Combustor for gas turbine engine

Abstract

A combustor for a gas turbine engine includes a forward liner section and an aft liner section downstream of the forward liner section relative to a flow direction through the combustor. The forward liner section and the aft liner section at least partially define a combustion chamber. Further, the combustor includes a dilution tank frame located between the forward liner section and the aft liner section along a longitudinal centerline of the gas turbine engine. Further, the dilution tank frame defines a plurality of dilution tanks spaced apart from each other in a circumferential direction of the gas turbine engine such that the plurality of dilution tanks provide an annular ring of dilution air to the combustion chamber.

Description

[0001] This application is a divisional application of the invention patent application with application number 202210097922.3 filed on January 26, 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] Gas turbine engines generally include 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 produce 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. The 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] Typically, the combustion section includes an annular burner. Each burner in turn 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 between them. Therefore, the fuel nozzle supplies a fuel and air mixture to the combustion chamber for combustion therein.

[0005] In some configurations, the inner liner and / or outer liner define a plurality of dilution holes located downstream of the fuel nozzle. The dilution holes in turn provide additional air to the combustion chamber to mix with the combustion products from the main area of ​​the combustion chamber and quickly complete the combustion process, thereby reducing NO x However, such dilution holes are usually spaced apart from each other around the circumference of the liner.

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

[0007] Aspects and advantages of the invention 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 invention.

[0008] In one aspect, the present subject matter relates to a combustor for a gas turbine engine. The gas turbine engine in turn defines a longitudinal centerline, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal direction. The combustor includes a front liner segment and an aft liner segment, the aft liner segment being located downstream of the front liner segment relative to a flow direction through the combustor, wherein the front liner segment and the aft liner segment at least partially define a combustion chamber. In addition, the combustor includes a dilution slot frame, which is located between the front liner segment and the aft liner segment along the longitudinal centerline. In addition, the dilution slot frame defines a plurality of dilution slots spaced apart from each other in a circumferential direction, such that the plurality of dilution slots provide an annular ring of dilution air to the combustion chamber.

[0009] In another aspect, the present subject matter relates to a gas turbine engine defining a longitudinal centerline, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal direction. The gas turbine engine includes a compressor; a turbine; and a combustor. The combustor in turn includes a front liner segment and an aft liner segment, the aft liner segment being located 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. In addition, the combustor includes a dilution slot frame located between the front liner and the aft liner along the longitudinal centerline. In addition, the dilution slot frame defines a plurality of dilution slots spaced apart from each other in a circumferential direction, such that the plurality of dilution slots provide an annular ring of dilution air to the combustion chamber.

[0010] These and other features, aspects and advantages of the present invention will be 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 invention and, together with the description, serve to explain the principles of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] A full and enabling disclosure of the present invention, including the best mode thereof, to one of ordinary skill in the art is set forth in the specification with reference to the accompanying drawings, in which:

[0012] Figure 1 is a schematic cross-sectional view of one embodiment of a gas turbine engine;

[0013] Figure 2 is a cross-sectional side view of one embodiment of a combustion section of a gas turbine engine;

[0014] Figure 3 is a partial perspective view of an embodiment of a combustor of a gas turbine engine;

[0015] Figure 4 yes Figure 3 A partial cross-sectional side view of the burner is shown;

[0016] Figure 5is a partial cross-sectional side view of another embodiment of a combustor of a combustion section of a gas turbine engine;

[0017] Figure 6 is a cross-sectional side view of one embodiment of a dilution slot frame for use within a combustor of a combustion section of a gas turbine engine;

[0018] Figure 7 is a front view of one embodiment of a fence for use within a combustor of a combustion section of a gas turbine engine;

[0019] Figure 8 is a front view of another embodiment of a fence for use within a combustor of a combustion section of a gas turbine engine;

[0020] Fig. 9 yes Figure 8 Bottom view of the fence shown;

[0021] Fig.10 is a partial front view of another embodiment of a fence for use within a combustor of a combustion section of a gas turbine engine;

[0022] Fig.11 is a partial front view of yet another embodiment of a fence for use within a combustor of a combustion section of a gas turbine engine;

[0023] Fig.12 is a cross-sectional side view of yet another embodiment of a fence for use within a combustor of a combustion section of a gas turbine engine; and

[0024] Fig.13 is a cross-sectional side view of another embodiment of a fence for use within a combustor of a combustion section of a gas turbine engine.

[0025] Repeat use of reference characters in the present specification and drawings is intended to represent the same or analogous features or elements of the invention. DETAILED DESCRIPTION

[0026] Reference will now be made in detail to exemplary embodiments of the subject matter of the present disclosure, one or more examples of which are shown in the accompanying drawings. Each example is provided by way of explanation 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 to 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 cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0027] 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.

[0028] In addition, the terms "upstream" and "downstream" refer to the relative direction of the fluid flow in the fluid channel. For example, "upstream" refers to the direction from which the fluid flows out, and "downstream" refers to the direction to which the fluid flows.

[0029] In addition, unless otherwise stated, the terms "low", "high" or their respective comparatives (e.g., lower, higher, where applicable) refer to relative speeds within the engine. For example, a "low-pressure turbine" operates at a pressure that is generally lower than a "high-pressure turbine". Alternatively, unless otherwise stated, the above terms may be understood in their highest form. For example, a "low-pressure turbine" may refer to the lowest maximum pressure turbine within a turbine section, while a "high-pressure turbine" may refer to the highest maximum pressure turbine within a turbine section.

[0030] In general, the present subject matter relates to a combustor for a gas turbine engine. As will be described below, the combustor includes a front liner segment and an aft liner segment located downstream of the front liner segment. In this regard, the front liner segment and the aft liner segment at least partially define a combustion chamber in which a fuel and air mixture is burned to produce combustion gases.

[0031] In addition, the combustor includes a dilution slot frame located between the front liner segment and the rear liner segment along the longitudinal centerline of the engine. In this regard, the dilution slot frame defines a plurality of dilution slots spaced apart from each other in a circumferential direction of the engine. For example, in some embodiments, the dilution frame includes a plurality of frame members separating the dilution slots. In addition, in several embodiments, the dilution slots are longer in the circumferential direction than in the longitudinal direction (e.g., at least three times longer). Therefore, unlike conventional combustors that provide discrete jets 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 circulation of dilution air reduces the formation of hot spots in the combustion chamber, thereby further reducing NO x emission.

[0032] Furthermore, in some embodiments, the burner includes a fence located adjacent to the dilution slot frame. More specifically, the fence extends into the combustion chamber in a radial direction. Thus, the fence directs the 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 a faster and more uniform mixing of the dilution air and the combustion gases, thereby further reducing NO x emission.

[0033] Now referring to the accompanying drawings, Figure 1is 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 propfan engine, a turbojet engine, a turboprop engine, a turboshaft gas turbine engine, or any other suitable type of gas turbine engine.

[0034] 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 .

[0035] In general, the engine 10 includes a fan 14, a low pressure (LP) spool 16, and a high pressure (HP) spool 18, which are at least partially surrounded 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 each other in a circumferential direction C and extend outwardly from the fan rotor 22 in a radial direction R. In addition, the LP spool 16 and the HP spool 18 are located 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 each other in the circumferential direction C extend between a casing 28 surrounding the LP spool 16 and the HP spool 18 and the nacelle 20 in the radial direction R. As such, 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 therebetween.

[0036] 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 series 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 located 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 intersecting 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 located 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 intersecting with one or more rows of turbine rotor blades 54.

[0037] 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 positioned concentrically about the LP shaft 56. In some embodiments, 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.

[0038] In some embodiments, the engine 10 may generate thrust to propel the aircraft. More specifically, during operation, air (indicated by arrow 62) enters the 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 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, wherein the rotor blades 46 gradually compress the second portion 68 of the air 62 therein. Next, the second portion 68 of the air 62 flows through the HP compressor 42, wherein the rotor blades 46 continue to gradually compress the second portion 68 of the air 62 therein. 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 produce high temperature and high pressure combustion gases 70. Thereafter, the combustion gases 70 flow through the HP turbine 48, wherein the HP turbine rotor blades 54 extract a first portion of kinetic energy and / or thermal energy therefrom. This energy extraction rotates the HP shaft 58, 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 the kinetic and / or thermal energy therefrom. This energy extraction rotates the LP shaft 56, 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.

[0039] Described above and in Figure 1 The configuration of the gas turbine engine 10 shown in the figure is provided only for the purpose of placing the present subject matter in an exemplary field of use. Therefore, the present subject matter can be easily adapted to any type of gas turbine engine configuration, including other types of aviation-based gas turbine engines, marine-based gas turbine engines, and / or land-based / industrial-based gas turbine engines.

[0040] 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 located outside 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 located downstream of the front liner segment 108 relative to a flow direction of the combustion gases 70 through the combustor 100. In addition, the combustor 100 includes one or more fuel nozzles 112 that supply a mixture of fuel and compressed air 68 to the combustion chamber 106. The fuel and air mixture within the combustion chamber 106 is combusted to produce the combustion gases 70. Although Figure 2 A single annular combustor 100 is shown, but in other embodiments, the combustion section 34 may include multiple combustors 100 .

[0041] In several embodiments, the combustor 100 includes one or more dilution slot frames 114 and / or one or more fences 116 positioned adjacent to the dilution slot frames 114. As will be described below, the dilution slot frames 114 allow dilution air to enter the combustion chamber 106 during operation, which reduces the NOx of the engine 10. x In addition, as will be 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 one dilution slot frame 114 located between the front liner segment 108 and the rear liner segment 110 of the liner 102 and another dilution slot frame 114 located 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 one fence 116 extending outwardly from the liner 102 along the radial direction R and another fence 116 extending inwardly from the outer liner 104 along the radial direction R. However, in alternative embodiments, the combustor 100 may include any other suitable number of dilution slot frames 114 and / or fences 116.

[0042] 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 compressed air 68 exiting the HP compressor 42 is directed into the compressor discharge plenum 120 by the inlet guide vanes 122. The compressed 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.

[0043] Figure 3 and Figure 4 1 are different views of one embodiment of a combustor 100 for a gas turbine engine. As described above, the combustor 100 includes one or more dilution slot frames 114. Specifically, as shown, the dilution slot frame 114 is located between the front liner segment 108 and the rear liner segment 110 along the longitudinal centerline 12 of the engine 10 (i.e., along the longitudinal direction L). Further, as shown, the dilution slot frame 114 defines a plurality of dilution slots 124 spaced apart from one another along a circumferential direction C. In several embodiments, the dilution slots 124 are arranged around the circumference of the combustor 100 such that the dilution slots 124 provide an annular ring of dilution air to the combustion chamber 106. As will be described below, the annular ring of air delivered to the combustion chamber 106 by the dilution slot frame 114 reduces the NOx of the engine 10. x Emissions.

[0044] In general, the dilution slot frame 114 includes various frame members that define each dilution slot 124. For example, as shown, in some embodiments, the dilution slot frame 114 includes front and rear circumferential frame members 126, 128 extending around the combustor 100 in the circumferential direction C. In addition, the rear circumferential frame member 128 is spaced apart from and located behind the front circumferential frame member 126 (i.e., with respect to the flow direction of the combustion gases 70). The dilution slot frame 114 further includes a plurality of longitudinal frame members 130 extending from the front circumferential frame member 126 to the rear circumferential frame member 128 along the longitudinal axis 12 (i.e., in the longitudinal direction L). In addition, the longitudinal frame members 130 are spaced apart from each other in the circumferential direction C around the circumference of the combustor 100. Therefore, in such embodiments, each dilution slot 124 is defined between the front circumferential frame member 126 and the rear circumferential frame member 128 in the longitudinal direction L, and is defined between a pair of adjacent longitudinal frame members 130 in the circumferential direction C. Thus, each dilution slot 124 extends in the longitudinal direction L and the circumferential direction C. However, as will be described below, the dilution slot frame 114 may have any other suitable configuration defining a plurality of dilution slots 124 that provide an annular ring of dilution air to the combustion chamber 106 .

[0045] The dilution slots 124 may have any suitable dimensions that allow an annular ring of air to be delivered to the combustion chamber 106. For example, in some embodiments, each dilution slot 124 is at least three times longer in the circumferential direction C than in the longitudinal direction L.

[0046] Additionally, the dilution slot frame 114 may define any suitable number of dilution slots 124 that allow an annular ring of air to be delivered to the combustion chamber 106. For example, in some embodiments, the dilution slot frame 114 may define a number of dilution slots 124 that is 0.2 to 20 times the number of fuel nozzles 112 within the combustor 100.

[0047] Furthermore, the dilution slot frame 114 may be coupled to the front liner segment 108 and the aft liner segment 110 in any suitable manner. For example, as shown, in several embodiments, the dilution slot frame 114 may be coupled to the aft liner segment 110 via a gasket 132. In some embodiments, the aft liner segment 110 and the gasket 132 define a plurality of cooling holes 134 spaced apart from one another along the circumferential direction C. Thus, the cooling holes 134 may fluidly couple the compressor discharge plenum 120 and the combustion chamber 106. For example, in one embodiment, the cooling holes 134 may be spaced apart from one another by a distance of one to three times the diameter of the hole 134.

[0048] Additionally, as described above, the combustor 100 may include one or more fences 116. For example, as shown, the fence 116 is positioned adjacent to the dilution slot frame 114 and extends in a radial direction R to (e.g., inwardly) the combustion chamber 106. Specifically, in several embodiments, the fence 116 is located behind the dilution slot 124 (i.e., relative to the flow direction of the combustion gases 70). In this regard, as will be described below, the fence 116 directs the dilution air entering the combustion chamber via the dilution slot 124 to the center of the combustion chamber 106. In some embodiments, as will be described below, the fence 116 may be positioned adjacent to the dilution slot frame 114 and may extend in a radial direction R to (e.g., inwardly) the combustion chamber 106. Figure 3 and Figure 4 As shown, the fence 116 extends into the combustion chamber 106 such that the fence 116 is oriented perpendicular to the longitudinal axis 12 of the engine 10. In other embodiments, such as Figure 5 As shown, the fence 116 extends into the combustion chamber 106 such that the fence 116 is oriented at an oblique angle relative to the longitudinal axis 12 of the engine 10. For example, in such an embodiment, the fence 116 may be angled in the direction of flow of the combustion gases 70 or in a direction opposite to the direction of flow of the combustion gases 70. Additionally, in the illustrated embodiment, the fence 116 is integrally formed with the dilution slot frame 114. However, in alternative embodiments, the fence and the dilution slot frame 114 may be separate components.

[0049] like Figure 4 As shown, the dilution slot frame 116 and the fence 116 provide dilution air (indicated by arrows 136) to the combustion chamber 106 of the combustor 100 to reduce the NO x More specifically, as shown, dilution air 136 from the compressor discharge plenum 120 flows through the dilution slots 124 into the combustion chamber 106 downstream of the fuel nozzles 112. Unlike conventional combustors that provide discrete jets of dilution air to the combustion chamber, the arrangement of the dilution slots 124 around the circumference of the combustor 100 and the size / shape of the dilution slots 124 provide an annular ring of dilution air 136 to the combustion chamber 106. This annular ring of dilution air 136 in turn prevents the formation of hot spots within the combustion chamber 106, thereby allowing for greater reductions in NOx emissions than conventional combustors. x In addition, the fence 116 directs the dilution air 136 entering the combustion chamber 106 via the dilution slots 124 toward the center of the combustion chamber 106. In addition, the fence 116 increases turbulence within the combustion chamber 106. In this regard, the fence 116 provides for faster and more uniform mixing of the dilution air 136 and the combustion chamber gases 70, thereby further reducing NO emissions. x Additionally, cooling holes 134 may deliver compressed air from the compressor discharge plenum 120 to the rear side of the fence 116 , thereby cooling the fence 116 .

[0050] Figure 6 Another embodiment of the dilution tank frame 114 is shown. Figures 3 to 5 The embodiment of the dilution tank frame 114 shown, Figure 6 The illustrated dilution slot frame 114 defines a plurality of dilution slots 124 spaced apart from one another in the circumferential direction C. Figures 3 to 5 The illustrated embodiments of the dilution tank frame 114 are different. Figure 6 The illustrated dilution slot frame 114 defines multiple rows of dilution slots 124. The multiple rows of dilution slots 124 are in turn spaced apart from each other along the longitudinal axis 12 (i.e., in the longitudinal direction L). For example, as shown, in the illustrated embodiment, the dilution slot frame 114 defines a first or front row 138 of dilution slots 124, a second or rear row 140 of dilution slots 124, and a third or center row 142 of dilution slots 124. In this regard, each dilution slot 124 in the front row 138 and the rear row 140 extends in the radial direction R and in the circumferential direction C. Each dilution slot 124 in the center row 142 is located between the dilution slots 124 in the front row 138 and the rear row 140 along the longitudinal centerline 12 (i.e., in the longitudinal direction L). Therefore, each dilution slot 124 in the center row 142 extends along the longitudinal centerline 12 (i.e., in the longitudinal direction L) and in the circumferential direction C. However, in alternative embodiments, the dilution slot frame 114 may have any other suitable configuration such that the frame 114 defines a plurality of dilution slots 124 to provide an annular ring of dilution air to the combustion chamber 106 .

[0051] Figures 7 to 13 Various embodiments of fence 116 are shown. For example, Figure 7 As shown, in one embodiment, the fence 116 may include a first fence segment 144 and a second fence segment 146. The segments 144, 146 in turn form an arcuate wall that contacts each other at a first joint 148 and a second joint 150 to form a continuous ring around the circumference of the combustor 100. The joints 148, 150 may be butt joints that overlap each other through appropriate mechanical arrangements. Using multiple fence segments 144, 146 to form the fence 116 reduces the hoop stress experienced by the fence 116.

[0052] Figure 8 and Fig. 9 Another embodiment of the fence 116 is shown. As shown, the fence 116 is formed of a plurality of fence segments 152. Specifically, each fence segment 152 is aligned with one another along the longitudinal centerline 12 (i.e., in the longitudinal direction L) to form a continuous ring around the circumference of the combustor 100. In addition, each pair of adjacent fence segments partially overlap one another in the circumferential direction 152, thereby forming a scarf joint 154. Using a plurality of fence segments 152 to form the fence 116 reduces the hoop stress experienced by the fence 116.

[0053] Fig.10Another embodiment of the fence 116 is shown. As shown, in the illustrated embodiment, the fence 116 has a comb-like configuration. Specifically, the fence 116 includes an annular base 156 coupled to the dilution tank frame 114 and / or the back liner segment 110. In addition, the fence 116 includes a plurality of teeth 158 extending from the base 156 in the radial direction R, and the teeth 158 are spaced apart from each other in the circumferential direction C.

[0054] Fig.11 Another embodiment of the fence 116 is shown. As shown, in the illustrated embodiment, the fence 116 has a brush-like configuration. Specifically, the fence 116 includes an annular base 160 coupled to the dilution tank frame 114 and / or the rear liner segment 110. In addition, the fence 116 includes a plurality of bristles 162 extending from the base 160 in the radial direction R, and the bristles 162 are spaced apart from each other in the circumferential direction C and the longitudinal direction L.

[0055] Fig.12 Yet another embodiment of the enclosure 116 is shown. As shown, in the illustrated embodiment, the enclosure 116 includes an interior honeycomb portion 164. Specifically, the honeycomb portion 164 includes a plurality of walls 168 that define a plurality of voids or spaces 166 within the interior of the enclosure 116. The honeycomb portion 164 reduces the weight of the enclosure 116, thereby reducing the weight of the engine 10.

[0056] Fig.13 Another embodiment of the fence 116 is shown. As shown, in the illustrated embodiment, the fence 116 includes a plurality of ribs 168 (one is shown) that reinforce the fence 116. Specifically, the ribs 168 extend downstream (i.e., relative to the flow direction of the combustion gases 70 through the combustion chamber 100) from the rear side 170 of the fence 116. In addition, the ribs 168 increase the surface area of ​​the rear side 170 of the fence 116, thereby increasing the effectiveness of the cooling provided to the fence 116 through the cooling holes 134 ( Figure 3-5 ).

[0057] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to one skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims.

[0058] Further aspects of the invention are provided by the subject matter of the following clauses:

[0059] A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline, a radial direction and a circumferential direction, the radial direction extending orthogonally outward from the longitudinal centerline, the circumferential direction extending concentrically around the longitudinal direction, the combustor comprising: a front liner segment; an aft liner segment, the aft liner segment being located 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 a dilution slot frame, the dilution slot frame being located between the front liner segment and the aft liner segment along the longitudinal centerline, the dilution slot frame defining a plurality of dilution slots spaced apart from each other in a circumferential direction, such that the plurality of dilution slots provide an annular ring of dilution air to the combustion chamber.

[0060] The combustor according to one or more of these clauses, wherein the dilution slot frame includes a plurality of frame members extending along the longitudinal centerline and spaced apart from each other in a circumferential direction such that each pair of adjacent frame members of the plurality of frame members partially defines one of the plurality of dilution slots.

[0061] The combustor according to one or more of these clauses, wherein each of the plurality of dilution slots is at least three times longer in a circumferential direction than in a longitudinal direction.

[0062] The combustor according to one or more of these clauses, further comprising: a fence positioned adjacent to the dilution slot frame and extending into the combustion chamber in a radial direction.

[0063] A burner according to one or more of these clauses, wherein the fence extends inwardly from the dilution slot frame into the combustion chamber in a radial direction.

[0064] A burner according to one or more of these clauses, wherein the fence is oriented perpendicular to the longitudinal axis.

[0065] A burner according to one or more of these clauses, wherein the fence is oriented at an oblique angle relative to the longitudinal axis.

[0066] The burner according to one or more of these clauses, wherein the fence forms a continuous ring extending around the burner in a circumferential direction.

[0067] A burner according to one or more of these clauses, wherein the fence comprises a plurality of segments.

[0068] The combustor of one or more of these clauses, wherein a first segment of the plurality of segments is at least partially aligned with a second segment of the plurality of segments along a longitudinal centerline.

[0069] The combustor according to one or more of these clauses, wherein the first segment partially overlaps the second segment in a circumferential direction.

[0070] The burner according to one or more of these clauses, wherein the fence comprises an annular base and a plurality of teeth extending from the base in a radial direction, the plurality of teeth being spaced apart from each other in a circumferential direction.

[0071] A burner according to one or more of these clauses, wherein the fence includes a honeycomb portion.

[0072] A burner according to one or more of these clauses, wherein the fence comprises a plurality of ribs extending downstream in the direction of flow through the burner.

[0073] A burner according to one or more of these clauses, wherein the fence comprises an annular base and a plurality of bristles extending from the base in a radial direction.

[0074] The combustor of one or more of these clauses, wherein a first dilution slot of the plurality of dilution slots is spaced apart from a second dilution slot of the plurality of dilution slots along the longitudinal centerline.

[0075] A combustor according to one or more of these clauses, wherein the first dilution slot and the second dilution slot extend in a radial direction and a circumferential direction, the plurality of dilution slots include a third dilution slot, the third dilution slot is located between the first dilution slot and the second dilution slot along the longitudinal centerline, and the third dilution slot extends along the longitudinal centerline and the circumferential direction.

[0076] The combustor according to one or more of these clauses further comprises: a gasket connecting the dilution slot frame and the aft liner.

[0077] According to the combustor of one or more of these clauses, the gasket and the aft liner define a plurality of cooling holes.

[0078] A gas turbine engine, the gas turbine engine defines a longitudinal centerline, a radial direction and a circumferential direction, the radial direction extends orthogonally outward from the longitudinal centerline, and the circumferential direction extends concentrically around the longitudinal direction, the gas turbine engine includes: a compressor; a turbine; and a combustor, the combustor includes: a front liner segment; an aft liner segment, the aft liner segment is located downstream of the front liner segment relative to the flow direction through the combustor, the front liner segment and the aft liner segment at least partially define a combustion chamber; and a dilution slot frame, the dilution slot frame is located between the front liner and the aft liner along the longitudinal centerline, the dilution slot frame defines a plurality of dilution slots spaced apart from each other in the circumferential direction, so that the plurality of dilution slots provide an annular ring of dilution air to the combustion chamber.

Claims

1. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline, a radial direction and a circumferential direction, the radial direction extending orthogonally outward from the longitudinal centerline, the circumferential direction extending concentrically around the longitudinal direction, characterized in that: The burner comprises: Front lining section; an aft liner segment located 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; a dilution slot frame located between the forward liner segment and the aft liner segment along the longitudinal centerline, the dilution slot frame defining a plurality of dilution slots spaced apart from one another in the circumferential direction such that the plurality of dilution slots provide an annular ring of dilution air to the combustion chamber; and A fence is positioned adjacent to the dilution slot frame and extends into the combustion chamber in the radial direction, the fence forming a continuous ring extending around the combustor in the circumferential direction.

2. The burner according to claim 1, characterized in that The dilution slot frame includes a plurality of frame members extending along the longitudinal centerline and spaced apart from one another along the circumferential direction such that each pair of adjacent frame members of the plurality of frame members partially defines one of the plurality of dilution slots.

3. The burner according to claim 1, characterized in that in, Each of the plurality of dilution slots is at least three times longer in the circumferential direction than in the longitudinal direction.

4. The burner according to claim 1, characterized in that The fence extends inwardly from the dilution slot frame into the combustion chamber along the radial direction.

5. The burner according to claim 1, characterized in that Wherein the fence is oriented perpendicular to the longitudinal centerline.

6. The burner according to claim 1, characterized in that Wherein the fence is oriented at an oblique angle relative to the longitudinal centerline.

7. The burner according to claim 1, characterized in that Wherein the fence comprises a plurality of segments.

8. The burner according to claim 7, characterized in that Wherein a first segment of the plurality of segments is at least partially aligned with a second segment of the plurality of segments about the longitudinal centerline.

9. The burner according to claim 8, characterized in that The first section partially overlaps with the second section in the circumferential direction.

10. The burner according to claim 1, characterized in that The fence includes an annular base and a plurality of teeth extending from the base in the radial direction, and the plurality of teeth are spaced apart from each other in the circumferential direction.

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