Combustor with alternating dilution grid

Abstract

A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. At least one of the outer liner and the inner liner has an upstream liner portion and a downstream liner portion with an annular gap therebetween. At least one dilution flow assembly is arranged across the annular gap. The at least one dilution flow assembly includes an upstream liner panel and a downstream liner panel with a dilution opening disposed therebetween, and a plurality of dilution grid members arranged within the dilution opening and extending into the combustion chamber. The plurality of dilution grid members are arranged in a continuous arrangement in a circumferential direction and are arranged such that consecutive dilution grid members are alternately offset in an axial direction.

Description

Technical Field

[0001] This disclosure relates to the dilution of combustion gases in the combustion chamber of a gas turbine engine. More specifically, this disclosure relates to a combustor having alternating dilution grids for diluting the combustion gases. Background Technology

[0002] In conventional gas turbine engines, it is known to provide a dilution airflow to the combustion chamber downstream of the main combustion zone. Typically, an annular combustor liner may include an inner liner and an outer liner, forming the combustion chamber between them. The inner and outer liners may include dilution orifices through the liner, which provide an airflow (i.e., a dilution jet) from a passage surrounding the annular combustor liner into the combustion chamber. Some applications are known to use circular orifices to provide a dilution airflow to the combustion chamber. The airflow through the circular dilution orifices in a conventional combustor mixes with the combustion gases within the combustion chamber to provide quenching of the combustion gases. The high-temperature region seen behind the dilution jet (i.e., the wake region of the dilution jet) is associated with the formation of high nitrogen oxides (NOx). Furthermore, the circular dilution air jet does not diffuse laterally, thus generating high temperatures between the dilution jets, which also contributes to the formation of high NOx. Attached Figure Description

[0003] The features and advantages of this disclosure will be apparent from the following description of various exemplary embodiments, as shown in the accompanying drawings, wherein similar reference numerals generally denote the same, functionally similar and / or structurally similar elements.

[0004] Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine according to one aspect of this disclosure.

[0005] Figure 2 This is a cross-sectional side view of an exemplary combustion section according to one aspect of this disclosure.

[0006] Figure 3 This is a top view depicting a portion of an exemplary dilution flow component according to one aspect of this disclosure, taken from... Figure 2 The view in Figure 3-3 Or AA.

[0007] Figure 4 It is based on one aspect of this disclosure. Figure 1 and Figure 2 The diagram shows a partial cross-sectional view of the burner taken from plane 4-4.

[0008] Figure 5 It is based on one aspect of this disclosure. Figure 3 A cross-sectional view of an exemplary dilution flow assembly taken from plane 5-5.

[0009] Figure 6It is based on one aspect of this disclosure. Figure 3 A cross-sectional view of an exemplary dilution flow assembly taken from plane 6-6.

[0010] Figure 7 It is based on one aspect of this disclosure. Figure 3 Rear view of a partial cross-section of the dilution flow assembly, taken from plane 7-7.

[0011] Figures 8A to 8E Various shapes of dilution grid members according to aspects of this disclosure are depicted.

[0012] Figure 9 It is based on another aspect of this disclosure. Figure 3 A cross-sectional view of the alternative arrangement of the dilution flow assembly, taken from plane 5-5.

[0013] Figure 10 It is based on another aspect of this disclosure. Figure 3 A cross-sectional view of the alternative arrangement of the dilution flow assembly, taken at plane 5-5.

[0014] Figure 11 It is based on another aspect of this disclosure. Figure 3 A partial cross-sectional view of another arrangement of the dilution flow assembly, taken from plane 5-5.

[0015] Figure 12 It is based on another aspect of this disclosure. Figure 3 A partial cross-sectional view of another arrangement of the dilution flow assembly, taken from plane 6-6.

[0016] Figure 13 This is a top view depicting a portion of another exemplary dilution flow component according to another aspect of this disclosure, taken from... Figure 3 The view in Figure 3-3 Or AA.

[0017] Figure 14 It is based on another aspect of this disclosure. Figure 3 A partial cross-sectional view of another exemplary dilution flow component, taken from plane 5-5. Detailed Implementation

[0018] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the art will recognize that other components and configurations can be used without departing from the spirit and scope of this disclosure.

[0019] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of individual components.

[0020] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction in which the fluid flows.

[0021] In the combustion section of a turbine engine, air flows through an outer passage surrounding the burner liner and through an inner passage surrounding the burner liner. Air typically flows from the upstream end to the downstream end of the burner liner. Some of the airflow in the outer and inner passages is diverted through dilution orifices in the burner liner and enters the combustion chamber as dilution air. One purpose of the dilution airflow is to cool (i.e., quench) the combustion gases before they enter the turbine section. However, the combustion products from the main combustion zone must be quenched quickly and effectively to minimize the high-temperature region, thereby reducing NOx emissions from the combustion system.

[0022] This disclosure aims to reduce NOx emissions by improving the dilution quenching of hot combustion gases from the main combustion zone. According to this disclosure, a burner liner includes a dilution flow assembly connecting an upstream liner portion and a downstream liner portion, wherein the dilution flow assembly includes a plurality of dilution grid members alternately arranged within a dilution opening. The dilution grid members extend circumferentially around the burner liner and are alternately arranged upstream and downstream. In various arrangements, the upstream dilution grid members allow dilution air to penetrate deeper into the combustion chamber and can be arranged at an angle to provide dilution air in an upstream direction. As a result, the upstream dilution grid members can provide greater turbulence for mixing with the combustion gases, thereby providing better combustion gas quenching. The downstream dilution grid members can provide dilution air closer to the liner downstream of the dilution zone for faster reattachment of the dilution air and better cooling of the liner. Consequently, better mixing of the dilution air with the combustion gases and higher turbulence can be achieved, thereby reducing NOx emissions.

[0023] Now refer to the attached diagram, Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10, referred to herein as "engine 10," which can be incorporated into various embodiments of this disclosure. Although further described below with reference to turbofan engines, the invention is also applicable to general turbomachinery, including turbojet engines, turboprop engines, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Figure 1 As shown, engine 10 has an axial centerline axis 12 extending from an upstream end 98 to a downstream end 99 for reference. Typically, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0024] The core engine 16 typically includes a housing 18 defining an annular inlet 20. The housing 18 surrounds or at least partially forms, in a series flow relationship, a compressor section (22 / 24), a combustor 26, a turbine section (28 / 30), and an injection exhaust nozzle section 32. The compressor section (22 / 24) has a turbocharger or low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24. The turbine section (28 / 30) includes a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30. A high-pressure (HP) rotor shaft 34 drivesly connects the HP turbine 28 to the HP compressor 24. A low-pressure (LP) rotor shaft 36 drivesly connects the LP turbine 30 to the LP compressor 22. The rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In certain embodiments, such as Figure 1 As shown, the LP rotor shaft 36 can be connected to the fan shaft 38 via a reduction gear 40, for example in an indirect drive configuration or a gear drive configuration. In other embodiments, although not shown, the engine 10 may also include an intermediate pressure (IP) compressor and a turbine that rotates with the intermediate pressure shaft.

[0025] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan housing or nacelle 44 circumferentially surrounds at least a portion of the fan assembly 14 and / or the core engine 16. In one embodiment, the nacelle 44 may be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. Furthermore, at least a portion of the nacelle 44 may extend externally to the core engine 16 to define a bypass airflow passage 48 therebetween.

[0026] Figure 2 Is it like this? Figure 1 A cross-sectional side view of an exemplary combustor 26 of the core engine 16 shown. Figure 2 As shown, the burner 26 can typically define a burner centerline 111, which can correspond to the axial centerline axis 12. Figure 1 ),and Figure 2A partial cross-sectional view is depicted, showing a burner 26 extending circumferentially around a burner centerline 111. The burner 26 also generally defines an axial direction (L) along the burner centerline 111, a radial direction (R) extending from the burner centerline 111, and a circumferential direction (C) extending around the burner centerline 111. The burner 26 includes a burner bushing 50 having an inner bushing 52 and an outer bushing 54, a cowling 60, and a dome assembly 56. The outer bushing 54 and the inner bushing 52 extend circumferentially around the burner centerline 111. The dome assembly 56 extends radially between the outer bushing 54 and the inner bushing 52, and also extends circumferentially around the burner centerline 111. The inner bushing 52, the outer bushing 54, and the dome assembly 56 together define a combustion chamber 62 that extends circumferentially around the burner centerline 111. Both the inner liner 52 and the outer liner 54 extend from the upstream end 131 of the combustion chamber 62 to the downstream end 133 of the combustion chamber 62. The combustion chamber 62 may more specifically define various regions, including a main combustion zone 71, in which the initial chemical reactions of the fuel-oxidant mixture and / or the recirculation of the combustion gases 86 may occur, before flowing further downstream to a dilution zone 72. In the dilution zone 72, as will be described in more detail below, the combustion gases 86 may flow through the turbine inlet 68 to reach the HP turbine 28 and the LP turbine 30 (…). Figure 1 It is mixed with compressed air 82(c) beforehand.

[0027] It can be seen that the outer bushing 54 includes an upstream bushing portion 100 extending from the upstream end 131 of the combustion chamber 62 to the dilution zone 72 of the combustion chamber 62, a downstream bushing portion 104 extending from the dilution zone 72 of the combustion chamber 62 to the downstream end 133 of the combustion chamber 62, and an annular gap 108 of the outer bushing 54 passing through the dilution zone 72. As will be described in more detail below, the outer bushing dilution flow assembly 92 crosses the annular gap 108 to connect the upstream bushing portion 100 and the downstream bushing portion 104 of the outer bushing 54. Similarly, it can be seen that the inner liner 52 includes an upstream liner portion 102 extending from the upstream end 131 of the combustion chamber 62 to the dilution zone 72 of the combustion chamber 62, a downstream liner portion 106 extending from the dilution zone 72 of the combustion chamber 62 to the downstream end 133 of the combustion chamber 62, and an inner liner annular gap 110 passing through the inner liner 52 at the dilution zone 72. The inner liner dilution flow assembly 94 spans the inner liner annular gap 110 to connect the upstream liner portion 102 and the downstream liner portion 106. Both the outer liner dilution flow assembly 92 and the inner liner dilution flow assembly 94 extend circumferentially around the burner centerline 111. Various aspects of the outer liner dilution flow assembly 92 and the inner liner dilution flow assembly 94 will be described in more detail below.

[0028] like Figure 2As shown, the inner bushing 52 can be installed within the inner housing 65, and the outer bushing 54 can be installed within the outer housing 64. An outer oxidizer flow passage 88 is defined between the outer housing 64 and the outer bushing 54, and an inner oxidizer flow passage 90 is defined between the inner housing 65 and the inner bushing 52. Typically, the outer bushing dilution flow assembly 92 and the inner bushing dilution flow assembly 94 provide compressed air 82(c) flows from the outer oxidizer flow passage 88 and the inner oxidizer flow passage 90, respectively, into the dilution zone 72 of the combustion chamber 62. The compressed air 82(c) flow can therefore be used to provide quenching of the combustion gases 86 in the dilution zone 72, thereby cooling the combustion gas 86 flow entering the turbine section (28 / 30).

[0029] exist Figure 2 In the cross-sectional view, it can be seen that the burner 26 includes a swirler assembly 58 and a fuel nozzle assembly 70 connected to the swirler assembly 58. However, it is well known that the burner 26 includes a plurality of swirler assemblies 58 connected to corresponding openings (not shown) in the dome assembly 56, the plurality of swirler assemblies 58 being circumferentially spaced around the burner centerline 111. Similarly, a plurality of fuel nozzle assemblies 70 are provided for the corresponding plurality of swirler assemblies 58. Therefore, Figure 2 The cross-sectional view represents only one of the multiple cyclone assembly 58 and fuel nozzle assembly 70.

[0030] During the operation of engine 10, common reference Figure 1 and 2 As indicated by the arrows, a volume of air 73 enters the engine 10 from the upstream end 98 through the relevant inlet 76 of the nacelle 44 and / or fan assembly 14. As the volume of air 73 passes through the fan blades 42, a portion of the air 73, as indicated by the arrow 78, is directed or guided into the bypass airflow passage 48, while another portion of the air 80, as indicated by the arrows, is directed or guided into the LP compressor 22. The air 80 is gradually compressed as it flows through the LP compressor 22 and the HP compressor 24 towards the combustor 26.

[0031] refer to Figure 2The compressed air 82, as schematically indicated by the arrow, flows into the diffuser cavity 84 of the burner 26 and pressurizes the diffuser cavity 84. A first portion of the compressed air 82, as schematically indicated by arrow 82(a), flows from the diffuser cavity 84 into the pressure chamber 66 within the shroud 60, where it is rotated by the vortex assembly 58 and mixed with fuel supplied by the fuel nozzle assembly 70 to produce a swirling fuel / oxidizer mixture 85, which is then ignited and burned to produce combustion gases 86. The swirling fuel / oxidizer mixture 85 can swirl around the vortex centerline 95 in the vortex flow direction 97, and can rotate clockwise or counterclockwise around the vortex centerline 95. A second portion of the compressed air 82 entering the diffuser cavity 84, as schematically indicated by the arrow, can be used for various purposes other than combustion. For example, as... Figure 2 As shown, compressed air 82(b) can be directed into the outer oxidizer flow passage 88 and the inner oxidizer flow passage 90. A portion of the compressed air 82(b), schematically shown by an arrow as compressed air 82(c), can then be directed from the outer oxidizer flow passage 88 through the outer bushing dilution flow assembly 92 and into the dilution zone 72 of the combustion chamber 62 to provide quenching of the combustion gases 86 in the dilution zone 72. The compressed air 82(c) can also provide turbulence to the flow of the combustion gases 86, thereby improving the mixing of the compressed air 82(c) with the combustion gases 86. A similar flow is sent from the inner oxidizer flow passage 90 through the inner bushing dilution flow assembly 94 of the inner bushing 52. Furthermore, or alternatively, at least a portion of the compressed air 82(b) can be drawn from the diffuser cavity 84 through various flow passages (not shown) to provide cooling air to at least one of the HP turbine 28 or the LP turbine 30.

[0032] Return to common reference Figure 1 and Figure 2 The combustion gases 86 generated in combustion chamber 62 flow from burner 26 into HP turbine 28, thereby rotating HP rotor shaft 34 and supporting the operation of HP compressor 24. Figure 1 As shown, the combustion gases 86 are then directed through the LP turbine 30, thereby rotating the LP rotor shaft 36, which in turn supports the operation of the LP compressor 22 and / or the rotation of the fan shaft 38. The combustion gases 86 are then discharged through the injection exhaust nozzle section 32 of the core engine 16 to provide propulsion at the downstream end 99.

[0033] Figure 3 This is a top view depicting a portion of an exemplary dilution flow assembly according to one aspect of this disclosure, such as an outer bushing dilution flow assembly 92. It is worth noting that... Figure 3 The top view also applies to the inner liner dilution flow assembly 94 of the inner liner 52. Figure 3 The view can also be with Figure 2 The AA view shown is the same. Therefore, in Figure 3 In this drawing, some elements are depicted using reference numerals applicable to the outer liner dilution flow assembly 92, while corresponding elements of the inner liner dilution flow assembly 94 are depicted in parentheses. Elements without corresponding parenthetical elements apply to both the outer liner dilution flow assembly 92 and the inner liner dilution flow assembly 94. Figure 3 As shown, the outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94) includes an upstream bushing plate 112 and a downstream bushing plate 114. The upstream bushing plate 112 is connected or engaged with the upstream bushing portion 100 of the outer bushing (the upstream bushing portion 102 of the inner bushing), and the downstream bushing plate 114 is connected or engaged with the downstream bushing portion 104 of the outer bushing (the downstream bushing portion 106 of the inner bushing). A dilution opening 118 is located in the annular gap 108 of the outer bushing (the annular gap 110 of the inner bushing) (…). Figure 2 The dilution opening 118 is located between the upstream bushing 112 and the downstream bushing 114. The width of the dilution opening 118 may be the same circumferentially around the outer bushing 54 or the inner bushing 52, or alternatively, the width of the dilution opening 118 may vary circumferentially to provide more or less dilution air at different locations around the combustion chamber 62. A plurality of ribs 116 are spaced apart from each other in the circumferential direction and extend across the dilution opening 118 to connect the upstream bushing 112 and the downstream bushing 114. For example, the first rib 120 and the second rib 122 may be spaced apart from each other by a distance 126 in the circumferential direction, and the second rib 122 and the third rib 124 may be spaced apart from each other by a distance 128 in the circumferential direction. In some respects, for each of the plurality of ribs 116, the distances 126 and 128 may be the same, or the distances 126 and 128 may be different from each other (e.g., the distance 126 may be less than the distance 128). Furthermore, when the width of the dilution opening 118 varies circumferentially, the length of the rib member 116 spanning the dilution opening 118 can also vary according to the width of the dilution opening 118.

[0034] The outer liner dilution flow assembly 92 (inner liner dilution flow assembly 94) also includes a plurality of dilution grid members 130 disposed within the dilution opening 118 and extending into the combustion chamber 62. The plurality of dilution grid members 130 are connected to a plurality of rib members 116. For example, a first dilution grid member 132 may be connected to a first rib member 120 and a second rib member 122, and a second dilution grid member 134 may be connected to a second rib member 122 and a third rib member 124. Figure 3As shown, a plurality of dilution gate members 130 are arranged continuously in the circumferential direction, and arranged such that the continuous dilution gate members 130 are alternately offset in the axial direction. For example, the first dilution gate member 132 may be arranged at a distance 136 from the downstream side 140 of the upstream bushing plate 112, and the second dilution gate member 134 may be arranged at a distance 138 from the downstream side 140 of the upstream bushing plate 112. Therefore, the first dilution gate member 132 may be arranged upstream of the second dilution gate member 134 in the axial direction (L).

[0035] Figure 4 This is a partial cross-sectional view of the burner bushing and dilution flow assembly according to one aspect of this disclosure. Figure 1 and Figure 2 The cut-off point is at plane 4-4 as shown. Figure 4 As shown, a plurality of outer bushing dilution flow assemblies 92 may be arranged circumferentially around an outer bushing 54. Each of the plurality of outer bushing dilution flow assemblies 92 may engage with an adjacent outer bushing dilution flow assembly 92 at a sealing joint 152. The sealing joint 152 may be arranged as a bayonet joint, or any other type of joint that provides a seal between successive outer bushing dilution flow assemblies 92. Similarly, a plurality of inner bushing dilution flow assemblies 94 may be arranged circumferentially around an inner bushing 52. Each of the plurality of inner bushing dilution flow assemblies 94 may engage with an adjacent inner bushing dilution flow assembly 94 at a sealing joint 154. The sealing joint 154 may be arranged as a bayonet joint, or any other type of joint that provides a seal between successive inner bushing dilution flow assemblies 94.

[0036] Figure 5 Is Figure 3 A cross-sectional view of the outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94) taken from plane 5-5. Figure 5 In the diagram, the upstream dilution gate member 142 is shown arranged within the dilution opening 118. The upstream dilution gate member 142 is connected to the rib member 156. Figure 3The upstream dilution grid member 142 may be arranged at a distance 136 from the downstream side 140 of the upstream bushing plate 112. Therefore, the upstream dilution grid member 142 is arranged within the dilution opening 118 to establish an upstream dilution flow path 158 between the upstream bushing plate 112 and the upstream side 160 of the upstream dilution grid member 142. Similarly, the upstream dilution grid member 142 is arranged within the dilution opening 118 to establish a downstream dilution flow path 162 between the downstream side 164 of the upstream dilution grid member 142 and the downstream bushing plate 114. The upstream dilution grid member 142 extends into the combustion chamber 62 and may extend a length 170 within the combustion chamber, from the hot surface side 174 of the outer bushing upstream bushing portion 100 (inner bushing upstream bushing portion 102) to the end 172 of the upstream dilution grid member 142. Figure 5 As shown, the upstream dilution grid member 142 can typically extend radially (R) into the combustion chamber 62. However, as described below, the upstream dilution grid member 142 can alternatively extend at an angle.

[0037] exist Figure 5 As can be seen, the downstream bushing plate 114 is connected to the cold surface side 190 of the downstream bushing portion 104 (downstream bushing portion 106 of the inner bushing) of the outer bushing via a solid connection such as a welded joint 166. Conversely, the upstream bushing plate 112 can be joined to the cold surface side 192 of the upstream inner bushing portion 100 (upstream bushing portion 102 of the inner bushing) of the outer bushing via a floating connection, for example, by providing a seal 168 between the upstream bushing portion 100 (upstream bushing portion 102 of the inner bushing) and the upstream bushing plate 112 to create a sealed joint. Alternatively, a welded joint can be provided between the upstream bushing portion 100 (upstream bushing portion 102 of the inner bushing) and the upstream bushing plate 112 as a solid connection, and a floating connection can be provided between the downstream bushing portion 104 (downstream bushing portion 106 of the inner bushing) and the downstream bushing plate 114. Alternatively, a solid connection can be implemented for both the upstream bushing plate 112 and the downstream bushing plate 114.

[0038] Figure 6 Is Figure 3 A cross-sectional view of the outer bushing dilution flow assembly 92 (outer bushing dilution flow assembly 94) taken from plane 6-6. Figure 6 In the middle section, the downstream dilution gate member 144 is shown arranged within the dilution opening 118. The downstream dilution gate member 144 is connected to rib member 148 and rib member 146 ( Figure 3The downstream dilution grid member 144 may be arranged at a distance 138 from the downstream side 140 of the upstream bushing plate 112. Therefore, the downstream dilution grid member 144 is arranged within the dilution opening 118 to establish an upstream flow path 176 between the upstream bushing plate 112 and the upstream side 178 of the downstream dilution grid member 144. Similarly, the downstream dilution grid member 144 is arranged within the dilution opening 118 to establish a downstream dilution flow path 180 between the downstream side 182 of the downstream dilution grid member 144 and the downstream bushing plate 114. The downstream dilution grid member 144 extends into the combustion chamber 62 and may extend a length 184 within the combustion chamber, from the hot surface side 186 of the downstream bushing portion 104 of the outer bushing (downstream bushing portion 106 of the inner bushing) to the end 188 of the downstream dilution grid member 144. Figure 6 As shown, the downstream dilution grid member 144 typically extends radially (R) into the combustion chamber 62. However, as described below, the downstream dilution grid member 144 may alternatively extend at an angle. Furthermore, although Figure 5 and 6 Generally depicted, the upstream dilution grid member 142 and the downstream dilution grid member 144 extend into the combustion chamber with the same length (i.e., lengths 170 and 184 are the same), but different lengths may be provided alternatively, as described below.

[0039] Figure 7 Is Figure 3 A partial cross-sectional rear view of the dilution flow assembly, taken from plane 7-7. (See figure) Figure 7 As shown, upstream dilution gate member 142 and upstream dilution gate member 150 can have a generally rectangular cross-sectional shape. Downstream dilution gate member 144 can also have a generally rectangular cross-sectional shape. However, dilution gate members of other shapes can be used. For example, as... Figure 8A As shown, it may include a parabolic or semi-elliptical dilution grid member 130. Alternatively, as... Figure 8B As shown, it may include a trapezoidal dilution grid member 130, or as... Figure 8C As shown, it may include an inverted trapezoidal dilution gate member 130. However, as... Figure 8D As shown, it may include a funnel-shaped or lampshade-shaped dilution grid member 130, or as... Figure 8E As shown, the dilution grid member 130 may include an inverted funnel-shaped or inverted lampshade-shaped component. Furthermore, various combinations of the aforementioned dilution grid member shapes may be used together and implemented within the outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94).

[0040] Figure 9 and 10 Is Figure 3 A cross-sectional view of the alternative arrangement of the outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94) taken at plane 5-5. Figure 9 and 10 The cross-section is similar to Figure 5 The cross-section shown depicts an arrangement where the upstream dilution gate member 142 and the downstream dilution gate member 144 have different lengths. Figure 9 In the arrangement, the length 170 of the upstream dilution grid member 142 is greater than the length 184 of the downstream dilution grid member 144. By including the shorter downstream dilution grid member 144, the downstream dilution grid member 144 can help provide better cooling to the hot surface side 186 of the outer bushing downstream bushing portion 104 (inner bushing downstream bushing portion 106). Meanwhile, the longer upstream dilution grid member 142 allows compressed air 82(c) to penetrate deeper into the dilution zone 72 of the combustion chamber 62. On the other hand, in Figure 10 In this arrangement, the upstream dilution grid member 142 is shown to have a shorter length 170 than the downstream dilution grid member 144, which has a length 184. This arrangement helps achieve the desired quenching effect of the combustion gas 86 to reduce NOx emissions. Furthermore, although... Figure 9 and 10 Different lengths between the upstream dilution gate member 142 and the downstream dilution gate member 144 are depicted, but different dilution gate lengths can also be implemented circumferentially. For example, the length 170 of the upstream dilution gate member 142 can be greater than that of the upstream dilution gate member 150 ( Figure 3 The length of ) is 170.

[0041] Figure 11 Is Figure 3 A partial cross-sectional view of another arrangement of the dilution flow assembly, taken from plane 5-5. Figure 12 Is Figure 3 A partial cross-sectional view of another arrangement of the dilution flow assembly, taken from plane 6-6. Figure 5 and Figure 6 In the arrangement of the outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94) shown, both the upstream dilution grid member 142 and the downstream dilution grid member 144 are depicted extending radially into the combustion chamber 62. Conversely, in Figure 11 In the arrangement, the upstream dilution grid member 142 is shown arranged at an upstream angle 194. The upstream angle 194 can range from fifteen to thirty degrees. Of course, the upstream angle 194 is not limited to the above range, and other angles can be used instead. By setting the upstream dilution grid member 142 at the upstream angle 194, greater turbulence can be obtained from the flow of compressed air 82(c) mixed with combustion gas 86 in combustion chamber 62. The upstream dilution grid member 142 is not limited to extending in the radial direction or at the upstream angle 194; instead, the upstream dilution grid member 142 can extend at a downstream angle 198. The downstream angle 198 can range from fifteen to thirty degrees, but other angles can be implemented instead.

[0042] exist Figure 11 As can be seen, the downstream dilution grid member 144 extends radially into the combustion chamber 62. However, as... Figure 12 As shown, the downstream dilution grid member 144 can be arranged at a downstream angle 196. The downstream angle 196 can be in the range of fifteen to thirty degrees. Of course, the downstream angle 196 is not limited to the above range, and other angles can also be used. By providing the downstream dilution grid member 144 at the downstream angle 196, the dilution air can be more quickly reattached from the downstream dilution flow path 180 to the downstream bushing portion 104 of the outer bushing (the downstream bushing portion 106 of the inner bushing). The downstream dilution grid member 144 is not limited to extending in the radial direction or at the downstream angle 196; instead, the downstream dilution grid member 144 can extend at an upstream angle 200. The upstream angle 200 can have a range of fifteen to thirty degrees, but other angles can also be implemented.

[0043] Apart from Figure 11 and Figure 12 The arrangement shown, each corresponding dilution gate member 130 ( Figure 3 The angle of the dilution gate member 130 can be arranged differently in the circumferential direction for each member. For example, refer to the reference. Figure 3 The upstream dilution gate component 142 can be arranged at an upstream angle 194, such as Figure 11 As shown, the downstream dilution gate member 144 can be arranged at a downstream angle 196, as... Figure 12 As shown. Continuing along the circumferential direction, the upstream dilution gate member 150 can be arranged at a downstream angle 198, as... Figure 11 As shown, the second dilution gate member 134 can be arranged at an upstream angle 20°, as... Figure 12 As shown. Therefore, each corresponding dilution grid member 130 can be arranged at different angles in the circumferential direction.

[0044] Figure 13 A top view depicting a portion of another exemplary dilution flow component arrangement according to another aspect of this disclosure, taken from... Figure 2 The view Figure 3-3 Or AA. In Figure 13In this arrangement, each dilution grid member 130 is configured to provide a lateral component to the oxidant flow entering the combustion chamber 62. For example, an upstream dilution grid member 142 may be arranged at an angle 202 relative to the downstream side 140 of the upstream bushing plate 112 to provide a lateral component to the oxidant flow entering the combustion chamber 62 in a first lateral direction 204. Alternatively, an upstream dilution grid member 142 (shown as dilution grid member 142a) may be arranged at an angle 206 relative to the downstream side 140 of the upstream bushing plate 112 to provide a lateral component to the oxidant flow entering the combustion chamber 62 in a second lateral direction 208. Similarly, a downstream dilution grid member 144 may be arranged at an angle 210 relative to the downstream side 140 of the upstream bushing plate 112 to provide a lateral component to the oxidant flow entering the combustion chamber 62 in a second lateral direction 208. Alternatively, the downstream dilution grid member 144 (shown as dilution grid member 144a) may be arranged at an angle 212 relative to the downstream side 140 of the upstream bushing plate 112 in order to provide a lateral flow component for the oxidant flow entering the combustion chamber 62 in the first lateral direction 204.

[0045] In the circumferential arrangement of the dilution grid members 130 surrounding the outer bushing 54 or inner bushing 52, the upstream dilution grid members, such as upstream dilution grid members 142, 150 and the first dilution grid member 132, along with all other upstream dilution grid members, can all be arranged at the same angle 202 or the same angle 206. Alternatively, each corresponding upstream dilution grid member can be arranged at a different angle 202 or a different angle 206. Similarly, in the circumferential arrangement of the downstream dilution grid members, such as the second dilution grid member 134 and the downstream dilution grid member 144, along with all other downstream dilution grid members, can be arranged at the same angle 210 or the same angle 212. Alternatively, each corresponding downstream dilution grid member can be arranged at a different angle 210 or a different angle 212. Therefore, by arranging the upstream and / or downstream dilution grid members at certain angles to provide their respective lateral flow components, better mixing of the diluted oxidant (air) and combustion gas in the lateral direction can be achieved.

[0046] Figure 14 It is based on another aspect of this disclosure. Figure 3 A partial cross-sectional view of the dilution flow assembly taken at plane 5-5. Figure 14 The layout and Figure 5 Similar to what is shown. However, in Figure 14 As can be seen from the diagram, the upstream dilution grid member 142 includes an upstream deflection portion 214, which is arranged to deflect the oxidant flow from the upstream dilution flow path 158 in the combustion chamber 62 in the upstream direction 218 (i.e., towards the upstream end 131). Figure 14As shown, the upstream deflection portion 214 can be disposed at the end 172 of the upstream dilution gate member 142. Figure 5 The upstream dilution grid member 142 is implemented in the form of a spoon, which extends in the upstream direction 218. By providing the upstream deflection portion 214 to the upstream dilution flow path 158, increased turbulence between the oxidant flow and the combustion gas 86 can be achieved.

[0047] It can be seen that the downstream dilution grid member 144 includes a downstream deflection portion 216, which is arranged to deflect the oxidant flow from the downstream dilution flow path 180 in the combustion chamber 62 in the downstream direction 220. Similar to the upstream deflection portion 214, the downstream deflection portion 216 can be disposed at the end 188 of the dilution grid member 144. Figure 6 The downstream dilution gate member 144 is implemented using a spoon, which extends in the downstream direction 220. By providing the downstream deflection portion 216 to the downstream dilution gate member 144, the oxidant flow can be reattached more quickly to the hot surface side 186 of the outer bushing downstream bushing portion 104 (inner bushing downstream bushing portion 106). Of course, the upstream dilution gate member 142 may be provided with the downstream deflection portion 217 instead of the upstream deflection portion 214, and the downstream dilution gate member 144 may be provided with the upstream deflection portion 215 instead of the downstream deflection portion 216. Of course, the upstream dilution gate member 142 may be provided with the upstream deflection portion 214 and the downstream dilution gate member 144 may be provided with the upstream deflection portion 215, or the upstream dilution gate member 142 may be provided with the downstream deflection portion 217 and the downstream dilution gate member 144 may be provided with the downstream deflection portion 216. Furthermore, any combination of upstream and downstream deflection portions can be implemented circumferentially in a continuous dilution gate.

[0048] The outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94) can be manufactured as separate, assemblable components. For example, the upstream bushing plate 112 and the downstream bushing plate 114 can be manufactured from separate metal parts compatible with the outer bushing upstream bushing portion 100 (inner bushing upstream bushing portion 102) and the outer bushing downstream bushing portion 104 (inner bushing downstream bushing portion 106). The rib member 116 and the dilution grid member 130 can also be manufactured as separate components that can be joined (e.g., welded) to the upstream bushing plate 112 and the downstream bushing plate 114 to fabricate the outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94). Alternatively, the outer bushing dilution flow assembly 92 (inner bushing dilution flow assembly 94) can be manufactured using an additive manufacturing process.

[0049] In the preceding description, Figures 5 to 14Various arrangements of the dilution grid member 130 are described, which may be implemented within the outer bushing dilution flow assembly 92 or the inner bushing dilution flow assembly 94. Within each of the outer bushing dilution flow assembly 92 and / or the inner bushing dilution flow assembly 94, the following arrangements may be implemented: Figures 5 to 14 Any combination of the aspects shown and described. For example, the outer bushing dilution flow assembly 92 may include Figure 5 and Figure 6 All dilution gate members 130 in the illustrated arrangement. Alternatively, different aspects for the dilution gate members 130 may be provided within the outer bushing dilution flow assembly 92. For example, the outer bushing dilution flow assembly 92 may include, for example, Figure 4 The upstream dilution gate member 142 shown includes, as Figure 12 The downstream dilution gate member 144 shown includes, as... Figure 13 The upstream dilution gate component 150 is shown. Therefore, Figures 5 to 14 Any combination of the dilution grid members 130 depicted can be implemented within the outer bushing dilution flow assembly 92 and the inner bushing dilution flow assembly 94.

[0050] While the foregoing description generally pertains to gas turbine engines, it is readily understood that gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in aircraft, but it can also be implemented in non-aircraft applications, such as power plants, marine applications, or oil and gas production applications. Therefore, this disclosure is not limited to use in aircraft.

[0051] Other aspects of this disclosure are provided for in the subject matter of the following provisions.

[0052] A burner bushing for a gas turbine burner, the burner bushing defining a circumferential direction around a burner centerline, an axial direction along the burner centerline, and a radial direction extending outward from the burner centerline, characterized in that the burner bushing comprises:

[0053] An outer bushing extending circumferentially around the centerline of the burner; and

[0054] An inner liner extending circumferentially around the centerline of the burner.

[0055] The outer liner and the inner liner define a combustion chamber therebetween, and

[0056] At least one of the outer bushing and the inner bushing includes (a) an upstream bushing portion, (b) a downstream bushing portion and (c) at least one dilution flow assembly, with an annular gap provided between the upstream bushing portion and the downstream bushing portion, the at least one dilution flow assembly being arranged across the annular gap, the dilution flow assembly including (i) an upstream bushing plate, (ii) a downstream bushing plate and (iii) a plurality of dilution grid members, a dilution opening being provided between the upstream bushing plate and the downstream bushing plate, the plurality of dilution grid members being arranged within the dilution opening and extending into the combustion chamber, the plurality of dilution grid members being arranged in a continuous arrangement in the circumferential direction and arranged such that the continuous dilution grid members are alternately offset in the axial direction.

[0057] According to any of the foregoing clauses, the upstream bushing portion extends from the upstream end of the combustion chamber to the dilution zone of the combustion chamber in the axial direction, the downstream bushing portion extends from the dilution zone to the downstream end of the combustion chamber in the axial direction, and the annular gap is circumferentially disposed between the upstream bushing portion and the downstream bushing portion at the dilution zone of the combustion chamber.

[0058] According to any of the foregoing clauses, each of the plurality of dilution grid members is arranged within the dilution opening to provide an upstream dilution flow path between the upstream bushing plate and the upstream side of the dilution grid member, and a downstream dilution flow path between the downstream side of the dilution grid member and the downstream bushing plate.

[0059] According to any of the foregoing clauses, the burner bushing includes at least one dilution flow assembly comprising a plurality of dilution flow assemblies arranged circumferentially around the outer bushing and / or the inner bushing, and each of the plurality of dilution flow assemblies is engaged with a dilution flow assembly adjacent in the circumferential direction of the plurality of dilution flow assemblies via a sealing joint.

[0060] The burner bushing according to any of the foregoing clauses, wherein the upstream bushing portion includes an upstream bushing portion cold surface side, and the downstream bushing portion includes a downstream bushing portion cold surface side, and the upstream bushing plate is connected to the upstream bushing portion cold surface side, and the downstream bushing plate is connected to the downstream bushing portion cold surface side.

[0061] The burner bushing according to any of the foregoing clauses, wherein the plurality of dilution grid members include a cross-sectional shape of one of a rectangle, trapezoid, and parabola extending in the radial and circumferential directions.

[0062] The burner bushing according to any of the foregoing clauses, wherein the dilution flow assembly is manufactured by an additive manufacturing process.

[0063] The burner bushing according to any of the foregoing clauses, wherein the dilution flow assembly further includes (iv) a plurality of ribs spaced apart from each other in the circumferential direction and extending across the dilution opening, the plurality of ribs connecting the upstream bushing plate and the downstream bushing plate, and the plurality of dilution grid members connected to the plurality of ribs.

[0064] The burner bushing according to any of the foregoing clauses, wherein the plurality of rib members includes a first rib member, a second rib member, and a third rib member, and the plurality of dilution grid members includes a first dilution grid extending between the first rib member and the second rib member, and a second dilution grid extending between the second rib member and the third rib member.

[0065] According to any of the foregoing clauses, the burner bushing wherein the first rib and the second rib are arranged to be spaced apart from each other by a first distance in the circumferential direction, the second rib and the third rib are arranged to be spaced apart from each other by a second distance in the circumferential direction, the second distance being less than the first distance, and the length of the first dilution grid in the circumferential direction being greater than the length of the second dilution grid in the circumferential direction.

[0066] The burner bushing according to any of the foregoing clauses, wherein the first dilution grid is arranged upstream of the second dilution grid in the axial direction.

[0067] The burner bushing according to any of the foregoing clauses, wherein the length of one of the first dilution grid and the second dilution grid extending into the combustion chamber is greater than the length of the other of the first dilution grid and the second dilution grid extending into the combustion chamber.

[0068] The burner bushing according to any of the foregoing clauses, wherein one of the first dilution grid and the second dilution grid extends into the combustion chamber in the radial direction, and the other of the first dilution grid and the second dilution grid extends into the combustion chamber at an upstream angle.

[0069] The burner bushing according to any of the foregoing clauses, wherein one of the first dilution grid and the second dilution grid extends into the combustion chamber in the radial direction, and the other of the first dilution grid and the second dilution grid extends into the combustion chamber at a downstream angle.

[0070] The burner bushing according to any of the foregoing clauses, wherein one of the first dilution grid and the second dilution grid extends into the combustion chamber at an upstream angle, and the other of the first dilution grid and the second dilution grid extends into the combustion chamber at a downstream angle.

[0071] According to any of the foregoing clauses, the burner bushing is wherein the first dilution grid is arranged at a first angle relative to the downstream side of the upstream bushing plate to provide a lateral flow component for the oxidant flow in a first lateral direction, and the second dilution grid is arranged at a second angle relative to the downstream side of the upstream bushing plate to provide a lateral flow component for the oxidant flow in a second lateral direction.

[0072] According to any of the foregoing clauses, one of the first dilution grid and the second dilution grid includes an upstream deflection portion arranged to deflect the oxidant flow in the combustion chamber in an upstream direction, and the other of the first dilution grid and the second dilution grid includes a downstream deflection portion arranged to deflect the oxidant flow in the combustion chamber in a downstream direction.

[0073] The burner bushing according to any of the foregoing clauses, wherein the upstream deflection portion includes a spoon disposed at the end of the dilution grid member and extending in the upstream direction, and the downstream deflection portion includes a spoon disposed at the end of the dilution grid member and extending in the downstream direction.

[0074] The burner bushing according to any of the foregoing clauses, wherein the downstream bushing plate is connected to the downstream bushing portion by a solid connection and the upstream bushing plate is connected to the upstream bushing portion by a floating connection.

[0075] The burner bushing according to any of the foregoing clauses, wherein the solid connection is a welded joint, and the floating connection includes a seal disposed between the upstream bushing portion and the upstream bushing plate.

[0076] While the foregoing description is directed to some exemplary embodiments of the present disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner bushing for a gas turbine burner, the burner bushing defining a circumferential direction around a burner centerline, an axial direction along the burner centerline, and a radial direction extending outward from the burner centerline, characterized in that, The burner bushing includes: An outer bushing extending circumferentially around the centerline of the burner; and An inner liner extending circumferentially around the centerline of the burner. Wherein, the outer bushing and the inner bushing define a combustion chamber therebetween, and At least one of the outer bushing and the inner bushing includes (a) an upstream bushing portion, (b) a downstream bushing portion and (c) at least one dilution flow assembly, with an annular gap provided between the upstream bushing portion and the downstream bushing portion, the at least one dilution flow assembly being arranged across the annular gap, the dilution flow assembly including (i) an upstream bushing plate, (ii) a downstream bushing plate and (iii) a plurality of dilution grid members, a dilution opening being provided between the upstream bushing plate and the downstream bushing plate, the plurality of dilution grid members being arranged within the dilution opening and extending into the combustion chamber, the plurality of dilution grid members being arranged in a continuous arrangement in the circumferential direction and arranged such that the continuous dilution grid members are alternately offset in the axial direction.

2. The burner bushing according to claim 1, characterized in that, in, The upstream bushing portion extends from the upstream end of the combustion chamber to the dilution zone of the combustion chamber in the axial direction, and the downstream bushing portion extends from the dilution zone of the combustion chamber to the downstream end of the combustion chamber in the axial direction. The annular gap is circumferentially disposed between the upstream bushing portion and the downstream bushing portion, at the dilution zone of the combustion chamber.

3. The burner bushing according to claim 1, characterized in that, in, Each of the plurality of dilution grid members is arranged within the dilution opening to provide an upstream dilution flow path between the upstream bushing and the upstream side of the dilution grid member, and a downstream dilution flow path between the downstream side of the dilution grid member and the downstream bushing.

4. The burner bushing according to claim 1, characterized in that, in, The at least one dilution flow assembly includes a plurality of dilution flow assemblies arranged circumferentially around the outer bushing and / or the inner bushing, and each of the plurality of dilution flow assemblies engages an adjacent dilution flow assembly in the circumferential direction via a sealing joint.

5. The burner bushing according to claim 1, characterized in that, in, The upstream bushing portion includes a cold surface side, and the downstream bushing portion includes a cold surface side. The upstream bushing plate is connected to the cold surface side of the upstream bushing portion, and the downstream bushing plate is connected to the cold surface side of the downstream bushing portion.

6. The burner bushing according to claim 1, characterized in that, in, The plurality of dilution grid members include a cross-sectional shape of one of rectangle, trapezoid, and parabola extending in the radial direction and the circumferential direction.

7. The burner bushing according to claim 1, characterized in that, in, The dilution flow assembly is manufactured using an additive manufacturing process.

8. The burner bushing according to claim 1, characterized in that, in, The dilution flow assembly further includes (iv) a plurality of ribs spaced apart from each other in the circumferential direction and extending across the dilution opening, the plurality of ribs connecting the upstream bushing plate and the downstream bushing plate, and the plurality of dilution grid members connected to the plurality of ribs.

9. The burner bushing according to claim 8, characterized in that, in, The plurality of rib members include a first rib member, a second rib member, and a third rib member, and the plurality of dilution gate members include a first dilution gate extending between the first rib member and the second rib member, and a second dilution gate extending between the second rib member and the third rib member.

10. The burner bushing according to claim 9, characterized in that, in, The first rib and the second rib are arranged to be spaced apart from each other by a first distance in the circumferential direction, and the second rib and the third rib are arranged to be spaced apart from each other by a second distance in the circumferential direction, the second distance being less than the first distance, and the length of the first dilution gate in the circumferential direction being greater than the length of the second dilution gate in the circumferential direction.

11. The burner bushing according to claim 9, characterized in that, in, The first dilution gate is arranged upstream of the second dilution gate in the axial direction.

12. The burner bushing according to claim 11, characterized in that, in, The length of one of the first and second dilution grids extending into the combustion chamber is greater than the length of the other of the first and second dilution grids.

13. The burner bushing according to claim 11, characterized in that, in, One of the first dilution grid and the second dilution grid extends into the combustion chamber in the radial direction, and the other of the first dilution grid and the second dilution grid extends into the combustion chamber at an upstream angle.

14. The burner bushing according to claim 11, characterized in that, in, One of the first dilution grid and the second dilution grid extends into the combustion chamber in the radial direction, and the other of the first dilution grid and the second dilution grid extends into the combustion chamber at a downstream angle.

15. The burner bushing according to claim 11, characterized in that, in, One of the first dilution grid and the second dilution grid extends into the combustion chamber at an upstream angle, and the other of the first dilution grid and the second dilution grid extends into the combustion chamber at a downstream angle.

16. The burner bushing according to claim 11, characterized in that, in, The first dilution gate is arranged at a first angle relative to the downstream side of the upstream bushing plate, thereby providing a lateral flow component for the oxidant flow in a first lateral direction, and the second dilution gate is arranged at a second angle relative to the downstream side of the upstream bushing plate, thereby providing a lateral flow component for the oxidant flow in a second lateral direction.

17. The burner bushing according to claim 11, characterized in that, in, One of the first and second dilution gates includes an upstream deflection portion arranged to deflect the oxidant flow in the combustion chamber in an upstream direction, and the other of the first and second dilution gates includes a downstream deflection portion arranged to deflect the oxidant flow in the combustion chamber in a downstream direction.

18. The burner bushing according to claim 17, characterized in that, in, The upstream deflection portion includes a spoon disposed at the end of the dilution gate member and extending in the upstream direction, and the downstream deflection portion includes a spoon disposed at the end of the dilution gate member and extending in the downstream direction.

19. The burner bushing according to claim 1, characterized in that, in, The downstream bushing plate is connected to the downstream bushing portion via a solid connection, and the upstream bushing plate is engaged with the upstream bushing portion via a floating connection.

20. The burner bushing according to claim 19, characterized in that, in, The solid connection is a welded joint, and the floating connection includes a seal disposed between the upstream bushing portion and the upstream bushing plate.

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