Aerodynamic combustor liner design for emissions reduction

Abstract

A combustor liner has an annular outer liner and an annular inner liner defining a combustion chamber therebetween, the combustion chamber having a dilution zone. The annular outer liner and the annular inner liner each have a converging-diverging section extending into the dilution zone of the combustion chamber, forming a throat therebetween. Each converging-diverging section includes at least one dilution opening defined through the respective converging-diverging section at the throat for providing an oxidant flow through the respective liner to the dilution zone of the combustion chamber.

Description

Technical Field

[0001] This disclosure relates to the burner liner and dilution of combustion gases in the combustion chamber of a gas turbine engine. Background Technology

[0002] In conventional gas turbine engines, it is known to provide a dilution airflow to a combustion chamber downstream of the primary combustion zone. Typically, an annular combustor may include both an inner liner and an outer liner, with the combustion chamber formed between them. The inner and outer liners may include dilution orifices passing through the liner, which provide airflow from channels surrounding the combustor liner to the dilution zone of the combustion chamber. Conventional combustors are known to employ a combustor liner that is generally straight in its length from the dome assembly of the primary combustion zone closest to the upstream end of the combustor, through the dilution zone in the middle of the combustor, and then gradually converges in the secondary combustion zone downstream of the dilution zone near the turbine section inlet. Attached Figure Description

[0003] The features, advantages, and embodiments of this disclosure will become apparent from the following more specific 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 an embodiment of the present disclosure.

[0005] Figure 2 This is a cross-sectional side view of an exemplary combustion section according to an embodiment of the present disclosure.

[0006] Figure 3 A partial cross-sectional side view of an exemplary convergence-divergence section of a burner bushing according to aspects of this disclosure is depicted.

[0007] Figure 4 A partial cross-sectional side view depicting an exemplary convergence-divergence section of a burner bushing according to another aspect of this disclosure is shown.

[0008] Figure 5 A partial cross-sectional side view of an exemplary convergence-divergence section of a burner bushing according to yet another aspect of this disclosure is depicted.

[0009] Figure 6 A partial cross-sectional side view of an exemplary convergence-divergence section of a burner bushing according to yet another aspect of this disclosure is depicted.

[0010] Figure 7 A partial cross-sectional view of a joint for a burner bushing according to aspects of this disclosure is depicted.

[0011] Figure 8 A partial cross-sectional side view of an exemplary convergence-divergence section of a burner bushing according to yet another aspect of this disclosure is depicted.

[0012] Figure 9 A partial cross-sectional side view of an exemplary convergence-divergence section of a burner bushing according to yet another aspect of this disclosure is depicted.

[0013] Figure 10 A partial cross-sectional side view of an exemplary convergence-divergence section of a burner bushing according to yet another aspect of this disclosure is depicted.

[0014] Figure 11 It is based on one aspect of this disclosure. Figure 2 A partial cross-sectional front view of an exemplary convergent-divergent burner bushing, taken at plane 11-11.

[0015] Figure 12 Is Figure 11 A magnified detailed view of a portion of the burner bushing, cropped at 12-12.

[0016] Figure 13 It is based on one aspect of this disclosure. Figure 11 A partial cross-sectional side view of the burner taken at plane 13-13. Detailed Implementation

[0017] Various embodiments are discussed in detail below. Although specific embodiments are discussed, they are 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.

[0018] 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 the individual components.

[0019] 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 out, while "downstream" is the direction in which it flows.

[0020] Various features, advantages, and embodiments of this disclosure will be set forth or become apparent from consideration of the following detailed description, drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure.

[0021] In the combustion section of a turbine engine, air flows through an external 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 external passage is diverted through dilution orifices in the burner liner and enters the combustion chamber as dilution air. One purpose of the dilution air flow is to cool (i.e., quench) the combustion gases before they enter the turbine section. However, the quenching of combustion products from the primary zone must be carried out quickly and efficiently to minimize the high-temperature zone, thereby reducing NOx emissions from the combustion system.

[0022] This disclosure aims to reduce NOx emissions by improving the dilution and quenching of hot combustion gases from the primary combustion zone. According to this disclosure, the burner liner includes a convergent-divergent section located in the dilution zone, with a dilution gas flow opening disposed in the throat section of this convergent-divergent section. The implementation of the convergent-divergent section in the combustion chamber liner reduces the cross-sectional area of ​​the burner within the dilution zone, allowing the dilution gas flow to penetrate deeper into the dilution zone, thereby improving the quenching of hot combustion gases and 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 may be incorporated into various embodiments of this disclosure. Although further description is given below with reference to turbofan engines, this disclosure 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, the engine 10 has a longitudinal or axial centerline axis 12 for reference purposes, which extends from an upstream end 98 through the engine 10 to a downstream end 99. Generally, the 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 a compressor section in a series flow relationship, having a turbocharger or low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24; a combustion section 26; a turbine section including a high-pressure (HP) turbine 28, a low-pressure (LP) turbine 30; and an exhaust nozzle section 32. 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 LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In a specific embodiment, as... Figure 1As 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 can rotate 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 combustion section 26 of the core engine 16 shown. Figure 2 As shown, combustion section 26 typically includes an annular combustor assembly 50 having an annular inner liner 52, an annular outer liner 54, and a dome assembly 56, which together define combustion chamber 62. Combustion chamber 62 may more specifically define various zones, including a primary combustion zone 70, where initial chemical reactions of the fuel-oxidant mixture and / or recirculation of combustion gases 86 can occur before further downstream flow to dilution zone 72, where mixing and / or recirculation of combustion products and air can occur before flow to secondary combustion zone 74, in which combustion products flow into HP turbine 28 and LP turbine 30. Dome assembly 56 extends radially between an upstream end 76 of annular outer liner 54 and an upstream end 77 of annular inner liner 52.

[0027] like Figure 2 As shown, the annular inner liner 52 and the annular outer liner 54 can be encapsulated within the housing 64. An outer flow passage 68 is defined between the housing 64 and the annular outer liner 54, and an inner flow passage 69 is defined between the housing 64 and the annular outer liner 54. The annular inner liner 52 can extend from the upstream end 77 of the dome assembly 56 to the turbine nozzle or HP turbine 28 (…). Figure 1 The annular inner liner 52 at the inlet of the turbine nozzle is located at its downstream end 67. The annular outer liner 54 may extend from the upstream end 76 of the dome assembly 56 to the downstream end 66 of the annular outer liner 54 at the turbine nozzle. Thus, the annular outer liner 54 and the annular inner liner 52 at least partially define the hot gas path between the combustor assembly 50 and the HP turbine 28.

[0028] like Figure 2As further shown, the annular inner liner 52 may include a plurality of dilution openings 90 and the annular outer liner 54 may include a plurality of dilution openings 88. As will be described in more detail below, the dilution openings 88 and 90 provide a compressed air flow 82(c) through which and into the combustion chamber 62. Thus, the compressed air flow 82(c) can be used to provide quenching of the combustion gases 86 in the dilution zone 72 downstream of the primary combustion zone 70, thereby cooling the combustion gas flow 86 entering the turbine section.

[0029] During the operation of engine 10, common reference Figure 1 and Figure 2 As indicated schematically by the arrows, a volume of air 73 enters the engine 10 from the upstream end 98 through the nacelle 44 and / or the associated inlet 75 of the fan assembly 14. As the volume of air 73 passes through the fan blades 42, a portion of the air (as indicated schematically by arrow 78) is directed or routed to the bypass airflow passage 48, while another portion (as indicated schematically by arrow 80) is directed or routed to the LP compressor 22. As the air portion 80 flows through the LP and HP compressors 22, 24 toward the combustion chamber 26, the air portion 80 is gradually compressed. Figure 2 As shown, the compressed air, schematically indicated by arrow 82, flows through the compressor outlet guide vane (CEGV) (not shown) and through the pre-diffuser (not shown) into the diffuser chamber 84 of the combustion section 26.

[0030] Compressed air 82 pressurizes diffuser cavity 84. As schematically indicated by arrow 82(a), a first portion of the compressed air 82 flows from diffuser cavity 84 into pressure chamber 65, where it is swirled and mixed with fuel supplied by fuel nozzle assembly 58 via mixer assembly 60 to produce a swirling fuel-air mixture, which is then ignited and burned to produce combustion gases 86 within primary combustion zone 70 of burner assembly 50. Typically, LP and HP compressors 22, 24 supply more compressed air to diffuser cavity 84 than is required for combustion. Therefore, as schematically indicated by arrow 82(b), a second portion of the compressed air 82 can be used for various purposes other than combustion. For example, as... Figure 2As shown, compressed air 82(b) can be directed to the outer flow passage 68 and into the inner flow passage 69. A portion of the compressed air 82(b) can then be directed through the dilution opening 88 (schematically shown as compressed air 82(c)) and into the dilution zone 72 of the combustion chamber 62 to provide quenching of the combustion gases 86 in the dilution zone 72, and can also provide turbulence to the flow of combustion gases 86 to provide better mixing of the diluted oxidant gas (compressed air 82(c)) with the combustion gases 86. A similar flow of compressed air 82(c) occurs from the inner flow passage 69 through the dilution opening 90. Alternatively, at least a portion of the compressed air 82(b) can be directed out of the diffuser cavity 84. For example, a portion of the compressed air 82(b) can be directed through various flow passages to provide cooling air delivery to at least one of the HP turbine 28 or LP turbine 30.

[0031] Return to common reference Figure 1 and Figure 2 Combustion gases 86 generated in combustion chamber 62 flow from burner assembly 50 into HP turbine 28, causing HP rotor shaft 34 to rotate, thereby supporting the operation of HP compressor 24. Figure 1 As shown, the combustion gases 86 are then directed through the LP turbine 30, causing the LP rotor shaft 36 to rotate, thereby supporting the operation of the LP compressor 22 and / or the rotation of the fan shaft 38. The combustion gases 86 are then exhausted through the injection exhaust nozzle section 32 of the core engine 16 to provide propulsion at the downstream end 99.

[0032] As will be described in more detail below, burner 50 includes a burner liner convergence-divergence section 100. The burner liner convergence-divergence section 100 includes an outer liner convergence / divergence section 102 located in the dilution zone 72 of the combustion chamber 62 (see [link to documentation]). Figure 3 ), and the lining convergence / divergence section 104 in the dilution zone 72 of combustion chamber 62 ( Figure 3 One purpose of the burner bushing convergence / divergence section 100 is to provide better quenching of the deeper combustion gases 86 within the dilution zone 72 of the combustion chamber 62, thereby reducing NOx emissions. Various arrangements of the burner bushing convergence-divergence section 100 and various arrangements of the dilution openings passing through it will be referenced below. Figures 3 to 10 Describe it.

[0033] Figure 3This is a partial cross-sectional side view of the burner liner convergence-divergence section 100 according to an aspect of this disclosure. The burner liner convergence-divergence section 100 includes an outer liner convergence-divergence section 102 and an inner liner convergence-divergence section 104, each of which will be described in more detail below. Both the outer liner convergence-divergence section 102 and the inner liner convergence-divergence section 104 extend circumferentially around the burner centerline 112 of the burner and also extend longitudinally L relative to the burner centerline 112. Here, the burner centerline 112 may be the same as the engine centerline 12. A dilution zone 72 is defined between the outer liner convergence-divergence section 102 and the inner liner convergence-divergence section 104.

[0034] The outer liner convergent-divergent section 102 (hereinafter referred to as the "OLCD section") extends radially inward relative to the burner centerline 112 into the dilution zone 72 of the combustion chamber 62. Similarly, the annular inner liner 52 includes an inner liner convergent-divergent section 104 (hereinafter referred to as the "ILCD section") that extends radially outward relative to the burner centerline 112 into the dilution zone 72 of the combustion chamber 62. The OLCD section 102 and the ILCD section 104 generally pass through the combustion chamber 62 and are radially opposite to each other.

[0035] OLCD section 102 includes at least one dilution opening 88 defined through OLCD section 102 for providing an oxidant flow (i.e., compressed air 82(c)) through the dilution zone 72 from the annular outer liner 54 to the combustion chamber 62. Similarly, ILCD section 104 includes at least one dilution opening 90 defined through ILCD section 104 for providing an oxidant flow (i.e., compressed air 82(c)) through the dilution zone 72 from the annular inner liner 52 to the combustion chamber 62. Various arrangements of the dilution openings will be discussed in more detail below.

[0036] Still referencing Figure 3The OLCD section 102 can generally be composed of three common parts: a converging part, a diverging part, and a transition part. More specifically, the OLCD section 102 includes an OLCD section converging part 106, which converges radially inward and longitudinally backward relative to the burner centerline 112 from the upstream end 108 of the OLCD section 102 to the upstream end 110 of the OLCD section transition part 114 into the combustion chamber 62. The OLCD section converging part 106 may be semi-circular, with its center 111 located within the combustion chamber 62. Alternatively, the OLCD section converging part 106 may have a parabolic or straight shape. The OLCD section 102 also includes an OLCD section diverging part 116, which extends radially outward and longitudinally backward relative to the burner centerline 112 from the downstream end 118 of the OLCD section transition part 114 to the downstream end 120 of the OLCD section 102. The OLCD section diverging portion 116 may also have a semi-circular shape, with its center 113 located within the combustion chamber 62. Optionally, the OLCD section diverging portion 116 may have a parabolic or straight shape. The OLCD section transition portion 114 connects the downstream end 122 of the OLCD section converging portion 106 and the upstream end 124 of the OLCD section diverging portion 116. The OLCD section transition portion 114 may have a parabolic shape, with its focal point 107 located radially outward relative to the burner centerline 112. The parabolic shape of the OLCD section transition portion 114 may have a width-to-depth ratio of 1:4. Alternatively, the OLCD section transition portion 114 may have a semi-circular or straight shape.

[0037] ILCD segment 104 is similar to OLCD segment 102 and is more or less a mirror image of OLCD segment 102. Therefore, ILCD segment 104 includes an ILCD segment convergence portion 126 that converges radially outward and longitudinally rearward relative to the burner centerline 112 from the upstream end 128 of ILCD segment 104 to the upstream end 130 of ILCD segment transition portion 132 into combustion chamber 62. The ILCD segment convergence portion 126 may have a semi-circular shape with its center 115 located within combustion chamber 62. Alternatively, the ILCD segment convergence portion 126 may have a parabolic or linear shape. The ILCD segment includes an ILCD segment divergence portion 134 that extends radially inward and longitudinally rearward relative to the burner centerline 112 from the downstream end 136 of ILCD segment transition portion 132 to the downstream end 138 of ILCD segment 104. The ILCD section diverging portion 134 may have a semi-circular shape, with its center 117 located within the combustion chamber 62. Alternatively, the ILCD section diverging portion 134 may have a parabolic or straight shape. The ILCD section transition portion 132 connects the downstream end 140 of the ILCD section converging portion 126 and the upstream end 142 of the ILCD section diverging portion 134. The ILCD section transition portion 132 may have a parabolic shape, with its focal point 109 located radially inward relative to the burner centerline 112. The parabolic shape of the ILCD section transition portion 132 may have a width-to-depth ratio of 1:4. Alternatively, the ILCD section transition portion 132 may have a semi-circular or straight shape.

[0038] like Figure 2 and Figure 3 As shown, both OLCD section 102 and ILCD section 104 have a generally smoothly transitioning sinusoidal shape to provide aerodynamic flow of compressed air 82(b) along the outer surfaces of the outward-facing flow channels 68, 69 and aerodynamic flow of combustion gas 86 within the combustion chamber 62. However, either or both of OLCD section 102 and ILCD section 104 may be formed by a trapezoidal structure with straight segments rather than a smoothly curved sinusoid. OLCD section transition portion 114 and ILCD section transition portion 132 form a throat 119 between them, and various forms of dilution openings are provided through the transition portions to provide a dilution airflow at the throat 119, as will be described in more detail below.

[0039] Still referencing Figure 3 The dilution opening 88 of the annular outer liner 54 and the dilution opening 90 of the annular inner liner 52 will now be described. Figure 3In the diagram, dilution opening 88 is shown as defined through the OLCD segment transition portion 114, and dilution opening 90 is shown as defined through the ILCD segment transition portion 132. However, as will be described in more detail below, dilution openings can be alternatively implemented through other portions of the OLCD segment 102 and the ILCD segment 104. Additionally, Figure 3 The cross-sectional view depicts a single dilution opening 88 passing through the OLCD section transition portion 114, but it will be readily understood that multiple dilution openings 88 may be included. For example, multiple dilution openings 88 may be circumferentially spaced around the annular outer liner 54. Similarly, multiple dilution openings 90 may be circumferentially spaced around the annular inner liner 52. Furthermore, although dilution openings 88 and 90 are shown directly opposite each other for passing through the combustion chamber 62, they may be circumferentially or longitudinally offset from each other.

[0040] exist Figure 3 In the diagram, dilution openings 88 and 90 are generally shown as circular or cylindrical holes generally perpendicular to the burner centerline 112. However, other shapes, such as squares, ellipses, racetrack shapes, triangles, etc., can be implemented for dilution openings 88 and 90. Furthermore, although dilution openings 88 and 90 are shown arranged generally perpendicular to the burner centerline 112, they can alternatively be angled. For example, dilution opening 88 can be arranged at a radial angle of 144 or 146, where radial angle 144 can be in the range from zero to -30 degrees, and radial angle 146 can be in the range from zero to +30 degrees. Similarly, dilution opening 90 can be angled at a radial angle of 148 or 150, where radial angle 148 can be in the range from zero to +30 degrees, and radial angle 150 can be in the range from zero to -30 degrees. Of course, the foregoing ranges are merely exemplary, and other angular ranges can be implemented alternatively to obtain the desired dilution flow rate of air through the dilution openings.

[0041] Figure 4 This is a partial cross-sectional side view of an exemplary burner bushing convergence-divergence section 100 according to another aspect of this disclosure. Except for the dilution opening, Figure 4 Similar in all aspects Figure 3 In this respect. Therefore, Figure 3 and Figure 4 The same reference numerals used in the figures will not be discussed further. Recall that in Figure 3 In this respect, the dilution openings form dilution holes that pass through the transition portion of the annular outer liner 54 and the annular inner liner 52. Conversely, Figure 4The annular groove dilution opening 152 extends through the annular outer liner 54 and the annular groove dilution opening 154 extends through the annular inner liner 52. The annular groove dilution opening 152 extends circumferentially around the annular outer liner 54, and the annular groove dilution opening 154 extends circumferentially around the annular inner liner 52. Since the annular groove is implemented as a dilution opening, Figure 4 The aspect includes a double bushing. That is, the annular outer bushing 54 consists of a front section 156 and a rear section 158. Naturally, the front section 156 and the rear section 158 are connected by a plurality of connecting members 163. For example, each of the plurality of connecting members 163 may be a beam (or bridge) brazed, welded, or bolted to the front section 156 and the rear section 158. The connecting members 163 may be circumferentially spaced around the annular outer bushing 54. Similarly, the annular groove dilution opening 154 extends circumferentially around the annular inner bushing 52. Connecting members (not shown) are also used to connect the front section 160 and the rear section 162 of the inner bushing. Figure 4 In the diagram, the annular groove dilution opening 152 and the annular groove dilution opening 154 are shown directly opposite each other across the combustion chamber 62. However, they may alternatively be offset from each other in the longitudinal direction.

[0042] Figure 5 This is a partial cross-sectional side view of the convergent-divergent portion 100 of the burner bushing according to another aspect of this disclosure. Figure 5 The convergence-divergence section aspect is realized. Figure 3 Dilution opening and Figure 4 Regarding the dilution opening. For example... Figure 5 As shown, the annular outer liner 54 includes both an annular groove dilution opening 152 and a circular aperture dilution opening 88. Similarly, the annular inner liner 52 includes both an annular groove dilution opening 154 and a circular aperture dilution opening 90. Figure 5 In the illustrated aspect, the annular groove dilution opening 152 is shown opposite the dilution zone 72 of the combustion chamber 62 across the dilution opening 90. Similarly, the annular groove dilution opening 154 is shown opposite the dilution zone 72 of the combustion chamber 62 via the dilution opening 88. Of course, this disclosure is not limited to the foregoing arrangement, and other arrangements may be implemented alternatively. For example, the annular groove dilution opening 152 and the annular groove dilution opening 154 may be opposite each other, similar to... Figure 4 As shown, dilution openings 88 and 90 can be as follows Figure 3 They are facing each other.

[0043] Figure 6 This is a partial cross-sectional side view of the convergent-divergent portion 100 of the burner bushing according to another aspect of this disclosure. Figure 6 Similar to Figure 4 In this respect, the difference lies in Figure 6This includes an annular groove dilution opening 152 as a dilution opening passing through the annular outer liner 54 and an annular groove dilution opening 154 as a dilution opening passing through the annular inner liner 52. Figure 6 In the annular liner 54, the annular groove dilution opening 152 includes a liner dilution flow extension member 164 that extends radially outward from the annular liner 54 relative to the burner centerline 112. Also, Figure 6 As shown, the liner dilution flow extension member 164 may also extend upstream relative to the burner centerline 112 at a first angle 166 (i.e., towards the upstream end 76 of the annular liner 54). In an exemplary aspect, the first angle 166 may range from -45 degrees (negative in the upstream direction) to zero degrees, where zero degrees is generally perpendicular to the burner centerline 112. In another aspect, the first angle 166 may range from zero degrees to +45 degrees (in the downstream direction towards the downstream end 66 of the annular liner 54). Of course, the range of the first angle 166 is not limited to the aforementioned range, and other ranges may be used alternatively. One purpose of the first angle 166 of the liner dilution flow extension member 164 is to provide directional flow of dilution air into the dilution zone 72 of the combustion chamber 62.

[0044] As mentioned above Figure 4 The discussed method involves implementing an annular groove dilution opening 152 in the annular outer liner 54 to create a double bushing comprising a front section 156 and a rear section 158. This also applies to the provisions of this paper concerning... Figure 6 In terms of the disclosed aspects, the front section 156 of the outer liner includes a front portion 168 of the outer liner dilution flow extension member 164, and the rear section 158 of the outer liner includes a rear portion 170 of the outer liner dilution flow extension member. The front portion 168 of the outer liner dilution flow extension member may be formed via a bend 172 in the bushing material of the front section of the outer liner, or it may be a separate member brazed or welded in place. Similarly, the rear portion 170 of the outer liner dilution flow extension member may be formed via a bend 174 in the bushing material of the rear section of the outer liner, or it may be a separate element brazed or welded to the outer liner material.

[0045] The radial length (i.e., height) of the outer liner dilution flow extension member 164 can be obtained relative to the outer liner surface 178, shown as a dashed line connecting the outer surface 180 of the front section and the outer surface 182 of the rear section. The radial length is obtained as a distance 176 from the outer liner surface 178 of the rear portion 170 of the outer liner dilution flow extension member to the radial outer surface 184, and from the outer liner surface 178 of the front portion 168 of the outer liner dilution flow extension member to the radial outer surface 185. Figure 6 As shown, the radial outer surface 184 of the rear portion 170 of the outer liner dilution flow extension member can be arranged at a distance 176 from the outer surface 178 of the outer liner, such as... Figure 6As shown, the radial outer surface 184 may be below the outer surface 178 of the liner (i.e., radially inward). Alternatively, the radial outer surface 184 may be flush with the outer surface 178 of the liner, such that the distance 176 is zero, or the radial outer surface 184 may extend radially outward from the outer surface 178 of the liner, such that the distance 176 extends above the outer surface 178 of the liner. The same distance 176 applies to the radial outer surface 185 of the front portion 168 of the liner dilution flow extension member. Additionally, although in Figure 6 The diagram shows the radial outer surface 185 of the front portion 168 of the outer liner dilution flow extension member and the radial outer surface 184 of the rear portion 170 of the outer liner dilution flow extension member arranged at the same distance 176 from the outer surface 178 of the outer liner, but they can alternatively have different lengths. For example, the distance 176 to the radial outer surface 185 of the front portion 168 of the outer liner dilution flow extension member can be as follows: Figure 6 As shown (i.e., below the outer surface 178 of the outer liner), the distance 176 to the radially outer surface 184 of the rear portion 170 of the outer liner dilution flow extension member can be flush with the outer surface 178 of the outer liner, or extend radially outward beyond the outer surface 178 of the outer liner. When this arrangement is implemented, the longer rear portion 170 of the outer liner dilution flow extension member can be used to deflect more air into the outer liner dilution flow extension member 164.

[0046] Figure 6 The aspect also includes an annular groove dilution opening 154 as a dilution opening through the annular liner 52. The annular groove dilution opening 154 of the annular liner 52 includes a liner dilution flow extension member 186, which may be a mirror image of the liner dilution flow extension member 164. Therefore, the liner dilution flow extension member 186 extends radially inward from the annular liner 52 relative to the burner centerline 112. Figure 6 As shown, the liner dilution flow extension member 186 may also extend upstream relative to the burner centerline 112 at a second angle 188 (i.e., towards the upstream end 77 of the annular liner 52). In an exemplary aspect, the second angle 188 may range from -45 degrees (negative for the upstream direction) to zero degrees, where zero degrees is generally perpendicular to the burner centerline 112. In another aspect, the second angle 188 may range from zero degrees to +45 degrees (positive for the downstream direction towards the downstream end 67 of the annular liner 52). Of course, the range of the second angle 188 is not limited to the aforementioned range and may be used alternatively for other ranges. Similar to the first angle 166, one purpose of the second angle 188 of the liner dilution flow extension member 186 is to provide directional flow of dilution air into the dilution zone 72 of the combustion chamber 62.

[0047] Again, as described above, the implementation of the annular groove dilution opening 154 in the annular liner 52 results in a double bushing comprising a front section 160 and a rear section 162 of the liner. Therefore, relative to the liner dilution flow extension member 186, the front section 160 comprises a front portion 190 of the liner dilution flow extension member, and the rear section 162 comprises a rear portion 192 of the liner dilution flow extension member. The front portion 190 of the dilution flow extension member may be formed via a bend 194 in the liner material, or may be a separate member brazed or welded in place. Similarly, the rear portion 192 of the liner dilution flow extension member may be formed via a bend 196 in the liner material, or may be a separate element brazed or welded to the outer liner material.

[0048] The radial length (i.e., height) of the liner dilution flow extension member 186 can be obtained relative to the outer surface 200 of the liner, shown as a dashed line connecting the outer surface 202 of the front section of the liner and the outer surface 204 of the rear section of the liner. The radial length is obtained as the distance 198 from the outer surface 200 of the rear portion 192 of the liner to the radially inner surface 206 of the rear portion 192 of the liner, and from the outer surface 200 of the front portion 190 of the liner to the radially inner surface 207 of the front portion 190 of the liner. (As shown...) Figure 6 As shown, the radial inner surface 206 of the rear portion 192 of the liner dilution flow extension member can be arranged at a distance 198 from the outer surface 200 of the liner, such as... Figure 6 As shown, the radial inner surface 206 may be below the outer surface 200 of the liner (i.e., radially outward). Alternatively, the radial inner surface 206 may be flush with the outer surface 200 of the liner, such that the distance 198 is zero, or the radial inner surface 206 may extend radially inward of the outer surface 200 of the liner, such that the distance 198 extends above the outer surface 200 of the liner. The same distance 198 applies to the radial inner surface 207 of the front portion 190 of the liner dilution flow extension member. Additionally, although... Figure 6 The diagram shows the radially inner surface 207 of the front portion 190 of the liner dilution flow extension member and the radially inner surface 206 of the rear portion 192 of the liner dilution flow extension member arranged at the same distance 198 from the outer surface 200 of the liner, but they can alternatively have different lengths. For example, the distance 198 to the radially inner surface 207 of the front portion 190 of the liner dilution flow extension member can be as follows: Figure 6 As shown (i.e., above the outer surface 200 of the liner), the distance 198 to the radially inner surface 206 of the rear portion 192 of the liner dilution flow extension member can be flush with the outer surface 200 of the liner, or extend radially inward beyond the outer surface 200 of the liner. When this arrangement is implemented, the longer rear portion 192 of the liner dilution flow extension member can be used to deflect more air into the liner dilution flow extension member 186.

[0049] AlthoughFigure 6 The aspects depicted generally show the inner liner dilution flow extension member 186 as a mirror image of the outer liner dilution flow extension member 164, but they are not necessarily mirror images of each other. Rather, as an example only, they can be arranged at different angles. For instance, the outer liner dilution flow extension member 164 can be arranged at a first angle 166 at -45 degrees, while the inner liner dilution flow extension member 186 can be arranged at a second angle 188 at -30 degrees. Furthermore, the first angle 166 of the outer liner dilution flow extension member 164 can vary circumferentially about the burner centerline 112. Similarly, the second angle 188 of the inner liner dilution flow extension member 186 can vary circumferentially about the burner centerline 112. In this case, when the first angle 166 and the second angle 188 vary circumferentially, in such a way... Figure 6 At any particular cross-section shown, the outer liner dilution flow extension member 164 and the inner liner dilution flow extension member 186 may or may not be mirror images of each other.

[0050] Figure 7 It is along Figure 6 Detailed view in Figures 7-7 Detailed view of the cut bushing joint. Figure 7 An exemplary technique is shown for connecting the front section 156 and the rear section 158 of the outer liner at the outer liner dilution flow extension member 164. Figure 7 A bolted joint is shown, in which a spacer 208 is inserted between the front portion 168 and the rear portion 170 of the outer liner dilution flow extension member. Bolts 210, washers 212, and nuts 214 are inserted through holes in the front portion 168, the rear portion 170, and the spacer 208 of the outer liner dilution flow extension member. Thus, a bolted joint is formed. Multiple bolted joints may be intermittently arranged circumferentially around the annular outer liner 54. Of course, this disclosure is not limited to this. Figure 7 The bolted joint shown can be used, and other techniques for connecting the front section 156 and the rear section 158 of the outer liner can be implemented alternatively. For example, the spacer can be brazed or welded in place instead of being implemented as part of the bolted joint. It should also be noted that, although Figure 6 or Figure 7 As not shown, the same connection technique (e.g., bolted joint) can be applied to the annular liner 52 to connect the front section 160 of the liner to the rear section 162 of the liner.

[0051] Figure 8 This is a partial cross-sectional side view of an exemplary burner bushing convergence-divergence section 100 according to yet another aspect of this disclosure. Figure 8 Similar to Figure 6 However, it has some additional features, which will not be discussed in more detail below. Figure 6 and Figure 8 In common aspects, and the above regardingFigure 6 The same description applies to common characteristics. Figure 8 This includes perforations in the inner and outer liners, as well as additional features such as directional flow inserts. The perforations in the liner help provide surface cooling of the liner, while the directional flow inserts provide an air jet through the dilution flow extension members, allowing the airflow to penetrate deeper into the dilution zone of the combustion chamber. More specifically, such as... Figure 8 As shown, a directional flow insert 216 is disposed in both the outer liner dilution flow extension member 164 and the inner liner dilution flow extension member 186. The directional flow insert 216 may include a directional flow insert nozzle 218, which may be a through-hole in the directional flow insert 216. Alternatively, the directional flow insert nozzle 218 may be a tapered orifice with a larger opening on one side of the nozzle (e.g., the inlet side) and a smaller opening on the other side of the nozzle (e.g., the outlet side).

[0052] The directional flow insert 216 can also be used to form a connection between the front section 156 and the rear section 158 of the outer liner by brazing or welding to the front portion 168 of the outer liner dilution flow extension member and the rear portion 170 of the inner liner dilution flow extension member. A similar connection is made on the annular inner liner 52, wherein the directional flow insert 216 is disposed between the front portion 190 and the rear portion 192 of the inner liner dilution flow extension member. The directional flow insert nozzle 218 is used to provide a directional airflow through the outer liner dilution flow extension member 164 into the dilution zone 72 of the combustion chamber 62, in order to help provide airflow that penetrates even deeper into the dilution zone. (Regarding...) Figure 7 Similar to the bolted joints discussed, multiple directional flow inserts 216 may be circumferentially spaced relative to the burner centerline 112 around the annular outer liner 54 and the annular inner liner 52.

[0053] Still referencing Figure 8The annular outer liner 54 may also include a plurality of perforations 220 passing through the OLCD section 102, and the annular inner liner 52 may include a plurality of perforations 220 passing through the ILCD section 104. Referring to the OLCD section 102, the plurality of perforations 220 may be provided through the OLCD section convergence portion 106, the OLCD section divergence portion 116, and the OLCD section transition portion 114, including any one of the outer liner front section bend 172 or the outer liner rear section bend 174, and the outer liner dilution flow extension member front portion 168 or the outer liner dilution flow extension member rear portion 170. A similar arrangement of the plurality of perforations 220 may be provided through the ILCD section convergence portion 126, the ILCD section divergence portion 134, and the ILCD section transition portion 132, including any one of the inner liner front section bend 194 or the inner liner rear section bend 196, and the inner liner dilution flow extension member front portion 190 or the inner liner dilution flow extension member rear portion 192. Multiple perforations 220 may be circumferentially spaced around the respective inner and outer liners, or may be included in discrete circumferential sections of each bushing. The number, size, position, and angular arrangement of the multiple perforations 220 may vary to provide the desired cooling effect to the surface of the bushing.

[0054] Figure 9 A partial cross-sectional side view of an exemplary burner bushing convergence-divergence section 100 according to another aspect of this disclosure is depicted. Figure 9 The aspects shown are similar to Figure 3 and Figure 4 However, in Figure 9 In this embodiment, the outer liner dilution opening guide 222 is implemented adjacent to the dilution opening 88, which is depicted as a through-hole dilution opening by way of example. Similarly, the inner liner dilution opening guide 224 is implemented adjacent to the annular groove dilution opening 154, which is depicted as an annular groove dilution opening by way of example. When the dilution opening 88 is implemented as a circular hole, for example, a plurality of outer liner dilution flow guides 222 may be included, such that each dilution opening 88 includes a corresponding outer liner dilution flow guide 222. When the annular groove dilution opening 154 is disposed in the inner liner 52, the inner liner dilution opening guide 224 may be disposed circumferentially around the inner liner adjacent to the annular groove dilution opening 154. Of course, this disclosure is not limited to implementing the dilution opening 88 with the outer liner dilution opening guide 222 in the OLCD section 102, and the annular groove dilution opening 152 may be implemented in the OLCD section 102. Figure 3 and Figure 4 The dilution opening 90 is replaced by an externally lined dilution guide 222. Similarly, the dilution opening 90 has an internally lined dilution guide 224. Figure 3 This can be implemented alternatively in ILCD segment 104. Alternatively, any combination of the foregoing can be implemented between OLCD segment 102 and ILCD segment 104.

[0055] The outer liner deflection angle 226 of the outer liner dilution opening guide 222 and the inner liner deflection angle 228 of the inner liner dilution opening guide 224 can be set to obtain a desired amount of airflow into the dilution zone 72 of the combustion chamber 62, and / or a desired directional flow of air into the dilution zone 72 of the combustion chamber 62. Figure 2 As an example, the outer liner deflection angle can range from zero degrees (i.e., perpendicular to the burner centerline 112) to -45 degrees (i.e., towards the upstream end 76 of the annular outer liner 54). Similarly, the inner liner deflection angle 228 can range from zero degrees (i.e., perpendicular to the burner centerline 112) to +45 degrees (i.e., towards the upstream end 77 of the annular inner liner 52). Of course, other angles can also be used. Furthermore, the height of each deflector can be varied to obtain the desired airflow through the dilution opening. For example, as... Figure 9 As shown, the height of the outer liner dilution opening guide 222 can be such that the outer end 230 of the outer liner deflector is arranged flush with the outer surface 178 of the annular outer liner 54. Alternatively, the height of the outer liner dilution opening guide 222 can be such that the outer end 230 extends radially outward beyond the outer surface 178, or the outer end 230 is radially inward of the outer surface 178. The height of the inner liner dilution opening guide 224 can be similar, such that the outer end 232 of the inner liner guide is flush with the outer surface 200 of the inner liner and is radially inward or radially outward of the outer surface 200.

[0056] Figure 10 A partial cross-sectional side view depicting an exemplary convergence-divergence section of a burner bushing according to yet another aspect of this disclosure is shown. Figure 10 The image depicts an arrangement in which multiple dilution flow extension members are provided. Figure 10 In the example, the first dilution flow extension member 234 and the second dilution flow extension member 236 are disposed in the OLCD section transition portion 114. Each of the first dilution flow extension member 234 and the second dilution flow extension member 236 may be similar to Figure 8 The illustrated outer liner dilution flow extension member 164 may include a directional flow insert 216. Although Figure 10 A dilution opening 90 is depicted through the annular liner 52, but the annular liner 52 may also include multiple dilution flow extension members similar to the annular outer liner 54.

[0057] Figure 11 Based on aspects of this disclosure Figure 2 A partial cross-sectional front view of an exemplary convergent-divergent burner bushing, taken at plane 11-11. Figure 11 The aspects shown are Figure 3The cross-section shown is taken at plane 11-11, circumferentially passing through the burner bushing around the burner centerline 112. Figure 11 In the image, it can be seen that the annular inner liner 52 and the annular outer liner 54 include convergent-divergent portions 100, for example... Figure 3 The and shown Figure 11 As shown in plane 3-3, the non-convergent-divergent segments 105 circumferentially around the burner centerline 112, and the alternating circumferential segments, are as follows: Figure 13 As shown, and in Figure 11 As shown in plane 13-13. For example, in the circumferential direction, it may include a convergent-divergent portion 100, such as the portion representing the convergent-divergent portion 100 shown in plane 3-3, and alternatively, in the circumferential direction C, it may include a non-convergent-divergent portion 105, such as... Figure 13 As shown, it can be located on either side of the convergent-divergent section 100. Here, in the non-convergent-divergent section 105, the outer liner non-convergent-divergent section 101 may include a plurality of dilution holes 238 in the annular outer liner 54, and the inner liner non-convergent-divergent section 103 may include a plurality of dilution holes 240 in the annular inner liner 52.

[0058] Figure 12 Is Figure 11 A magnified detail image cropped at point 12-12. Figure 12 In the image, the annular outer liner 54 can be seen to include a dilution opening 88 that passes through the OLCD section transition portion 114, as shown in the image. Figure 3 As seen in the diagram. Along the circumferential direction, a plurality of dilution nozzles 242 may be included, which pass through an annular liner 54 adjacent to the dilution opening 88. The dilution nozzles 242 may be angled inward to provide an air jet toward the airflow passing through the dilution opening 88.

[0059] While the foregoing description generally pertains to gas turbine engines, it will be 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.

[0060] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0061] A burner bushing for a gas turbine burner, the burner bushing comprising: an annular outer liner extending circumferentially around a burner centerline of the burner and extending longitudinally from an upstream end of the annular outer liner to a downstream end of the annular outer liner relative to the burner centerline; and an annular inner liner extending circumferentially around a burner centerline and extending longitudinally from an upstream end of the annular inner liner to a downstream end of the annular inner liner relative to the burner centerline, the annular outer liner and the annular inner liner defining a combustion chamber therebetween, the combustion chamber having a primary combustion zone defined at an upstream end of the combustion chamber, a secondary combustion zone defined at a downstream end of the combustion chamber, and a dilution zone defined between the primary combustion zone and the secondary combustion zone, wherein the annular outer liner includes an outer liner convergence-divergence (OLCD) section, The outer liner convergence-divergence (OLCD) section extends radially inward in the longitudinal direction relative to the burner centerline into the dilution zone of the combustion chamber, and the annular inner liner includes an inner liner convergence-divergence (ILCD) section extending radially outward in the longitudinal direction relative to the burner centerline into the dilution zone of the combustion chamber. The OLCD section and the ILCD section cross the combustion chamber and are radially opposite each other. The OLCD section includes at least one outer liner dilution opening defined through the OLCD section for providing oxidant flow through the annular outer liner to the dilution zone of the combustion chamber, and the ILCD section includes at least one inner liner dilution opening defined through the ILCD section for providing oxidant flow through the annular inner liner to the dilution zone of the combustion chamber.

[0062] The burner bushing according to any one of the preceding clauses, wherein, circumferentially around the burner centerline, the OLCD segment extends further radially inward relative to the burner centerline in the circumferential direction into the dilution zone of the combustion chamber, and the ILCD segment extends further radially outward relative to the burner centerline in the circumferential direction into the dilution zone of the combustion chamber, the OLCD segment and the ILCD segment radially opposite each other across the combustion chamber, and wherein the burner bushing further includes a plurality of outer liner non-convergent-divergent segments and a plurality of inner liner non-convergent-divergent segments, the plurality of outer liner non-convergent-divergent segments being alternately spaced circumferentially around the burner centerline between corresponding OLCD segments of the plurality of OLCD segments, and the plurality of inner liner non-convergent-divergent segments being alternately spaced circumferentially around the burner centerline between corresponding ILCD segments of the plurality of ILCD segments.

[0063] According to any one of the preceding clauses, the annular outer liner further includes at least one outer liner dilution opening guide, the at least one outer liner dilution opening guide being adjacent to a corresponding outer liner dilution opening in the at least one outer liner dilution opening, and wherein the annular inner liner further includes at least one inner liner dilution opening guide, the at least one inner liner dilution opening guide being adjacent to a corresponding inner liner dilution opening in the at least one inner liner dilution opening.

[0064] According to any one of the preceding clauses, the burner bushing, wherein the OLCD section comprises: (i) an OLCD section convergence portion, the OLCD section convergence portion radially inward and longitudinally rearward relative to the burner centerline from the upstream end of the OLCD section to the upstream end of the OLCD section transition portion into the combustion chamber; (ii) an OLCD section divergence portion, the OLCD section divergence portion extending radially outward and longitudinally rearward relative to the burner centerline from the downstream end of the OLCD section transition portion to the downstream end of the OLCD section; and (iii) the OLCD section transition portion, the OLCD section transition portion connecting the downstream end of the OLCD section convergence portion and the OLC. The ILCD section comprises: (i) an ILCD section convergence portion, which converges radially outward and longitudinally backward relative to the burner centerline from the upstream end of the ILCD section to the upstream end of the ILCD section transition portion into the combustion chamber; (ii) an ILCD section divergence portion, which extends radially inward and longitudinally backward relative to the burner centerline from the downstream end of the ILCD section transition portion to the downstream end of the ILCD section; and (iii) the ILCD section transition portion, which connects the downstream end of the ILCD section and the upstream end of the ILCD section divergence portion.

[0065] The burner bushing according to any of the preceding clauses, wherein the OLCD section transition portion has a parabolic shape, the focal point of which is located radially outward of the OLCD section transition portion relative to the burner centerline, and the ILCD section transition portion has a parabolic shape, the focal point of which is located radially inward of the ILCD section transition portion relative to the burner centerline.

[0066] The burner liner according to any of the preceding clauses, wherein the at least one outer liner dilution opening is defined through the OLCD section transition portion, and the at least one inner liner dilution opening is defined through the ILCD section transition portion.

[0067] The burner liner according to any of the preceding clauses, wherein the at least one outer liner dilution opening comprises a plurality of outer liner dilution holes, and the at least one inner liner dilution opening comprises a plurality of inner liner dilution holes.

[0068] The burner bushing according to any one of the preceding clauses, wherein a corresponding outer liner dilution hole of the plurality of outer liner dilution holes is directly opposite a corresponding inner liner dilution hole of the plurality of inner liner dilution holes across the combustion chamber.

[0069] The burner bushing according to any of the preceding clauses, wherein a corresponding outer liner dilution hole of the plurality of outer liner dilution holes is arranged at a radial angle relative to the burner centerline in the range of -30 degrees to +30 degrees, and wherein a corresponding inner liner dilution hole of the plurality of inner liner dilution holes is arranged at a radial angle relative to the burner centerline in the range of -30 degrees to +30 degrees.

[0070] The burner liner according to any of the preceding clauses, wherein both the at least one outer liner dilution opening and the at least one inner liner dilution opening comprise an annular groove.

[0071] The burner liner according to any one of the preceding clauses, wherein a front section of the outer liner is defined in front of the annular groove passing through the outer liner, and a rear section of the outer liner is defined behind the annular groove passing through the outer liner, a plurality of outer liner connecting members connecting the front section and the rear section of the outer liner, and wherein a front section of the inner liner is defined in front of the annular groove passing through the inner liner, and a rear section of the inner liner is defined behind the annular groove passing through the inner liner, a plurality of inner liner connecting members connecting the front section and the rear section of the inner liner.

[0072] The burner liner according to any of the preceding clauses, wherein the at least one outer liner dilution opening further comprises a plurality of outer liner dilution holes, and wherein the at least one inner liner dilution opening further comprises a plurality of inner liner dilution holes.

[0073] The burner liner according to any one of the preceding clauses, wherein the annular groove through the outer liner is opposite to the plurality of inner liner dilution holes across the combustion chamber, and the annular groove through the inner liner is opposite to the plurality of outer liner dilution holes across the combustion chamber.

[0074] The burner liner according to any one of the preceding clauses, wherein the annular groove of the annular outer liner includes an outer liner dilution flow extension member extending radially outward from the annular outer liner relative to the burner centerline, and the annular groove of the annular inner liner includes an inner liner dilution flow extension member extending radially inward from the annular inner liner relative to the burner centerline.

[0075] According to any of the preceding clauses, the burner liner, wherein the outer liner dilution flow extension member further extends upstream at a first angle relative to the burner centerline, and the inner liner dilution flow extension member further extends upstream at a second angle relative to the burner centerline.

[0076] The burner liner according to any of the preceding clauses, wherein the front section of the outer liner includes the front portion of the outer liner dilution flow extension member, and the rear section of the outer liner includes the rear portion of the outer liner dilution flow extension member, and wherein the front section of the inner liner includes the front portion of the inner liner dilution flow extension member, and the rear section of the inner liner includes the rear portion of the inner liner dilution flow extension member.

[0077] The burner liner according to any one of the preceding clauses, wherein the annular outer liner further includes a plurality of outer liner perforations passing through the OLCD section convergent portion, the OLCD section divergent portion, and / or the OLCD section transition portion, and wherein the annular inner liner further includes a plurality of inner liner perforations passing through the ILCD section convergent portion, the ILCD section divergent portion, and / or the ILCD section transition portion.

[0078] The burner liner according to any one of the preceding clauses, wherein the outer liner dilution flow extension member includes a plurality of outer liner directional flow inserts spaced circumferentially around the burner centerline, and the inner liner dilution flow extension member includes a plurality of inner liner directional flow inserts spaced circumferentially around the burner centerline.

[0079] The burner liner according to any of the preceding clauses, wherein at least one of the outer liner front section, the outer liner rear section, the inner liner front section and / or the inner liner rear section includes a plurality of dilution flow extension members, each dilution flow extension member having a directional flow insert.

[0080] The burner liner according to any one of the preceding clauses, wherein the at least one outer liner dilution opening is defined to pass through one or more of the OLCD section convergence portion, the OLCD section divergence portion, and the OLCD section transition portion, and wherein the at least one inner liner dilution opening is defined to pass through one or more of the ILCD section convergence portion, the ILCD section divergence portion, and the ILCD section transition portion.

[0081] A combustor for a gas turbine, the combustor comprising: a combustor bushing; a dome assembly connected to an upstream end of the combustor bushing; a vortex assembly connected to the dome assembly; and a fuel nozzle assembly connected to the vortex assembly, wherein the combustor bushing includes: (a) an annular outer liner extending circumferentially around a combustor centerline of the combustor and extending longitudinally from an upstream end of the annular outer liner to a downstream end of the annular outer liner relative to the combustor centerline; and (b) an annular inner liner extending circumferentially around a combustor centerline and extending longitudinally from an upstream end of the annular inner liner to a downstream end of the annular inner liner relative to the combustor centerline, the annular outer liner and the annular inner liner defining a combustion chamber therebetween, the combustion chamber having a primary combustion zone defined at an upstream end of the combustion chamber. The combustion chamber includes a secondary combustion zone at its downstream end and a dilution zone defined between the primary combustion zone and the secondary combustion zone. The annular outer liner includes an outer liner convergent-divergent (OLCD) section extending radially in the longitudinal direction relative to the burner centerline into the dilution zone of the combustion chamber. The annular inner liner includes an inner liner convergent-divergent (ILCD) section extending radially outward in the longitudinal direction relative to the combustion chamber centerline into the dilution zone of the combustion chamber. The OLCD section and the ILCD section cross the combustion chamber and are radially opposite each other. The OLCD section includes at least one outer liner dilution opening through the OLCD section to provide an oxidant flow through the outer liner to the dilution zone of the combustion chamber. The ILCD section includes at least one inner liner dilution opening defined by the ILCD section for providing an oxidant flow through the inner liner to the dilution zone of the combustion chamber.

[0082] According to any of the preceding clauses, the OLCD section comprises: (i) an OLCD section convergence portion, the OLCD section convergence portion converging radially inward and longitudinally backward relative to the burner centerline into the combustion chamber, from the upstream end of the OLCD section to the upstream end of the OLCD section transition portion; (ii) an OLCD section divergence portion, the OLCD section divergence portion extending radially outward and longitudinally backward relative to the burner centerline from the downstream end of the OLCD section transition portion to the downstream end of the OLCD section; and (iii) the OLCD section transition portion connecting the downstream end of the OLCD section convergence portion and the OLCD section divergence portion. The ILCD section comprises: (i) an ILCD section convergence portion, which converges radially outward and longitudinally backward relative to the burner centerline from the upstream end of the ILCD section to the upstream end of the ILCD section transition portion into the combustion chamber; (ii) an ILCD section divergence portion, which extends radially inward and longitudinally backward relative to the burner centerline from the downstream end of the ILCD section transition portion to the downstream end of the ILCD section transition portion; and (iii) the ILCD section transition portion connecting the downstream end of the ILCD section and the upstream end of the ILCD section divergence portion.

[0083] The burner according to any one of the preceding clauses, wherein the at least one outer liner dilution opening is defined through the OLCD section transition portion, and the at least one inner liner dilution opening is defined through the ILCD section transition portion.

[0084] 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, characterized in that, The burner bushing includes: An annular liner extending circumferentially around the burner centerline and extending longitudinally from an upstream end to a downstream end relative to the burner centerline; and An annular liner extends circumferentially around the burner centerline and extends longitudinally from an upstream end to a downstream end relative to the burner centerline. The annular outer liner and the annular inner liner define a combustion chamber therebetween, the combustion chamber having a primary combustion zone defined at an upstream end of the combustion chamber, a secondary combustion zone defined at a downstream end of the combustion chamber, and a dilution zone defined between the primary combustion zone and the secondary combustion zone. The annular outer liner includes an outer liner convergence-divergence (OLCD) section, which extends radially inward in the longitudinal direction relative to the burner centerline into the dilution zone of the combustion chamber. The annular inner liner includes an inner liner convergence-divergence (ILCD) section, which extends radially outward in the longitudinal direction relative to the burner centerline into the dilution zone of the combustion chamber. The OLCD section and the ILCD section are radially opposite each other across the combustion chamber. The OLCD section includes at least one outer liner dilution opening defined through the OLCD section for providing oxidant flow through the annular outer liner to the dilution zone of the combustion chamber, and the ILCD section includes at least one inner liner dilution opening defined through the ILCD section for providing oxidant flow through the annular inner liner to the dilution zone of the combustion chamber. The at least one outer liner dilution opening includes an annular groove in the outer liner and a plurality of outer liner dilution holes longitudinally offset from the annular groove. The at least one inner liner dilution opening includes an annular groove in the inner liner and a plurality of inner liner dilution holes longitudinally offset from the annular groove in the inner liner. The annular groove in the outer liner is opposite to the plurality of inner liner dilution holes across the combustion chamber.

2. The burner bushing according to claim 1, characterized in that, in, The OLCD segment extends radially inward relative to the burner centerline in the circumferential direction into the dilution zone of the combustion chamber, and the ILCD segment extends radially outward relative to the burner centerline in the circumferential direction into the dilution zone of the combustion chamber. The OLCD segment and the ILCD segment are radially opposite each other across the combustion chamber. The burner bushing further includes multiple outer liner non-convergent-divergent sections and multiple inner liner non-convergent-divergent sections. The multiple outer liner non-convergent-divergent sections are alternately spaced in the circumferential direction between corresponding OLCD sections in the multiple OLCD sections. The multiple inner liner non-convergent-divergent sections are alternately spaced in the circumferential direction between corresponding ILCD sections in the multiple ILCD sections.

3. The burner according to claim 1, characterized in that, in, The annular outer liner further includes at least one outer liner dilution opening guide, the at least one outer liner dilution opening guide being adjacent to a corresponding outer liner dilution opening among the at least one outer liner dilution openings, and The annular liner further includes at least one liner dilution opening guide, which is adjacent to a corresponding liner dilution opening in the at least one liner dilution opening.

4. The burner bushing according to claim 1, characterized in that, in, The OLCD segment includes: (i) an OLCD section convergence portion, which converges radially inward and longitudinally backward relative to the burner centerline from the upstream end of the OLCD section to the upstream end of the OLCD section transition portion into the combustion chamber; (ii) an OLCD section divergence portion, which extends radially outward and longitudinally backward relative to the burner centerline from the downstream end of the OLCD section transition portion to the downstream end of the OLCD section; and (iii) the OLCD section transition portion, which connects the downstream end of the OLCD section convergence portion and the upstream end of the OLCD section divergence portion. The ILCD segment includes: (i) a convergent portion of the ILCD section, which converges radially outward and longitudinally backward relative to the burner centerline from the upstream end of the ILCD section to the upstream end of the ILCD section transition portion into the combustion chamber; (ii) a divergent portion of the ILCD section, which extends radially inward and longitudinally backward relative to the burner centerline from the downstream end of the ILCD section transition portion to the downstream end of the ILCD section; and (iii) the ILCD section transition portion, which connects the downstream end of the ILCD section and the upstream end of the ILCD section divergent portion.

5. The burner bushing according to claim 4, characterized in that, in, The OLCD section transition portion has a parabolic shape, with its focal point located radially outward relative to the burner centerline of the OLCD section transition portion, and the ILCD section transition portion has a parabolic shape, with its focal point located radially inward relative to the burner centerline of the ILCD section transition portion.

6. The burner bushing according to claim 4, characterized in that, in, The at least one outer liner dilution opening is defined to pass through the OLCD section transition portion, and the at least one inner liner dilution opening is defined to pass through the ILCD section transition portion.

7. The burner bushing according to claim 1, characterized in that, in, The respective outer liner dilution holes of the plurality of outer liner dilution holes are arranged at a radial angle relative to the burner centerline in the range of -30 degrees to +30 degrees, and The respective lining dilution holes in the plurality of lining dilution holes are arranged at a radial angle relative to the burner centerline in the range of -30 degrees to +30 degrees.

8. The burner bushing according to claim 1, characterized in that, in, The front section of the outer liner is defined in front of the annular groove of the outer liner, and the rear section of the outer liner is defined behind the annular groove of the outer liner. A plurality of outer liner connecting members connect the front section and the rear section of the outer liner. The front section of the liner is defined in front of the annular groove of the liner, and the rear section of the liner is defined behind the annular groove of the liner. A plurality of liner connecting members connect the front section of the liner and the rear section of the liner.

9. The burner bushing according to claim 8, characterized in that, in, At least one of the outer liner annular grooves includes an outer liner dilution flow extension member that extends radially outward from the annular outer liner relative to the burner centerline, or the inner liner annular groove includes an inner liner dilution flow extension member that extends radially inward from the annular inner liner relative to the burner centerline.

10. The burner bushing according to claim 9, characterized in that, in, The outer liner dilution flow extension member further extends upstream at a first angle relative to the burner centerline, and the inner liner dilution flow extension member further extends upstream at a second angle relative to the burner centerline.

11. The burner bushing according to claim 10, characterized in that, in, The front section of the outer liner includes the front portion of the outer liner dilution flow extension member, and the rear section of the outer liner includes the rear portion of the outer liner dilution flow extension member. The front section of the liner includes the front portion of the liner dilution flow extension member, and the rear section of the liner includes the rear portion of the liner dilution flow extension member.

12. The burner bushing according to claim 9, characterized in that, in, The annular outer liner further includes multiple liner perforations passing through the convergent portion of the OLCD section, through the divergent portion of the OLCD section, and / or through the transition portion of the OLCD section. The annular liner further includes a plurality of liner perforations passing through the convergent portion of the ILCD section, the divergent portion of the ILCD section, and / or the transition portion of the ILCD section.

13. The burner bushing according to claim 9, characterized in that, in, The outer liner dilution flow extension member includes a plurality of outer liner directional flow inserts spaced circumferentially around the burner centerline, and the inner liner dilution flow extension member includes a plurality of inner liner directional flow inserts spaced circumferentially around the burner centerline.

14. The burner bushing according to claim 9, characterized in that, in, At least one of the outer liner front section, the outer liner rear section, the inner liner front section, or the inner liner rear section includes a plurality of dilution flow extension members, each dilution flow extension member having a directional flow insert.

15. The burner bushing according to claim 4, characterized in that, in, The at least one outer liner dilution opening is defined to pass through one or more of the OLCD segment convergence portion, the OLCD segment divergence portion, and the OLCD segment transition portion, and The at least one liner dilution opening is defined to pass through one or more of the ILCD segment convergence portion, the ILCD segment divergence portion, and the ILCD segment transition portion.

16. A burner bushing for a gas turbine burner, characterized in that, The burner bushing includes: An annular liner extending circumferentially around the burner centerline and extending longitudinally from an upstream end to a downstream end relative to the burner centerline; and An annular liner extends circumferentially around the burner centerline and extends longitudinally from an upstream end to a downstream end relative to the burner centerline. The annular outer liner and the annular inner liner define a combustion chamber therebetween, the combustion chamber having a primary combustion zone defined at an upstream end of the combustion chamber, a secondary combustion zone defined at a downstream end of the combustion chamber, and a dilution zone defined between the primary combustion zone and the secondary combustion zone. The annular outer liner includes an outer liner convergence-divergence (OLCD) section, which extends radially inward in the longitudinal direction relative to the burner centerline into the dilution zone of the combustion chamber. The annular inner liner includes an inner liner convergence-divergence (ILCD) section, which extends radially outward in the longitudinal direction relative to the burner centerline into the dilution zone of the combustion chamber. The OLCD section and the ILCD section are radially opposite each other across the combustion chamber. The OLCD section includes at least one outer liner dilution opening defined by the OLCD section for providing an oxidant flow through the annular outer liner to the dilution zone of the combustion chamber, and the ILCD section includes at least one inner liner dilution opening defined by the ILCD section for providing an oxidant flow through the annular inner liner to the dilution zone of the combustion chamber. Wherein, the at least one outer liner dilution opening includes an outer liner annular groove, and the at least one inner liner dilution opening includes an inner liner annular groove. The outer liner front section is defined in front of the annular groove passing through the annular outer liner, and the outer liner rear section is defined behind the annular groove passing through the annular outer liner. A plurality of outer liner connecting members connect the outer liner front section and the outer liner rear section. Similarly, the inner liner front section is defined in front of the annular groove passing through the annular inner liner, and the inner liner rear section is defined behind the annular groove passing through the annular inner liner. A plurality of inner liner connecting members connect the inner liner front section and the inner liner rear section. Wherein, at least one of the outer liner annular grooves includes an outer liner dilution flow extension member, the outer liner dilution flow extension member extending radially outward from the annular outer liner relative to the burner centerline, or the inner liner annular groove includes an inner liner dilution flow extension member, the inner liner dilution flow extension member extending radially inward from the annular inner liner relative to the burner centerline.

17. The burner bushing according to claim 16, characterized in that, in, The outer liner dilution flow extension member further extends upstream at a first angle relative to the burner centerline, and the inner liner dilution flow extension member further extends upstream at a second angle relative to the burner centerline.

18. The burner bushing according to claim 17, characterized in that, in, The front section of the outer liner includes the front portion of the outer liner dilution flow extension member, and the rear section of the outer liner includes the rear portion of the outer liner dilution flow extension member. The front section of the liner includes the front portion of the liner dilution flow extension member, and the rear section of the liner includes the rear portion of the liner dilution flow extension member.

19. The burner bushing according to claim 16, characterized in that, in, The annular outer liner further includes multiple liner perforations passing through the convergent portion of the OLCD section, through the divergent portion of the OLCD section, and / or through the transition portion of the OLCD section. The annular liner further includes a plurality of liner perforations passing through the convergent portion of the ILCD section, the divergent portion of the ILCD section, and / or the transition portion of the ILCD section.

20. The burner bushing according to claim 16, characterized in that, in, The outer liner dilution flow extension member includes a plurality of outer liner directional flow inserts spaced circumferentially around the burner centerline, and the inner liner dilution flow extension member includes a plurality of inner liner directional flow inserts spaced circumferentially around the burner centerline.

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