Ceramic composite burner dome and liner

Abstract

A combustor for a turbine engine includes a dome made of ceramic matrix composite (CMC) material, the dome being fixed within a support structure. The combustor includes an outer liner made of CMC material, the outer liner being fixed to the dome within the support structure. The combustor also includes an inner liner made of CMC material, the inner liner being fixed to the dome within the support structure.

Description

Technical Field

[0001] This disclosure relates to a turbine engine including a burner. Background Technology

[0002] The combustor in a turbine engine receives a mixture of fuel and highly compressed air, which is ignited to produce hot combustion gases. These hot gases are used to provide torque in the turbine, thus providing mechanical power and thrust. A typical combustor layout is at least partially constructed of metal, which is heavy and requires multi-walled structures and high levels of cooling to protect the combustor from extremely high temperatures. The expansion of the metal at high temperatures can also create gaps that interfere with airflow and reduce fuel efficiency. 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 An example of an aircraft turbine engine is shown.

[0005] Figure 2 It shows along Figure 1 The schematic cross-sectional view of the burner, taken from line 2-2 of the turbine engine shown.

[0006] Figure 3 It shows along Figure 2 The schematic cross-sectional view of the combustion chamber shown is taken from line 3-3 of the burner.

[0007] Figure 4 It shows along Figure 3 The schematic cross-sectional view of the combustion chamber shown is taken from line 4-4 of the burner.

[0008] Figure 5 An embodiment of a burner is schematically shown in some examples, wherein the dome, outer liner, and inner liner are all made of CMC material.

[0009] Figure 6 Cross-sectional views of fasteners according to some embodiments are shown.

[0010] Figure 7 A perspective view of the outer and inner arrays of structural mounting components and fasteners is schematically shown, with the dome, inner liner, and outer liner removed for clarity.

[0011] Figure 8A An outer array of fasteners is shown, in which structural mounting components have been removed.

[0012] Figure 8BThe inner array of fasteners is shown, with structural mounting components removed.

[0013] Figure 9 A rear view of the combustion chamber is shown.

[0014] Figure 10 A rear view of the combustion chamber is shown, with structural mounting components removed.

[0015] Figure 11 Another burner, representing some embodiments, is shown schematically. Detailed Implementation

[0016] 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.

[0017] 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.

[0018] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0019] The terms "front" and "rear" refer to relative positions within a turbine engine or carrier, and specifically to the normal operating posture of the turbine engine or carrier. For example, in a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0020] The terms "outer" and "inner" refer to the relative positions of the turbine engine's interior relative to the engine's centerline. For example, "outer" refers to the position further away from the centerline, while "inner" refers to the position closer to the centerline.

[0021] Unless otherwise stated, the terms “connection,” “fixed,” “attached to,” etc., refer to both direct connection, fixation, or attachment, and indirect connection, fixation, or attachment via one or more intermediate components or features.

[0022] This disclosure and various embodiments relate to turbine engines, also known as gas turbine engines, turboprop engines, or turbines. These turbine engines are applicable to a wide range of technologies and industries. Various embodiments can be described herein within the context of aero-engines and aircraft mechanics.

[0023] In some cases, turbine engines are constructed as direct-drive engines. In others, turbine engines can be constructed as geared engines with a gearbox. In some cases, the propeller of a turbine engine can be a fan enclosed in a fan casing and / or nacelle. This type of turbine engine can be referred to as a "piped engine." In other cases, the propeller of a turbine engine can be exposed (e.g., not in a fan casing or nacelle). This type of turbine engine can be referred to as an "open rotor engine" or a "non-piped engine."

[0024] Ceramic matrix composites (CMCs) are desirable in burner design because they have a much higher heat capacity than metals. While some burner designs have incorporated CMCs in certain parts of the burner, these still rely on metals for the dome and other burner components. The advantages of a full CMC design, due to the replacement of heavier metal components and the simplification of the internal design, include reduced cooling, lighter weight, and shorter burner length. Compared to partially CMC burner designs, a full CMC design may also offer improved airflow control by eliminating the attachment gap between the dome and the liner, reduced weight by eliminating additional baffles, and reduced cooling on the dome.

[0025] Some embodiments of this disclosure provide a full CMC design for the dome and liner of a combustor in a turbine engine. This design includes dedicated mounting hardware to prevent damage from direct metal-to-metal contact between the engine's support structure and the CMC on the CMC dome and liner, and to provide flexibility and maintain the separation and position of the CMC components relative to each other during thermal expansion of the surrounding metal engine and combustor components.

[0026] Figure 1 An example of a turbine engine 100 according to an embodiment of the present disclosure is shown. Types of such engines include turboprop engines, turbofan engines, turbines, and turbojet engines. The turbine engine 100 is covered by a protective shield 105, so the only visible component in this external view is the fan assembly 110. Figure 1 The nozzle, not shown, also protrudes beyond the protective cover 105 from the rear end of the turbine engine 100.

[0027] Figure 2 It shows along Figure 1The schematic cross-sectional view of the turbine engine 100 shown, taken by line 2-2, can be incorporated into one or more embodiments of this disclosure. In this example, the turbine engine 100 is a twin-shaft turbine comprising a high-speed system and a low-speed system, both partially covered by a protective shield 105. The low-speed system of the turbine engine 100 includes a fan assembly 110, a low-pressure compressor 210 (also referred to as a turbocharger), and a low-pressure turbine 215, all connected by a low-speed shaft extending along the centerline axis 220 of the turbine engine 100. Figure 2 (Not shown in the image) Connections. The fan assembly 110, low-pressure compressor 210, and low-pressure turbine 215 all rotate uniformly about the central axis 220.

[0028] The high-speed system of the turbine engine 100 includes a high-pressure compressor 225, a combustor 230, and a high-pressure turbine 235, all connected by a high-speed shaft extending along the centerline axis 220 of the turbine engine 100. Figure 2 (Not shown in the diagram) Connection. The high-pressure compressor 225 and the high-pressure turbine 235 rotate in unison about the centerline axis 220 at a different rotational speed than the low-pressure components (and in some embodiments, at a higher rotational speed and / or in the opposite direction of rotation relative to the low-pressure system).

[0029] The components of the low-pressure and high-pressure systems are positioned such that a portion of the air drawn into the turbine engine 100 flows through the turbine engine 100 from front to back through the fan assembly 110, low-pressure compressor 210, high-pressure compressor 225, combustor 230, high-pressure turbine 235, and low-pressure turbine 215. Another portion of the air drawn into the turbine engine 100 bypasses the low-pressure and high-pressure systems and flows from front to back along arrow 240.

[0030] Combustor 230 is located between high-pressure compressor 225 and high-pressure turbine 235. Combustor 230 may include features for receiving fuel from a fuel system. Figure 2 The configuration includes one or more mixtures of fuel (not shown) and air from high-pressure compressor 225. This mixture is ignited, producing hot combustion gases that flow from front to back through high-pressure turbine 235, which provides torque to rotate the high-pressure shaft, thereby rotating high-pressure compressor 225. After leaving the high-pressure turbine, the combustion gases continue to flow from front to back through low-pressure turbine 215, which provides torque to rotate the low-pressure shaft, thereby rotating low-pressure compressor 210 and fan assembly 110.

[0031] In other words, the pre-stage of the turbine engine 100, namely the fan assembly 110, the low-pressure compressor 210, and the high-pressure compressor 225, all prepare the intake air for ignition. The pre-stage requires power to rotate. The post-stage of the turbine engine 100, namely the combustor 230, the high-pressure turbine 235, and the low-pressure turbine 215, provides this required power by igniting compressed air and using the resulting hot combustion gases to rotate the low-pressure and high-pressure shafts (also called rotors). In this way, the post-stage uses air to physically drive the pre-stage, and the pre-stage is driven to supply air to the post-stage.

[0032] As the exhaust leaves the rear end of the stage, it reaches the nozzle at the rear end of the turbine engine 100. Figure 2 (Not shown in the image). When exhaust gas passes through the nozzle and combines with bypass air, an exhaust force is generated, which is the thrust generated by the turbine engine 100.

[0033] Figure 3 It shows along Figure 2 The diagram shows a schematic cross-sectional view of the combustor 230 of the turbine engine 100, taken along line 3-3. The combustor 230 is axially symmetrical about its centerline axis 220, with annular rings of fuel nozzles 305 spaced circumferentially and facing rearward. Compressed air 310 from the preceding stage of the turbine engine 100 flows into the combustor and mixes with fuel from the fuel nozzles 305 in the combustion chamber 315. The fuel-air mixture is ignited in the combustion chamber 315 to produce a stable combustion gas flow 320, which enters the turbine in the subsequent stage. Figure 4 (Not shown in the image).

[0034] Figure 4 It shows along Figure 3 The diagram shows a schematic cross-sectional view of the combustion chamber 315, taken by line 4-4 of the burner 230. The combustion chamber 315 is an annular open space about a central axis 220, defined at its front end by a dome 405 supporting and positioning the fuel nozzle 305, and an outer liner 410 and an inner liner 415 on the outer and inner annular surfaces, respectively. Figure 4 A coaxial cylinder (not shown) has an outer liner 410 and an inner liner 415 radially spaced apart. A dome 405 forms an annular wall oriented perpendicular to and coaxial with the central axis 220, with orifices spaced circumferentially to receive each fuel nozzle 305. Due to its proximity to the combustion chamber, hot gases, and the extreme temperatures generated therein, the dome must be constructed to withstand harsh environments. The combustion chamber 315 opens rearward to allow combustion gases to flow to the high-pressure turbine 235 (…). Figure 4 (Not shown in the image).

[0035] The outer liner 410 and the inner liner 415 have a centerline axis 220 ( Figure 4(Not shown) A rotationally symmetric cylindrical shape, with the radius of the outer liner 410 being larger than the radius of the inner liner 415. Both the outer liner 410 and the inner liner 415 extend in the rearward direction along the central axis 220.

[0036] exist Figure 4 In the example, the dome 405, outer liner 410, and inner liner 415 are all made of metal. Therefore, the dome 405 and outer liner 410 are joined together at the outer flange 417 of the dome 405 by an outer array 420 of fasteners, and the dome 405 and inner liner 415 are joined together at the inner flange 418 of the dome 405 by an inner array 425 of fasteners. These fasteners may include one or more of pins, bolts, nuts, nut plates, screws, and any other suitable fasteners.

[0037] The outer array 420 and inner array 425 are also used to connect the dome 405, outer liner 410, and inner liner 415 to the burner housing 430 of the burner 230. Note that in this example, since the dome 405, outer liner 410, and inner liner 415 are all made of metal, fasteners are directly attached to these components.

[0038] The burner housing 430 defines an inlet 435 for compressed air from the high-pressure compressor 225. Figure 4 (Not shown, but along arrow 440) Air flows and enters the combustion chamber 315 surrounding the fuel nozzle 305. Air also flows through airflow holes in the outer liner 410 (e.g., along arrow 445) and the inner liner 415 (e.g., along arrow 447). Figure 4 (Not shown) flows into combustion chamber 315. Additionally, one or more heat shields and / or deflectors ( Figure 4 (Not shown in the image) can also be provided on the dome 405 to help protect the dome 405 from the heat of the combustion gases.

[0039] Furthermore, the burner housing 430 supports the dome 405 via a mounting arm 455 connected to a shroud mount 450, which has annular symmetry about a centerline axis 220, forming a rearward-facing channel to receive the dome 405 and a forward-facing orifice to receive the fuel nozzle 305. The shroud mount 450 is directly connected to the outer flange 417 and inner flange 418 of the dome 405 via an outer array 420 of fasteners and an inner array 425 of fasteners, respectively.

[0040] In some embodiments, non-traditional non-metallic high-temperature materials, such as ceramic matrix composites (CMCs), can be used for various components within turbine engines. Because CMCs can withstand relatively extreme temperatures, there is particular interest in replacing components within the flow path of combustion gases with CMCs. For example, combustor liners and domes have surfaces and / or features exposed to or within the flow path of combustion gases. Constructing domes, liners, and outer liners from CMCs would be advantageous, for example, by reducing weight through replacing metal components with CMC shells, reducing cooling of the liner due to the greater material strength, and shortening the combustor construction because the dome can be constructed with a single-walled rather than a multi-walled structure.

[0041] Furthermore, the all-CMC construction of all three components (dome, outer liner, and inner liner) also offers advantages over solutions with CMC liners and metal domes, as described, for example, in U.S. Patent Publication 2017 / 0370583, which is incorporated herein by reference. These advantages may include improved airflow control in the attachment gap between the dome and the liner, reduced dome weight and elimination of deflectors required to protect the dome from extreme temperatures, reduced engine length due to the single-walled dome structure, and reduced cooling to the dome due to greater material strength.

[0042] However, CMC components cannot be directly coupled to metal components because the expansion of the coupled metal components at high temperatures would cause the coupled CMC components to crack. Therefore, the mounting hardware for CMC components must allow the CMC components to maintain their relative positions without direct contact with metal.

[0043] Examples of CMC materials used for such components may include silicon carbide, silicon, silica, or alumina-based materials and combinations thereof. Ceramic fibers may be embedded in the matrix, such as oxidation-stabilized reinforcing fibers, including monofilaments (e.g., sapphire and silicon carbide, such as SCS-6). TM (Textron, Providence, Rhode Island, United States) and rovings and yarns, including silicon carbide (e.g.) (Nippon Carbon, Tokyo, Japan) (UbeIndustries,Tokyo,Japan) and (Dow Corning, Midland, Michigan, United States)), aluminum silicate (e.g.) 440 and 480 (3M, Saint Paul, Minnesota, United States), chopped whiskers and fibers (e.g.) (Unifrax, Tonawanda, New York, United States)), ceramic particles (e.g., oxides of Si, Al, Zr, Y, and combinations thereof), and inorganic fillers (e.g., pyrophyllite, wollastonite, mica, talc, kyanite, and montmorillonite). As a further example, CMC materials may also include silicon carbide (SiC) or carbon fiber cloth.

[0044] Figure 5 A burner 500 of some embodiments is schematically shown, wherein the dome 505, outer liner 510, and inner liner 515 are all made of CMC material. In this example, a mounting arm 520 is connected to a structural mount 525 with a double-ring design, the structural mount 525 having an outer channel 530 and an inner channel 531, both facing rearward. The outer channel 530 and the inner channel 531 are coaxial and have annular symmetry about a central axis 220, with the outer channel 530 having a larger radius than the inner channel 531. Between the two channels, the structural mount 525 also has an orifice (not shown) for a fuel nozzle, which is omitted in this view for clarity.

[0045] The outer channel 530 has an outer wall 532 and an inner wall 534, wherein the outer wall 532 is radially positioned further away from the centerline axis 220 than the inner wall 534. An outer array 535 of fasteners connects the outer wall 532, the outer liner 510, the dome 505, and the inner wall 534 of the outer channel 530. The outer array 535 of fasteners ensures clearance on all sides between the inner metal surface of the outer channel 530 and the CMC surfaces of the dome 505 and the outer liner 510. This clearance allows for thermal expansion of the outer channel 530 while protecting the CMC components from physical damage by providing space for the dome 505 and the outer liner 510 to float within the outer channel 530, while maintaining separation between the dome 505, the outer liner 510, the outer wall 532, and the inner wall 534 of the outer channel 530. Further details of the fastener hardware are described below.

[0046] Similarly, the inner channel 531 has an outer wall 536 and an inner wall 538, wherein the outer wall 536 is radially positioned further away from the centerline axis 220 than the inner wall 538. An inner array 540 of fasteners connects the outer wall 536, dome 505, liner 515, and inner wall 538 of the inner channel 531. The inner array 540 of fasteners ensures clearance on all sides between the metal inner surface of the inner channel 531 and the CMC surfaces of the dome 505 and liner 515. This clearance allows for thermal expansion of the inner channel 531 while protecting the CMC components from physical damage by providing space for the dome 505 and liner 515 to float within the inner channel 531, while maintaining separation between the dome 505, liner 515, outer wall 536, and inner wall 538 of the inner channel 531. Further details of the fastener hardware are described below.

[0047] Figure 6 Cross-sectional views of fasteners 600 for outer array 535 and inner array 540 are shown in some embodiments. In this example, fastener 600 is a bolt-nut assembly with bolt 605 extending through an engine component and nut 610 for securing bolt 605. Bolt 605 is wound along its length by bushing 615, and bushing 615 is surrounded by one or more grommets 620, 625 that receive CMC components (e.g., dome 505, outer liner 510, and inner liner 515). In some embodiments, two grommets 620, 625 are used, each grommet having a single channel to receive a separate CMC component. In other embodiments, a single grommet with two channels may be used, each channel receiving a separate CMC component.

[0048] The grommets 620 and 625 allow the CMC component to move radially along the bushing 615 during thermal expansion of the metal components of the structural mount 525 (e.g., the outer wall 532 and inner wall 534 of the outer channel 530, and the outer wall 536 and inner wall 538 of the inner channel 531). The interface between the bushing 615 and the grommets 620 and 625 maintains the proper position of the CMC component relative to the structural mount 525 (which is made of metal) while reducing wear and preventing damage to the CMC component during engine operation.

[0049] The bolts 605 and nuts 610 in fastener 600 can be made of nickel alloy (e.g., (United Technologies Corporation, Farmington, Connecticut)). Bushing 615 can be made of a cobalt-chromium alloy (e.g., 25 (L-605) (Haynes International, Kokomo, Indiana) is constructed, while the grommets 620 and 625 can be constructed from a cobalt alloy (e.g., Haynes 188 (MetalTek, Waukesha, Wisconsin, United States)). However, any suitable complementary metal that wears well with each other can be selected. In some embodiments, a coating is also applied to the outer surface of bolt 605 and / or bushing 615 to provide additional wear protection. Suitable coating materials include T- (Deloro, Koblenz, Germany).

[0050] Figure 7 A perspective view schematically illustrates the structural mount 525, the outer array 535 of the fasteners, and the inner array 540, with the dome 505, inner liner 515, and outer liner 510 omitted for clarity. The orifice 705 for the fuel nozzle (not shown) is also visible in this view. Only a single segment of the structural mount 525 and portions of the outer array 535 and inner array 540 are shown; the remainder extends circumferentially around the centerline axis 220. This perspective view shows how the outer array 535 of the fasteners penetrates the wall of the outer channel 530, and how the inner array 540 of the fasteners penetrates the wall of the inner channel 531.

[0051] Figure 8A The outer array 535 of fasteners is shown, and Figure 8B An inner array 540 of fasteners is shown, with structural mounting 525 removed. Fasteners 801, 802, 803, and 804 are part of an outer array 535, and each has a set of inner loops 807, 808, 809, and 810 and a set of outer loops 811, 812, 813, and 814. Fasteners 815 and 816 are part of the inner array 540, and each has a set of outer loops 817 and 818 and a set of inner loops 819 and 820. A dome 505 (not shown) is received by the set of inner loops 807, 808, 809, and 810 in the outer array 535 and the set of outer loops 817 and 818 in the inner array 540. The outer liner 510 (not shown) is received by the set of outer loops 811, 812, 813, and 814 in the outer array 535, and the inner liner 515 (not shown) is received by the set of inner loops 819 and 820 in the inner array 540. (As mentioned above...) Figure 6 As noted, the inner and outer grommets are used to maintain the separation of the lining from the dome and to provide flexibility for the movement of these components during the thermal expansion of structural mounting 525 without contact with metal.

[0052] Figure 9A rearward view of the combustion chamber is shown. In this view, structural mount 525 is in the foreground, with a portion of dome 505 visible in the background. The three orifices 905, 910, and 915 for the fuel nozzles are visible, extending through structural mount 525 and dome 505. Outer liner 510 and inner liner 515 are obscured from the view by structural mount 525. Fasteners 801 to 804 in the outer array 535 are partially visible as they extend through the outer wall 532 of the outer passage 530. Fasteners 815 and 816 in the inner array 540 are partially visible as they extend through the inner wall 538 of the inner passage 531.

[0053] Figure 10 A rear view of the combustion chamber is shown, with structural mounting 525 removed. Three orifices 905, 910, and 915 for the fuel nozzle are visible, extending through the dome 505.

[0054] Fasteners 801 to 804 in outer array 535 are partially visible as they extend through outer liner 510 and dome 505. The flanges of the grommets 811 to 814 and 807 to 810 of fasteners 801 to 804 are also visible around the edges of outer liner 510 and dome 505, respectively. Corresponding bushings 1001, 1002, 1003, and 1004 of fasteners 801 to 804 are also partially visible in this view.

[0055] Fasteners 815 and 816 in the inner array 540 are partially visible as they extend through the dome 505 and the liner 515. The flanges of the grommets 817, 818, 819, and 820 of fasteners 815 and 816 are also visible around the edges of the dome 505 and the liner 515, respectively. Corresponding bushings 1015 and 1016 of fasteners 815 and 816 are also partially visible in this view.

[0056] Figure 11 Another embodiment of the burner 1100 is schematically shown among some embodiments. The burner 1100 is similar to those described above. Figures 5 to 10 The burner 500 embodiments discussed herein use similar reference numerals to refer to the same or similar components. Detailed descriptions of these components will be omitted, and the following discussion focuses on the differences between these embodiments. Any of the various features discussed in conjunction with any of the embodiments discussed herein may also be applied to and used with any other embodiment.

[0057] exist Figure 11In the example, an outer spacer 1105 is used between the dome 505 and the outer liner 510 to provide a more precise separation between the dome 505 and the outer liner 510. Alternatively or in combination, an inner spacer 1110 is used between the dome 505 and the inner liner 515 to provide a more precise separation between the dome 505 and the inner liner 515. In some embodiments, each fastener 600 in the outer array 535 and / or the inner array 540 has its own spacer surrounding the bushing 615 between the grommets 620, 625.

[0058] In some embodiments, the outer spacer 1105 may be a single integral structure having a cylindrical shape around a central axis 220 (not shown), with a radius greater than that of the dome 505 and smaller than that of the outer liner 510. The outer spacer 1105 is secured in place between the dome 505 and the outer liner 510 by an outer array 535 of fasteners.

[0059] In some embodiments, the inner spacer 1110 may be a single integral structure having a cylindrical shape around a central axis 220 (not shown), with a radius smaller than that of the dome 505 and larger than that of the liner 515. The inner spacer 1110 is secured in place between the dome 505 and the liner 515 by an inner array 540 of fasteners.

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

[0061] A combustor for a turbine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being fixed within a support structure. The combustor further includes: an outer liner made of the CMC material, the outer liner being fixed to the dome within the support structure; and an inner liner made of the CMC material, the inner liner being fixed to the dome within the support structure.

[0062] According to the combustor described in the foregoing clause, the outer liner and the inner liner have a cylindrical shape around the central axis of the turbine engine, and the radius of the outer liner is larger than the radius of the inner liner.

[0063] According to any of the preceding clauses, the burner, wherein the support structure is made of metal and includes an outer channel and an inner channel, each having an annular shape around the central axis, the radius of the outer channel being larger than the radius of the inner channel. The outer liner and a first section of the dome are secured within the outer channel by a first array of fasteners, and the inner liner and a second section of the dome are secured within the inner channel by a second array of fasteners.

[0064] The burner according to any of the foregoing clauses further includes an abrasion-resistant coating applied to at least one outer surface of one or more fasteners.

[0065] According to any of the preceding clauses, the outer channel of the support structure has an outer wall and an inner wall, and at least one fastener in the first fastener array has a metal bolt penetrating the outer wall, the outer liner, the dome and the inner wall, and a bushing that fits the metal bolt between the outer wall and the inner wall.

[0066] According to any of the preceding clauses, in the burner, at least one fastener in the first fastener array further has at least one loop surrounding at least a first portion of the bushing, the loop being made of a chromium-nickel alloy, and the bushing being made of a cobalt-molybdenum-chromium alloy.

[0067] According to any of the foregoing clauses, in a burner, at least one fastener in the first fastener array further has an outer loop surrounding a first portion of the bushing to receive the outer liner, and an inner loop surrounding a second portion of the bushing to receive the dome.

[0068] According to any of the preceding clauses, in a burner, at least one fastener in the first fastener array further has a spacer that surrounds a third portion of the bushing between the inner and outer cable rings.

[0069] The burner according to any of the foregoing clauses further includes a spacer secured within the outer channel by the first array of fasteners, the spacer having a cylindrical shape around the central axis and positioned between the outer liner and the dome. The radius of the spacer is smaller than the radius of the outer liner.

[0070] According to any of the preceding clauses, in a burner, at least one fastener in the first fastener array further has a grommets surrounding the bushing, the grommets having a first channel for receiving the outer liner and a second channel for receiving the dome.

[0071] According to any of the preceding clauses, the inner channel of the support structure has an outer wall and an inner wall, and at least one fastener in the second fastener array has a metal bolt penetrating the outer wall, the dome, the liner and the inner wall, and a bushing that fits the metal bolt between the outer wall and the inner wall.

[0072] According to any of the preceding clauses, in the burner, at least one fastener in the second fastener array further has at least one loop surrounding at least a first portion of the bushing, the loop being made of a chromium-nickel alloy, and the bushing being made of a cobalt-molybdenum-chromium alloy.

[0073] According to any of the foregoing clauses, in the burner, at least one fastener in the second fastener array further has an outer loop surrounding a first portion of the bushing to receive the dome, and an inner loop surrounding a second portion of the bushing to receive the inner liner.

[0074] According to any of the preceding clauses, in the burner, at least one fastener in the second fastener array further has a spacer that surrounds a third portion of the bushing between the inner and outer cable rings.

[0075] The burner according to any of the foregoing clauses further includes a spacer secured within the inner channel by the second array of fasteners, the spacer having a cylindrical shape about the central axis and positioned between the dome and the liner. The radius of the spacer is larger than the radius of the liner.

[0076] According to any of the preceding clauses, in the burner, at least one fastener in the second fastener array further has a loop surrounding the bushing, the loop having a first channel for receiving the dome and a second channel for receiving the liner.

[0077] A turbine engine includes: a fan assembly that provides intake air to a compressor section; a turbine section that drives the compressor section; and a combustor arranged to receive compressed air from the compressor section and provide hot gas to the turbine section. The combustor includes a dome made of a ceramic matrix composite (CMC) material, the dome being fixed within a support structure. The combustor further includes: an outer liner made of the CMC material, the outer liner being fixed to the dome within the support structure; and an inner liner made of the CMC material, the inner liner being fixed to the dome within the support structure.

[0078] According to any of the foregoing clauses, the turbine engine, wherein the support structure is made of metal and has an outer channel and an inner channel, the outer liner and the inner liner having a cylindrical shape around the central axis of the turbine engine, and the outer channel and the inner channel each having an annular shape around the central axis. The radius of the outer liner is larger than the radius of the inner liner, and the radius of the outer channel is larger than the radius of the inner channel. A first section of the outer liner and the dome is secured within the outer channel by a first fastener array, and a second section of the inner liner and the dome is secured within the inner channel by a second fastener array.

[0079] According to any of the preceding clauses of the turbine engine, wherein the outer passage of the support structure has an outer wall and an inner wall, and at least one fastener in the first fastener array comprises: (i) a metal bolt penetrating the outer wall, the outer liner, the dome, and the inner wall; (ii) a bushing that holds the metal bolt between the outer wall and the inner wall; (iii) an outer grommets surrounding a first portion of the bushing to receive the outer liner; and (iv) an inner grommets surrounding a second portion of the bushing to receive the dome.

[0080] According to any of the preceding clauses, the turbine engine wherein the inner channel of the support structure has an outer wall and an inner wall, and at least one fastener in the second fastener array comprises: (i) a metal bolt penetrating the outer wall, the dome, the liner, and the inner wall; (ii) a bushing that holds the metal bolt between the outer wall and the inner wall; (iii) an outer cable ring surrounding a first portion of the bushing to receive the dome; and an inner cable ring surrounding a second portion of the bushing to receive the liner.

[0081] While the foregoing description is directed to preferred embodiments, it should be noted that other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of this disclosure. Furthermore, features described in connection with one embodiment may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A combustor for a turbine engine, characterized in that, The burner includes: A support structure made of metal and comprising an outer channel, an inner channel, and a structural mounting member extending from the front end of the outer channel to the front end of the inner channel; A dome, the dome being made of ceramic matrix composite (CMC) material and fixed within the support structure; An outer liner, the outer liner being made of the CMC material, the outer liner being fixed to the dome within the support structure; and The liner, made of the CMC material, is fixed to the dome within the support structure.

2. The burner according to claim 1, characterized in that, in, The outer liner and the inner liner have a cylindrical shape surrounding the centerline axis of the turbine engine, with the radius of the outer liner being larger than the radius of the inner liner.

3. The burner according to claim 2, characterized in that, in, The outer channel and the inner channel each have an annular shape around the central axis, and the radius of the outer channel is larger than the radius of the inner channel. The outer liner and the first section of the dome are fixed within the outer channel by a first array of fasteners, and The inner lining and the second section of the dome are fixed within the inner channel by a second fastener array.

4. The burner according to claim 3, characterized in that, It further includes an abrasion-resistant coating applied to at least one outer surface of one or more fasteners.

5. The burner according to claim 3, characterized in that, in, The outer channel of the support structure includes an outer wall and an inner wall, and at least one fastener in the first fastener array includes (a) a metal bolt penetrating the outer wall, the outer liner, the dome and the inner wall, and (b) a bushing that fits the metal bolt between the outer wall and the inner wall.

6. The burner according to claim 5, characterized in that, in, The at least one fastener in the first fastener array further includes (c) at least one loop surrounding at least a first portion of the bushing, the loop being made of a chromium-nickel alloy, and the bushing being made of a cobalt-molybdenum-chromium alloy.

7. The burner according to claim 5, characterized in that, in, The at least one fastener in the first fastener array further includes (c) an outer cable loop surrounding a first portion of the bushing to receive the outer liner, and (d) an inner cable loop surrounding a second portion of the bushing to receive the dome.

8. The burner according to claim 7, characterized in that, in, The at least one fastener in the first fastener array further includes (e) a spacer surrounding a third portion of the bushing between the inner and outer cable rings.

9. The burner according to claim 7, characterized in that, The device further includes a spacer fixed within the outer channel by the first fastener array. The spacer has a cylindrical shape around the central axis and is positioned between the outer liner and the dome, wherein the radius of the spacer is smaller than the radius of the outer liner.

10. The burner according to claim 5, characterized in that, in, The at least one fastener in the first fastener array further includes (c) a grommets surrounding the bushing, the grommets including a first channel for receiving the outer liner and a second channel for receiving the dome.

11. The burner according to claim 3, characterized in that, in, The inner channel of the support structure includes an outer wall and an inner wall, and at least one fastener in the second fastener array includes (a) a metal bolt penetrating the outer wall, the dome, the liner and the inner wall, and (b) a bushing that fits the metal bolt between the outer wall and the inner wall.

12. The burner according to claim 11, characterized in that, in, The at least one fastener in the second fastener array further includes (c) at least one loop surrounding at least a first portion of the bushing, the loop being made of a chromium-nickel alloy, and the bushing being made of a cobalt-molybdenum-chromium alloy.

13. The burner according to claim 11, characterized in that, in, The at least one fastener in the second fastener array further includes (c) an outer loop surrounding a first portion of the bushing to receive the dome, and (d) an inner loop surrounding a second portion of the bushing to receive the inner liner.

14. The burner according to claim 13, characterized in that, in, The at least one fastener in the second fastener array further includes (e) a spacer surrounding a third portion of the bushing between the inner and outer cable rings.

15. The burner according to claim 13, characterized in that, The device further includes a spacer secured within the inner channel by the second fastener array. The spacer has a cylindrical shape around the central axis and is positioned between the dome and the liner, wherein the radius of the spacer is greater than the radius of the liner.

16. The burner according to claim 11, characterized in that, in, The at least one fastener in the second fastener array further includes (c) a grommets surrounding the bushing, the grommets including a first channel for receiving the dome and a second channel for receiving the liner.

17. A turbine engine, characterized in that, include: (A) A fan assembly that provides air intake to the compressor section; (B) Turbine section, which drives the compressor section; as well as (C) A burner arranged to receive compressed air from the compressor section and supply hot gas to the turbine section, the burner comprising: A support structure, the support structure being made of metal and including an outer channel, an inner channel, and a structural mounting member extending from the front end of the outer channel to the front end of the inner channel; A dome, the dome being made of ceramic matrix composite (CMC) material and fixed within the support structure of the burner; An outer liner, the outer liner being made of the CMC material, the outer liner being fixed to the dome within the support structure; and The liner, made of the CMC material, is fixed to the dome within the support structure.

18. The turbine engine according to claim 17, characterized in that, in, The outer liner and the inner liner have cylindrical shapes around the centerline axis of the turbine engine, and the outer channel and the inner channel each have an annular shape around the centerline axis. Wherein, the radius of the outer liner is larger than the radius of the inner liner. Wherein, the radius of the outer channel is larger than the radius of the inner channel. The outer liner and the first section of the dome are fixed within the outer channel by a first array of fasteners, and The inner liner and the second section of the dome are fixed within the inner channel by a second fastener array.

19. The turbine engine according to claim 18, characterized in that, in, The outer channel of the support structure includes an outer wall and an inner wall, and at least one fastener in the first fastener array includes: (i) A metal bolt that penetrates the outer wall, the outer liner, the dome, and the inner wall; (ii) A bushing that holds the metal bolt between the outer wall and the inner wall; (iii) an outer cable loop that surrounds a first portion of the bushing to receive the outer bushing; and (iv) Inner loop, which surrounds the second portion of the bushing to receive the dome.

20. The turbine engine according to claim 18, characterized in that, in, The inner channel of the support structure includes an outer wall and an inner wall, and at least one fastener in the second fastener array includes: (i) A metal bolt that penetrates the outer wall, the dome, the liner, and the inner wall; (ii) A bushing that holds the metal bolt between the outer wall and the inner wall; (iii) an outer cable loop that surrounds a first portion of the bushing to receive the dome; and (iv) Inner loop, which surrounds a second portion of the bushing to receive the inner liner.

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