Combustor swirler to CMC dome attachment

Abstract

A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome and a swirler assembly. The CMC dome has a swirler mounting wall integrally formed therewith. The swirler assembly includes a plurality of clamp-dome attachment members for connecting the swirler assembly to the CMC dome. A sleeve is disposed within a plurality of dome-side swirler assembly mounting openings in the swirler mounting wall, and the CMC dome is disposed within a respective one of the plurality of clamp-dome attachment members of the swirler assembly. A swirler dome connection member is disposed through each of the clamp-dome attachment members to mount the swirler assembly to the CMC dome.

Description

Technical Field

[0001] The present disclosure relates to connecting a combustor swirler to 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 metal swirler assembly connected to a metal dome structure. The metal dome structure is known to include an inducer wall on the combustion chamber side of the dome, wherein the inducer 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 inducer 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 is a partial cross-sectional side view of an exemplary CMC dome structure according to aspects of the present disclosure.

[0007] Figure 4 is a partial cross-sectional side view of a swirler-CMC dome connection according to aspects of the present disclosure.

[0008] Figure 5 is an exemplary cyclone-CMC dome connection according to aspects of the present disclosure Figure 4 An enlarged partial cross-sectional view taken at detailed view 150 of FIG.

[0009] Figure 6 is a front-to-rear perspective view of a separated cyclone assembly and CMC dome according to aspects of the present disclosure.

[0010] Figure 7 is a front-to-rear perspective view of a coupled swirler assembly and CMC dome according to aspects of the present disclosure. DETAILED DESCRIPTION

[0011] 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.

[0012] 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.

[0013] 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.

[0014] 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.

[0015] Some gas turbine engines include rich-burn combustors, which typically utilize a metal swirler assembly connected to a metal dome structure. It is known that the metal dome structure includes an inducer wall on the combustion chamber side of the dome, wherein the inducer 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 inducer wall. The metal swirler assembly is generally brazed or welded to the dome structure.

[0016] 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. Additionally, the CMC dome structure does not require a deflector 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 presents challenges with respect to the ability to connect the metal cyclone to the CMC dome and to provide thermal decoupling between the metal cyclone assembly and the CMC dome. The present disclosure provides a clamp joint attachment technology to connect the metal cyclone to the CMC dome, thereby thermally decoupling the cyclone assembly from the CMC dome.

[0017] Referring now to the accompanying drawings, Figure 1is 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 1 Instead 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, the engine 10 has an axial centerline axis 12 extending therethrough from an upstream end 98 to a downstream end 99. Generally speaking, the engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0018] 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.

[0019] 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.

[0020] Figure 2 Yes Figure 1A 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 engine axial 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 (C C ).like Figure 2 As shown, the combustor 26 may generally include a combustor liner 50 having an inner liner 52 and an outer liner 54. The inner liner 52 and the outer liner 54 are each annular liners extending circumferentially about the combustor axial centerline 112. The ceramic matrix composite (CMC) dome 56 extends in the combustor radial direction R C The combustion chamber 62 is formed by a swirler assembly 58 and a CMC dome 56. The swirler assembly 58 is configured to provide a combustion chamber 62 ... Figure 1 ). Although Figure 2 A single swirler assembly 58 is depicted, but it is 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 .

[0021] 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.

[0022] 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 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.

[0023] Figure 3 A partial cross-sectional view of a CMC dome 56 according to aspects of the present disclosure is depicted. As described above, the CMC dome 56 is circumferentially (C C ) extends. The CMC dome 56 is suitably connected (connection not shown) to the outer liner 54 and the inner liner 52. The CMC dome 56 includes a cyclone assembly opening 100 (also see Figure 6 ), wherein the cyclone assembly opening 100 defines a CMC opening centerline 102 therethrough. The CMC opening centerline 102 defines a CMC opening longitudinal direction (L D ), the CMC opening radial direction (R D ), and the CMC opening circumferential direction (C D ). It is understandable, although Figure 3 A single swirler assembly opening 100 is depicted, but multiple swirler assembly openings 100 may be spaced circumferentially around the CMC dome 56. Thus, multiple swirler assemblies 58 ( Figure 2 ) can be connected to the CMC dome 56 as will be described below.

[0024] The CMC dome 56 also includes a cyclone mounting wall 104 that may also have a CMC structure and may be integrally formed with the CMC dome 56. The cyclone mounting wall 104 extends circumferentially around the CMC opening centerline 102 and extends in the CMC longitudinal direction L. D The cyclone mounting wall 104 extends upstream from the upstream side 106 of the CMC dome 56. The cyclone mounting wall 104 includes a plurality of dome-side cyclone mounting openings 108 therethrough (see also FIG. Figure 6 ), multiple dome side cyclone installation openings 108 are in the radial direction R of the CMC opening DThe cyclone mounting wall 104 may include, for example, two, three, or four dome-side cyclone mounting openings 108 (see FIG. Figure 6 Of course, the number of dome side cyclone mounting openings 108 is not limited to the above, and any number may be implemented to provide the cyclone assembly 58 ( Figure 2 ) with the desired connection to the CMC dome 56. It is seen that the dome-side cyclone mounting opening 108 is generally a cylindrical hole through the cyclone mounting wall 104, and the size 114 (e.g., diameter) of the dome-side cyclone mounting opening 108 is generally arranged to accommodate a sleeve (to be described below) therethrough. The CMC dome 56 may optionally include a plurality of dome cooling channels 115 through the CMC dome 56. It is further seen that the CMC dome 56 includes a CMC opening radial direction R D A shoulder 110 extends between the cyclone assembly opening 100 and the cyclone mounting wall 104. As will be described below, the dome-side cyclone mounting opening 108 is used to mount the cyclone assembly 58 to the CMC dome 56, and the shoulder 110 is used to seat the cyclone assembly 58 against the CMC dome 56.

[0025] Figure 4 An example of a cyclone assembly according to aspects of the present disclosure is depicted with a CMC dome connected thereto. Figure 4 , it can be seen that the swirler assembly 58 defines a swirler assembly upstream direction 116 and a swirler assembly downstream direction 118. The swirler assembly 58 further defines a swirler assembly in the longitudinal direction (L S ) extends through the cyclone centerline 120 of the cyclone assembly 58. The radial direction (R S ) extends outward from the cyclone centerline 120, and the cyclone assembly circumferential direction (C S ) extends circumferentially about the swirler centerline 120. In contrast to the CMC dome 56, the swirler assembly 58 is substantially a metallic swirler assembly. That is, the various components of the swirler assembly 58 are constructed, in part, 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.

[0026] The swirler assembly 58 includes a primary swirler 122 and a secondary swirler 124 connected to a downstream side 126 of the primary swirler 122. The primary swirler 122 includes a plurality of primary swirl vanes 128 that are circumferentially spaced within the primary swirler 122 about the swirler centerline 120. The primary swirl vanes 128 direct radially inward swirl into the plenum 66 ( Figure 2) of the compressed air 82(a) passing through the primary swirler 122. The secondary swirler 124 includes an upstream radial wall 130 extending circumferentially around the swirler centerline 120, and a downstream radial wall 132 extending circumferentially around the swirler centerline 120. The secondary swirler 124 also includes a plurality of secondary swirl vanes 134 disposed between the upstream radial wall 130 and the downstream radial wall 132. The secondary swirl vanes 134 direct radially inward swirl into the compressed air 82(a) passing through the secondary swirler 124 from the pressure plenum 66. The secondary swirler 124 further includes a flared connecting wall 136 extending circumferentially around the swirler centerline 120 and swirls in the swirler axial direction L. S The upper portion extends downstream from the radially inner end 138 of the downstream radial wall 132. The flared connecting wall 136 is adapted to connect to the flare 140, as will be described below.

[0027] The secondary swirler 124 further includes a plurality of outer axial walls 142 , which are oriented in the swirler axial direction L. S The secondary swirler 124 extends downstream from the radial outer end 144 of the downstream radial wall 132, and the secondary swirler 124 also extends in the swirler circumferential direction C. S The plurality of outer axial walls 142 are circumferentially spaced apart around the cyclone centerline 120. The number of the outer axial walls 142 and the circumferential spacing of the outer axial walls 142 are the same as the plurality of dome-side cyclone mounting openings 108. Figure 6 As shown, the cyclone mounting wall 104 of the CMC dome 56 includes three dome-side cyclone mounting openings 108 equally spaced about the cyclone mounting wall 104, and the secondary cyclone 124 includes three outer axial walls 142 also equally spaced circumferentially about the cyclone centerline 120. Each outer axial wall 142 has an outer axial wall opening 146 therethrough (see also FIG. Figure 5 ), the outer axial wall opening 146 is in the radial direction R of the cyclone S The outer axial wall opening 146 may include a recessed portion 152 ( Figure 5 ) to accommodate the swirler dome connection member 148. Thus, each of the plurality of outer axial walls 142 is more or less a lug (ie, a plate with a hole sized to accommodate a clip pin).

[0028] Figure 5 It is captured at detail view 150 Figure 4 A magnified view of a portion of the Figure 5 The swirler dome connection member 148 has been removed. The swirler assembly 58 includes a flare 140 having an inner flare axial wall 154 extending in the swirler axial direction L. SThe flared axial wall 154 is connected to the flared connecting wall 136 of the secondary swirler 124, such as by brazing. The flare 140 also includes a flared end wall 168 that extends radially outward from a downstream end 170 of the inner flared axial wall 154 and extends circumferentially around the swirler centerline 120. The flared end wall 168 may define a flared cone or tapered wall 172 that extends circumferentially around the swirler centerline 120. The tapered wall 172 may define the swirler assembly 58 ( Figure 4 ) outlet 141 and may extend to the combustion chamber 62 ( Figure 2 ), beyond the downstream surface 107 of the CMC dome. The radially outer end 174 of the flared endwall 168 includes a step 176 that extends circumferentially about the swirler centerline 120 and forms a flared endwall radial surface 178.

[0029] The flare 140 further includes a plurality of outer flare axial walls 156. Each outer flare axial wall 156 extends in the longitudinal direction L of the cyclone. S The flared end wall 168 extends upstream from the radially outer end 174 and further extends in the swirler circumferential direction C. S Each outer flared axial wall 156 further includes an outer flared axial wall opening 160 therethrough, the outer flared axial wall opening 160 extending in the radial direction R of the cyclone. S When the flare 140 is connected to the secondary cyclone 124 ( Figure 4 ), the outer axial wall opening 146 and the outer flare axial wall opening 160 are radially aligned with each other. Thus, each outer flare axial wall 156 is essentially a lug, with its opening 160 aligned with the outer axial wall opening 146 of the outer axial wall 142, thereby forming a clamp structure. That is, corresponding pairs of the outer axial wall 142 of the secondary swirler 124 and the outer flare axial wall 156 of the flare 140 together define corresponding clamp dome attachment members 162, wherein the outer axial wall 142 may correspond to a clamp outer portion 164, and the outer flare axial wall 156 may correspond to a clamp inner portion 166.

[0030] Still refer to Figure 5 , it is seen that a sleeve 180 is provided within the dome side cyclone mounting opening 108. The sleeve 180 includes a sleeve opening 182 therethrough. The sleeve 180 may be a cylindrical spacer, and the height 184 of the sleeve 180 is set to be between the radially outer surface 186 of the outer flared axial wall 156 and the secondary cyclone 124 ( Figure 4 ) is slidingly fitted between the radial inner surface 188 of the outer axial wall 142.

[0031] Figure 6is a front-to-back perspective view of a separated cyclone-CMC dome structure according to aspects of the present disclosure. Figure 7 is a front-to-back perspective view of a coupled cyclone-CMC dome structure according to aspects of the present disclosure. Figure 6 and 7 In both cases, only a portion of the CMC dome 56 is depicted, and as described above, the CMC dome 56 extends circumferentially around the combustor axial centerline 112. During installation of the swirler assembly 58 to the CMC dome 56, a corresponding sleeve 180 is inserted into each dome-side swirler mounting opening 108 of the CMC dome 56. Return to Reference Figure 5 The swirler assembly 58 is then inserted onto the CMC dome 56 by arranging each respective one of the plurality of clamp dome attachment members 162 of the swirler assembly 58 with a respective one of the sleeves 180, with the flared end wall radial surface 178 aligned with the CMC dome 56 ( Figure 5 ) of the shoulder 110. The outer axial wall opening 146, the sleeve opening 182 and the outer flared axial wall opening 160 are each radially aligned, and the swirler dome connecting member 148 ( Figure 4 ) is inserted through each opening (146, 182, 160) until the head 190 of the swirler dome connection member 148 interfaces with the recessed portion 152 of the outer axial wall opening 146. The head 190 can then be connected (e.g., brazed) to the outer axial wall 142. Thus, as Figure 7 As can be seen, the cyclone assembly 58 can be coupled to the CMC dome 56, but in a manner that thermally decouples the CMC dome 56 from the cyclone assembly 58 to accommodate thermal expansion differences between the metal cyclone assembly 58 and the CMC dome 56. Additionally, the cyclone dome connection member 148, while not completely constrained by the CMC dome 56, still limits rotation of the cyclone assembly 58 about the cyclone mounting wall 104, but allows for rotation by the shoulder 110 ( Figure 6 ) constrains some axial movement of the swirler assembly 58.

[0032] 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.

[0033] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0034] A combustor for a gas turbine, the combustor comprising: a ceramic matrix composite (CMC) dome, the CMC dome including (a) a swirler assembly opening through the CMC dome and (b) a swirler mounting wall, the swirler mounting wall extending from an upstream side of the CMC dome and having a plurality of dome-side swirler assembly mounting openings therethrough; a swirler assembly, the swirler assembly including a plurality of clamp dome attachment members for connecting the swirler assembly to the CMC dome; a plurality of sleeves having openings therethrough, the plurality of sleeves being arranged in respective dome-side swirlers in the plurality of dome-side swirler assembly mounting openings. and a plurality of swirler dome connecting members, wherein the swirler assembly is connected to the CMC dome via corresponding ones of the plurality of clamp dome attachment members, the corresponding ones of the plurality of clamp dome attachment members intersecting corresponding ones of the plurality of dome-side swirler assembly mounting openings in which corresponding ones of the plurality of bushings are disposed, and corresponding ones of the plurality of swirler dome connecting members are disposed through corresponding ones of the clamp dome attachment members and corresponding ones of the plurality of bushings.

[0035] The combustor of any of the preceding clauses, wherein the plurality of swirler dome connection members constrain the swirler assembly to rotate about the swirler mounting wall.

[0036] The combustor of any of the preceding clauses, wherein the plurality of clamp dome attachment members comprises two to four clamp dome attachment members, the clamp dome attachment members being circumferentially spaced about a swirler centerline axis of the swirler assembly.

[0037] A combustor according to any of the preceding clauses, wherein the combustor defines a combustor axial centerline along a longitudinal direction of the combustor, a combustor radial direction extending outward from the combustor axial centerline, and a combustor circumferential direction extending circumferentially around the combustor axial centerline, and the CMC dome extends circumferentially around the combustor axial centerline.

[0038] The burner of any of the preceding clauses, wherein each clamp dome attachment member comprises a clamp outer portion and a clamp inner portion.

[0039] A burner according to any of the preceding clauses, wherein the clamp outer portion is defined by a secondary swirler of the swirler assembly and the clamp inner portion is defined by a flare connected to the secondary swirler.

[0040] The combustor of any of the preceding clauses, wherein each swirler dome connection member of the plurality of swirler dome connection members comprises a pin.

[0041] A burner according to any of the preceding clauses, wherein each pin is engaged to the clamp outer part.

[0042] A combustor according to any of the preceding clauses, wherein the swirler assembly opening of the CMC dome defines a CMC opening centerline therethrough defining a CMC opening longitudinal direction, a CMC opening radial direction extending outward from the CMC opening centerline, and a CMC opening circumferential direction extending circumferentially about the CMC opening centerline, the swirler mounting wall extending circumferentially about the CMC opening centerline and extending upstream from the upstream side of the CMC dome in the CMC opening longitudinal direction.

[0043] The combustor of any of the preceding clauses, wherein the plurality of dome side swirler assembly mounting openings extend in a radial direction of the CMC opening.

[0044] A combustor according to any of the preceding clauses, wherein the swirler assembly defines a swirler centerline therethrough defining a swirler longitudinal direction, a swirler radial direction extending outwardly from the swirler centerline, and a swirler circumferential direction extending circumferentially about the swirler centerline, the swirler assembly comprising (a) a primary swirler and (b) a secondary swirler connected to a downstream side of the primary swirler.

[0045] A combustor according to any of the preceding clauses, wherein the secondary swirler comprises a downstream radial wall extending circumferentially around the swirler centreline and a flared connecting wall extending circumferentially around the swirler centreline and extending downstream from a radially inner end of the downstream radial wall in the swirler longitudinal direction.

[0046] A combustor according to any of the preceding clauses, wherein the secondary swirler comprises a plurality of outer axial walls extending downstream in the swirler longitudinal direction from a radially outer end of a downstream radial wall, each outer axial wall having an outer axial wall opening therethrough, the outer axial wall opening extending in the swirler radial direction, each respective outer axial wall defining a clamp outer portion of a respective clamp dome attachment member.

[0047] A combustor according to any of the preceding clauses, wherein the swirler assembly includes a flare connected to the flare connecting wall of the secondary swirler and comprising (i) a flare end wall extending radially outwardly from a downstream end of a flare inner axial wall and extending circumferentially around the swirler centreline, and (ii) a plurality of outer flare axial walls, each outer flare axial wall extending upstream in the swirler longitudinal direction from a radially outer end of the flare end wall and including an outer flare axial wall opening therethrough, the outer flare axial wall opening extending in the swirler radial direction, each outer flare axial wall defining a clamp inner portion of a respective clamp dome attachment member.

[0048] The combustor of any of the preceding clauses, wherein the CMC dome includes a shoulder extending between the swirler assembly opening and the swirler mounting wall in a radial direction of the CMC opening.

[0049] The combustor of any of the preceding clauses, wherein the radially outer end of the flared endwall includes a step extending circumferentially about the swirler centerline and forming a flared endwall radial surface that intersects the shoulder of the CMC dome.

[0050] The combustor of any of the preceding clauses, wherein the flare comprises a tapered wall defining an outlet of the swirler assembly, the tapered wall extending through the swirler opening into the combustion chamber beyond a downstream surface of the CMC dome.

[0051] The combustor of any of the preceding clauses, wherein the CMC dome comprises a plurality of swirler assembly openings circumferentially spaced apart in the combustor circumferential direction, each respective swirler assembly opening of the plurality of swirler assembly openings having a respective swirler mounting wall.

[0052] The combustor of any of the preceding clauses, comprising a plurality of said swirler assemblies connected to said CMC dome.

[0053] A combustor according to any of the preceding clauses, wherein each respective swirler assembly is connected to the CMC dome via a respective one of the plurality of clamp dome attachment members, the respective one of the plurality of clamp dome attachment members intersecting a respective one of the plurality of dome side swirler assembly mounting openings in which a respective one of the plurality of sleeves is arranged, and the respective one of the plurality of swirler dome connection members being arranged to pass through the respective one of the clamp dome attachment members and the respective one of the plurality of sleeves.

[0054] 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: a ceramic matrix composite (CMC) dome comprising (a) a cyclone assembly opening through the CMC dome and (b) a CMC cyclone mounting wall integrally formed with the CMC dome and extending from an upstream side of the CMC dome and having a plurality of dome-side cyclone assembly mounting openings therethrough; a swirler assembly comprising a plurality of clamp dome attachment members for connecting the swirler assembly to the CMC dome; a plurality of sleeves having openings therethrough, the plurality of sleeves being disposed within respective ones of the plurality of dome side swirler assembly mounting openings; and A plurality of cyclone dome connecting members, wherein the swirler assembly is connected to the CMC dome via respective ones of the plurality of clamp dome attachment members, the respective ones of the plurality of clamp dome attachment members intersecting respective ones of the plurality of dome-side swirler assembly mounting openings in which respective ones of the plurality of bushings are disposed, and respective ones of the plurality of swirler dome connection members being disposed through respective ones of the clamp dome attachment members and respective ones of the plurality of bushings.

2. The burner according to claim 1, characterized in that The plurality of swirler dome connection members constrain the swirler assembly to rotate about the CMC swirler mounting wall.

3. The burner according to claim 1, characterized in that Wherein the plurality of clamp dome attachment members comprises two to four clamp dome attachment members, the clamp dome attachment members being circumferentially spaced about a swirler centerline axis of the swirler assembly.

4. The burner according to claim 1, characterized in that The combustor defines a combustor axial centerline along a 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, and the CMC dome extends circumferentially around the combustor axial centerline.

5. The burner according to claim 1, characterized in that Each clamp dome attachment member includes a clamp outer portion and a clamp inner portion.

6. The burner according to claim 5, characterized in that The outer portion of the clamp is defined by a secondary cyclone of the cyclone assembly, and the inner portion of the clamp is defined by a flare connected to the secondary cyclone.

7. The burner according to claim 5, characterized in that Wherein each swirler dome connection member of the plurality of swirler dome connection members comprises a pin.

8. The burner according to claim 7, characterized in that Each pin is coupled to an outer portion of the clamp.

9. The burner according to claim 1, characterized in that wherein the swirler assembly opening of the CMC dome defines a CMC opening centerline therethrough defining a CMC opening longitudinal direction, a CMC opening radial direction extending outward from the CMC opening centerline, and a CMC opening circumferential direction extending circumferentially about the CMC opening centerline, and wherein the CMC swirler mounting wall extends circumferentially about the CMC opening centerline and extends upstream from the upstream side of the CMC dome in the CMC opening longitudinal direction.

10. The burner according to claim 9, characterized in that The plurality of dome-side swirler assembly mounting openings extend in a radial direction of the CMC opening.

11. The burner according to claim 10, characterized in that The swirler assembly defines a swirler centerline passing therethrough and defining a swirler longitudinal direction, a swirler radial direction extending outward from the swirler centerline, and a swirler circumferential direction extending circumferentially around the swirler centerline, the swirler assembly comprising (a) a primary swirler and (b) a secondary swirler connected to a downstream side of the primary swirler.

12. The burner according to claim 11, characterized in that The secondary swirler includes a downstream radial wall extending circumferentially around the swirler centerline and a flared connecting wall, wherein the flared connecting wall extends circumferentially around the swirler centerline and extends downstream from a radially inner end of the downstream radial wall in the swirler longitudinal direction.

13. The burner according to claim 12, characterized in that The secondary swirler includes a plurality of outer axial walls extending downstream from a radially outer end of a downstream radial wall in a longitudinal direction of the swirler, each outer axial wall having an outer axial wall opening therethrough, the outer axial wall opening extending in a radial direction of the swirler, each respective outer axial wall defining a clamp outer portion of a respective clamp dome attachment member.

14. The burner according to claim 13, characterized in that wherein the swirler assembly includes a flare connected to the flare connecting wall of the secondary swirler and comprising (i) a flare end wall extending radially outward from a downstream end of a flare inner axial wall and extending circumferentially about a centerline of the swirler, and (ii) a plurality of outer flare axial walls, each outer flare axial wall extending upstream in the swirler longitudinal direction from a radially outer end of the flare end wall and including an outer flare axial wall opening therethrough, the outer flare axial wall opening extending in the swirler radial direction, each outer flare axial wall defining a clamp inner portion of a corresponding clamp dome attachment member.

15. The burner according to claim 14, characterized in that The CMC dome includes a shoulder extending in a radial direction of the CMC opening between the swirler assembly opening and the CMC swirler mounting wall.

16. The burner according to claim 15, characterized in that The radially outer end of the flared endwall includes a step that extends circumferentially around the swirler centerline and forms a flared endwall radial surface that intersects the shoulder of the CMC dome.

17. The burner according to claim 16, characterized in that The flare includes a tapered wall defining an outlet of the swirler assembly, the tapered wall extending through the swirler assembly opening into the combustion chamber beyond a downstream surface of the CMC dome.

18. The burner according to claim 4, characterized in that The CMC dome includes a plurality of swirler assembly openings circumferentially spaced apart in a circumferential direction of the combustor, each respective swirler assembly opening of the plurality of swirler assembly openings having a respective CMC swirler mounting wall.

19. The burner according to claim 18, characterized in that A plurality of said swirler assemblies are included coupled to said CMC dome.

20. The burner according to claim 19, characterized in that wherein each respective swirler assembly is connected to the CMC dome via a respective one of the plurality of clamp dome attachment members, the respective one of the plurality of clamp dome attachment members intersecting a respective one of the plurality of dome-side swirler assembly mounting openings in which a respective one of the plurality of bushings is disposed, and the respective one of the plurality of swirler dome connection members being disposed through the respective one of the clamp dome attachment members and the respective one of the plurality of bushings.

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