstream of the front liner segment 108 relative to the flow direction of the combustion gases 70 through the combustor 100. In some cases, the front liner segment 108 and the aft liner segment 110 may form a single outer liner 104. That is, the front liner segment 108 and the aft liner segment 110 may each be part of a single discrete element. In addition, the combustor 100 includes one or more fuel nozzles 112 that supply a mixture of fuel and air 68 to the combustion chamber 106. The fuel and air mixture is combusted within the combustion chamber 106 to generate the combustion gases 70. Figure 2 A single annular combustor 100 is shown, but in other embodiments, the combustion section 34 may include multiple combustors 100 .

[0108] In several embodiments, the combustor 100 includes one or more dilution slots 114 and / or one or more fences 116 positioned adjacent to the dilution slots 114. As described below, the dilution slots 114 allow dilution air to enter the combustion chamber 106 during operation, which reduces NOx emissions from the engine 10. x In addition, as described below, fence 116 directs dilution air toward the center of combustion chamber 106 and increases turbulence within combustion chamber 106, thereby further reducing NO emissions from engine 10. x As shown, in the illustrated embodiment, the combustor 100 includes a dilution slot 114 positioned between the front liner segment 108 and the rear liner segment 110 of the inner liner 102, and another dilution slot 114 positioned between the front liner segment 108 and the rear liner segment 110 of the outer liner 104. In addition, in the illustrated embodiment, the combustor 100 includes a fence 116 extending outward from the inner liner 102 in the radial direction R and another fence 116 extending inward from the outer liner 104 in the radial direction R. The fence 116 can define an annular body that can extend continuously in the circumferential direction. In alternative embodiments, the combustor 100 may include any other suitable number of dilution slots 114 and / or fences 116.

[0109] Additionally, in several embodiments, the combustion section 34 includes a compressor discharge casing 118. In such embodiments, the compressor discharge casing 118 at least partially surrounds or otherwise encloses the combustor 100 in a circumferential direction C. In this regard, a compressor discharge plenum 120 is defined between the compressor discharge casing 118 and the liners 102, 104. The compressor discharge plenum 120, in turn, is configured to supply compressed air to the combustor 100. Specifically, as shown, the air 68 exiting the HP compressor 42 is directed into the compressor discharge plenum 120 by the inlet guide vanes 122. The air 68 within the compressor discharge plenum 120 is then supplied to the combustion chamber 106 of the combustor 100 through the fuel nozzles 112 for combustion of the fuel.

[0110] Figure 3 A cross-sectional view of an outer liner 104 according to an exemplary embodiment of the present disclosure is shown. It should be understood that although reference is made below to the outer liner 104, in other embodiments, one or more features described herein may be incorporated into the inner liner 102 or both the inner liner 102 and the outer liner 104.

[0111] In an embodiment, the outer liner 104 may define a loop feature 124 disposed between the front liner segment 108 and the rear liner segment 110. The loop feature 124 may include a portion of the outer liner 104 that is curved to form an airflow feature configured to affect airflow in the combustion chamber 106. As an example, the loop feature 124 may include multiple portions with curves therebetween. For example, Figure 3 As shown, the loop feature 124 may include a first portion 121, a second portion 123, a third portion 125, and a fourth portion 127. In some cases, the first, second, third, and fourth portions 121, 123, 125, and 127 may be integral with each other and separated by a bend in the outer liner 104. In other cases, at least one of the first, second, third, and fourth portions 121, 123, 125, and 127 may include a discrete component attached to the outer liner 104.

[0112] The loop feature 124 may extend in the longitudinal direction. The loop feature 124 may be formed by portions 121, 123, and 125. The first portion 121 may extend substantially parallel to the third portion 125 (e.g., within ±30 degrees of parallel, such as within ±15 degrees of parallel) along the longitudinal direction. In an embodiment, the first portion 121 and the third portion 125 may be angularly offset from each other by a relative angle. The first portion 121 and the third portion 125 may be joined together by the second portion 123. Figure 31 , the second portion 123 may be disposed upstream (in the longitudinal direction) of the dilution slot 114. In another embodiment, the second portion 123 may be disposed downstream of the dilution slot 114. In this regard, the loop feature 124 may extend longitudinally relative to the dilution slot 114. In other embodiments, the loop feature 124 may extend in a radial direction in addition or alternatively. In this manner, the loop feature 124 may extend away from the combustion chamber 106 so as to capture the airflow passing through the combustion chamber 106 and redirect it into the combustion chamber 106.

[0113] Figure 3 The loop feature 124 depicted in the figure is exemplary only. The loop feature 124 may include a fewer or greater number of portions. In addition, in some cases, at least one pair of adjacent portions (e.g., the second and third portions 123 and 125) may be joined together between the front liner segment 108 and the rear liner segment 110 by a connection interface (e.g., a weld). The loop feature 124 may deviate from the shape of the adjacent outer liner 104. For example, the loop feature 124 may extend from an adjacent portion of the outer liner 104 in a radial direction, a longitudinal direction, or both radial and longitudinal directions.

[0114] At least a portion of the loop feature 124 may extend in a direction away from the outer liner 104 in a direction generally radially outward from the longitudinal centerline 12 of the engine 10. The loop feature 124 may be disposed at or adjacent to the dilution slot 114. In certain embodiments, a straight line extending in a radial direction from the longitudinal centerline 12 may intersect both the dilution slot 114 and the loop feature 124.

[0115] In the illustrated embodiment, the loop feature 124 is integral with the front liner segment 108 and the rear liner segment 110. That is, the loop feature 124, the front liner segment 108, and the rear liner segment 110 may be formed from a single piece. The loop feature 124 may be formed into the outer liner 104, for example, by bending a portion of the liner material at one or more locations, such as at two or more locations, such as at three or more locations, such as at four or more locations, such as at five or more locations, such as at six or more locations, such as at seven or more locations, such as at eight or more locations. In some cases, the loop feature 124 may extend continuously around the combustor 100. In a particular embodiment, the loop feature 124 may define a constant or substantially constant cross-sectional shape or size at all circumferential locations of the combustor 100. In another embodiment, the loop feature 124 may extend continuously around the combustor 100 while having a variable cross-sectional shape or size. In other cases, the loop feature 124 may not be continuous around the combustor 100. That is, the loop feature 124 may include loop feature segments that are spaced apart from each other in the circumferential direction. In this regard, the loop feature 124 may only provide airflow benefits at specific locations along the combustor 100.

[0116] The loop features 124 may provide several advantageous performance and emissions benefits, including increased aerodynamic performance of the engine 10, reduced NO X Emissions, and increase the durability and operating life of the outer liner 104. In an embodiment, the loop feature 124 may define one or more windows 138 extending through the loop feature 124. In the illustrated embodiment, the loop feature 124 includes two windows 138, a front window and a radially outer window. In other embodiments, from a cross-section, the loop feature 124 may include at least three windows, such as at least four windows, such as at least five windows. The relative size of the window 138 may vary with the window. For example, the front window may have a smaller air size than the radially outer window. Alternatively, the front window may have a larger air size than the radially outer window. In addition, in some embodiments, at least one of the front window and the radially outer window may include a plurality of windows, for example, arranged in one or more rows around the circumference of the combustor 100.

[0117] The size of the window 138 relative to the dilution slot 114 may vary. For example, the dilution slot 114 may define an area A measured in the circumferential and longitudinal directions. DS The window 138 may define a total area A measured in the circumferential, longitudinal, and radial directions. W In an embodiment, A W Can be greater than A DS For example, A W Can be in 2A DS and 20ADS In the range of 4A DS and 15A DS In the range of 6A DS and 10A DS In another embodiment, A W Can be smaller than A DS At this point, A W The flow of the cooling medium through the dilution slot 114 may be metered. In some cases, the number of windows 138 may vary relative to the number of fuel nozzles 112 in the engine 10. In an embodiment, the ratio of windows 138 to fuel nozzles 112 [windows:fuel nozzles] may be in the range of 1:5 and 2:1.

[0118] In an embodiment, the fence 116 may be part of the loop feature 124. The fence 116 may extend radially inward toward the center (core) of the combustion chamber 106. In an embodiment, the fence 116 may be disposed downstream of at least one window 138, such as downstream of all windows 138. The cooling medium that enters the loop feature 124 through the window 138 may be directed by the fence 116 to penetrate deeper into the combustion chamber 106. As used herein, a "cooling medium" may include a fluid, such as a gas (e.g., air). The cooling medium may include ambient air passing through the gas turbine engine 10. The cooling medium may define a temperature that is substantially lower than the operating temperature of the combustion chamber 106. In this manner, the cooling medium may cool the combustion chamber 106. Cooling of the combustion chamber 106, particularly cooling at an area near the outer liner 104, may increase engine performance and efficiency. In addition, cooling of the combustion chamber 106 may reduce NO X emission.

[0119] In an embodiment, the fence 116 of the loop feature 124 may define one or more internal cooling holes 129 configured to discharge the cooling medium to a location 131 behind the fence 116 to reduce NO at the location 131. X In the illustrated embodiment, the fence 116 includes a curved segment of the loop feature 124 that defines the groove 107. The cooling holes 129 of the fence 116 can be in fluid communication with the groove 107 so that air entering the groove 107 passes through the cooling holes 129. In an embodiment, at least some of the cooling holes 129 can be arranged along the longitudinal surface of the groove 107 (such as Figure 3 In another embodiment, at least some of the cooling holes 129 may be disposed along the bottom 109 of the groove 107 (see, e.g. Fig.21 ).

[0120] The cooling holes 129 may be arranged in one or more rows extending continuously or discontinuously around the circumference of the combustor 100. In some cases, the cooling holes 129 may be arranged relative to the longitudinal centerline 12 ( Figure 1 ). For example, the cooling holes 129 can be tilted at a relative angle of at least 1°, such as at least 10°, such as at least 15°, such as at least 20°, relative to the longitudinal centerline 12. In this way, the flow path of the cooling medium can be controlled and directed to a desired location.

[0121] In an embodiment, the outer liner 104 may further include one or more cooling holes extending from the outer surface 126 of the outer liner 104 through the outer liner 104 and spaced apart from the loop feature 124. The cooling holes may include, for example, a first group of cooling holes 128 and a second group of cooling holes 130, the first group of cooling holes 128 being disposed upstream of the loop feature 124, and the second group of cooling holes 130 being disposed downstream of the loop feature 124. In an embodiment, at least one of the first group of cooling holes 128 or the second group of cooling holes 130 may include at least one row of cooling holes, such as at least two rows of cooling holes, such as at least three rows of cooling holes, such as at least four rows of cooling holes, such as at least five rows of cooling holes, such as at least six rows of cooling holes, such as at least seven rows of cooling holes. In the illustrated embodiment, the first group of cooling holes 128 includes seven rows of cooling holes, and the second group of cooling holes 130 includes four rows of cooling holes. The number of cooling holes of the first group of cooling holes 128 and the second group of cooling holes 130 may be the same as or different from each other. In some cases, the rows of cooling holes in the first group of cooling holes 128 or the second group of cooling holes 130 may be staggered.

[0122] In some cases, the cooling holes may be angled relative to the outer surface 126 of the outer liner 104. For example, Figure 3As shown, at least one cooling hole in the first group of cooling holes 128 or the second group of cooling holes 130 may have a centerline 132 that is angularly offset from a plane 134 by an angle α, and the plane 134 is oriented to be tangent to the outer surface 126 of the outer liner 104 at the inlet 136 of the cooling hole. As a non-limiting example, α may be at least 1°, such as at least 5°, such as at least 15°, such as at least 30°, such as at least 45°. In some cases, the offset angle of the cooling hole may vary, that is, at least two cooling holes have different angular offsets compared to each other. As an example, the first group of cooling holes 128 may define a first angular offset that is different from the angular offset of the second group of cooling holes 130. In another embodiment, at least two cooling holes within the first group of cooling holes 128 may have different angular offsets compared to each other. In a further embodiment, at least two cooling holes within the second group of cooling holes 130 may have different angular offsets compared to each other. The cooling holes may introduce a cooling medium through the outer liner 104, thereby reducing the possibility of overheating.

[0123] Figure 4 Another embodiment of an outer liner 104 including a multi-piece (eg, two-piece) construction is shown. The outer liner 104 includes a disconnected front liner segment 108 and a rear liner segment 110 defining a dilution slot 114 therebetween. Figure 3 Unlike the illustrated embodiment, the front liner segment 108 and the rear liner segment 110 are joined together at or adjacent to the loop feature 124. More specifically, in the illustrated embodiment, the loop feature 124 is formed by the front liner segment 108. The rear liner segment 110 may be coupled to the loop feature 124 at a downstream location. In another embodiment, the loop feature 124 may be a portion of the rear liner segment 110, and the front liner segment 108 may be coupled to the loop feature 124, e.g., upstream of the loop feature 124.

[0124] In the illustrated embodiment, the aft liner segment 110 is coupled to the loop feature 124 at an interface 140. The aft liner segment 110 may be coupled to the loop feature 124 at the interface 140, for example, using brazing techniques, welding, fasteners, etc. The loop feature 124 having a multi-part construction may facilitate easier construction, assembly, or both.

[0125] Figure 5Another embodiment of an outer liner 104 is shown that includes a two-part structure in which the rear liner segment 110 is coupled to the loop feature 124 downstream of the fence. In the illustrated embodiment, the loop feature 124 includes a flange 142 extending in the longitudinal direction. The flange 142 can define a support surface 144 on which the rear liner segment 110 can be supported or even mounted. The flange 142 can be integrally formed as part of the loop feature 124. For example, the flange 142 can be formed by bending the front liner segment 108. In an embodiment, the flange 142 can be part of the fence 116 or extend from the fence 116. Figure 4 Similar to the embodiment shown in , the rear liner segment 110 can be coupled to the loop feature 124 at the interface 140, for example, using brazing techniques, welding, fasteners, etc. However, similar to Figure 4 The embodiment shown is different. Figure 5 In the illustrated embodiment, the interface 140 may occur at or along the flange 142 , or along the flange 142 and the back side of the fence 116 .

[0126] Figure 6 Another embodiment of an outer liner 104 comprising a two-part structure is shown. The outer liner 104 comprises a separate front liner section 108 and a rear liner section 110. Figure 4 and 5 The embodiments shown are different. Figure 6 The loop feature 124 shown in FIG. 1 is formed at least in part by the front liner segment 108 and at least in part by the rear liner segment 110. That is, a portion of the loop feature 124 may be defined by the front liner segment 108, and another portion of the loop feature 124 may be defined by the rear liner segment 110. The front liner segment 108 and the rear liner segment 110 may be joined together at an interface 140 defined within the loop feature 124. For example, Figure 6 The interface 140 depicted in FIG. 1 may be disposed between the two windows 138 along the front end of the loop feature 124. For example, the interface may be formed using brazing techniques, welding, fasteners, etc. Forming the loop feature 124 may occur by bending both the front liner segment 108 and the rear liner segment 110 to form two formed portions that may be joined together to form the loop feature 124. In some cases, the step of joining the two formed portions of the loop feature 124 may be performed prior to installing the outer liner 104. In other cases, the step of joining the two formed portions may be performed in situ on the combustor 100.

[0127] Figures 7 to 10 A cross-sectional view of an outer liner 104 is shown according to other embodiments of the present disclosure.

[0128] Figure 7An embodiment is depicted in which the rear liner segment 110 includes a fence 116 and a loop feature 124. In an embodiment, one or both of the fence 116 or the loop feature 124 can be integral with the rear liner segment 110. Thus, the rear liner segment 110 can be coupled to the front liner segment 108 at an interface 140, which is formed between the loop feature 124 and the front liner segment 108. In some cases, the interface 140 can be a fixed interface. That is, the interface 140 can include a fixed (i.e., non-dynamic) connection between the front liner segment 108 and the rear liner segment 110. For example, the interface 140 can be coupled using brazing techniques, welding, fasteners, etc. In other cases, the interface 140 can be dynamic, such that the loop feature 124 is movable (slidable) relative to the front liner segment 108.

[0129] The loop feature 124 may include one or more of the above-mentioned windows 138. For example, referring to Figure 7 , the loop feature 124 may include two windows 138 spaced apart from each other in the longitudinal direction. Figure 8 , the loop feature 124 may alternatively include a single window 138. In an embodiment, the fence 116 may include a discrete component separate from the loop feature 124, and the discrete component is coupled to the rear liner segment 110. That is, the fence 116 may be connected separately from the rear liner segment 110.

[0130] Fig. 9 and 10 An embodiment of the outer liner 104 is shown in which the loop feature 124 is part of the front liner segment 108. In such an embodiment, the loop feature 124 can extend across the dilution slot 114 and meet the rear liner segment 110 at an interface 140 disposed downstream of the dilution slot 114. In an embodiment, the rear liner segment 110 may include an extension 146 to which the loop feature 124 can be attached. In an embodiment, the extension 146 can extend in a radial direction or a substantially radial direction away from the longitudinal centerline 12. The extension 146 can be disposed at a longitudinal end of the rear liner segment 110. More specifically, the extension 146 can be disposed adjacent to the dilution slot 114. In an embodiment, the extension 146 can be disposed adjacent to the fence 116. In a more specific embodiment, the extension 146 and the fence 116 can be located along substantially the same plane extending in a radial direction. As described with respect to Figure 7 and 8 As mentioned, loop feature 124 may include one or more windows 138 that fluidly couple combustion chamber 106 to a cooling medium that passes through engine 10 outside of combustor 100 . Fig. 9 A loop feature 124 is depicted having two windows 138 spaced apart from one another in the longitudinal direction. Fig.10 A loop feature 124 having a single window 138 is depicted.

[0131] Fig. 9 and 10 The illustrated embodiment includes a first set of cooling holes 128 and a second set of cooling holes 130. In an embodiment, the first set of cooling holes 128 may be arranged to be longitudinally aligned with the one or more windows 138 of the loop feature 124. That is, a straight line extending in a radial direction may intersect both the first set of cooling holes 128 and the one or more windows 138. It should be understood that although shown without cooling holes, Figure 7 and 8 The illustrated embodiment may alternatively include one or more of the first and second sets of cooling holes 128 or 130. In addition, Fig. 9 and 10 The illustrated embodiment may alternatively be formed without one or both of the first and second groups of cooling holes 128 or 130. In some cases, at least the first group of cooling holes 128 may increase the formation of turbulence within the combustion chamber 106, while the dilution slots 114 form a film of dilution air directed into the combustion chamber 106 through the fence 116. Although the cooling medium passing through the cooling holes 128 may be turbulent, the film of dilution air may include a thin layer of less turbulent cooling medium, resulting in deeper penetration into the center (core) of the combustion chamber 106. The upstream turbulence caused by the cooling medium passing through the first group of cooling holes 128 may allow the film of dilution air to penetrate further into the center (core) of the combustion chamber 106.

[0132] Fig.11 An embodiment of an outer liner 104 according to another embodiment is shown. The outer liner 104 includes a scoop interface 148 configured to capture the passing cooling medium and redirect the cooling medium, for example, in a more radial direction, toward the combustion chamber 106. In some cases, the scoop interface 148 can generate an airflow film 150 passing along the fence 116. The formation of the airflow film 150 against the fence 116 can enhance mixing within the combustion chamber 106 by pushing the airflow deeper into the combustion chamber 106.

[0133] In an embodiment, the scooped interface 148 may define a scooped surface 152 against which the airflow film 150 is redirected, such as rotated, toward the combustion chamber 106. The scooped surface 152 may define a curved surface having a minimum radius of curvature within a range of 0.1 mm and 50 mm.

[0134] When the cooling medium enters the combustion chamber 106, the cooling medium may enter the scoop interface 148 through the window 138 and pass through the dilution slot 114. In the illustrated embodiment, the outer liner 104 includes a first group of cooling holes 128. The first group of cooling holes 128 is depicted as having a first cooling hole 154 disposed upstream of the window 138 and a second cooling hole 156 disposed downstream of the window 138. In an embodiment, the first cooling hole 154 may include a plurality of first cooling holes 154 in the first group of cooling holes 128. In another embodiment, the second cooling hole 156 may include a plurality of second cooling holes 156 in the first group of cooling holes 128. In an embodiment, the first and second cooling holes 154 or 156 may individually or together increase the operating life of the outer liner 104.

[0135] In an embodiment, the scoop interface 148 may define an inclined leading edge surface 158. The inclined leading edge surface 158 may be located along a straight line, a curve, or a segmented line. In an embodiment, the inclined leading edge surface 158 may be located along a line 160 or a best fit line that is angularly offset from the radial direction by an angle α. S , angle α S At least 1°, such as at least 5°, such as at least 15°, such as at least 30°, such as at least 45°. The inclination of the leading edge surface 158 can direct the airflow film 150 in a controlled manner to increase the effectiveness of the airflow film 150 along the fence 116.

[0136] Fig.11 The outer liner 104 depicted in FIG. 1 has a one-piece structure. That is, the front liner segment 108 and the rear liner segment 110 are integral with each other. Fig.12 An exemplary embodiment of an outer liner 104 including a shovel-type interface 148 is shown, wherein a front liner segment 108 and a rear liner segment 110 comprise discrete pieces. The front liner segment 108 and the rear liner segment 110 may be joined together at an interface 140. In an embodiment, the interface 140 may define a dynamic (movable) interface, such as a sliding interface, such that the front liner segment 108 and the rear liner segment 110 may move relative to each other. As a non-limiting example, thermal loading occurring during use of the engine 10 may cause one or both of the front liner segment 108 or the rear liner segment 110 to deflect at least in a longitudinal direction. The movable interface 140 may allow the front liner segment 108 and the rear liner segment 110 to move relative to each other at least in a longitudinal direction. Thus, stress accumulation on the outer liner 104 may be reduced. That is, the movable interface 140 may define one or more thermal expansion features configured to accommodate thermally induced stresses. Again referring to Figures 3 to 10, the loop feature 124 can form a thermal expansion feature. When stress is introduced into the outer liner 104 due to thermal expansion, the loop feature 124 can accommodate the relative spatial changes of the outer liner, for example, deflecting to absorb the relative spatial changes of the outer liner. In this way, the loop feature 124 can absorb the deflection caused in another portion of the outer liner 104 or on the entire outer liner 104. This can reduce liner wear and increase operational life. In some cases, the shovel interface 148 (or another arrangement described herein) may not be configured to accommodate such relative spatial changes of the outer liner 104. The use of the movable interface 140 can provide the same or similar benefits by allowing relative movement between the front liner segment 108 and the rear liner segment 110.

[0137] Fig.13 and 14 Shown along Fig.11 AA in FIG. 1 is a view of the spade interface 148 seen in the longitudinal direction. Fig.11 The windows 138 are shown as a row of windows including a plurality of windows 138 extending in a circumferential direction around the outer liner 104 . Fig.13 The plurality of windows 138 depicted in the drawings each share a common shape and size compared to one another. In another embodiment, at least two of the plurality of windows 138 may have a relatively different size or shape compared to one another. Viewed in the longitudinal direction, the windows 138 may have a generally arcuate or rectilinear shape. Exemplary shapes of the windows 138 include polygons such as triangles, squares, pentagons, etc.; arcuate shapes such as circles, ellipses, etc.; alphanumeric shapes; segmented shapes including a plurality of different segments, some of which may be rectilinear and other segments may be arcuate; or any other known shape in the art for passing a fluid between two or more locations. Fig.13 The illustrated embodiment includes a single row of windows 138. At the same time, Fig.14 The illustrated embodiment includes multiple rows of windows 138. More specifically, Fig.14 The embodiment includes two rows of windows 138. However, in other embodiments, the windows 138 may be arranged in at least three rows, such as at least four rows, such as at least five rows, such as at least six rows, etc. Using multiple rows while maintaining the same overall size of the windows 138 in the radial direction may produce a better airflow film 150, which allows a more uniform flow structure to feed the dilution slot 114.

[0138] Fig.15 A view of an outer liner 104 according to another embodiment is shown. In the illustrated embodiment, the front liner segment 108 and the rear liner segment 110 are coupled together at an interface 140 located upstream of the dilution slot 114. The rear liner segment 110 may include one or more windows 138 into the dilution slot 114.

[0139] In the illustrated embodiment, the front liner segment 108 includes a first interface feature 162, and the rear liner segment 110 includes a second interface feature 164, which is configured to interface with the first interface feature 162 at the location of the interface 140. The interface 140 can define a dynamic (e.g., sliding) interface, so that the first interface feature 162 and the second interface feature 164 can move (e.g., slide) relative to each other, such as along the longitudinal axis. As an example, the first interface feature 162 can include an extension 166 extending in the longitudinal direction. The second interface feature 164 can include an extension receiving area 168, which extends in the longitudinal direction and is configured to receive the extension 166. In some cases, the first interface feature 162 and the second interface feature 164 can define a movable interface, so that the front liner segment 108 and the rear liner segment 110 can move relative to each other, such as during thermal deflection.

[0140] The interface 140 between the first interface feature 162 and the second interface feature 164 can be formed, for example, by a press fit. In certain embodiments, one or both of the front and rear liner segments 108 or 110 can be subjected to a thermal differential prior to joining. For example, in an embodiment, one of the front and rear liner segments 108 or 110 can be cooled with liquid nitrogen to allow the first interface feature 162 and the second interface feature 164 to fit together more easily during assembly. In certain embodiments, the use of Fig.15 As with the illustrated embodiment, it is possible to use different materials for the front liner segment 108 and the rear liner segment 110. Exemplary materials include metals, alloys, ceramic matrix composites (CMC), and the like.

[0141] Fig.16 Another embodiment of the outer liner 104 is shown in which it is possible to use different materials for the front liner segment 108 and the rear liner segment 110 while still allowing for relative deformation and deflection therebetween. Fig.16In the illustrated embodiment, at least one of the forward liner segment 108 or the aft liner segment 110 may include a piston seal 170 configured to move relative to the other of the forward liner segment 108 or the aft liner segment 110. For example, the piston seal 170 may include an annular sealing ring configured to extend around the combustor 106 in a circumferential direction. In an embodiment, the piston seal 170 may be disposed in a piston seal receiving area 172 of at least one of the forward liner segment 108 or the aft liner segment 110. The piston seal 170 may protrude from the piston seal receiving area 172 so as to contact the forward liner segment 108 or the aft liner segment 110. In certain embodiments, at least one of the forward liner segment 108 or the aft liner segment 110 may include a stop feature 174 configured to prevent the forward liner segment 108 and the aft liner segment 110 from deflecting beyond a specified limit set by the stop feature 174. In the illustrated embodiment, the stop feature 174 includes a wall that extends parallel or substantially parallel to the fence 116. During deformation, such as caused by thermal expansion, the front liner segment 108 may contact the stop feature 174 to prevent an undesirable reduction in the size of the dilution slot 114.

[0142] In an embodiment, the piston seal 170 can define a sealing interface configured to maintain a fluid seal between the front liner segment 108 and the rear liner segment 110. In another embodiment, the piston seal 170 can maintain a low friction interface between the front liner segment 108 and the rear liner segment 110.

[0143] Fig.17 and 18 An outer liner 104 is shown according to another embodiment. Fig.17 A cross-sectional view of the outer liner 104 is shown. Fig.18 As shown in circle B Fig.17 104 . In the illustrated embodiment, the interface portions of the front liner segment 108 and the rear liner segment 110 are spaced apart in the radial direction by a spacer 176. Similar to the piston seal 170, the spacer 176 can maintain a fluid seal between the front liner segment 108 and the rear liner segment 110. In addition, in some cases, the spacer 176 can maintain a low friction interface between the front liner segment 108 and the rear liner segment 110. The spacer 176 can be configured to deform under load, for example, deform under load presented on the spacer 176 in the radial direction by the front liner segment 108 and the rear liner segment 110. In an embodiment, the spacer 176 can include an annular ring or a segmented annular ring, the segmented annular ring including a plurality of segments that together define an annular ring or a substantially annular ring. The annular ring can define a plurality of lattices, curves, grooves, etc. to absorb radial loads. The annular ring can be made of an elastic material (e.g., spring steel).

[0144] Fig.19 A cross-sectional view of an outer liner 104 according to yet another embodiment is shown. In the depicted embodiment, the front liner segment 108 and the rear liner segment 110 are coupled together at the interface 140 by a swaging process. The resulting outer liner 104 can be coupled to the casing 72 of the gas turbine engine 10. In a more specific embodiment, the rear liner segment 110 can be coupled to the casing 72. In an embodiment, the outer liner 104 can be indirectly coupled to the casing 72, for example, by one or more connecting members 74. In another embodiment, the outer liner 104 can be directly coupled to the casing 72. For example, the outer liner 104 can include an integral member extending to the casing 72 and coupled to the casing 72. In some cases, the outer liner 104 can be removably coupled to the casing 72. For example, the outer liner 104 can be fastened to the casing 72 by one or more fasteners, such as threaded fasteners (not shown).

[0145] Fig. 20 An outer liner 104 is shown according to another embodiment. Figure 1 The outer liner 104 depicted in FIG. 1 includes a fence 116 extending radially through the dilution slot 114 into the combustion chamber 106. The outer liner 104 further includes one or more windows 138 in fluid communication with the dilution slot 114. The interface 140 between the forward liner segment 108 and the aft liner segment 110 is dynamic so as to allow relative movement therebetween. For example, relative movement between the forward liner segment 108 and the aft liner segment 110 may occur when a thermal gradient present on the outer liner 104 causes thermal deflection. As a non-limiting example, the thermal deflection may cause the aft liner segment 110 to move forward or expand forwardly in a longitudinal direction relative to the forward liner segment 108 by a thermal deflection distance D TD In some cases, the interface 140 may include a piston seal, such as described above with respect to Fig.16 In other cases, the interface 140 may include a spacer, such as described above with respect to the piston seal 170. Fig.18 The spacer 176 is described.

[0146] Fig.21 A further embodiment of the outer liner 104 is shown that is configured to absorb relative deflection between the front liner segment 108 and the rear liner segment 110 in at least the longitudinal direction. In the illustrated embodiment, the outer liner 104 further includes a longitudinal interface 178 disposed between the front liner segment 108 and the rear liner segment 110. The longitudinal interface 178 can provide one or more beneficial properties to the interface 40 formed between the front liner segment 108 and the rear liner segment 110. For example, in situations where contact between the front liner segment 108 and the rear liner segment 110 is desired or likely to occur, such as in Fig.21In the embodiment of the present invention, the longitudinal interface 178 can be configured to reduce wear between the front liner segment 108 and the rear liner segment 110. This can be done, for example, by including a wear-resistant coating on one or both of the front liner segment 108 or the rear liner segment 110. In some configurations, the wear-resistant coating can be a material that defines a greater hardness than the material of the rest of the front liner segment 108 or the rear liner segment 110. In the illustrated embodiment, the longitudinally extending protrusion 180 of the front liner segment 108 contacts the longitudinal interface 178 of the rear liner segment 110. The longitudinally extending protrusion 180 and the longitudinal interface 178 can provide a positive stop between the front liner segment 108 and the rear liner segment 110 when deflected in the longitudinal direction due to, for example, thermal growth of the components. This is an example of a size control feature formed by the protrusion 180 and the longitudinal interface 178. Other size control features that control the size of the dilution slot 114 can be used, especially when the front liner segment 108 and the rear liner segment 110 are movable relative to each other in the longitudinal direction. In some embodiments, the size control may be fixed. That is, the size control function may only provide one control function. For example, Fig.21 In the illustrated embodiment, the protrusion 180 has a relatively rigid structure that limits the size control of the dilution slot 114 to the length of the protrusion 180. In one or more embodiments not shown, the size control can be variable. That is, the size control feature can variably control the size of the dilution slot 114. As non-limiting examples, this can include the use of a varying geometry of the longitudinal interface 178, or the use of a movable or deformable protrusion 180 that is configured to provide multiple size controls, such as under varying operating conditions.

[0147] In the illustrated embodiment, the window 138 defines a ratio of, for example, Fig. 20 The exemplary embodiment shown has a larger circumferential dimension of the windows 138. That is, the relative sizes of the windows 138 in the circumferential dimension can vary and are not intended to be limited to the embodiments described herein. For example, in some embodiments, the windows 138 can all have the same relative size or shape. In other embodiments, at least two of the windows 138 can have different relative sizes or shapes compared to each other. As another example, Fig. 20 The illustrated embodiment includes two rows of windows 138, and Fig.21 The illustrated embodiment includes a single row of windows 138. The relative size and shape of the windows 138 may vary depending on design requirements, adjacent engine architecture, etc. For example, as described above with respect to Fig.11 and 12 As described, the use of the scooped interface 148 can shift the dilution air flow further into the combustion chamber 106, which can reduce NO X And increase engine performance.

[0148] In some cases, the above-described longitudinal interface 178 may form a portion of an interface 140 between the front liner segment 108 and the aft liner segment 110. In other cases, the interface 140 may further include a secondary interface, such as a radial interface 182, which is disposed, for example, in a radial direction between the front liner segment 108 and the aft liner segment 110. In the illustrated embodiment, the radial interface 182 is depicted upstream of the dilution slot 114. In embodiments where the front liner segment 108 bridges the gap formed by the dilution slot 114, the radial interface 182 may be disposed downstream of the dilution slot 114. Other arrangements and combinations of the designs and locations of the longitudinal interface 178 and the radial interface 182 are possible.

[0149] The radial interface 182 may include a press-fit interface between the forward liner segment 108 and the aft liner segment 110. In the illustrated embodiment, a press fit is formed between the longitudinal extension 184 of the aft liner segment 110 and the radial outer surface of the forward liner segment 108. In some cases, the radial interface 182 may provide one or more beneficial properties to the interface formed between the forward liner segment 108 and the aft liner segment 110. For example, the radial interface 182 may be configured to reduce wear between the forward liner segment 108 and the aft liner segment 110. This may be done, for example, by including a wear-resistant coating on one or both of the forward liner segment 108 or the aft liner segment 110. In an embodiment, the wear-resistant coating may be further configured to reduce sliding resistance between the forward liner segment 108 and the aft liner segment 110.

[0150] Fig.21 The fence 116 depicted in FIG. 1 includes a curved segment of the aft liner segment 110. The curved segment may define a groove 107 that may extend around at least a portion of the circumference of the aft liner segment 110. The groove 107 may define a bottom 109 that may include a plurality of cooling holes 129 configured to pass a cooling medium into the combustion chamber 106. In some cases, the cooling holes 129 may be configured to pass between approximately 20% and 50% of the total dilution air. The use of the cooling holes 129 may increase air turbulence, which results in better fuel-air mixing. This may reduce NO X The use of the grooves 107 can further help cool at least the frontmost surface of the fence 116. When the cooling medium passes through the cooling holes 129 at or near the bottom 109 of the grooves 107, the cooling medium can pass through the frontmost surface of the fence 116 to provide additional cooling thereto. Additional cooling of the frontmost surface of the fence 116 may be required when the frontmost surface of the fence 116 will experience the highest temperature during operation.

[0151] In some cases, the engine 10 may further include an intermediate member, at least a portion of which is longitudinally disposed between the front liner segment 108 and the rear liner segment 110. The intermediate member may include a discrete component separate from the front liner segment 108 and the rear liner segment 110 that can be freely attached to one or both of the front liner segment 108 and the rear liner segment 110, the engine frame, or the float. Fig. 22 and 23 Two exemplary embodiments of the outer liner 104 including the intermediate member 186 are shown in cross-sectional views. Fig. 22 10, the intermediate member 186 includes a body 188 coupled to at least one of the forward liner segment 108 or the aft liner segment 110, such as both of the forward liner segment 108 or the aft liner segment 110. The body 188 may include an annular body (a single piece or a multi-piece structure) that can extend around the combustion chamber 106. As an example, the body 188 may be coupled to at least one of the forward liner segment 108 or the aft liner segment 110 via a swaged interface. The body 188 may define one or more windows 190 configured to communicate a cooling medium to the dilution slot 114. Fig. 22 The fence 116 depicted in FIG. 1 is integral with the rear liner segment 110 . Fig.23 An embodiment of an intermediate member 186 is depicted in which the fence 116 is integral therewith. That is, the fence 116 is formed by the intermediate member 186. In some cases, only a portion of the fence 116 may be formed by the intermediate member 186. That is, in certain embodiments, the fence 116 may be formed by the intermediate member 186 and one or both of the front liner 108 or the rear liner 110.

[0152] The intermediate member 186 can be formed, for example, using an additive manufacturing process such as 3D printing, machining, forging, casting, stamping, etc., and can include one or more parts attached together by welding, brazing, swaging, bolting, etc. The intermediate member 186 can be single or include multiple pieces coupled together. In some cases, the intermediate member 186 can be at least partially assembled before being operably positioned relative to the outer liner 104. In certain cases, the intermediate member 186 can be fully assembled before being operably positioned relative to the outer liner 104. In yet another case, the intermediate member 186 can be assembled relative to the outer liner 104 at the operating site. For example, the intermediate member 186 can be at least partially assembled while being operably positioned relative to the outer liner 104.

[0153] Fig.24 A perspective cross-sectional view of the outer liner 104 is shown including an intermediate member 186 having an integral fence 116. The body 188 of the intermediate member 186 includes a first engagement feature 192 extending toward the forward liner segment 108 and a second engagement feature 194 extending toward the aft liner segment 110. Fig.24 The body 188 depicted in FIG further includes a connecting member 196 that is configured to extend from the intermediate member 186 to the casing 72 of the gas turbine engine 10. In the illustrated embodiment, the connecting member 196 includes a radial portion 198 extending in a generally radial direction and a longitudinal portion 200 extending in a generally longitudinal direction. In some cases, the longitudinal portion 200 of the connecting member 196 may be engageable with the casing 72. For example, the longitudinal portion 200 may be press-fit with the casing 72 or a structure coupled to the casing 72, fastened to the casing, etc. One or more windows 202 may extend through the connecting member 196 to enable the cooling medium to pass through the intermediate member 186 and prevent all cooling medium from entering the dilution slot 114 into the combustion chamber 106.

[0154] In an embodiment, the intermediate member 186 (or another intermediate member described according to another embodiment of the present invention) can be maintained in a relatively fixed position relative to at least one of the front liner segment 108 or the aft liner segment 110 by, for example, a support member (e.g., a connecting member 196) extending between the intermediate member 186 and the casing 72. As used herein, the intermediate member 186 is maintained in a "relatively fixed position" can refer to a static or substantially static configuration of the intermediate member 186 relative to another feature. That is, the intermediate member 186 can be maintained in a relatively static position relative to one or more of the front liner segment 108, the aft liner segment 110, the casing 72, another element of the gas turbine engine 10, or any combination thereof. In some cases, the static position can be absolutely fixed, such that no relative movement occurs between the intermediate member 186 and the other feature (e.g., the front liner segment 108, the aft liner segment 110, etc.). In other cases, the intermediate member 186 can be relatively static, such that there is substantially no relative movement between the intermediate member 186 and the other feature. With a relatively static engagement, some movement between the intermediate member 186 and other features can be expected, for example, due to vibration frequencies, thermal expansion, and operational stresses. However, when in a relatively fixed position, the intermediate member 186 is generally restrained from moving. It should be understood that the intermediate member 186 may also or alternatively be maintained in a relatively fixed position by a support member that is coupled to another section of the gas turbine engine 10 other than the casing 72.

[0155] Fig.25 Shows Fig.24 A close-up view of the outer liner 104 is shown in FIG. More specifically, Fig.25Sealing portions 204 and 206 of the first and second engagement features 192 and 194, respectively, are shown. The sealing portions 204 and 206 of the intermediate member 186 can interface with the forward liner segment 108 and the aft liner segment 110, respectively. That is, the sealing portion 204 of the first engagement feature 192 can interface with the forward liner segment 108, and the sealing portion 206 of the second engagement feature 194 can interface with the aft liner segment 110. In an embodiment, at least one sealing portion 204 or 206 of the intermediate member 186 can include a multi-seal arrangement such that the sealing portion 204 or 206 contacts the respective liner segments at or along two or more interfaces. Fig.25 In the illustrated embodiment, the sealing portion 206 of the second engagement feature 194 has a multi-seal arrangement, wherein the first sealing interface 208 is disposed along the outside of the rear liner segment 110, and the second sealing interface 210 is disposed along the inside of the rear liner segment 110. The sealing portion 204 of the first engagement feature 192 has a single seal arrangement, wherein the sealing interface 212 is disposed along the outside of the front liner segment 108. In an embodiment, one or more of the sealing interfaces 208, 210, or 212 may include a spacer 214. The spacer 214 may be similar to or different from the aforementioned spacer 176. As a non-limiting example, the spacer 214 may include a piston sealing ring, a W-seal connection, a wear-resistant coating, etc. In an embodiment, one or more of the sealing interfaces 208, 210, or 212 may be a press-fit connection with the underlying liner segment.

[0156] In an embodiment, one or more of the front liner segment 108, the rear liner segment 110, or the intermediate member 186 may be configured to deflect, for example, due to exposure to high temperatures encountered at the combustion chamber 106 during operation of the gas turbine engine 10. To accommodate such deflection, the intermediate member 186 may be configured to move relative to at least one of the front and rear liner segments 108 or 110. In an embodiment, such deflection may be absorbed at the sealing portion 204 or 206. For example, the sealing portion 204 of the first engagement feature 192 may be configured to move relative to the front liner segment 108. For example, the front liner segment 108 may be elongated in the longitudinal direction and slide relative to the sealing portion 204. In another case, the sealing portion 206 of the second engagement feature 194 may be configured to move relative to the rear liner segment 110. For example, the rear liner segment 110 may be elongated in the longitudinal direction and slide relative to the sealing portion 206. In this way, the intermediate member 186 may absorb deflection of either or both of the front and rear liner segments 108 or 110. In some cases, the intermediate member 186 itself may deflect, such as in response to longitudinal loading caused by the cooling medium flowing against the fence 116. The interface formed between the intermediate member 186 and the front liner segment 108 or the rear liner segment 110 can be configured to absorb at least a portion of this deflection. In other cases, the deflection load on the intermediate member 186 caused by the longitudinal loading can be absorbed by the shell 72 or the connecting member 196.

[0157] In some cases, the front liner segment 108 or the rear liner segment 110 may deflect relative to the intermediate member 186 beyond a desired distance. In these cases, a stop feature may be used to prevent undesired deflection. Fig.26 and 27 , the stop feature 216 may extend from the intermediate member 186 and prevent the front liner segment 108 from deflecting beyond a specified deflection limit. In an embodiment, the stop feature 216 may terminate in a radial direction before entering the combustion chamber 106. The stop feature 216 may define a maximum thermal deflection distance D TD1 In addition to or in lieu of the stop feature 216 on the first engagement feature 192, the sealing portion 206 of the second engagement feature 194 may include a stop feature 218. In the illustrated embodiment, the stop feature 218 of the second engagement feature 194 is defined by the rear surface of the fence 116. The stop feature 218 may define the maximum thermal deflection distance D TD2 Other causes of deflection besides the heat-generated deflection described above may cause any one or more of the front liner segment 108 , the rear liner segment 110 , or the intermediate member 186 to deflect.

[0158] The stop feature 216 or 218 can limit the deformation of the front liner segment 108 or the rear liner segment 110 so that the dilution slot 114 maintains its effective size. That is, for example, without the stop feature 216, the front liner segment 108 may deflect into the dilution slot 114 so as to severely restrict the passage of the cooling medium. The stop feature 216 can prevent such restriction and thus maintain a more consistent operating dilution airflow.

[0159] Fig.28 An embodiment of an exemplary spacer 220 for use at the sealing portion 204 or 206 of the first engagement feature 192 or the second engagement feature 194 is shown. Fig.29 Shown along Fig.28 220 is a cross-sectional view of the spacer 220 as seen along line CC in FIG. The depicted spacer 220 is a piston seal having a body 222, wherein a split 224 extends through the longitudinal direction of the spacer 220. The body 222 defines an inner surface 226 in which a groove 228 is formed. The groove 228 can allow a fluid to pass therethrough. For example, the groove 228 can be used to help control airflow during purging, cooling, etc. The groove 228 can have an arcuate cross-sectional shape (as depicted), a polygonal cross-sectional shape, or a combination thereof. The grooves 228 can have the same or different relative sizes compared to each other. In an embodiment, the grooves 228 can be equally spaced from each other in a circumferential direction. In another embodiment, at least two grooves 228 can have different spacings compared to each other.

[0160] Figures 30 to 33 Another embodiment of the outer liner 104 and the intermediate member 186 is shown. The intermediate member 186 may include a plurality of spokes 230 extending at least partially on the dilution slot 114 (such as between the front liner segment 108 and the rear liner segment 110). In an embodiment, the spokes 230 may be coupled to the casing 72 or another element of the gas turbine engine 10 by an annular support ring 232. In some cases, the annular support ring 232 and the spokes 230 may be discrete pieces coupled together. In other cases, the annular support ring 232 and the spokes 230 are integral with each other. That is, the annular support ring 232 and the spokes 230 may be formed by a single piece. As an example, the annular support ring 232 and the spokes 230 may be formed by an additive manufacturing process. In another embodiment, the annular support ring 232 and the spokes 230 may be formed by a subtractive removal process. For example, exemplary materials include CoCr and Hastalloy alloys. The annular support ring 232 may be fastened to the casing 72 by one or more threaded or non-threaded fasteners, brazing, welding, etc. In an embodiment, the annular support ring 232 is bolted to the flange 76 of the housing 72 via a plurality of bolts 234 .

[0161] In an embodiment, at least some of the spokes 230 may be coupled to at least one of the front liner segment 108 or the rear liner segment 110. The spokes 230 may help control thermal deflection of one or both of the front liner segment 108 or the rear liner segment 110. In some cases, the spokes 230 and the annular support ring 232 may be combined to couple the front liner segment 108 or the rear liner segment 110 to the shell 72. In some cases, where one or both of the front liner segment 108 or the rear liner segment 110 include a ceramic material, the spokes 230 may be a separate piece suspended from the shell 72.

[0162] The spokes 230 may have several different shapes. Fig.32 In certain embodiments, the spokes 230 may form a hook joint having a generally rounded U-shaped or V-shaped cross-sectional profile. The arms 236 or 238 may be adjusted to provide desired benefits to the outer liner 104. For example, the arms 236 or 238 may have a desired spring constant to control the axial and radial deformation of the front liner segment 108 and the rear liner segment 110. Fig.33 , the spoke 230 may further include one or more features 240 configured to further control adjustment of the spoke 230 . Fig.33 The feature 240 depicted in FIG. 2 is a non-linear portion of the arms 236, 238, such as a bend (e.g., a V-shaped or U-shaped bend) or a baffle in the arms 236, 238. More specifically, for Fig.33 In the embodiment depicted in FIG. 2 , feature 240 is the wishbone ends of arms 236 and 238 that are configured to adjust the stiffness of spoke 230 for desired characteristics.

[0163] Fig.34 and 35 An embodiment of an intermediate member 186 according to another embodiment is shown. Fig.34The intermediate member 186 depicted in FIG. 1 generally includes a fence 116 extending in a radial direction toward the combustion chamber 106, one or more windows 190, stop features 216 and 218, sealing portions 204 and 206, a first set of cooling holes 242 disposed upstream of the dilution slot 114, and a second set of cooling holes 244 disposed downstream of the first set of cooling holes 242. Sealing interfaces 251 and 253 may be formed between the intermediate member 186 and the front liner segment 108 and the rear liner segment 110, respectively. A support 246 is depicted as extending radially from the intermediate member 186. The support 246 may extend to the casing 72 or another element within the gas turbine engine 10. In an embodiment, the support 246 may be configured to couple the intermediate member 186 to the casing 72. In another embodiment, the support 246 may carry an internal load, such as a spring load, within the support 246 to provide a biasing force against the intermediate member 186 in a desired direction. For example, the support 246 may be configured to bias the intermediate member 186 into the outer liner 104 in a direction along the radial axis.

[0164] The support 246 may define a window 248 configured to allow cooling medium to pass longitudinally downstream of the support 246. In some cases, the support 246 may define a dilution slot window 250 configured to allow cooling medium to pass to the dilution slot 114. The dilution slot window 250 may be in fluid communication with one or more windows 190 of the intermediate member 186. For example, the dilution slot window 250 may be in fluid communication with a radially outer window 190 of the intermediate member 186.

[0165] The intermediate member 186 may include only the front window 190, or only the dilution slot window 250, or only the rear window 191, or only the front window 190 and the rear window 191, or only the front window 190 and the dilution slot window 250, or only the dilution slot window 250 and the rear window 191. In an embodiment, the intermediate member 186 may include the front window 190, the dilution slot window 250, and the rear window 191. The air flow may enter the combustion chamber through the cooling holes 242 or 244 through the stop features 216 or 218 in addition. The air passing through the cooling holes 242 or 244 may prevent hot gases from being sucked into the cavity formed between the intermediate member 186 and the front liner segment 108 or the rear liner segment 110. This may improve the hot section life of the engine 10. The sealing interfaces 251 and 253 may reduce leakage between the intermediate member 186 and the front liner segment 108 and the rear liner segment 110.

[0166] The windows 248 in the support 246 may help distribute air through the intermediate member 186 , resulting in a more even distribution of air exiting the dilution slot 114 and entering the combustion chamber.

[0167] refer to Fig.35 , the stop feature 216 may extend a radial distance into the combustion chamber 106 beyond the forward liner segment 108. The stop feature 216 may prevent the forward liner segment 108 from deflecting beyond a maximum deflection distance in at least the longitudinal direction. Similar to the stop feature 216, the stop feature 218 may prevent the aft liner segment 110 from deflecting beyond a maximum deflection distance in at least the longitudinal direction.

[0168] The channel 252 may be disposed between the stop feature 216 and the fence 116 to fluidly couple the combustion chamber 106 with a cooling medium that enters the combustion chamber 106 through the window 190 of the intermediate member 186. In an embodiment, one or more connecting members 254 may extend across the channel 252. The connecting members 254 may extend between the stop feature 216 and the fence 116. Adjacent connecting members 254 may be spaced apart from one another so as to define a channel opening 256. The connecting members 254 may maintain the channel 252 in a desired state, for example, maintaining the channel 252 at a relatively fixed size, and preventing the channel 252 from collapsing, for example, if the front liner segment 108 or the rear liner segment 110 is deformed to bias the stop feature 216 or 218 sufficiently to close the channel 252. The cooling medium, for example, dilution air, may enter the channel opening 256 and pass through the channel 252 into the combustion chamber 106.

[0169] In an embodiment, at least one of the first group of cooling holes 242 or the second group of cooling holes 244 may allow the cooling medium to pass into the combustion chamber 106 through the dilution slot 114 between the intermediate member 186 and the front liner segment 108 or the rear liner segment 110, respectively. That is, the fluid flow path through the cooling holes 242 or 244 may be separated from the fluid flow path through the channel 252. In a more specific embodiment, the fluid flow path through the cooling holes 242 or 244 may be in fluid communication with the fluid flow path through the channel 252 into the combustion chamber 106.

[0170] In another embodiment, the cooling medium entering the cooling holes 242 or 244, or the back pressure generated elsewhere in the system, can be swept through the spacer 258 disposed between the intermediate member 186 and the front liner segment 108 and the rear liner segment 110. The spacers 258 and 258 can be disposed in at least one of the sealing interfaces 251 or 253. In an embodiment, the spacers 258 and 258 can have similar operating modes. That is, for example, both the spacers 258 and 258 can provide a sealing interface for controlling the air flow entering the combustion chamber 106. In another embodiment, the spacers 258 and 258 can have one or more different characteristics or functions compared to each other. For example, the spacer 258 in contact with the rear liner segment 110 can prevent the development of high stress levels on the rear liner segment 110. The spacer 258 in contact with the rear liner segment 110 can also provide cooling medium to the back of the fence 116, thereby increasing the operating life of the intermediate member 186. At the same time, the spacers 258 in contact with the forward liner segment 108 may allow for purging of the cooling medium and prevent hot gases from being ingested into the combustion chamber 106 .

[0171] The first group of cooling holes 242 or the second group of cooling holes 244 may include a plurality of cooling holes. In some cases, each cooling hole may have the same relative size or shape compared to each other. In other cases, at least one cooling hole may have a different size or shape compared to another cooling hole. In an embodiment, the cooling hole has a size in the range of 5 mils and 100 mils, such as a size in the range of 10 mils and 50 mils, such as a size in the range of 20 mils and 35 mils. In a particular embodiment, the cooling hole has a diameter of approximately 30 mils. In some cases, the cooling holes of the first group of cooling holes 242 or the second group of cooling holes 244 may be configured to inject at least 1% of the total cooling medium, such as at least 2% of the total cooling medium, such as at least 3% of the total cooling medium, such as at least 4% of the total cooling medium, such as at least 5% of the total cooling medium, such as at least 10% of the total cooling medium, such as at least 15% of the total cooling medium into the combustion chamber 106. The remaining cooling medium injected into the combustion chamber 106 may come from, for example, the channel 252.

[0172] refer to Fig.36 , the intermediate member 186 may include an annular body 188 defining a plurality of segments 260. The segments 260 may each define a portion of the circumference of the intermediate member 186. In an embodiment, the intermediate member 186 may include at least two segments 260, such as at least three segments 260, such as at least four segments 260, etc. Each segment 260 may define one or more windows 190 configured to allow the cooling medium to pass to the combustion chamber 106.

[0173] Fig.37A cross-sectional view of a portion of a gas turbine engine 10 according to an embodiment is shown, wherein an intermediate member 186 is coupled to an aft liner segment 110. The aft liner segment 110 is coupled to the casing 72 via a connecting member 74. The connecting member 74 includes a portion disposed between a first portion 78 of the casing 72 and a second portion 80 of the casing 72, i.e., a portion compressed by the first portion 78 of the casing 72 and the second portion 80 of the casing 72. The first portion 78 and the second portion 80 may correspond to different portions of the casing 72 that are mated together. In some cases, the connecting member 74 may utilize the mating point as a location for coupling with the casing 72. The connecting member 74 may have a window that allows air to pass to the rear side of the engine 10 or the aft liner segment 110.

[0174] Figures 38 to 43 Other exemplary attachment schemes that may be used to secure intermediate member 186 within gas turbine engine 10 are depicted.

[0175] Start Reference Fig.38 In embodiments, the intermediate member 186 can be configured to float relative to at least one of the shell 72, the front liner segment 108, the rear liner segment 110, or a combination thereof. As used herein, the term "floating" is intended to refer to a non-fixed connection whereby two or more elements are configured to move relative to each other. In some cases, the floating connection can include press-fit connections, spring-loaded connections, and other adjustable interfaces whereby two or more elements can move relative to each other. Fig.38 In the illustrated embodiment, the intermediate member 186 is free-floating relative to the shell 72, the front liner segment 108, and the rear liner segment 110. As used herein, "free-floating" can refer to a condition having at least one degree of freedom relative to a reference feature (e.g., along the longitudinal centerline 12). For example, the intermediate member 186 can have at least one degree of freedom relative to the front liner segment 108, the rear liner segment 110, or both. In this manner, the intermediate member 186 can be movable relative to at least one of the front liner segment 108 or the rear liner segment 110 in at least one manner, such as the longitudinal centerline 12. Alternatively, the intermediate member 186 can define at least two degrees of freedom relative to the front liner segment 108, the rear liner segment 110, or both (e.g., both along the longitudinal centerline 12 and in the radial direction). Therefore, the free-floating intermediate member 186 can be free to move relative to at least one of the front and rear liner segments 108 or 110 in at least two manners, such as in the longitudinal and radial directions.

[0176] The intermediate member 186 forms a press fit or the like with the front liner segment 108 and the rear liner segment 110 .

[0177] Fig.39 An embodiment is shown in which the intermediate member 186 is free floating. Fig.38The embodiments depicted are different. Fig.39 The embodiment depicted in includes one or more rods 262 extending from the housing 72 to bias the intermediate member 186. As used herein, the term "bias" is intended to refer to the application of a force so as to load an element, which may or may not cause that element to move. The one or more rods 262 can form a spring bias against the intermediate member 186, biasing the intermediate member 186 into at least one of the front liner segment 108 or the rear liner segment 110. The rods 262 can be fixed to the housing 72 by an intermediate member 264 coupled to the housing 72, such as by one or more threaded or non-threaded fasteners.

[0178] Fig.40 An embodiment is shown in which the intermediate member 186 is free floating. Fig.39 The embodiment depicted is similar, Fig.40 The embodiment depicted in utilises a support 246 to bias the intermediate member 186. The support 246 includes a window 248 to allow a cooling medium to flow downstream of the support 246.

[0179] Fig.41 An embodiment is shown in which the intermediate member 186 is free floating. Fig.39 and 40 Unlike the embodiments depicted in Fig.41 The embodiment depicted in the drawings utilizes a support 266 that is coupled to the combustor center casing portion 82 disposed upstream of the intermediate member 186. That is, the intermediate member 186 may be offset from the support 246, which extends from a position longitudinally downstream of the intermediate member 186, or from the support 266, which extends from a position longitudinally upstream of the intermediate member 186. Alternatively, a support approximately longitudinally centered on the intermediate member 186 may also be used.

[0180] Fig.42 An embodiment is shown in which the intermediate member 186 is coupled to the combustor intermediate casing portion 82 using a rod 268 that extends from the casing 72 to bias the intermediate member 186 .

[0181] Fig.43 An embodiment is shown in which the intermediate member 186 is free floating. However, the intermediate member 186 is biased by a spring-loaded element 270, which is configured to generate a biasing force by compression of a spring (e.g., a coil spring). The spring-loaded element 270 can generally extend between the intermediate member 186 and the housing 72.

[0182] Fig.44 186. A vector diagram of the forces acting on or through the intermediate member 186 is shown. These forces may include a force F that biases the intermediate member 186. SPFor example, the force F SP The force F may be generated by support 246, support 266, rod 262, or rod 268. SP The intermediate member 186 may be biased into the front liner segment 108 and the rear liner segment 110. In particular, the force F SP can be divided into two components F SP1 and F SP2 , where F SP1 The front liner segment 108 is offset, and F SP2 The rear liner segment 110 is biased. In an embodiment, two forces F SP1 and F SP2 The front liner segment 108 and the rear liner segment 110 can be offset by the spacer 258. In this regard, in some embodiments, the spacer 258 can be configured to deform to absorb the force exerted by the F SP Some radial loading forces are generated. Two forces F SP1 and F SP2 The forward liner segment 108 and the aft liner segment 110 may be offset to control radial deflection (shown by dashed lines). In some cases, the F may be adjusted to control radial deflection, taking into account material selection for one or both of the forward liner segment 108 or the aft liner segment 110, operating conditions of the gas turbine engine 10, etc. SP To provide the desired biasing force. For example, F SP The adjustment can be made by material selection of the support 246 or 266 or the rod 262 or 268, by design selection, etc.

[0183] As mentioned above Fig. 22 and 23 As described, in some cases, the intermediate member 186 can be coupled to the front liner segment 108 or the rear liner segment 110. Additional exemplary attachment schemes for attaching the intermediate member 186 to the front liner segment 108 or the rear liner segment 110 are described in Figures 45 to 50 Start Reference Fig.45 , the front liner segment 108 and the rear liner segment 110 can each be connected to the intermediate member 186 using different attachment schemes. As a non-limiting example, the front liner segment 108 can be coupled to the intermediate member 186 by a press fit or a swage fit. The rear liner segment 110 can receive an extension 272 from the intermediate member 186. The extension 272 can be threaded and configured to receive a nut to couple the rear liner segment 110 to the intermediate member 186. A spacer 274, such as a washer, can be provided along the extension 272 to form an opening extending in the longitudinal direction between the intermediate member 186 and the rear liner segment 110. Thus, Fig.45The intermediate member 186 depicted in FIG. 1 can effectively define three windows 190 - a first window 276 disposed in front of the fence 116 , a second window 278 disposed behind the fence 116 , and a third window 280 disposed behind the second window 278 .

[0184] Fig.46 Another attachment scheme is shown, where the intermediate member 186 includes a flange 282 that is configured to engage with a flange 284 of the aft liner segment 110. Fasteners such as bolts 286 can couple the flanges 282 and 284 together. In another embodiment, the flanges 282 and 284 can be coupled together by a brazing process, welding, fluid coupling, or another type of joint interface. In the illustrated embodiment, the flange 282 is disposed downstream of the second window 278 of the window 190. In another embodiment, the flange 282 can be disposed upstream of the second window 278 or at any other relative location.

[0185] Fig.47 Another attachment scheme is shown, in which the intermediate member 186 uses the same method as described above with respect to Fig.46 The same scheme described is coupled to the rear liner segment 110. The front liner segment 108 is coupled to the intermediate member 186 using a rabbit fit 288. The fence 116 is equidistant or approximately equidistant from the front liner segment 108 and the rear liner segment 110. In an embodiment, the fence 116 can be disposed closer to the front liner segment 108 or the rear liner segment 110. In some cases, the fence 116 can define a front window 189 disposed upstream of the fence 116 and a rear window 191 disposed downstream of the fence 116. The length L of the front window 189 is F The length L of the rear window 191 A The ratio [L F :L A ] can be in the range of 0.1:10 and 10:0.1. In a specific embodiment, L F :L A The ratio is in the range of 1:9 and 9:1. F :L A The relative ratio of the turbulent kinetic energy (TKE) at the trailing edge of the fence 116 can affect the mixing and reduce NO X form.

[0186] Fig.48 Another attachment scheme is shown, where the flange 282 of the intermediate member 186 is coupled to the flange 284 of the rear liner segment 110. However, Fig.46 Different, in Fig.48In the illustrated embodiment, the flange 284 comprises a discrete piece from the aft liner segment 110. The flange 284 may be coupled to the aft liner segment 110 by welding, brazing, by one or more fasteners, etc. The flanges 282 and 284 may be coupled together by bolts 286, rivets, etc. The intermediate member 186 may be attached to the forward liner segment 108 by, for example, a swage fit, a press fit, brazing, welding, etc. In some cases, a separation element 290 may be disposed between the intermediate member 186 and the forward liner segment 108.

[0187] Fig.49 Another attachment scheme is shown, where the intermediate member 186 is coupled to the forward liner segment 108 by a swaged fit, and the intermediate member 186 is coupled to the aft liner segment 110 by a swaged fit with another decoupling element 292 .

[0188] Fig.50 Another attachment scheme is shown, where a separate element 292 is coupled to the aft liner segment 110, such as by a welding operation, and a bolt insert can be received in the separate element 292. Bolts 294 can be inserted through the intermediate member 186 and secured with the bolt insert to couple the intermediate member 186 to the aft liner segment 110.

[0189] In an embodiment, the intermediate member 186 may have a multi-piece structure. Fig.51 In an embodiment, the intermediate member 186 may include a plurality of segments 193 that together form an annular body. In an embodiment, the segments 193 may be positioned in use so that at least two adjacent segments 193 are spaced apart from each other by a gap 195 in the circumferential direction. The gap 195 may allow a cooling medium to enter the combustion chamber 106. The gap 195 may be configured to accommodate deformation of the segments 193, such as deformation of the segments 193 caused by, for example, thermal expansion during use. In an embodiment, the gap 195 may define a gap distance as measured between adjacent segments 193 in the range of 0.01 mm and 5 mm, such as in the range of 0.1 mm and 1 mm. In a particular embodiment, the gap distance is in the range of 0.25 mm and 0.5 mm. Using an intermediate member 186 having, for example, a multi-piece structure including segments 193 may allow for easier replacement of damaged portions of the intermediate member 186. For example, during maintenance and repair operations, only the damaged segments 193 need to be replaced, while the other (undamaged) segments 193 remain unchanged. Fig.52 A view of the gaps 195 between adjacent segments 193 is shown.

[0190] Fig.53 Shown with Fig.47 18 is a similar embodiment to that depicted in , except that the fence 116 divides the dilution slot 114 into a front window 189 and a rear window 191. However, Fig.47 Unlike the embodiments depicted in Fig.53 The fence 116 in the illustrated embodiment is formed by the rear liner segment 110. In an embodiment not shown, the fence 116 may alternatively be formed by the front liner segment 108. A portion 197 of the outer liner 104 is depicted as extending in a radially outward direction into the cold side passage of the gas turbine engine 10. The portion 197 may be integral with the fence 116. Although the fence 116 and the portion 197 are depicted as being disposed along a common plane, in other embodiments, the fence 116 and the portion 197 may be offset in a longitudinal direction. The front liner segment 108 and the rear liner segment 110 may be joined together by any suitable technique, such as brazing, welding, one or more fasteners, etc.

[0191] Fig.54 Shown as Fig.53 1 and 2. A cross-sectional view of the outer liner 104 as viewed along line FF in FIG. 1 . The fence 116 extends through the center of the dilution slot 114. One or more front windows 199 may be formed upstream of the fence 116. One or more rear windows 201 may be formed downstream of the fence 116. In some cases, the front window 199 and the rear window 201 may have the same number of windows as compared to each other. In other cases, the front window 199 and the rear window 201 may have a different number of windows as compared to each other. The one or more front windows 199 may be aligned or staggered in a circumferential direction relative to the one or more rear windows 201. In an embodiment, the front window 199 may be configured to allow more cooling medium to pass into the combustion chamber 106 compared to the rear window 201. It should be understood that the front window 199 and the rear window 201 may be used with other embodiments described herein. For example, as a non-limiting example, Figures 7 to 10 and Figures 15 to 21 Embodiments may further include a rear window 201 disposed downstream of the fence 116 .

[0192] Fig.55An embodiment is shown in which the fence 116 includes a plurality of passages 203 extending from the front side 205 of the fence 116 to the rear side 207 of the fence 116. The passages 203 can allow a cooling medium to pass through the fence 116 to cool the outer liner 104. The passages 203 can include a plurality of holes. Each hole can extend through the fence 116 in one or more straight segments or one or more arc segments. In an embodiment, at least one passage 203 has a central axis oriented orthogonally to at least one of the front and rear sides 205 or 207 of the fence 116. The passage 203 can provide a protective layer of cooling medium on the rear liner segment 110 and flush out trapped hot gases. In another embodiment, at least one passage 203 has a central axis that is inclined at an angle relative to at least one of the front and rear sides 205 or 207 of the fence 116. For example, the central axis of the passage 203 can be angularly offset from the front side 205 of the fence 116 by at least 10 degrees, such as at least 20 degrees, such as at least 30 degrees, such as at least 40 degrees.

[0193] Fig.56 A longitudinal view of a fence 116 including passages 203 arranged in a staggered pattern is shown. In another embodiment, passages 203 may be aligned in one or more rows or columns. The outer liner 104 is disposed between the fence 116 and the radially outwardly extending portion 197.

[0194] Figures 57 to 62 Another embodiment of the outer liner 104 is shown, which includes a fence 296 configured to be coupled thereto. The fence 296 can be similar to the fence 116 described previously. However, in Figures 57 to 62 , the fence 296 does not extend through the dilution slot 114. Instead, the fence 296 is directly coupled to the interior of the outer liner 104, such as the interior of the aft liner segment 110. The fence 296 may be coupled to the aft liner segment 110 at a location longitudinally downstream of the dilution slot 114. One or more scoop interfaces 148 may be formed along the outer liner 104 to generate air flow into the dilution slot 114. The air flow may form a film against the fence 296 as previously described for further injection into the combustion chamber 106.

[0195] refer to Figures 57 to 59 The fence 296 may extend from a support member, such as a flange 298, which is configured to be coupled to the outer liner 104. The flange 298 may include an extension 300 configured to pass through an opening in the outer liner 104 and be secured thereto by a securing element, such as a nut 302. Fig.59As shown, the outer liner 104 may include one or more holes 304 disposed between adjacent dilution slots 114. The holes 304 may form purge openings that may reduce or even eliminate secondary recirculation zones. The reduction or elimination of secondary recirculation zones may help to form a more annular layer of dilution air flowing from the dilution slots 114 to the combustion chamber 106. This may significantly reduce NO X And increase engine performance.

[0196] Fig.61 A simplified cross-sectional view of another embodiment is shown in which the fence 296 is coupled to the outer liner 104 by a fastener 306 that extends through the flange 298. The fastener 306 may be secured to the aforementioned nut 302, another securing element, by mechanical or structural action on the fastener 306, or the like.

[0197] In some cases, the fence 296 can have a multi-piece structure. For example, the fence 296 can include a plurality of segments 308 that together form an annular body. Fig.61 Shown is a longitudinal view of a plurality of segments 308 arranged as they might appear during use, according to an exemplary embodiment. Fig.62 A side view of the fence 296 is shown, with some of the segments 308 shown from the side view. Fig.62 As shown, in some cases, the segments 308 can be configured to overlap each other. In an embodiment, at least one pair of adjacent segments 308 can define an interlocking shape that is configured to maintain the segments 308 in a desired position relative to each other. In the depicted embodiment, the interlocking shape is a stepped shape shared by adjacent segments 308.

[0198] Fig.63 An exemplary embodiment of the outer liner 104 is depicted as seen in a radial view in a direction toward the combustion chamber 106. The outer liner 104 and the intermediate member 316 may define a plurality of rows of openings extending in a circumferential direction around the circumference of the outer liner 104. The openings may include a first opening 310, a second opening 312, and a third opening 314. All of the openings 310, 312, and 314 may be in fluid communication with the combustion chamber 106. The relative amount of air passing through the openings 310, 312, and 314 may be adjusted. For example, the first opening 310 may be configured to allow 5% to 95% of the cooling medium to pass into the combustion chamber 106, while the second opening 312 may be configured to allow the remainder or a majority of the remaining cooling medium to pass into the combustion chamber 106. At least two of the first, second, and third openings 310, 312, or 314 may define a multi-stage cooling arrangement. The multi-stage cooling arrangement may be configured to cool the combustion chamber 106, improve efficiency and performance, and reduce NO XFor example, the first opening 310 may represent a first cooling stage configured to allow the cooling medium to pass into the combustion chamber 106 upstream of the fence 318 ( Fig.64 ). The second opening 312 may represent a second cooling stage configured to allow a cooling medium to pass through the fence 318 into the combustion chamber 106. The third opening 314 may represent a third cooling stage configured to allow a cooling medium to pass into the combustion chamber 106 downstream of the fence 318.

[0199] In an embodiment, the cooling medium entering the first opening 310 can reduce the temperature of the intermediate member 316 at the fence 318, forming a cooling medium flow against the fence 318 to prevent surface oxidation of the front surface of the fence 318. The cooling medium passing through the second opening 312 can cool the rear surface 326 of the fence 318 and the internal structure of the intermediate member 316. The difference in the velocity of the cooling medium passing through the first opening 310 and the second opening 312 can form a shear layer within the combustion chamber 106, which can improve the mixing of the dilution air with the products from the primary zone, thereby reducing the temperature in the core of the combustion chamber 106, which can reduce NO X The cooling medium passing through the second openings 312 can also act as a hydraulic support, i.e., forming a high-velocity film of dilution air entering the combustion chamber 106, against which the cooling medium passing through the first openings 310 can be supported. As a result, the cooling medium penetrates further into the combustion chamber 106. This can reduce the temperature in the center of the combustion chamber and reduce NO X emission.

[0200] In an embodiment, at least two openings may be associated with the dilution slot 114. For example, referring to Fig.64 , the first opening 310 may be disposed upstream of the intermediate member 316 and extend through the dilution slot 114. The second opening 312 may extend through the intermediate member 316 and thus through the dilution slot 114. The third opening 314 may be disposed rearward of the intermediate member 316. For example, the third opening 314 may extend through the rear liner segment 110.

[0201] The intermediate member 316 may include any one or more of the features or characteristics described above with respect to the intermediate member 316. In an embodiment, the intermediate member 316 may define a fence 318 that includes any one or more of the features or characteristics described above with respect to the fence 116. The fence 318 may include any one or more of the features or characteristics described above with respect to the fence 116. Fig.64 316. The fence 318 may facilitate diversion of the cooling medium entering the first opening 310 and direct the cooling medium into the combustion chamber 106.

[0202] In some cases, the intermediate member 316 may be referred to as a cooling fence. Cooling may be performed by passing a cooling medium through one or more internal passages 320 of the intermediate member 316, including, for example, through a main internal passage 322 extending into the combustion chamber 106 and one or more secondary internal passages 324 branching out from the main internal passage 322. The cooling medium may enter the third opening 312 and pass through at least one of the main internal passage 322 and one or more secondary internal passages 324, and enter the combustion chamber 106. The cooling medium passing through the one or more secondary internal passages 324 may pass along the rear surface 326 of the fence 318 at the front side of the intermediate member 316 and the rear wall 328 of the intermediate member 316. The secondary internal passages 324 may converge toward each other to produce a relatively low pressure at the outlet of the secondary internal passages 324. This may pull more cooling medium flow closer to the core of the combustion chamber 106.

[0203] In an embodiment, the cooling medium may pass through the upstream secondary internal passage 324A at a first volume flow rate, and the cooling medium may pass through the downstream secondary internal passage 324B at a second volume flow rate that is less than the first volume flow rate. For example, the ratio of the first volume flow rate to the second volume flow rate may be at least 1.5:1, such as at least 2:1, such as at least 3:1, such as at least 4:1. This may enhance cooling along the fence 318 where the temperature may be the highest. In addition, the cooling medium may further penetrate into the core of the combustion chamber 106 when exiting the upstream secondary internal passage 324A. The rear wall 328 may be cooled by the downstream secondary internal passage 324B before the cooling flow is discharged into the combustion chamber 106.

[0204] In an embodiment, the inlet of the second opening 312 may have a concave profile, such as a curved shape (eg, a bowl shape) that is recessed into the body of the intermediate member 316. Using a concave profile may facilitate increased air flow, such as to one or more internal passages 320 of the intermediate member 316.

[0205] In an embodiment, the first opening 310 can be defined as at least 1 mil measured in the longitudinal direction, such as at least 5 mils, such as at least 20 mils, such as at least 50 mils, such as a height of at least 95 mils. In another embodiment, the second opening 312 can be defined as at least 1 mil measured in the longitudinal direction, such as at least 5 mils, such as at least 20 mils, such as a height of at least 30 mils. In another embodiment, the intermediate member 316 can have a size of at least 50 mils measured in the radial direction, such as at least 75 mils, such as at least 100 mils, such as at least 150 mils, such as at least 200 mils, such as at least 250 mils, such as at least 275 mils.

[0206] Fig.65 Shown along Fig.64 DD in FIG. 3 shows an exemplary view of the outlet of the secondary internal passage 324 as seen from line DD in FIG. Each cooling hole 330 of the secondary internal passage 324 can be staggered to provide increased cooling performance. The cooling holes 330 can be arranged in rows, columns, staggered arrangements, random placement, or other suitable spatial arrangements.

[0207] refer to Fig.66 In certain embodiments, the secondary internal passage 324 may have a tangential flow direction relative to the primary internal passage 322. The tangential flow direction may impart a uniform or substantially uniform flow across the rear wall 328 and the fence 318 to cool the rear wall 328 and the fence 318. The swirling flow may then be discharged into the combustion chamber 106 with a high amount of swirl, which further helps to improve the turbulence of the cooling medium and contents in the combustion chamber 106. The improved turbulence may improve the mixing of the dilution / cooling air with the combustion products of the gas 70. This reduces the temperature within the center of the combustion chamber 106 and, therefore, reduces NO X The cooling holes may also be configured to have an axial orientation such that they impinge on the fence 318 and the rear wall 328 at an angle of 90 degrees or approximately 90 degrees. Fig.67 Shown without rear wall 328 ( Fig.65 ) is another embodiment of the intermediate member 316. Therefore, the secondary internal passage 324 can discharge the cooling medium directly into the combustion chamber 106.

[0208] Fig.68 An embodiment of the intermediate member 316 is shown in which at least one of the fence 318 or the rear wall 328 converges. That is, at least one of the fence 318 or the rear wall 328 can be tilted or offset at an angle from the tangential orientation relative to the outer liner 104. The convergent fence 318 or the rear wall 328 can form a cooling medium that passes through the intermediate member 316 into a more discrete plane, which can further improve the penetration of the cooling medium into the combustion chamber 106. In the case where both the fence 318 and the rear wall 328 converge, the fence 318 and the rear wall 328 can have different angles relative to each other. For example, the fence 318 can be tilted at a first angle relative to the tangential direction, and the rear wall 328 can be tilted at a second angle relative to the tangential direction, wherein the absolute values ​​of the first and second angles are different from each other. By converging the flow at one location, a high turbulence level can be achieved. This can improve the mixing of the dilution air with the incoming primary zone product. In addition, the internal channel can be oriented perpendicular to the outer liner 104 so that the cooling channels within the fence 318 converge. This may result in lower pressures as the cooling flow paths converge and may drive more cooling flow into the combustion chamber 106 .

[0209] Fig.69An embodiment of an intermediate member 316 including a damper 332 is shown. The damper 332 can be a cold side damper that can provide additional volume 334 to the intermediate member 316 along the back side of the intermediate member 316. Alternatively or in addition, the damper 332 can be a hot side damper. The damper 332 can reduce the vibration frequency in the combustion chamber. The damper 332 can capture a wide range of vibration frequencies. The specific shape or size of the damper 332 can be adjusted in view of the vibrations encountered during operation. In some cases, the damper 332 can include multiple discrete dampers 332 that are each configured to operate at a specific vibration frequency or vibration frequency range. The damper 332 can be divided or otherwise separated into multiple independent volumes or include a single volume. The volume can be divided circumferentially. Other configurations and positions of the damper 332 are possible.

[0210] Fig.70 An embodiment of an intermediate member 336 is shown that includes a fence 338 having an internal passage 340. The internal passage 340 can define a plurality of fluid passages extending through the fence 338. In the illustrated embodiment, the internal passage 340 includes a first internal passage 342 and a second internal passage 344. The first internal passage 342 and the second internal passage 344 are shown extending in parallel in a direction generally toward the combustion chamber 106. In another embodiment described below, at least a portion of at least one internal passage 340 can be located along a different plane than one or more other internal passages 340.

[0211] In an embodiment, the internal passages 340 may all define the same relative length measured in the radial direction. In another embodiment, the internal passages 340 may have variable lengths measured in the radial direction. For example, the first internal passage 342 may define a first length L 1IP , the first length L 1IP Less than the length L of the second internal passage 344 2IP In an embodiment, the most upstream portion of the internal passage 340 may define the shortest length of the internal passage 340 . In another embodiment, the most downstream portion of the internal passage 340 may define the longest length of the internal passage 340 .

[0212] In an embodiment, the intermediate member 336 may be disposed within the dilution slot 114 to form a gap 348 between the most upstream point of the intermediate member 336 and the most downstream point of the front liner segment 108. The airflow may pass through the gap 348.

[0213] One or more scoop interfaces 346 may be configured to direct airflow into the inner passage 340. As shown, the scoop interfaces 346 may be disposed at the radially outer end of the inner passage 340. The scoop interfaces 346 may be integral with the fence 338, or a portion of another component coupled thereto or integral with the outer liner 104.

[0214] exist Fig.70 The intermediate member 336 depicted in FIG is coupled to the rear liner segment 110 by an interference fit. However, other attachment methods according to other embodiments may be used, or the intermediate member 336 may be free floating relative to the front and rear liner segments.

[0215] Fig.71 Another embodiment of the intermediate member 336 including the fence 338 is shown. The first internal passage 342 includes a longitudinal portion 350 extending from the radial portion 352 in the upstream direction. The second internal passage 344 includes a longitudinal portion 354 extending from the radial portion 356 in the downstream direction. Therefore, the airflow can be controlled and redirected into the combustion chamber 106 at a desired entry angle. Although depicted at right angles, in some embodiments, the angle between the longitudinal portions 350 and 354 relative to the radial portions 352 and 356 can be different. In this way, the longitudinal portions 350 and 354 can be angularly displaced from the longitudinal direction by at least 1°, such as at least 5°, such as at least 15°, such as at least 30°, such as at least 45°. In an embodiment, the gap formed between adjacent passages (e.g., between the first internal passage 342 and the second internal passage 344) can be in the range of 0.01 inches and 0.1 inches.

[0216] Fig.72 An embodiment of an intermediate member 336 having a single internal passage 340 is shown. The internal passage 340 can be similar to the first internal passage 342 or the second internal passage 344. Alternatively, the internal passages can also have different configurations. This can help direct part of the cooling medium to the front side of the burner and other parts of the cooling medium to the back side of the burner. This can reduce the temperature in the burner (especially at the core of the burner) and reduce NO X emission.

[0217] Fig.73 Shown along Fig.71BB in the cross-sectional top view of the intermediate member 336 seen. As shown in the figure, in some cases, the intermediate member 336 includes an internal rib 358. The internal rib 358 can be welded to the intermediate member 336 or integrated with the intermediate member 336. The internal rib 358 can be formed by a material similar to the adjacent part of the intermediate member, or include different materials. Exemplary materials include metals, alloys, ceramic matrix composites (CMC) and the like. The internal rib 358 can connect the wall of the intermediate member 336. In this regard, the internal rib 358 can increase the structural integrity of the intermediate member 336.

[0218] Fig.74 An embodiment of an outer liner 104 including a loop feature 124 is shown, and the loop feature 124 has a multi-fence arrangement. In particular, the loop feature 124 shown includes a multi-loop structure defining a first fence (e.g., at a first loop 360) and a second fence (e.g., at a second loop 362). The first loop 360 can be a front loop, and the second loop 362 can be a rear loop. The first loop 360 and the second loop 362 can be spaced apart from each other in a longitudinal direction, a radial direction, a circumferential direction, or any combination thereof. In an embodiment, the loop feature 124 may include one or more windows 364 disposed between the first loop 360 and the second loop 362. The one or more windows 364 may be arranged in one or more rows. The one or more windows 364 may be staggered or aligned relative to each other. Dilution air may enter the combustion chamber through the one or more windows 364.

[0219] The first loop 360 and the second loop 362 may be configured to allow cooling air to enter the combustion chamber through the first opening 366 and the second opening 368, respectively. The first opening 366 and the second opening 368 may function as described above with respect to Fig.71 Longitudinal portions 350 and 354 of internal passage 340 are depicted to function similarly.

[0220] In an embodiment, the first loop 360 and the second loop 362 may each define different lengths L1 and L2, respectively. In an embodiment, the ratio of the lengths of the first loop 360 and the second loop 362 [L1:L2] may be in the range of approximately 1:1 and 1:5. For example, the ratio [L1:L2] may be 1:1, or 1:1.5, or 1:2, or 1:2.5, or 1:3, or 1:3.5, or 1:4, or 1:4.5, or 1:5. The first loop 360 may be used as a fence to increase the penetration of dilution air into the combustion chamber. The second loop 362 may further increase the penetration of dilution air into the combustion chamber. That is, using the same Fig.74 The same graded fence structure shown can allow the dilution air to penetrate deeper into the combustion chamber, which can help reduce temperatures in the combustion chamber core and reduce NO X emission.

[0221] Fig.75 An embodiment of a dilution slot including a stepped interface 370 is shown. The stepped interface 370 defines a plurality of discrete dilution slot air flows 372, 374, and 376 separated from each other by a plurality of fences 378, 380, and 382. The fences 378, 380, and 382 may extend around the circumference of the dilution slot. The fences 378, 380, and 382 may have different relative lengths compared to each other. In a particular embodiment, the fences 378, 380, and 382 may have an increased length measured from the front fence 378 to the rear fence 382. In operation, the front fence 378 may generate a swirl of cooling medium, biasing the cooling medium into the combustion chamber. The air flows 374 and 376 may be introduced sequentially into a dilution film of cooling medium through the dilution slot, thereby increasing the penetration depth into the combustion chamber.

[0222] The distribution of the cooling medium through the air streams 372, 374, and 376 creates an axially staged dilution air flow that can improve the penetration of the cooling medium. Staging the air stream can allow for better control of the penetration of the cooling medium. Staging can allow for better control of the quenching of the incoming products from the primary zone of the combustor to improve NO X Additionally, the differences between the air flows 372, 374, and 376 create shear forces between the air flows 372, 374, and 376, thereby creating high turbulence levels in the core of the combustor, which further enhances mixing of the cooling medium with the combustion products.

[0223] Fig.76 Another embodiment of a hierarchical interface 370 is shown. Fig.75 The air flows 372, 374 and 376 passing through the fences 378, 380 and 382 in the embodiment depicted in FIG. Fig.76 The fences 378, 380, and 382 of the depicted embodiment define internal passages 384, 386, and 388, respectively. Similar to the air streams 372, 374, and 376, the internal passages 384, 386, and 388 can improve the penetration of the cooling medium and provide better control of the quenching of the incoming product to improve NO X discharge, while also creating shear forces between the airflows exiting the different internal passages 384, 386 and 388.

[0224] Fig.77An embodiment of the staging interface 370 is shown in which the intermediate fence 380 has a variable profile so that at least one of the shape, size, or speed of the air flow 376 entering the combustion chamber is different from at least one of the shape, size, or speed of at least one of the air flows 372 and 374. For example, the air flow 376 can define a thicker film of dilution air. The air flow 376 can travel at a slower speed. In the illustrated embodiment, the intermediate fence 380 defines a triangular cross-section. In other embodiments not shown, the intermediate fence 380 (or any one or more fences of the staging interface 370) can define another polygonal shape, such as a pentagon, a shape including straight segments, a shape including arc segments, a shape including arc and straight segments, or another shape that changes the air flow 376 (or any one or more other air flows of the staging interface 370).

[0225] Fig.78 An embodiment of the staged interface 370 is shown in which the internal passages 384, 386, and 388 define a converging flow path. That is, for example, the sidewalls of at least one of the internal passages 384, 386, or 388 can define a tapered profile. The resulting air flow can be accelerated through the internal passages 384, 386, or 388 into the combustion chamber. In the illustrated embodiment, the relative convergence of the internal passages 384, 386, and 388 is different. That is, the cone angles of the internal passages 384, 386, and 388 are all different. In another embodiment, the relative convergence of at least two of the internal passages 384, 386, and 388 can be the same or substantially the same.

[0226] Fig.79 An embodiment of the staging interface 370 is shown in which the trailing edge 390, 392, and 394 of each fence 378, 380, and 382 is relative to the longitudinal centerline 12 ( Figure 1 The inclined trailing edges 390, 392 and 394 can avoid the creation of a relatively low velocity region at the innermost edges of the fences 378, 380 and 382 within the combustion chamber.

[0227] In some cases, at least two of the internal passages 384, 386, and 388 may be connected together. Fig.80, the staging interface 370 can define two windows 396 and 398 that are in fluid communication with all of the internal passages 384, 386, and 388. The front window 396 can be larger than the rear window 398 or otherwise shaped to receive a larger percentage of the airflow through the staging interface 370. In this regard, more cooling medium can pass through the hottest portion of the staging interface 370, the front fence 378. After passing through at least a portion of the front fence 378, the airflow through at least the front window 396 can be distributed to at least two of the internal passages 384, 386, and 388. In the illustrated embodiment, the airflow through the front window 396 can pass through all of the internal passages 384, 386, and 388. However, it should be understood that other configurations are contemplated herein.

[0228] A burner according to one or more embodiments described herein can reduce NO X The invention relates to a method for improving the combustion process in a gas turbine engine by reducing the core temperature, increasing performance and efficiency, and otherwise improving the combustion process in a gas turbine engine. In particular, the use of one or more loop features, spade interfaces, intermediate members, fences, or any other features described herein can result in more efficient engine operation, which in turn can reduce operating costs and reduce environmental impact.

[0229] Further aspects of the disclosure are provided by the subject matter of the following clauses:

[0230] Item 1. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a front liner segment; a rear liner segment, the rear liner segment being disposed downstream of the front liner segment relative to a flow direction through the combustor, the front liner segment and the rear liner segment at least partially defining a combustion chamber; and a fence, the fence being disposed between the front liner segment and the rear liner segment, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

[0231] Clause 2. A combustor according to any one or more of the clauses, wherein the front liner segment and the rear liner segment are part of a single liner, wherein the front liner segment is disposed upstream of a dilution opening of the combustion chamber, and wherein the rear liner segment is disposed downstream of the dilution opening.

[0232] Clause 3. A burner according to any one or more of the clauses, wherein the fence is part of an intermediate member, and wherein the intermediate member includes a damper configured to reduce vibration frequencies in the combustion chamber.

[0233] Clause 4. The burner of any one or more of the clauses, wherein the fence comprises a multi-barrier arrangement comprising a first fence and a second fence, and wherein the first fence and the second fence converge.

[0234] Clause 5. The combustor of any one or more of the clauses, wherein the fence comprises a multi-piece structure including a plurality of segments configured to at least partially overlap one another in the circumferential direction.

[0235] Clause 6. The burner of any one or more of the clauses, wherein the fence comprises one or more cooling openings configured to allow a cooling medium to pass through the fence.

[0236] Clause 7. The combustor of any one or more of the clauses, wherein at least a portion of the fence is configured to move relative to at least one of the forward liner segment or the aft liner segment.

[0237] Clause 8. A burner according to any one or more of the clauses, wherein the burner comprises a multi-stage cooling arrangement, the multi-stage cooling arrangement being configured to cool the combustion chamber, the multi-stage cooling arrangement comprising: a first cooling stage, the first cooling stage being configured to allow a cooling medium to pass into the combustion chamber upstream of the fence, and a second cooling stage, the second cooling stage being configured to allow a cooling medium to pass through the fence into the combustion chamber.

[0238] Clause 9. The combustor of any one or more of the clauses, wherein a cooling medium passing through both the first cooling stage and the second cooling stage is used in the combustion process in the combustion chamber.

[0239] Item 10. A fence for a combustor of a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor having a front liner segment and a rear liner segment, the front liner segment and the rear liner segment at least partially defining a combustion chamber, the fence comprising: an annular body configured to extend into the combustion chamber in the radial direction; and a cooling arrangement configured to cool the combustion chamber.

[0240] Clause 11. A fence according to any one or more of the clauses, wherein the cooling arrangement comprises a multi-stage cooling arrangement, the multi-stage cooling arrangement comprising: a first cooling stage, the first cooling stage being configured to allow a cooling medium to pass into the combustion chamber upstream of the fence, and a second cooling stage, the second cooling stage being configured to allow a cooling medium to pass through the fence into the combustion chamber.

[0241] Clause 12. The fence of any one or more of the clauses, wherein the cooling medium comprises air passing through the gas turbine engine outside the combustion chamber.

[0242] Clause 13. A fence according to any one or more of the clauses, wherein the combustion chamber includes an opening disposed between the front liner segment and the rear liner segment and extending in a circumferential direction, wherein the fence extends through the opening in the radial direction, and wherein the first cooling stage includes a portion of the opening disposed upstream of the fence.

[0243] Clause 14. A fence as described in any one or more of the clauses, wherein the multi-stage cooling arrangement further comprises a third cooling stage, the third cooling stage being configured to pass a cooling medium into the combustion chamber downstream of the fence.

[0244] Clause 15. A fence according to any one or more of the clauses, wherein the cooling arrangement comprises one or more internal passages extending through the annular body of the fence in the radial direction, and wherein the one or more internal passages comprise a plurality of secondary internal passages configured to redirect the flow of cooling medium at least toward a rear surface of the fence.

[0245] Clause 16. A fence as described in any one or more of the clauses, wherein the one or more internal passages are in fluid communication with the combustion chamber, and wherein the one or more internal passages are configured to pass a cooling medium into the combustion chamber.

[0246] Clause 17. A fence as described in any one or more of the clauses, wherein the fence includes a recess extending into the annular body at a location adjacent to an entrance to the one or more internal passages.

[0247] Item 18. A fence for a combustor of a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor having a front liner segment and a rear liner segment, the front liner segment and the rear liner segment at least partially defining a combustion chamber, the fence comprising: an annular body, the annular body being configured to be disposed between the front liner segment and the rear liner segment and extending into the combustion chamber in the radial direction; and one or more thermal expansion features, the one or more thermal expansion features being configured to accommodate thermally induced stresses.

[0248] Clause 19. A fence according to any one or more of the clauses, wherein the annular body comprises a multi-piece structure, the multi-piece structure comprising a plurality of segments, the plurality of segments being configured to at least partially overlap each other in the circumferential direction.

[0249] Clause 20. The fence of any one or more of the clauses, wherein the one or more thermal expansion features comprise a loop feature of at least one of the front liner segment or the rear liner segment.

[0250] Item 21. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a front liner segment; a rear liner segment, the rear liner segment being disposed downstream of the front liner segment relative to a flow direction through the combustor, the front liner segment and the rear liner segment at least partially defining a combustion chamber; and an intermediate member, the intermediate member being at least partially disposed between the front liner segment and the rear liner segment and extending in the circumferential direction.

[0251] Clause 22. The combustor of any one or more of the clauses, wherein the front liner segment and the rear liner segment are coupled together by the intermediate member.

[0252] Clause 23. A burner according to any one or more of the clauses, wherein the intermediate member is additively manufactured.

[0253] Clause 24. A combustor according to any one or more of the clauses, wherein the connection between the rear liner segment and the front liner segment or the intermediate member is a brazed connection, a bolted connection, a welded connection, an interference fit, a swaged connection, or any combination thereof.

[0254] Clause 25. The combustor of any one or more of the clauses, wherein the intermediate member is free floating relative to the forward liner segment and the aft liner segment.

[0255] Clause 26. The burner according to any one or more of the clauses, wherein the intermediate member comprises a fence extending into the combustion chamber in the radial direction.

[0256] Clause 27. The combustor of any one or more of the clauses, wherein the intermediate member is integral with at least one of the forward liner segment and the aft liner segment.

[0257] Clause 28. A combustor according to any one or more of the clauses, wherein the front liner segment comprises a first material, wherein the rear liner segment comprises a second material, wherein the intermediate member comprises a third material, and wherein the third material is different from at least one of the first material and the second material.

[0258] Clause 29. A combustor according to any one or more of the clauses, wherein the intermediate member includes one or more spacers, wherein the one or more spacers are disposed between the intermediate member and at least one of the front liner segment or the rear liner segment, and wherein the spacer is a piston seal, a spring seal, or another seal configured to control airflow through the intermediate member.

[0259] Clause 30. The combustor according to any one or more of the clauses, wherein the intermediate member is offset towards the forward liner segment and the aft liner segment by a support extending from a casing of the gas turbine engine to the intermediate member.

[0260] Clause 31. A combustor according to any one or more of the clauses, wherein the intermediate member includes one or more windows configured to allow a cooling medium to pass into the combustion chamber of the gas turbine engine, the one or more windows being fluidly connected to a dilution slot extending between the front liner segment and the rear liner segment.

[0261] Clause 32. A combustor according to any one or more of the clauses, wherein the intermediate member comprises an annular support ring and a plurality of spokes each extending from the annular support ring, wherein at least one of the plurality of spokes is configured to contact at least one of the front liner segment or the rear liner segment.

[0262] Clause 33. The burner of any one or more of the clauses, wherein at least one of the spokes further comprises a feature configured to adjust the spoke.

[0263] Clause 34. The combustor of any one or more of the clauses, wherein the intermediate member forms a movable interface relative to at least one of the forward liner segment and the aft liner segment.

[0264] Item 35. An intermediate component for a combustor of a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor having a front liner segment and a rear liner segment, the front liner segment and the rear liner segment at least partially defining a combustion chamber, the intermediate component comprising: an annular body, the annular body being configured to be at least partially disposed in a gap formed between the front liner segment and the rear liner segment.

[0265] Clause 36. An intermediate member according to any one or more of the clauses, wherein the annular body includes one or more windows configured to allow dilution air to pass through a dilution slot formed between the front liner segment and the rear liner segment and enter the combustion chamber.

[0266] Clause 37. The intermediate member according to any one or more of the clauses, wherein the annular body further comprises a fence configured to extend into the combustion chamber in the radial direction.

[0267] Clause 38. The intermediate member of any one or more of the clauses, wherein the annular body is configured to move in the longitudinal direction relative to at least one of the front liner segment and the rear liner segment.

[0268] Clause 39. The intermediate member according to any one or more of the clauses, wherein the annular body comprises a plurality of segments arranged in a circumferential arrangement, and wherein the plurality of segments overlap each other in the circumferential direction.

[0269] Clause 40. The intermediate member according to any one or more of the clauses, wherein the annular body comprises one or more internal passages configured to convey dilution air through the annular body to the combustion chamber.

[0270] Item 41. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a front lining segment; and a rear lining segment, the rear lining segment being disposed downstream of the front lining segment relative to a flow direction through the combustor, the front lining segment and the rear lining segment at least partially defining a combustion chamber, wherein the front lining segment and the rear lining segment are connected together at a movable interface.

[0271] Clause 42. The combustor of any one or more of the clauses, wherein a portion of one of the forward liner segment or the aft liner segment is configured to contact and move relative to the other of the forward liner segment or the aft liner segment.

[0272] Clause 43. The combustor of any one or more of the clauses, wherein the portion of one of the forward liner segment or the aft liner segment is configured to form a press fit with the other of the forward liner segment or the aft liner segment.

[0273] Clause 44. A combustor according to any one or more of the clauses, wherein the movable interface formed between the portion of one of the front liner segment or the rear liner segment and the other of the front liner segment or the rear liner segment comprises a wear-resistant coating, a low-friction coating, a spacer, or any combination thereof.

[0274] Clause 45. A combustor according to any one or more of the clauses, wherein the movable interface includes an intermediate member disposed between the front liner segment and the rear liner segment, the intermediate member being configured to be movably coupled to at least one of the front liner segment and the rear liner segment.

[0275] Clause 46. A combustor according to any one or more of the clauses, wherein at least one of the front liner segment, the rear liner segment and the intermediate member includes one or more piston seals, and the one or more piston seals are configured to form a sealed interface at the movable interface.

[0276] Clause 47. The combustor of any one or more of the clauses, wherein the movable interface includes a size control feature configured to control a size of a gap between the forward liner segment and the aft liner segment.

[0277] Clause 48. The combustor of any one or more of the clauses, wherein the size control feature comprises a feature integral to at least one of the forward liner segment or the aft liner segment.

[0278] Clause 49. A combustor according to any one or more of the clauses, wherein the size control feature comprises: a protrusion extending from at least one of the front liner segment or the rear liner segment; and an interface disposed on the other of the at least one of the front liner segment or the rear liner segment, the interface being configured to receive the protrusion.

[0279] Clause 50. A combustor according to any one or more of the clauses, wherein the combustor defines one or more dilution grooves disposed between the front liner segment and the rear liner segment, the one or more dilution grooves being configured to connect the combustion chamber to a cooling medium fluid, wherein an intermediate member is disposed in at least one of the one or more dilution grooves, and wherein the intermediate member includes one or more windows, the one or more windows being configured to connect the cooling medium to the combustion chamber.

[0280] Clause 51. A combustor according to any one or more of the clauses, wherein the intermediate member or the liner comprises a fence extending into the combustion chamber in the radial direction.

[0281] Item 52. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a front liner segment; a rear liner segment, the rear liner segment being disposed downstream of the front liner segment relative to a flow direction through the combustor, the front liner segment and the rear liner segment at least partially defining a combustion chamber; and an intermediate member, the intermediate member being disposed longitudinally between the front liner and the rear liner, the intermediate member being configured to form a movable interface with at least one of the front liner segment and the rear liner segment.

[0282] Clause 53. The burner of any one or more of the clauses, wherein the movable interface comprises one or more piston seals configured to form a sealed interface at the movable interface.

[0283] Clause 54. A combustor according to any one or more of the clauses, wherein the intermediate member comprises a fence extending into the combustion chamber in the radial direction.

[0284] Clause 55. A combustor according to any one or more of the clauses, wherein the intermediate member further includes a secondary fence extending into the combustion chamber upstream of the fence, wherein the secondary fence is spaced apart from the fence in the longitudinal direction, wherein the secondary fence is spaced apart from the front liner in the longitudinal direction by a first deflection distance, the first deflection distance corresponding to the deflection of the front liner during operation.

[0285] Clause 56. The combustor of any one or more of the clauses, wherein the intermediate member comprises a channel extending between the fence and the secondary fence in the radial direction, wherein the channel is in fluid communication with a dilution slot of the liner.

[0286] Clause 57. A combustor according to any one or more of the clauses, wherein the front liner segment and the rear liner segment define one or more dilution slots, wherein the intermediate member is disposed in at least one of the one or more dilution slots, and wherein the intermediate member includes one or more fluid passages, and the one or more fluid passages are configured to connect a cooling medium to the at least one of the one or more dilution slots.

[0287] Clause 58. The combustor according to any one or more of the clauses, wherein the intermediate member is biased in the radial direction by a support extending from a casing of the gas turbine engine.

[0288] Clause 59. The combustor of any one or more of the clauses, wherein the intermediate member is free floating relative to at least one of the forward liner segment or the aft liner segment.

[0289] Clause 60. A combustor according to any one or more of the clauses, wherein at least one of the front liner segment or the rear liner segment is configured to deflect in at least one of the longitudinal direction and the radial direction according to thermal loading during operational use, and wherein the intermediate member is configured to reduce deflection of the front liner segment or the rear liner segment.

[0290] Clause 61. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a liner, the liner at least partially defining a combustion chamber, the liner further defining a gap; an intermediate member, the intermediate member at least partially disposed within the gap of the liner and connected to the combustion chamber fluid; and a support member extending from the intermediate member, the support member being configured to extend to a casing of the gas turbine engine to hold the intermediate member in an appropriate position relative to the casing.

[0291] Clause 62. A burner according to any one or more of the clauses, wherein the support is integral with the intermediate member.

[0292] Clause 63. A burner according to any one or more of the clauses, wherein the support comprises a discrete component from the intermediate member.

[0293] Clause 64. A burner according to any one or more of the clauses, wherein the support comprises a metal sheet.

[0294] Clause 65. The burner of any one or more of the clauses, wherein the support is coupled to the housing at a location along a rear side of the housing or in the middle of the housing.

[0295] Clause 66. The combustor of any one or more of the clauses, wherein the support defines one or more windows configured to allow a cooling medium to pass through the support to a location downstream of the support.

[0296] Clause 67. The combustor of any one or more of the clauses, wherein the intermediate member is free floating relative to the liner.

[0297] Clause 68. The combustor of any one or more of the clauses, wherein the intermediate member comprises a fence configured to extend into the combustion chamber in the radial direction, the fence configured to direct a cooling medium into the combustion chamber.

[0298] Clause 69. A burner according to any one or more of the clauses, wherein the intermediate member further comprises a secondary fence extending into the combustion chamber upstream of the fence, and wherein the secondary fence is spaced apart from the fence in the longitudinal direction.

[0299] Clause 70. A combustor according to any one or more of the clauses, wherein the liner comprises a front liner segment and a rear liner segment, wherein the intermediate member is disposed between the front liner segment and the rear liner segment, and wherein the intermediate member is configured to have a slidable interface with at least one of the front liner segment and the rear liner segment.

[0300] Clause 71. The combustor of any one or more of the clauses, wherein at least one of the forward liner segment or the aft liner segment comprises a protrusion extending through the gap and configured to control a size of the gap.

[0301] Clause 72. A combustor according to any one or more of the clauses, wherein the liner comprises a front liner segment and a rear liner segment separated from each other by the gap, and wherein the intermediate member is connected to one of the front liner segment or the rear liner segment by one or more piston seals.

[0302] Clause 73. The burner of any one or more of the clauses, wherein the support comprises a spring loaded connection configured to bias the intermediate member.

[0303] Clause 74. A burner according to any one or more of the clauses, wherein at least one of the one or more piston seals comprises at least one purge hole configured to allow purging of excess cooling medium prior to entering the combustion chamber.

[0304] Clause 75. The combustor of any one or more of the clauses, wherein the intermediate member comprises at least one seal configured to form a sealed interface relative to the liner.

[0305] Clause 76. An intermediate component in a combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor having a liner defining a combustion chamber, the intermediate component comprising: an annular body configured to be disposed at an opening in the liner; and a support member configured to extend between the intermediate component and a casing of the gas turbine engine.

[0306] Clause 77. An intermediate member according to any one or more of the clauses, wherein the annular body is free floating relative to the liner.

[0307] Clause 78. An intermediate member according to any one or more of the clauses, wherein the annular body is coupled to the housing via the support, and wherein the support is configured to bias the annular body into the liner in a radial direction.

[0308] Clause 79. An intermediate member according to any one or more of the clauses, wherein the annular body comprises a plurality of spokes extending from the liner to the casing of the gas turbine engine, and wherein the support member comprises an annular support ring coupled to the plurality of spokes.

[0309] Clause 80. An intermediate member according to any one or more of the clauses, wherein the annular body is spaced apart from the liner by one or more spacers, and wherein the spacers are configured to provide a movable interface between the annular body and the liner.

[0310] Clause 81. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a liner at least partially defining a combustion chamber, the liner including a dilution groove fluidically connected to the combustion chamber; and one or more guides, the one or more guides being configured to redirect a cooling medium into the dilution groove.

[0311] Clause 82. The combustor of any one or more of the clauses, wherein the liner comprises a forward liner segment and an aft liner segment, and wherein the dilution slot is disposed between the forward liner segment and the aft liner segment.

[0312] Clause 83. The combustor of any one or more of the clauses, wherein at least one of the one or more guides is integral with at least one of the forward liner segment and the aft liner segment.

[0313] Clause 84. A combustor according to any one or more of the clauses, wherein the one or more guides include an inclined leading edge surface that is angularly offset from the radial direction by an angle α S , the angle α S At least 1°.

[0314] Clause 85. The combustor of any one or more of the clauses, wherein the one or more guides extend outwardly from the liner in the radial direction.

[0315] Clause 86. The burner of any one or more of the clauses, wherein at least one of the one or more guides comprises a scoop interface.

[0316] Clause 87. The burner of any one or more of the clauses, wherein the one or more guides include a leading edge surface defining one or more rows of windows extending around the burner.

[0317] Clause 88. The combustor of any one or more of the clauses, further comprising a fence extending in the radial direction through the dilution slot into the combustion chamber.

[0318] Clause 89. The burner of any one or more of the clauses, wherein at least one of the one or more guides is disposed at least partially upstream of the fence.

[0319] Clause 90. The combustor of any one or more of the clauses, wherein the dilution slot comprises a plurality of dilution slots extending around the combustion chamber in the circumferential direction.

[0320] Item 91. A liner for a combustor of a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the liner comprising: an annular body configured to at least partially define a combustion chamber of the combustor, wherein the annular body includes a dilution groove extending into the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution groove.

[0321] Clause 92. A liner according to any one or more of the clauses, wherein the one or more guides are integral with the annular body.

[0322] Clause 93. A liner as described in any one or more of the clauses, wherein the one or more guides include one or more rows of cooling holes.

[0323] Clause 94. A liner according to any one or more of the clauses, wherein the front liner segment and the rear liner segment are connected together by a wavy annular body, and the wavy annular body is arranged between the front liner segment and the rear liner segment in the radial direction.

[0324] Clause 95. A liner according to any one or more of the clauses, wherein at least one of the one or more guides is integral with at least one of the front liner segment and the rear liner segment.

[0325] Clause 96. A liner as described in any one or more of the clauses, wherein at least one of the one or more guides comprises a spade interface.

[0326] Clause 97. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a liner at least partially defining a combustion chamber, the liner comprising a dilution groove fluidically connected to the combustion chamber; and a shovel interface configured to redirect a cooling medium into the dilution groove, the shovel interface defining a shovel surface, the shovel surface configured to form an airflow film entering the combustor.

[0327] Clause 98. A combustor according to any one or more of the clauses, wherein the scoop interface extends from the liner in a radially outward direction, and wherein the scoop interface is configured to redirect cooling medium to a fence of the combustor that extends into the combustion chamber.

[0328] Clause 99. A combustor according to any one or more of the clauses, wherein the scoop interface comprises one or more windows configured to allow a cooling medium to pass to the scoop surface, and wherein the one or more windows are arranged in one or more rows extending in the circumferential direction.

[0329] Clause 100. The combustor of any one or more of the clauses, wherein the scoop interface is coupled to an aft liner segment of the liner, and wherein the scoop interface is configured to move relative to a forward liner segment of the liner.

[0330] Clause 101. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising: a liner that at least partially defines a combustion chamber of the gas turbine engine, wherein the liner includes a loop feature.

[0331] Clause 102. A combustor according to any one or more of the clauses, wherein the liner comprises a front liner segment and a rear liner segment separated from each other by one or more dilution slots, and wherein the loop feature of the liner is disposed at a longitudinal position of the liner corresponding to the one or more dilution slots.

[0332] Clause 103. A combustor according to any one or more of the clauses, wherein the front liner segment and the rear liner segment are coupled together by brazing, welding, one or more fasteners, press fit, or the like.

[0333] Clause 104. A burner as described in any one or more of the clauses, wherein the loop feature comprises a plurality of segments interconnected by curved portions.

[0334] Clause 105. The combustor of any one or more of the clauses, wherein the loop feature extends from the liner in at least one of the radial direction or the longitudinal direction.

[0335] Clause 106. The combustor of any one or more of the clauses, wherein the loop feature is configured to absorb deflection of the liner during thermal expansion.

[0336] Clause 107. The combustor of any one or more of the clauses, wherein the loop feature defines one or more fluid passages configured to pass a cooling medium to the combustion chamber.

[0337] Clause 108. The combustor of any one or more of the clauses, wherein the loop feature further comprises a fence extending into the combustion chamber in the radial direction.

[0338] Clause 109. The burner of any one or more of the clauses, wherein the loop feature comprises a spade interface.

[0339] Clause 110. The combustor of any one or more of the clauses, wherein the loop feature is configured to absorb thermal loading during operational use, and wherein the shape or size of the loop feature is configured to change during thermal loading.

[0340] Clause 111. A liner for a combustor of a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending outwardly orthogonally from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the liner comprising: an annular body configured to at least partially define a combustion chamber of the combustor, wherein the annular body comprises: a dilution groove extending to the combustion chamber; and an annular feature configured to absorb deflection during thermal expansion of the liner.

[0341] Clause 112. A liner as described in any one or more of the clauses, wherein the liner comprises a front liner segment and a rear liner segment, wherein the loop feature is integral to one or both of the front liner segment or the rear liner segment.

[0342] Clause 113. A liner as described in any one or more of the clauses, wherein the loop feature is integral with one of the front liner segment or the rear liner segment, and wherein the other of the front liner segment or the rear liner segment is connected to the loop feature by a brazed joint.

[0343] Clause 114. The liner of any one or more of the clauses, wherein the loop feature further comprises a flange, and wherein the other of the front liner segment or the rear liner segment is coupled to the flange.

[0344] Clause 115. A liner as described in any one or more of the clauses, wherein the liner comprises a one-piece structure.

[0345] Clause 116. The liner of any one or more of the clauses, wherein the loop feature comprises a fence configured to extend into the combustion chamber in the radial direction.

[0346] Clause 117. A liner as described in any one or more of the clauses, wherein the loop feature extends away from one or more adjacent portions of the liner in the radial direction.

[0347] Clause 118. The liner of any one or more of the clauses, wherein the loop feature further comprises one or more windows configured to allow a cooling medium to pass to the combustor.

[0348] Clause 119. The liner of any one or more of the clauses, wherein the annular body of the liner further comprises a first set of cooling holes disposed upstream of the loop feature and a second set of cooling holes disposed downstream of the loop feature.

[0349] Clause 120. The liner of any one or more of the clauses, wherein the cooling holes of at least one of the first set of cooling holes or the second set of cooling holes are inclined relative to the liner.

Claims

1. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, It is characterized in that The burner comprises: front lining section; and an aft liner segment disposed downstream of the forward liner segment relative to a flow direction through the combustor, the forward liner segment and the aft liner segment at least partially defining a combustion chamber, and a loop feature disposed between the forward liner segment and the aft liner segment, the loop feature comprising one or more windows disposed radially outward relative to the longitudinal centerline of the forward liner segment and the aft liner segment, wherein the one or more windows are configured to communicate a cooling medium from radially outward of the combustor, between the forward liner segment and the aft liner segment, to the combustion chamber.

2. The burner according to claim 1, It is characterized in that Wherein a portion of one of the front liner segment or the rear liner segment is configured to contact the other of the front liner segment or the rear liner segment via the loop feature at the interface.

3. The burner according to claim 2, It is characterized in that Wherein the interface is a fixed connection between the front lining segment and the rear lining segment.

4. The burner according to claim 2, It is characterized in that The interface is formed by brazing, welding or fasteners.

5. The burner according to claim 1, It is characterized in that The one or more windows include two windows spaced apart from each other in the longitudinal direction.

6. The burner according to claim 1, It is characterized in that Wherein the aft liner segment includes an extension extending in the radial direction, the loop feature being attached to the extension.

7. The burner according to claim 1, It is characterized in that Further included are one or more dilution slots defined between the front liner segment and the rear liner segment.

8. The burner according to claim 1, It is characterized in that Wherein the aft liner segment comprises a fence extending into the combustion chamber in the radial direction.

9. The burner according to claim 8, It is characterized in that Wherein the fence is integral with the rear lining section.

10. The burner according to claim 9, It is characterized in that Wherein the loop feature is integral with the rear liner segment.

Images