Attachment of burner swirler to dome

Abstract

A combustor for a gas turbine, the combustor comprising: a ceramic matrix composite (CMC) dome comprising a swirler opening therethrough, having a flared interface surface about the swirler opening; a swirler assembly comprising (a) a secondary swirler having a threaded flared attachment portion and (b) a flare having (i) a threaded secondary swirler attachment portion, and (ii) a dome interface wall that interfaces with the flared interface surface of the CMC dome; and a swirler dome attachment member. The flare is connected to the secondary swirler via the threaded flared attachment portion and the threaded secondary swirler attachment portion, and the swirler dome attachment member applies a force to the CMC dome to engage the dome interface wall and the flared interface surface, thereby connecting the CMC dome and the swirler assembly.

Description

Technical Field

[0001] This disclosure relates to a combustor swirler connected to a CMC (ceramic matrix composite) dome in a gas turbine engine. Background Technology

[0002] Some conventional gas turbine engines are known to include a rich-fuel combustor, which typically uses a metal swirler assembly connected to a metal dome structure. The metal dome structure is known to include guide walls on the combustion chamber side of the dome, whereby the guide walls deflect heat generated in the combustor during combustion. Cooling holes typically penetrate the dome structure to provide some surface cooling to the dome and guide walls. The metal swirler assembly is typically brazed or welded to the dome structure. Attached Figure Description

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

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

[0005] Figure 2 This is a partial cross-sectional side view of an exemplary burner according to aspects of this disclosure.

[0006] Figure 3 This is a partial cross-sectional side view of an exemplary CMC dome structure according to aspects of this disclosure.

[0007] Figure 4 Based on aspects of this disclosure Figure 2 A detailed view of the partial cross-sectional side view of the connection between the hydrocyclone and the CMC dome, taken at point 122.

[0008] Figure 5 It is a front and rear partial sectional enlarged perspective view of the dome-flare-spacer arrangement according to aspects of this disclosure.

[0009] Figure 6 This is a front and rear perspective view of the cyclone assembly and the CMC dome connection according to aspects of this disclosure.

[0010] Figure 7 This is a partial cross-sectional side view of an exemplary CMC dome structure according to another aspect of this disclosure.

[0011] Figure 8 Based on aspects of this disclosure Figure 7 The cross-section of the hydrocyclone mounting wall taken at point 8-8 on the plane.

[0012] Figure 9 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the connection between the hydrocyclone and the CMC dome, taken at detail view 122.

[0013] Figure 10 Based on aspects of this disclosure Figure 9 The cross-section of the dome interface wall taken at point 10-10 on the plane.

[0014] Figure 11 Based on aspects of this disclosure Figure 9 The cross-section of the downstream attachment wall taken at plane 11-11.

[0015] Figure 12 It is a magnified perspective view of the dome and flare inserted according to aspects of this disclosure.

[0016] Figure 13 This is a front and rear magnified perspective view of the connection from the cyclone to the dome according to an aspect of this disclosure. Detailed Implementation

[0017] The features, advantages, and embodiments of this disclosure will be set forth or 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, and does not limit the scope of the claimed disclosure.

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

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

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

[0021] The use of non-metallic materials in burners 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 metallic materials; therefore, CMC domes require less cooling than conventional metal domes. Less cooling means more air can be used for other purposes, including as dilution air. Furthermore, CMC dome structures do not require guide walls, thus reducing the overall axial length of the dome, which in turn reduces the length of the burner module. However, implementing a CMC dome with a metallic swirler presents challenges in the ability to connect the metallic swirler to the CMC dome. This disclosure provides a threaded sandwich-type connection between the swirler components and the CMC dome to connect the swirler assembly to the CMC dome.

[0022] 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") that can be incorporated into various embodiments of the present disclosure. Although further described below with reference to a ducted turbofan engine, the present 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. Furthermore, the present disclosure is not limited to... Figure 1 The illustrated inline fan turbine engine can be implemented in a non-inline fan (UDF) turbine engine. For example... Figure 1 As shown, the engine 10 has an axial centerline axis 12 that extends through it from an upstream end 98 to a downstream end 99 for reference. Typically, the engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0023] The core engine 16 typically includes a housing 18 defining an annular inlet 20. The housing 18 surrounds or at least partially forms, in a series flow relationship, a compressor section (22 / 24) having a boost 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 injection 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 the fan shaft 38 of the fan assembly 14. In certain embodiments, such 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 or gear transmission configuration. In other embodiments, although not shown, the engine 10 may also include an intermediate pressure (IP) compressor and a turbine that rotates with the intermediate pressure shaft.

[0024] 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 over the outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0025] Figure 2 Is it like this? Figure 1 A cross-sectional side view of an exemplary burner 26 of the core engine 16 shown. Figure 2 The axial centerline 112 of the burner is depicted, which roughly corresponds to the axial centerline 12 of the engine. Therefore, Figure 2 The burner 26 defines the longitudinal direction of the burner corresponding to the axial centerline 112 of the burner (L). C ), the radial direction of the burner extending outward from the axial centerline 112 of the burner (R) C ), and the circumferential direction of the burner extending around the axial centerline 112 of the burner (C) C ).like Figure 2 As shown, the burner 26 may include a shroud 60 and a burner bushing 50, the burner bushing 50 having an inner liner 52 and an outer liner 54. Each of the inner liner 52 and the outer liner 54 is an annular bushing extending circumferentially around the axial centerline 112 of the burner. A ceramic matrix composite (CMC) dome 56 is located in the radial direction R of the burner. C The upper part extends between the inner liner 52 and the outer liner 54, and also extends circumferentially around the axial centerline 112 of the combustor. The inner liner 52, the outer liner 54, and the CMC dome 56 together define a combustion chamber 62 between them. In the combustion chamber 62, an initial chemical reaction can occur in which the ignited fuel-oxidant mixture injected into the combustion chamber 62 by the cyclone assembly 58 generates combustion gas 86. The combustion gas 86 then flows further downstream into the HP turbine 28 and the LP turbine 30.

[0026] The burner 26 also includes a housing 64 extending circumferentially around the burner axial centerline 112, and an inner housing 65 also extending circumferentially around the burner axial centerline 112. An outer flow passage 88 is defined between the housing 64 and the outer liner 54, and an inner flow passage 90 is defined between the inner housing 65 and the inner liner 52. The outer liner 54 may also include a plurality of liner dilution openings 68 circumferentially spaced around the outer liner 54. Similarly, the inner liner 52 may include a plurality of liner dilution openings 69 circumferentially spaced around the inner liner 52.

[0027] Return to reference Figure 1 During operation, air 73 enters the cabin 44 at cabin inlet 76, and a portion of the air 73 enters the compressor section (22 / 24) as compressor inlet airflow 80, where this portion of air 73 is compressed. Another portion of the air 73 enters the bypass airflow passage 48, thus providing bypass airflow 78. Figure 2 In the combustion chamber 26, compressed air 82 from the compressor section (22 / 24) enters via a diffuser (not shown). A portion of the compressed air 82(a) enters the shroud 60 and then the pressure chamber 66, while another portion of the compressed air 82(b) flows to the outer flow passage 88 and the inner flow passage 90. The compressed air 82(a) in the pressure chamber 66 passes through the swirler assembly 58, thereby mixing with the fuel injected by the fuel nozzle assembly 70, and igniting the fuel-air mixture injected into the combustion chamber 62 by the swirler assembly 58 to generate combustion gases 86. A portion of the compressed air 82(b) in the outer flow passage 88 can be used as dilution air supplied to the combustion chamber 62 through a plurality of 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 supplied to the combustion chamber 62 through a plurality of liner dilution openings 69.

[0028] Figure 3 A partial cross-sectional view of the CMC dome 56 according to an aspect of this disclosure is depicted. As described above, the CMC dome 56 is circumferentially oriented around the axial centerline 112 of the burner (C... C 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 hydrocyclone opening 100 through which the hydrocyclone opening 100 has a CMC opening centerline 102 extending therethrough, defining an upstream direction 103 and a downstream direction 105 of the CMC dome. The CMC opening centerline 102 defines a longitudinal direction (L...) of the CMC opening. D ), the radial direction of the CMC opening extending outward from the centerline 102 of the CMC opening (R) D ), and the circumferential direction of the CMC opening extending circumferentially around the CMC opening centerline 102 (C D ).

[0029] CMC dome 56 defines a downstream surface 104 and an upstream surface 106. A recess 108 extends from the downstream surface 104 in an upstream direction 103 and is disposed on the downstream side of the hydrocyclone opening 100. The recess 108 has a diameter 114 larger than the diameter 116 of the hydrocyclone opening 100 and defines a shoulder 110 extending radially outward from the hydrocyclone opening 100. The shoulder 110 may also be referred to as a flared interface surface 118 surrounding the hydrocyclone opening 100. CMC dome 56 may also include a plurality of cooling channels 120 extending through CMC dome 56.

[0030] Figure 4 Based on aspects of this disclosure Figure 2 A detailed cross-sectional side view of the cyclone assembly 58 attached to the dome, taken at detail view 122. The cyclone assembly 58 is defined in the longitudinal direction of the cyclone (L...). S The axis 124 of the hydrocyclone extends upward through the hydrocyclone's centerline. The upstream direction 126 and the downstream direction 128 of the hydrocyclone are defined at either end of the hydrocyclone's centerline axis 124, and the circumferential direction of the hydrocyclone (C...) S (Extends around axis 124, the centerline of the hydrocyclone.) The radial direction of the hydrocyclone (R) S The cyclone assembly 58 is defined as extending outward from the cyclone centerline axis 124. It can be seen that the cyclone assembly 58 includes a primary cyclone 130, a secondary cyclone 132 connected to a downstream side 136 of the primary cyclone 130, and a flare 134. The secondary cyclone 132 includes a flared attachment wall 138 that extends circumferentially around the cyclone centerline axis 124 and extends downstream from the downstream side 140 of the secondary cyclone downstream radial wall 142 in the downstream direction 128 of the cyclone. The flared attachment wall 138 includes a threaded flared attachment portion 144 forming the threaded outer surface of the flared attachment wall 138.

[0031] The flare 134 includes a dome-shaped interface wall 146, which extends circumferentially around the hydrocyclone centerline axis 124 and extends radially in the hydrocyclone direction R. S Extending upwards. The dome interface wall 146 includes an upstream surface 148, which interfaces with the flared interface surface 118 of the CMC dome 56, as will be described below. The flare 134 also includes an annular flared axial wall 150, which extends circumferentially around the hydrocyclone centerline axis 124 and extends in the longitudinal direction L of the hydrocyclone. S Extending upwards. The annular flared axial wall 150 includes a threaded secondary cyclone attachment portion 152 forming the threaded inner surface 153 of the annular flared axial wall 150. The annular flared axial wall 150 includes a plurality of spacer engagement members 154 extending radially outward from the outer surface 155 of the annular flared axial wall 150. Figure 5Multiple spacer joint components 154 can also be seen in the middle. Figure 5 It is a front and rear partial sectional perspective view depicting the flared opening 134 associated with the CMC dome 56.

[0032] The burner 26 also includes a cyclone dome attachment member 156 as a part connecting the cyclone assembly 58 to the CMC dome 56. Figure 4 In this aspect of the present disclosure, the hydrocyclone dome attachment member 156 is considered as a spacer 158, disposed between the downstream radial wall 142 of the secondary hydrocyclone 132 and the upstream surface 106 of the CMC dome 56. The spacer 158 is considered as an annular ring extending circumferentially around the hydrocyclone centerline axis 124 and includes a plurality of flared engagement grooves 160 on the inner surface 167 of the spacer 158 (see...). Figure 5 The plurality of flared engagement grooves 160 engage with corresponding spacer engagement members in the plurality of spacer engagement members 154 of the flared 134. The spacer 158 is also considered to include an outer surface 165 of the spacer 158 (see also...). Figure 5 Multiple platforms 162 (i.e., flat surfaces) on the surface.

[0033] When connecting the cyclone assembly 58 to the CMC dome 56, a flare 134 is inserted into the cyclone opening 100 of the CMC dome 56, with the dome interface wall inserted into the recess 108 to abut the shoulder 110. A spacer 158 is then mounted on the flare 134 to abut the upstream surface 106 of the CMC dome 56. Flare engagement groove 160 ( Figure 5The spacers 158 and flare 134 are arranged to engage with corresponding spacer engagement members in spacer engagement members 154 of the flare 134. A restraining mechanism (not shown) engages each of the plurality of platforms 162 to restrict rotation of the spacer 158 and the flare 134 within the hydrocyclone opening 100. The secondary hydrocyclone 132 (to which the primary hydrocyclone 130 has been attached) then threadedly engages with the flare 134 such that the threaded flare attachment portion 144 of the secondary hydrocyclone 132 engages with the threaded secondary hydrocyclone attachment portion 152 of the flare 134. Due to the threaded engagement of the secondary hydrocyclone 132 with the flare 134, the downstream end 164 of the spacer 158 engages with the upstream surface 106 of the CMC dome, and the upstream end 166 of the spacer 158 engages with the downstream radial wall 142 of the secondary hydrocyclone. A predetermined torque is applied to the secondary hydrocyclone 132, causing the spacer 158 (i.e., the hydrocyclone dome attachment member 156) to apply compressive force to the CMC dome 56 to engage the dome interface wall 146 and the flared interface surface 118 (i.e., the shoulder 110), thereby connecting the CMC dome 56 and the hydrocyclone assembly 58. An anti-rotation retaining member 168 can then be mounted via the annular flared axial wall 150 to engage the flared attachment wall 138 of the secondary hydrocyclone 132, thereby maintaining the threaded engagement between the secondary hydrocyclone 132 and the flare 134, and correspondingly maintaining the force applied between the dome interface wall 146 and the flared interface surface 118 of the CMC dome 56. Figure 6 It is a front and rear perspective view depicting the cyclone assembly 58 after being connected to the CMC dome 56 as described above.

[0034] Figure 7 This is a partial cross-sectional side view of a CMC dome according to another aspect of this disclosure. Figure 7 In this design, the CMC dome 56 includes a hydrocyclone mounting wall 170 disposed on the upstream side 178 of the CMC dome 56 and extending circumferentially around the CMC opening centerline 102. The hydrocyclone mounting wall 170 has a second hydrocyclone opening 172 therethrough. An annular cavity 174 is defined between the upstream surface 106 of the CMC dome 56 and the downstream surface 176 of the hydrocyclone mounting wall 170. The upstream surface 106 of the CMC dome 56 surrounding the hydrocyclone opening 100 can be considered to correspond to the flared interface surface 180.

[0035] Figure 8 Is Figure 7 The cross-section taken at point 8-8 of the plane through the hydrocyclone mounting wall 170. For example... Figure 8 As shown, the hydrocyclone mounting wall 170 includes a plurality of mounting wall grooves 182 therethrough, wherein the plurality of mounting wall grooves 182 are circumferentially spaced around the second hydrocyclone opening 172. The hydrocyclone mounting wall 170 may be integrally formed with the CMC dome 56.

[0036] Figure 9 It is based on another aspect of this disclosure. Figure 2 A detailed view at 122, a partial cross-sectional side view of the cyclone's attachment to the dome. Figure 9 The cyclone assembly 58 includes Figure 4 Some common components of the cyclone assembly 58 include the primary cyclone 130 and the secondary cyclone 132. Therefore, those having the same characteristics as... Figure 4 The common parts with the same reference numerals in the accompanying drawings. However, in Figure 9 In this aspect, the cyclone assembly 58 is connected to Figure 7 and Figure 8 CMC dome 56. Figure 9 The cyclone assembly 58 includes a flare 184 connected to the secondary cyclone 132. The flare 184 includes a dome-shaped interface wall 186 that extends circumferentially around the cyclone's central axis 124 and in the radial direction R of the cyclone. S Extend upwards.

[0037] refer to Figure 10 , in Figure 9 The cross-section taken at plane 10-10 is considered to include a plurality of interface wall grooves 214 spaced circumferentially around the dome interface wall 186.

[0038] Refer again Figure 9 The dome interface wall 186 includes a downstream surface 188, which, as will be described below, interfaces with the flared interface surface 180 of the CMC dome 56. The flare 184 also includes an annular flared axial wall 190, which extends circumferentially around the hydrocyclone centerline axis 124 and extends in the longitudinal direction L of the hydrocyclone. S Extending upwards. The annular flared axial wall 190 includes a threaded secondary hydrocyclone attachment portion 192 forming the threaded inner surface of the annular flared axial wall 190. The threaded secondary hydrocyclone attachment portion 192 can be coupled with... Figure 4 The threaded secondary hydrocyclone attachment portion 152 is the same. The annular flared axial wall 190 also includes a threaded hydrocyclone dome attachment portion 194, which forms the threaded outer surface of the annular flared axial wall 190 and is arranged on the outer surface 196 of the annular flared axial wall 190.

[0039] The burner 26 in this aspect also includes a cyclone dome attachment member 198 as a part connecting the cyclone assembly 58 and the CMC dome 56. The cyclone dome attachment member 198 includes an annular axial wall 208 extending circumferentially around the cyclone centerline axis 124 and including a threaded flared engagement portion 210 on its inner surface 212. Figure 9In the present aspect of this disclosure shown, the hydrocyclone dome attachment member 198 is essentially a ring (or nut) that threadedly engages the threaded hydrocyclone dome attachment member portion 194 of the flared end 184 (i.e., thread). The hydrocyclone dome attachment member 198 includes a downstream attachment wall 200 disposed at a downstream end 202 of the attachment member annular axial wall 208. The downstream attachment wall 200 extends circumferentially about the hydrocyclone centerline axis 124 and extends radially outward from the outer surface 204 of the attachment member annular axial wall 208.

[0040] refer to Figure 11 , Figure 11 Is Figure 9 The cross-section taken at plane 11-11 through the hydrocyclone dome attachment member 198, the downstream attachment wall 200 is considered to include a plurality of attachment member slots 216. The attachment member slots 216 are circumferentially spaced around the hydrocyclone centerline axis 124.

[0041] Return to reference Figure 9 The hydrocyclone dome attachment member 198 may also include a plurality of platforms 218 for limiting the hydrocyclone dome attachment member 198 during the attachment of the hydrocyclone assembly 58 to the CMC dome 56. As will be described below, when the hydrocyclone assembly 58 is attached to the CMC dome 56, the upstream surface 206 of the downstream attachment wall 200 engages with the downstream surface 176 of the hydrocyclone mounting wall 170 on the CMC dome 56.

[0042] When the hydrocyclone assembly 58 is attached to the CMC dome 56 according to the present aspect of this disclosure, the hydrocyclone dome attachment member 198 is attached to the flare 184. More specifically, the threaded flare engagement portion 210 of the hydrocyclone dome attachment member 198 and the threaded hydrocyclone dome attachment member portion 194 of the flare 184 are threaded together until the dome interface wall 186 of the flare 184 and the downstream attachment wall 200 of the hydrocyclone dome attachment member 198 contact each other. The plurality of interface wall grooves 214 and the plurality of attachment member grooves 216 of the dome interface wall 186 are aligned with each other (see [link to relevant documentation]). Figure 12 Then, the dome interface wall 186 and the downstream attachment wall 200 engage together through a plurality of mounting wall slots 182 in the hydrocyclone mounting wall 170, such that the dome interface wall 186 and the downstream attachment wall 200 of the hydrocyclone dome attachment member 198 are arranged within the annular cavity 174. The hydrocyclone dome attachment member 198 is then rotated such that the upstream surface 206 of the downstream attachment wall 200 engages with the downstream surface 176 of the hydrocyclone mounting wall 170, and the attachment member slot 216 aligns with the mounting wall slot 182.

[0043] Using multiple platforms 218, the hydrocyclone dome attachment member 198 is restricted to rotation, and the flare 184 rotates about the hydrocyclone centerline axis 124 to increase the distance between the downstream attachment wall 200 and the dome interface wall 186. A predetermined amount of torque is applied to the flare 184 to provide a predetermined force between the hydrocyclone dome attachment member 198 and the hydrocyclone mounting wall 170, and between the dome interface wall 186 and the flare interface surface 180 of the CMC dome 56. In other words, the hydrocyclone dome attachment member 198 engages the downstream surface 176 of the hydrocyclone mounting wall 170 within the annular cavity 174 to provide a first axial force between the hydrocyclone dome attachment member 198 and the hydrocyclone mounting wall 170, and the dome interface wall 186 engages the flared interface surface 180 of the CMC dome 56 within the annular cavity 174 to provide a second axial force between the dome interface wall 186 and the flared interface surface 180 of the CMC dome 56. The first axial force and the second axial force are in opposite directions to each other.

[0044] Return to reference Figure 9 Once the flare 184 and the hydrocyclone dome attachment member 198 are connected to the CMC dome 56 and twisted to apply a first axial force and a second axial force, the anti-rotation retainer 220 is installed. The anti-rotation retainer 220 is essentially an annular disk 224 extending circumferentially around the hydrocyclone centerline axis 124. The anti-rotation retainer 220 includes a plurality of retaining posts 222 extending axially from the annular disk 224 toward the downstream direction 128 of the hydrocyclone. The retaining posts 222 are inserted into corresponding mounting wall grooves 182 of the hydrocyclone mounting wall 170 (see...). Figure 13 In order to limit the rotation of the hydrocyclone dome attachment member 198 after the flare 184 is twisted. The secondary hydrocyclone 132, together with the primary hydrocyclone 130, is then connected to the flare 184 by threaded engagement of the threaded flare attachment portion 144 of the secondary hydrocyclone 132 and the threaded secondary hydrocyclone attachment portion 192 of the flare 184. Thus, the hydrocyclone assembly 58 is connected to the CMC dome 56.

[0045] While the foregoing description generally pertains to gas turbine engines, it is readily understood that gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in aircraft, but it can also be implemented in non-aircraft applications (such as power plants, marine applications, or oil and gas production applications). Therefore, this disclosure is not limited to use in aircraft.

[0046] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0047] A combustor for a gas turbine, the combustor comprising: a ceramic matrix composite (CMC) dome including a cyclone opening therethrough and a flared interface surface surrounding the cyclone opening; a cyclone assembly including (a) a secondary cyclone having a threaded flared attachment portion and (b) a flare having (i) a threaded secondary cyclone attachment portion and (ii) a dome interface wall interfaced with the flared interface surface of the CMC dome, the flare being connected to the secondary cyclone via the threaded flared attachment portion and the threaded secondary cyclone attachment portion; and a cyclone dome attachment member applying force to the CMC dome to engage the dome interface wall and the flared interface surface, thereby connecting the CMC dome and the cyclone assembly.

[0048] According to any of the foregoing clauses, the burner assembly further includes a primary swirler, the secondary swirler being connected to the downstream side of the primary swirler.

[0049] According to any of the preceding clauses, the burner has the flared interface surface including a recess extending upstream from the downstream surface of the CMC dome and defining a shoulder extending radially outward from the cyclone opening, and the dome interface wall engaging the shoulder.

[0050] According to any of the preceding clauses, the burner wherein the cyclone dome attachment member includes a spacer disposed between the upstream surface of the CMC dome and the downstream radial wall of the secondary cyclone.

[0051] According to any of the preceding clauses, the threaded flared attachment portion of the secondary cyclone and the threaded secondary cyclone attachment portion of the flared portion are threadedly engaged to apply force to the upstream surface of the CMC dome through the spacer, thereby applying a compressive force between the shoulder and the dome interface wall of the flared portion.

[0052] According to any of the preceding clauses, the burner includes an annular axial wall extending circumferentially around the axis of the cyclone's centerline, and the threaded secondary cyclone attachment portion is disposed on the inner surface of the annular axial wall.

[0053] According to any of the preceding clauses, the burner includes a plurality of spacer engagement members extending radially outward from the outer surface of the annular flared axial wall.

[0054] According to any of the preceding clauses, the burner wherein the spacer extends circumferentially around the cyclone centerline axis and the spacer includes a plurality of flared engagement grooves disposed on the inner surface of the spacer, wherein a corresponding flared engagement groove of the plurality of flared engagement grooves engages with a corresponding spacer engagement member of the plurality of spacer engagement members of the axial wall of the annular flare.

[0055] The burner according to any of the foregoing clauses further includes an anti-rotation retaining member configured to pass through the flare and engage the secondary vortex to maintain a threaded engagement between the flare and the secondary vortex.

[0056] According to any of the preceding clauses, the burner wherein the CMC dome further includes a swirler mounting wall disposed on the upstream side of the CMC dome and extending circumferentially about the centerline axis of the swirler opening, the swirler mounting wall having a second swirler opening therethrough, and an annular cavity being defined between the upstream surface of the CMC dome and the downstream surface of the swirler mounting wall.

[0057] According to any of the foregoing clauses, the burner wherein the swirler mounting wall is integrally formed with the CMC dome.

[0058] According to any of the preceding clauses, the upstream surface of the CMC dome surrounding the cyclone mounting opening includes the flared interface surface, and the dome interface wall of the flared portion interfaces with the upstream surface of the CMC dome.

[0059] According to any of the preceding clauses, the burner includes an annular axial wall extending circumferentially around the cyclone centerline axis, the threaded secondary cyclone attachment portion being disposed on the inner surface of the annular axial wall, and the annular axial wall further including a threaded cyclone dome attachment portion disposed on the outer surface of the annular axial wall.

[0060] According to any of the preceding clauses, the burner, wherein the cyclone dome attachment member includes an annular axial wall of the attachment member extending circumferentially around the axis of the cyclone centerline, and includes a threaded flared engagement portion located on its inner surface.

[0061] According to any of the preceding clauses, the burner wherein the cyclone dome attachment member includes a downstream attachment wall extending radially outward from the downstream end of the annular axial wall of the attachment member, the downstream attachment wall including a plurality of attachment member slots therethrough.

[0062] According to any of the preceding clauses, the burner, wherein the dome interface wall includes a plurality of interface wall slots therethrough, and the cyclone mounting wall of the CMC dome includes a plurality of mounting wall slots therethrough.

[0063] According to any of the preceding clauses, in a burner, the cyclone dome attachment member engages the downstream surface of the cyclone mounting wall within the annular cavity to provide a first axial force between the cyclone dome attachment member and the cyclone mounting wall, and the dome interface wall engages the upstream surface of the CMC dome within the annular cavity to provide a second axial force between the dome interface wall and the upstream surface of the CMC dome, the first axial force and the second axial force being in directions opposite to each other.

[0064] According to any of the preceding clauses of the burner, wherein, during assembly, the threaded flared engagement portion of the cyclone dome attachment member and the threaded cyclone dome attachment member portion of the flared portion are threadedly engaged with each other, the plurality of interface wall grooves and the plurality of attachment member grooves of the dome interface wall are aligned, and the dome interface wall and the downstream attachment wall are engaged together through the plurality of mounting wall grooves such that the dome interface wall and the downstream attachment wall of the cyclone dome attachment member are arranged within the annular cavity, the cyclone dome attachment member rotates such that the upstream surface of the downstream attachment wall engages with the downstream surface of the cyclone mounting wall, and while restricting the rotation of the cyclone dome attachment member, the flared portion rotates about the cyclone centerline axis to increase the distance between the downstream attachment wall and the dome interface wall, thereby providing a predetermined compressive force between the cyclone dome attachment member and the cyclone mounting wall, and between the dome interface wall and the upstream surface of the CMC dome.

[0065] The burner according to any of the foregoing clauses further includes an anti-rotation retainer having a plurality of retaining posts extending axially therefrom, the plurality of retaining posts engaging via corresponding mounting grooves in the plurality of mounting grooves to retain the cyclone dome attachment member to the CMC dome.

[0066] According to any of the preceding clauses, the burner includes an annular disk extending circumferentially around the cyclone's central axis, and the plurality of retaining posts extending from the annular disk in a downstream direction.

[0067] While the foregoing description is directed to some exemplary embodiments of the present disclosure, 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 for a gas turbine, characterized in that, The burner includes: A ceramic matrix composite (CMC) dome includes a hydrocyclone opening therethrough, having a flared interface surface surrounding the hydrocyclone opening on an upstream surface of the CMC dome, the CMC dome further including a hydrocyclone mounting wall disposed on an upstream side of the CMC dome and extending circumferentially around a centerline axis of the hydrocyclone opening, the hydrocyclone mounting wall having a second hydrocyclone opening therethrough, and an annular cavity defined between the upstream surface of the CMC dome and the downstream surface of the hydrocyclone mounting wall; A hydrocyclone assembly comprising (a) a primary hydrocyclone, (b) a secondary hydrocyclone having a threaded flared attachment portion and (c) a flared portion having (i) a threaded secondary hydrocyclone attachment portion, (ii) a dome interface wall that interfaces with the flared interface surface of the CMC dome, and (iii) a threaded hydrocyclone dome attachment member portion. A hydrocyclone dome attachment component, comprising a threaded flared attachment portion and an attachment wall. The flared end of the hydrocyclone dome attachment member and the dome interface wall of the attachment wall are arranged within the annular cavity, and the hydrocyclone dome attachment member is threadedly engaged with the threaded portion of the flared hydrocyclone attachment member to engage the dome interface wall of the flared end with the flared interface surface of the CMC dome and apply a first axial force therebetween, and to engage the attachment wall of the hydrocyclone dome attachment member with the downstream surface of the hydrocyclone mounting wall and apply a second axial force therebetween.

2. The burner according to claim 1, characterized in that, in, The hydrocyclone mounting wall is integrally formed with the CMC dome.

3. The burner according to claim 1, characterized in that, in, The flare includes an annular flare axial wall extending circumferentially around the centerline axis of the hydrocyclone opening, the threaded secondary hydrocyclone attachment portion being disposed on the inner surface of the annular flare axial wall, and the annular flare axial wall further including a threaded hydrocyclone dome attachment member portion disposed on the outer surface of the annular flare axial wall.

4. The burner according to claim 3, characterized in that, in, The hydrocyclone dome attachment member includes an annular axial wall that extends circumferentially around the centerline axis of the hydrocyclone opening and includes a threaded flared engagement portion located on its inner surface.

5. The burner according to claim 4, characterized in that, The attachment wall extends radially outward from the downstream end of the annular axial wall of the attachment member, and the attachment wall includes a plurality of attachment member grooves therethrough.

6. The burner according to claim 5, characterized in that, in, The dome interface wall includes a plurality of interface wall slots therethrough, and the cyclone mounting wall of the CMC dome includes a plurality of mounting wall slots therethrough.

7. The burner according to claim 1, characterized in that, in, The first axial force and the second axial force are in directions opposite to each other.

8. The burner according to claim 6, characterized in that, in, During assembly, the threaded flared engagement portion of the hydrocyclone dome attachment member and the flared threaded hydrocyclone dome attachment member portion are threadedly engaged with each other. The plurality of interface wall grooves and the plurality of attachment member grooves of the dome interface wall are aligned, and the dome interface wall and the attachment wall are engaged together through the plurality of mounting wall grooves, such that the dome interface wall and the attachment wall of the hydrocyclone dome attachment member are arranged within the annular cavity. The hydrocyclone dome attachment member rotates such that the upstream surface of the attachment wall engages with the downstream surface of the hydrocyclone mounting wall, and While restricting the rotation of the hydrocyclone dome attachment member, the flare rotates about the centerline axis of the hydrocyclone opening to increase the distance between the attachment wall and the dome interface wall, thereby providing a predetermined compressive force between the hydrocyclone dome attachment member and the hydrocyclone mounting wall, and between the dome interface wall and the upstream surface of the CMC dome.

9. The burner according to claim 6, characterized in that, The device further includes an anti-rotation retainer having a plurality of retaining posts extending axially therefrom, the plurality of retaining posts engaging via corresponding mounting grooves in the plurality of mounting grooves to retain the hydrocyclone dome attachment member to the CMC dome.

10. The burner according to claim 9, characterized in that, in, The anti-rotation retainer includes an annular disk extending circumferentially around the centerline axis of the cyclone opening, and the plurality of retaining posts extending from the annular disk in a downstream direction.

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