Combustor swirler to pseudo-dome attachment and interface with CMC dome

Abstract

A combustor for a gas turbine includes a shroud structure, a pseudo-dome structure, a ceramic matrix composite (CMC) dome, and a swirler assembly. The swirler assembly is connected to the pseudo-dome structure, which is connected to the shroud structure, and the CMC dome is connected to the shroud structure separately from the swirler assembly. The swirler assembly includes a swirler dome interface wall that interfaces with the CMC dome on an upstream side of the CMC dome, and a swirler outlet extends through a CMC dome swirler opening that passes through the CMC dome.

Description

Technical Field

[0001] The present disclosure relates to connecting a combustor swirler in a combustor to interface with a CMC (ceramic matrix composite) dome in a gas turbine engine. Background Art

[0002] Some conventional gas turbine engines are known to include rich-burn combustors, which typically utilize a swirler assembly connected to a dome structure. Both the swirler assembly and the dome structure are generally metallic and connected to one another. Metal dome structures are known to include a deflector wall on the combustion chamber side of the dome, wherein the deflector wall deflects heat generated in the combustor during combustion. Cooling holes are generally included through the dome structure to provide some surface cooling of the dome and the deflector wall. The metal swirler assembly is generally brazed or welded to the dome structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Features and advantages of the present disclosure will become apparent from the following description of various exemplary embodiments as illustrated in the drawings, in which like reference numbers generally indicate identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine according to aspects of the present disclosure.

[0005] Figure 2 is a partial cross-sectional side view of an exemplary combustor according to aspects of the present disclosure.

[0006] Figure 3 According to aspects of the present disclosure Figure 1 A partial cross-sectional rear-forward view of an exemplary combustor taken at plane 3-3.

[0007] Figure 4 According to aspects of the present disclosure Figure 2 Detailed view 114 is a partial cross-sectional side view of the cyclone to pseudo-dome connection and CMC dome interface.

[0008] Figure 5 According to aspects of the present disclosure Figure 2 A partial cross-sectional side view of the CMC dome and pseudo-dome structural connection to the cover taken at detail view 114 of FIG.

[0009] Figure 6 According to aspects of the present disclosure Figure 2 Detailed view 114 is an enlarged partial cross-sectional side view of the cyclone to pseudo-dome connection and CMC dome interface. DETAILED DESCRIPTION

[0010] The features, advantages and embodiments of the present disclosure are set forth or apparent from consideration of the following detailed description, drawings and claims. In addition, it should be understood that the following detailed description is exemplary and intended to provide further explanation, rather than limiting the scope of the disclosure as claimed.

[0011] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0012] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of each component.

[0013] The terms "upstream" and "downstream" refer to relative directions relative to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0014] The implementation of non-metallic materials in combustors is becoming increasingly common. In particular, the implementation of ceramic matrix composite (CMC) materials can be used to form dome structures instead of utilizing conventional metal dome structures. CMC materials have better thermal properties than conventional metal materials, and therefore, CMC domes require less cooling than conventional metal domes. Less cooling required for the dome means that more air can be used for other purposes, including as dilution air. In addition, the CMC dome structure does not require a guide wall, thereby reducing the overall axial length of the dome, which also reduces the length of the combustor module. However, the implementation of the CMC dome with a metal cyclone poses challenges in the ability to connect the metal cyclone to the CMC dome and provide thermal decoupling between the metal cyclone and the CMC dome. The present disclosure provides a technique for separately mounting the metal cyclone to the shroud using a metal pseudo-dome structure, and also separately mounting the CMC dome to the shroud. A cyclone assembly connected to the pseudo-dome structure away from the CMC dome can still interface with the CMC dome.

[0015] Referring now to the accompanying drawings, Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine 10, referred to herein as "engine 10," with which various embodiments of the present disclosure may be incorporated. Although the present disclosure is further described below with reference to a ducted turbofan engine, the present disclosure is also generally applicable to turbomachinery, including turbojets, turboprops, and turboshaft gas turbine engines, including marine and industrial turbine engines, and auxiliary power units. Additionally, the present disclosure is not limited to, for example, Figure 1Instead of the ducted fan turbine engine shown in FIG, it can be implemented in a non-ducted fan (UDF) turbine engine. Figure 1 As shown, for reference, engine 10 has a centerline axis 12 extending therethrough from an upstream end 98 to a downstream end 99. Generally speaking, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of fan assembly 14.

[0016] The core engine 16 may generally include an outer casing 18 defining an annular inlet 20. The outer casing 18 encloses or at least partially forms, in serial flow relationship, a compressor section (22 / 24) having a supercharger or low pressure (LP) compressor 22, a high pressure (HP) compressor 24, a combustor 26, a turbine section (28 / 30) including a high pressure (HP) turbine 28 and a low pressure (LP) turbine 30, and an ejection exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly 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 certain embodiments, as shown in FIG. Figure 1 As shown, LP rotor shaft 36 may be connected to fan shaft 38 via reduction gear 40, such as in an indirect drive or gear drive configuration. In other embodiments, although not shown, engine 10 may further include an intermediate pressure (IP) compressor and a turbine rotatable with the IP shaft.

[0017] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from a fan shaft 38. An annular fan casing or nacelle 44 circumferentially surrounds the fan assembly 14 and / or at least a portion of the core engine 16. In one embodiment, the nacelle 44 can be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. In addition, at least a portion of the nacelle 44 can extend over an outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0018] Figure 2 Yes Figure 1 A cross-sectional side view of an exemplary combustor 26 of the core engine 16 is shown. Figure 2 A combustor axial centerline 112 is depicted which may generally correspond to the centerline axis 12. Thus, Figure 2 The combustor 26 defines a combustor longitudinal direction (L) corresponding to the combustor axial centerline 112. C ), the radial direction of the burner extending outward from the axial centerline 112 of the burner (R C ), and the combustor circumferential direction (CC ).like Figure 2 As shown, the combustor 26 can generally include a shroud structure 60 and a combustor liner 50, the combustor liner 50 having an inner liner 52 and an outer liner 54, each of which is connected to the shroud structure 60. The shroud structure 60 extends in a circumferential direction relative to the combustor axial centerline 112 and, as will be described below, can be composed of a plurality of shroud segments that together extend circumferentially around the combustor axial centerline 112. The inner liner 52 and the outer liner 54 are each annular liners that extend circumferentially around the combustor axial centerline 112. A ceramic matrix composite (CMC) dome 56 extends in the combustor radial direction R C The CMC dome 56 extends between the inner liner 52 and the outer liner 54 and is connected to the shroud structure 60 at the shroud radially outer portion 57 and the shroud radially inner portion 59. The CMC dome 56 also extends circumferentially around the combustor axial centerline 112. The inner liner 52, the outer liner 54, and the CMC dome 56 together define a combustion chamber 62 therebetween.

[0019] The combustor 26 also includes a swirler assembly 58 mounted to a pseudo-dome structure 61. The pseudo-dome structure 61 is connected to the shroud structure 60 at a shroud radially outer portion 57 and a shroud radially inner portion 59. The pseudo-dome structure 61 may extend circumferentially about the combustor axial centerline 112 or, as will be described below, may include multiple segments extending around the circumference of the combustor 26. The swirler assembly 58 is mounted to the pseudo-dome structure 61 and extends through the CMC dome 56. The swirler assembly 58 is connected to a fuel nozzle assembly 70 that injects fuel into the swirler assembly 58. In the combustion chamber 62, an initial chemical reaction of the ignited fuel-oxidant mixture injected into the combustion chamber 62 by the swirler assembly 58 occurs to produce combustion gases 86. The combustion gases 86 then flow further downstream into the HP turbine 28 and the LP turbine 30. Although Figure 2 A single swirler assembly 58 is depicted, but as will be described below, it will be understood that multiple swirler assemblies 58 are present in the combustor 26 , with the respective swirler assemblies 58 circumferentially spaced from one another about the combustor axial centerline 112 .

[0020] The combustor 26 further includes an outer shell 64 extending circumferentially about the combustor axial centerline 112, and an inner shell 65 also extending circumferentially about the combustor axial centerline 112. An outer flow passage 88 is defined between the outer shell 64 and the outer liner 54, and an inner flow passage 90 is defined between the inner shell 65 and the inner liner 52. The outer liner 54 may also include a plurality of outer liner dilution openings 68 spaced circumferentially about the outer liner 54. Similarly, the inner liner 52 may include a plurality of inner liner dilution openings 69 spaced circumferentially about the inner liner 52.

[0021] Return Reference Figure 1 In operation, air 73 enters the nacelle 44 at the nacelle inlet 76, and a portion of the air 73 enters the compressor section (22 / 24) as the compressor inlet air flow 80, where it is compressed. Another portion of the air 73 enters the bypass airflow passage 48, thereby providing the bypass airflow 78. Figure 2 , compressed air 82 from the compressor section (22 / 24) enters the combustor 26 via a diffuser (not shown). A portion of the compressed air 82(a) enters the shroud structure 60 into the plenum 66, while another portion of the compressed air 82(b) passes into the outer flow passage 88 and the inner flow passage 90. The compressed air 82(a) in the plenum 66 passes through the swirler assembly 58 to mix with the fuel injected from the fuel nozzle assembly 70 and is ignited to produce combustion gases 86. A portion of the compressed air 82(b) in the outer flow passage 88 can be used as dilution air provided to the combustion chamber 62 through the plurality of outer liner dilution openings 68, and another portion of the compressed air 82(b) in the inner flow passage 90 can also be used as dilution air provided to the combustion chamber 62 through the plurality of inner liner dilution openings 69.

[0022] Figure 3 is Figure 1 A partial cross-sectional view of the burner 26 is shown taken at plane 3-3. Figure 3 As seen, the combustor 26 has a generally annular combustor liner 50 that extends circumferentially about the centerline axis 12 of the engine 10. As it may be associated with the combustor 26, the centerline axis 12 may also correspond to the combustor axial centerline 112. The combustor liner 50 includes an outer liner 54 and an inner liner 52 that each extend circumferentially about the combustor axial centerline 112. The CMC dome 56 also extends circumferentially about the combustor axial centerline 112. Figure 2 A cross-sectional view can be seen, for example, in Figure 3 The plane 2-2 is intercepted, and although Figure 2 The cross-section of FIG depicts a single cyclone assembly 58, but multiple representative cyclone assemblies 58(a), 58(b), etc. are shown in FIG. Figure 3112 . The combustor 26 is shown as being circumferentially spaced apart around the combustor axial centerline 112. With respect to each swirler assembly 58(a), 58(b), a portion of the combustor 26 can be considered a segment of the combustor 26. That is, while the combustor 26 may extend circumferentially around the combustor axial centerline 112, the combustor 26 can be considered to include multiple segments corresponding to each swirler assembly 58. For example, the first segment 100 corresponding to the swirler assembly 58(a) and extending circumferentially between the segment boundary end 104 and the segment boundary end 106 can be included in multiple segments. The second segment 102 corresponding to the swirler assembly 58(b) and extending circumferentially between the segment boundary end 106 and the segment boundary end 108 can be included in multiple segments. As can be readily appreciated, additional segments (not labeled) and swirler assemblies (not labeled) are provided around the entire circumference of the combustor 26. As described above, the pseudo-dome structure 61 can be implemented as multiple segments. In this case, instead of a pseudo-dome structure 61 extending circumferentially about the combustor axial centerline 112, a first segment of the pseudo-dome structure 61(a) may be implemented in the first segment 100, a second pseudo-dome structure 61(b) may be implemented in the second segment 102, etc. Thus, each pseudo-dome segment (61(a), 61(b)) may be included to mount the swirler assembly (58(a), 58(b)) of the corresponding segment.

[0023] Figure 4 Depicted in Figure 2 A partial cross-sectional view of the cyclone and dome connection taken at detail view 114 of FIG. Figure 4 In FIG. 7 , the fuel nozzle assembly 70 has been removed. Figure 4 As can be seen, the shroud structure 60 includes a shroud radially outer portion 57 and a shroud radially inner portion 59. The shroud radially outer portion 57 may include an outer shroud clamp 116 having a first outer clamp portion 118 radially outwardly of the shroud clamp 116 and a second outer clamp portion 120 radially inwardly of the shroud clamp 116. Similarly, the inner shroud radially inner portion 59 may include an inner shroud clamp 122 having a first inner clamp portion 124 radially inwardly of the shroud clamp 122 and a second inner clamp portion 126 radially outwardly of the shroud clamp 122. The pseudo-dome structure 61 is connected to the shroud structure 60 at the outer shroud radially outer portion 57 and the inner shroud radially inner portion 59. This connection will be described in more detail below. The CMC dome 56 and the outer liner 54 are connected to the shroud structure 60 within the outer shroud clamp 116 via mechanical connection members 128, such as bolted joints. Similarly, the inner liner 52 and CMC dome 56 are connected to the shroud structure 60 within the shroud fixture 122 via connecting members 128. The swirler assembly 58 is connected to the pseudo-dome structure 61 and extends through the CMC dome 56. This connection will also be described in more detail below.

[0024] Figure 5 Depicted in accordance with aspects of the present disclosure Figure 2 A cross-sectional view of the connection between the CMC dome 56 and the pseudo-dome structure 61 of the cover structure 60 is taken at the detail view 114 of FIG. Figure 5 , the connecting member 128 is not shown, and the swirler 58 has been removed, but for reference purposes, the swirler centerline axis 110 is depicted, and an upstream direction 146 and a downstream direction 148 are defined relative to the swirler centerline axis 110. The pseudo-dome structure 61 is connected to the shroud outer clamp 116. More specifically, a radially outer end 130 of the pseudo-dome structure 61 may extend in the upstream direction 146 and be connected (e.g., via a brazed or bolted joint) to a radially inner surface 132 of the outer clamp second portion 120. The pseudo-dome structure 61 is also connected to the shroud inner clamp 122, wherein a radially inner end 134 of the pseudo-dome structure 61 may extend in the upstream direction 146 and be connected (e.g., via a brazed or bolted joint) to a radially outer surface 136 of the inner clamp second portion 126. The pseudo-dome structure 61 also includes a pseudo-dome swirler opening 138 therethrough for mounting the swirler assembly 58, as will be described below. The pseudo-dome cyclone opening 138 may be a cylindrical opening having a pseudo-dome cyclone opening diameter 152 as will be described below, sized to match an annular outer axial wall diameter 162 ( Figure 6 ) for mounting the cyclone assembly 58 to the pseudo-dome structure 61. Thus, the cyclone centerline axis 110 ( Figure 4 ) can also be considered to correspond to the centerline through the pseudo-dome cyclone opening 138.

[0025] The CMC dome 56 as described above extends circumferentially around the combustor axial centerline 112 and also extends in the combustor radial direction (R C ) extends upward. It should be noted that although Figure 5 It appears that the CMC dome 56 is depicted parallel to the combustor radial direction R C Extension, but as Figure 4 As shown, the CMC dome 56, and correspondingly, the pseudo-dome structure 61, can be positioned relative to the combustor radial direction R C When the CMC dome 56 is arranged at the dome angle 144, the CMC dome 56 and the pseudo-dome structure 61 are still considered to be in the combustor radial direction R. C The radially outer end 140 of the CMC dome 56 can extend in an upstream direction 146 and into the shroud outer fixture 116, and the radially inner end 142 of the CMC dome 56 can extend in an upstream direction 146 and into the shroud inner fixture 122. The outer liner 54 also extends into the shroud outer fixture 116, and as shown in FIG. Figure 4 As shown, the radially outer end 140 of the CMC dome 56 and the outer liner 54 are suitably connected to the cover outer clamp 116 via the connecting member 128. Figure 4 As shown, the CMC dome 56 and outer liner 54 are connected to the hood outer fixture 116 via connection members 128 , and the CMC dome 56 and inner liner 52 are connected to the hood inner fixture 122 via connection members 128 .

[0026] The CMC dome 56 includes a CMC dome cyclone opening 150 through the CMC dome 56. The CMC dome cyclone opening 150 may be a cylindrical opening having a CMC dome cyclone opening diameter 154, which may be larger than a cyclone outlet end 161 ( Figure 4 ) to provide a circumferential gap 156 ( ) between the inner surface 158 of the CMC dome cyclone opening 150 and the cyclone outlet end 161 of the cyclone assembly 58. Figure 4 The CMC dome cyclone opening 150 is arranged so that it is generally centered about the cyclone centerline axis 110 and is generally axially aligned with the pseudo-dome cyclone opening 138. Of course, the CMC dome cyclone opening 150 and the pseudo-dome cyclone opening 138 may be slightly axially offset relative to the cyclone centerline axis 110, with the CMC dome cyclone opening diameter 154 being larger than the diameter 160 of the cyclone outlet end 161 of the cyclone assembly 58 to form the circumferential gap 156. The CMC dome 56 may optionally include a plurality of dome cooling channels 164 therethrough.

[0027] Figure 6 An example of a cyclone assembly 58 having a CMC dome 56 and a pseudo-dome structure 61 connected thereto is depicted in accordance with aspects of the present disclosure. Figure 6 , it can be seen that the cyclone assembly 58 defines a cyclone centerline axis 110, which is in the cyclone longitudinal direction (L S ) and defines a swirler upstream direction 166 and a swirler downstream direction 168. The swirler radial direction (R S ) extends outward from the cyclone centerline axis 110, and the cyclone assembly circumferential direction (C S ) extends circumferentially about the swirler centerline axis 110. In contrast to the ceramic matrix composite material of the CMC dome 56, the swirler assembly 58 is generally formed of a metallic material. That is, the various components of the swirler assembly 58 are partially constructed of a metallic alloy material that is more susceptible to structural expansion due to the increased temperatures within the combustor than the CMC material of the CMC dome 56.

[0028] The swirler assembly 58 includes a primary swirler 170 and a secondary swirler 172 connected to a downstream side 174 of the primary swirler 170. The primary swirler 170 introduces radially inward swirl into the secondary swirler 172 from the pressure chamber 66 ( Figure 2 ) passing through the primary swirler 170. The secondary swirler 172 directs radially inward swirl to the compressed air 82(a) passing through the secondary swirler 172 from the plenum 66. The swirler assembly 58 further includes a flare 176 connected to a downstream end 178 of the secondary swirler 172. The flare 176 and its connection to the pseudo-dome structure 61 and its interface with the CMC dome 56 will now be described in greater detail.

[0029] The flare 176 extends circumferentially around the cyclone centerline axis 110. It can be seen that the flare 176 includes an annular inner axial wall 180 that extends circumferentially around the cyclone centerline axis 110 and also extends in the cyclone longitudinal direction L. S The annular inner axial wall 180 is connected to the downstream end 178 of the secondary swirler, such as by brazing. The flare 176 also includes an annular outer axial wall 182 that extends circumferentially around the swirler centerline axis 110 and also extends in the flare longitudinal direction L. S 180 . An annular outer axial wall 182 is radially outward of the annular inner axial wall 180 , and a cavity 184 may be formed therebetween. The flare 176 further includes an annular conical wall 186 that extends circumferentially about the swirler centerline axis 110 and further extends radially outward and downstream from a downstream end 188 of the annular inner axial wall 180 . A swirler downstream end 190 of the annular conical wall 186 includes a swirler outlet 192 .

[0030] The annular outer axial wall 182 includes a cyclone mounting wall 194 extending radially outward from an annular outer axial wall outer surface 196 of the annular outer axial wall 182. The cyclone mounting wall 194 may also extend circumferentially about the cyclone centerline axis 110, although the cyclone mounting wall 194 need not extend about the entire circumference and may be comprised of various mounting wall segments (not shown) about the circumference of the annular outer axial wall outer surface 196. The annular outer axial wall diameter 162 is sized to be slightly smaller than the pseudo-dome cyclone opening 138 ( Figure 5) of the pseudo-dome cyclone opening diameter 152 so that the flare 176 can be inserted through the pseudo-dome cyclone opening 138. Thus, the flare 176 is inserted through the pseudo-dome cyclone opening 138 so that the upstream side 198 of the cyclone mounting wall 194 engages the downstream side 200 of the pseudo-dome structure 61. A cyclone mounting ring 204 can be positioned on the downstream side 202 of the pseudo-dome structure 61. The cyclone mounting ring 204 can extend circumferentially about the cyclone centerline axis 110 and can extend radially outward from the annular outer axial wall outer surface 196. The flare 176 can be connected to the pseudo-dome structure 61, for example, by brazing the cyclone mounting ring 204, the pseudo-dome structure 61, and the cyclone mounting wall 194 to one another. Of course, other connection mechanisms, such as bolted joints, can also be used to couple the flare 176 to the pseudo-dome structure 61. The connection between the flare 176 , the swirler mounting wall 194 , and the swirler mounting ring 204 prevents the flare 176 , and therefore the swirler assembly 58 , from rotating about the swirler centerline axis 110 .

[0031] The flare 176 further includes a cyclone dome interface wall 206 that extends radially outward from the annular outer axial wall outer surface 196 and extends circumferentially about the cyclone centerline axis 110. The outer diameter 208 of the cyclone dome interface wall 206 is greater than the CMC dome cyclone opening diameter 154 ( Figure 5 When the swirler assembly 58 is connected to the pseudo-dome structure 61 as described above, the downstream surface 218 of the swirler dome interface wall 206 interfaces with the CMC dome upstream surface 210 of the CMC dome swirler opening 150 surrounding the CMC dome 56. The swirler dome interface wall 206 may provide a slight axial force against the CMC dome 56, but allow the swirler assembly 58 to move radially during operation.

[0032] The downstream end 212 of the annular outer axial wall 182 extends circumferentially about the swirler centerline axis 110 and defines the swirler outlet end 161 of the swirler assembly 58. As described above, the diameter 160 of the swirler outlet end 161 is smaller than the CMC dome swirler opening diameter 154 of the CMC dome swirler opening 150, such that a circumferential gap 156 is defined between the inner surface 158 of the CMC dome swirler opening 150 and the annular outer axial wall outer surface 196 of the swirler outlet end 161. The swirler outlet end 161 and the swirler downstream end 190 extend through the CMC dome swirler opening 150 and may extend beyond the downstream surface 216 of the CMC dome 56 into the combustion chamber 62. The cyclone interface wall 206 may also include a plurality of purge holes 214 extending through the cyclone interface wall 206 and into the circumferential gap 156 to provide a purge flow of the oxidant through the purge holes 214 .

[0033] While the foregoing description generally relates 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 may be implemented in an aircraft, but may also be implemented in non-aircraft applications such as power plants, marine applications, or oil and gas production applications. Therefore, the present disclosure is not limited to use in aircraft.

[0034] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0035] A combustor for a gas turbine, the combustor comprising: a shroud structure; a pseudo-dome structure including a pseudo-dome swirler opening therethrough, the pseudo-dome structure being connected to the shroud structure; a ceramic matrix composite (CMC) dome including a CMC dome swirler opening therethrough and having a CMC dome upstream surface surrounding the CMC dome swirler opening, the CMC dome being connected to the shroud structure; and a swirler including a swirler dome interface wall, the swirler being connected to the pseudo-dome structure through the pseudo-dome swirler opening and extending through the CMC dome swirler opening, the swirler dome interface wall interfacing with the CMC dome upstream surface.

[0036] A combustor according to any one of the preceding clauses, wherein the combustor defines a combustor axial centerline along the combustor longitudinal direction, a combustor radial direction extending outward from the combustor axial centerline and a combustor circumferential direction extending circumferentially around the combustor axial centerline, the hood structure extends in the combustor circumferential direction and the combustor longitudinal direction and has a hood radial outer portion and a hood radial inner portion, the pseudo-dome structure extends in the combustor circumferential direction and extends in the combustor radial direction and is connected to the hood radial outer portion and the hood radial inner portion, the CMC dome extends circumferentially around the combustor axial centerline and extends in the combustor radial direction, the CMC dome is connected to the hood radial outer portion and the hood radial inner portion, the CMC dome, and the swirler limiter A pseudo-dome swirler is provided with a swirler centerline axis defined therethrough, the swirler centerline axis defining a longitudinal direction of the swirler, the swirler comprising: (a) a swirler outlet on a downstream side of the swirler, (b) a swirler dome interface wall extending radially outward in a swirler radial direction relative to the swirler centerline axis, the swirler dome interface wall being disposed upstream of a swirler outlet end, and (c) a swirler mounting wall extending radially outward relative to the swirler centerline axis, the swirler mounting wall being disposed upstream of the swirler dome interface wall, the swirler extending through the pseudo-dome swirler opening, the swirler mounting wall being connected to the pseudo-dome structure such that a downstream surface of the swirler dome interface wall interfaces with an upstream surface of the CMC dome, and the swirler outlet extends through the CMC dome swirler opening.

[0037] A combustor according to any of the preceding clauses, wherein the combustor comprises a plurality of segments arranged circumferentially about an axial centerline of the combustor, each segment comprising a respective shroud structure, a respective CMC dome swirler opening through the CMC dome, a respective pseudo-dome structure and a respective swirler mounted to the pseudo-dome structure.

[0038] The combustor according to any of the preceding clauses, further comprising a swirler mounting ring, wherein the pseudo-dome structure is mounted to an upstream side of the swirler mounting wall, and the swirler mounting ring is connected to the swirler and the upstream side of the pseudo-dome structure.

[0039] A combustor according to any of the preceding clauses, wherein the swirler is connected to the pseudo-dome structure and the swirler mounting ring via brazing or welding.

[0040] A combustor according to any of the preceding clauses, wherein the radially outer portion of the shroud comprises an outer clamp having a first outer clamp portion radially outside the outer clamp and a second outer clamp portion radially inside the outer clamp, and the pseudo-dome structure is connected to a radially inner surface of the second outer clamp portion.

[0041] A burner according to any of the preceding clauses, wherein the pseudo-dome structure is connected to the second outer clamp part via brazing or welding.

[0042] The combustor of any of the preceding clauses, wherein the CMC dome is connected to the shroud structure within the outer clamp between the first and second outer clamp parts.

[0043] The burner according to any of the preceding clauses, wherein the CMC dome is connected to the outer clamp via a mechanical connection member.

[0044] The combustor according to any of the preceding clauses, further comprising an outer liner extending circumferentially around the combustor axial centerline and in the combustor longitudinal direction, the outer liner being connected to the shroud structure within the outer clamp between the first outer clamp portion and the CMC dome.

[0045] A combustor according to any of the preceding clauses, wherein a circumferential gap is provided between an inner surface of the CMC dome swirler opening and an outer surface of the swirler outlet end.

[0046] A combustor according to any of the preceding clauses, wherein the swirler dome interface wall comprises a plurality of purge holes therethrough, the plurality of purge holes being arranged to provide a purge flow of oxidant to the circumferential gap.

[0047] A combustor according to any of the preceding clauses, wherein the pseudo-dome structure extends circumferentially around the combustor axial centerline.

[0048] A combustor according to any of the preceding clauses, wherein the combustor comprises a plurality of segments arranged circumferentially about an axial centerline of the combustor, each segment comprising a respective shroud structure, a respective CMC dome swirler opening through the CMC dome, a respective pseudo-dome swirler opening, and a respective swirler mounted to the pseudo-dome structure.

[0049] A combustor according to any of the preceding clauses, wherein the radially inner portion of the shroud comprises an inner clamp having a first inner clamp portion radially inwardly of the inner clamp and a second inner clamp portion radially outwardly of the inner clamp, and the pseudo-dome structure is connected to a radially outer surface of the second inner clamp portion.

[0050] The combustor of any of the preceding clauses, wherein the CMC dome is connected to the shroud structure within the inner clamp between the first and second inner clamp parts.

[0051] The combustor according to any of the preceding clauses, further comprising an inner liner extending circumferentially around the combustor axial centerline and extending in the combustor longitudinal direction, the inner liner being connected to the shroud structure within the inner clamp between the first inner clamp portion and the CMC dome.

[0052] A burner according to any of the preceding clauses, wherein the swirler comprises: (a) a primary swirler, (b) a secondary swirler connected to the downstream side of the primary swirler, and (c) a flare connected to the downstream end of the secondary swirler, the flare having (i) an annular inner axial wall extending circumferentially around the swirler centerline axis and in the longitudinal direction of the swirler, the annular inner axial wall being connected to the secondary swirler, (ii) an annular outer axial wall extending circumferentially around the swirler centerline axis and in the longitudinal direction of the swirler, the annular outer axial wall being radially outward of the annular inner axial wall, and (iii) an annular conical wall extending circumferentially around the swirler centerline axis and extending radially outward and downstream from the downstream end of the annular inner axial wall, the downstream end of the annular conical wall comprising the swirler outlet.

[0053] A combustor according to any of the preceding clauses, wherein the swirler mounting wall extends radially outwardly from an outer surface of the annular outer axial wall and extends circumferentially around the swirler centreline axis.

[0054] A combustor according to any of the preceding clauses, wherein the swirler dome interface wall extends radially outwardly from the outer surface of the annular outer axial wall and extends circumferentially about the swirler centreline axis.

[0055] Although the foregoing description is directed to some exemplary embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, features described in conjunction 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 for a gas turbine, characterized in that The burner comprises: Cover structure; a pseudo-dome structure including a pseudo-dome cyclone opening therethrough, the pseudo-dome structure being connected to the shroud structure; a ceramic matrix composite (CMC) dome including a CMC dome swirler opening therethrough and having a CMC dome upstream surface surrounding the CMC dome swirler opening, the CMC dome being coupled to the shroud structure; and a swirler including a swirler dome interface wall, the swirler connected to the pseudo-dome structure through the pseudo-dome swirler opening and extending through the CMC dome swirler opening, the swirler dome interface wall interfacing with the CMC dome upstream surface; The cover structure includes a radially outer part and a radially inner part of the cover, the pseudo-dome structure is connected to the radially outer part and the radially inner part of the cover, the radially outer part of the cover includes an outer clamp, the outer clamp has a first outer clamp part radially outside the outer clamp and a second outer clamp part radially inside the outer clamp, and the pseudo-dome structure is connected to the radial inner surface of the second outer clamp part.

2. The burner according to claim 1, characterized in that wherein the burner defines a burner axial centerline along a longitudinal direction of the burner, a burner radial direction extending outward from the burner axial centerline, and a burner circumferential direction extending circumferentially around the burner axial centerline, The cover structure extends in the circumferential direction of the burner and in the longitudinal direction of the burner, The pseudo-dome structure extends in the circumferential direction of the combustor and in the radial direction of the combustor. The CMC dome extends circumferentially around the axial centerline of the combustor and extends in the radial direction of the combustor, the CMC dome is connected to the radially outer portion of the shroud and the radially inner portion of the shroud, and The swirler defines a swirler centerline axis therethrough, the swirler centerline axis defining a longitudinal direction of the swirler, the swirler including (a) a swirler outlet on a downstream side of the swirler, (b) a swirler dome interface wall extending radially outward in a swirler radial direction relative to the swirler centerline axis, the swirler dome interface wall being disposed upstream of a swirler outlet end, and (c) a swirler mounting wall extending radially outward relative to the swirler centerline axis, the swirler mounting wall being disposed upstream of the swirler dome interface wall, the swirler extending through the pseudo-dome swirler opening, the swirler mounting wall being connected to the pseudo-dome structure such that a downstream surface of the swirler dome interface wall interfaces with an upstream surface of the CMC dome, and the swirler outlet extends through the CMC dome swirler opening.

3. The burner according to claim 2, characterized in that The combustor includes a plurality of segments circumferentially arranged around an axial centerline of the combustor, each segment including a corresponding shroud structure, a corresponding CMC dome swirler opening through the CMC dome, a corresponding pseudo-dome structure, and a corresponding swirler mounted to the pseudo-dome structure.

4. The burner according to claim 2, characterized in that further comprising a cyclone mounting ring, The pseudo-dome structure is mounted to the upstream side of the cyclone mounting wall, and the cyclone mounting ring is connected to the cyclone and the upstream side of the pseudo-dome structure.

5. The burner according to claim 4, characterized in that The cyclone is connected to the pseudo-dome structure and the cyclone mounting ring via brazing or welding.

6. The burner according to claim 1, characterized in that Wherein the pseudo-dome structure is connected to the second outer clamp part via brazing or welding.

7. The burner according to claim 1, characterized in that wherein the CMC dome is connected to the cover structure within the outer clamp between the first outer clamp portion and the second outer clamp portion.

8. The burner according to claim 7, characterized in that wherein the CMC dome is connected to the outer fixture via a mechanical connection member.

9. The burner according to claim 2, characterized in that Further included is an outer liner extending circumferentially about the combustor axial centerline and in the combustor longitudinal direction, the outer liner being connected to the shroud structure within the outer clamp between the first outer clamp portion and the CMC dome.

10. The burner according to claim 2, characterized in that A circumferential gap is provided between the inner surface of the CMC dome cyclone opening and the outer surface of the cyclone outlet end.

11. The burner according to claim 10, characterized in that The cyclone dome interface wall includes a plurality of purge holes therethrough, the plurality of purge holes being arranged to provide a purge flow of oxidant to the circumferential gap.

12. The burner according to claim 2, characterized in that The pseudo-dome structure extends circumferentially around the axial centerline of the combustor.

13. The burner according to claim 12, characterized in that The combustor includes a plurality of segments circumferentially arranged around an axial centerline of the combustor, each segment including a corresponding shroud structure, a corresponding CMC dome swirler opening through the CMC dome, a corresponding pseudo-dome swirler opening, and a corresponding swirler mounted to the pseudo-dome structure.

14. The burner according to claim 2, characterized in that The radially inner portion of the cover includes an inner clamp having a first inner clamp portion radially inside the inner clamp and a second inner clamp portion radially outside the inner clamp, and the pseudo dome structure is connected to a radially outer surface of the second inner clamp portion.

15. The burner according to claim 14, characterized in that Wherein the CMC dome is connected to the cover structure within the inner fixture between the first inner fixture portion and the second inner fixture portion.

16. The burner according to claim 15, characterized in that Further included is an inner liner extending circumferentially about the combustor axial centerline and in the combustor longitudinal direction, the inner liner being connected to the shroud structure within the inner jig between the first inner jig portion and the CMC dome.

17. The burner according to claim 2, characterized in that The swirler includes: (a) a primary swirler, (b) a secondary swirler connected to the downstream side of the primary swirler, and (c) a flare connected to the downstream end of the secondary swirler, the flare having (i) an annular inner axial wall extending circumferentially around the swirler centerline axis and in the longitudinal direction of the swirler, the annular inner axial wall being connected to the secondary swirler, (ii) an annular outer axial wall extending circumferentially around the swirler centerline axis and in the longitudinal direction of the swirler, the annular outer axial wall being radially outward of the annular inner axial wall, and (iii) an annular conical wall extending circumferentially around the swirler centerline axis and extending radially outward and downstream from the downstream end of the annular inner axial wall, the downstream end of the annular conical wall including a swirler outlet.

18. The burner according to claim 17, characterized in that The swirler mounting wall extends radially outward from an outer surface of the annular outer axial wall and extends circumferentially around the swirler centerline axis.

19. The burner according to claim 18, characterized in that The swirler dome interface wall extends radially outward from the outer surface of the annular outer axial wall and extends circumferentially around the swirler centerline axis.

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