A combustion chamber with a ceramic matrix composite flame tube

Abstract

The application discloses a combustion chamber with a ceramic matrix composite flame tube, which comprises a casing outer ring and a casing inner ring, the head of the casing outer ring is fixed with a radial diffuser with an air inlet, the casing inner ring first end is connected with the radial diffuser in the axial direction, the annular mounting cavity is formed between the casing outer ring inner wall, the radial diffuser in the axial direction and the casing outer ring outer wall, the flame tube is connected in the annular mounting cavity, the flame tube comprises an annular first flame tube body and a second flame tube body, the first flame tube body and the second flame tube body are arranged in the axial direction and are both made of ceramic matrix composite material, the first flame tube body is provided with a main combustion hole and a mixing hole, and the flame tube is floatingly connected with the casing outer ring and the casing inner ring; the flame tube made of ceramic matrix composite material is floatingly connected with the casing inner ring and the casing outer ring, the flame tube has a free space for thermal expansion, and the problem of thermal expansion mismatch between the composite material and the metal material is solved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to a combustion chamber with a ceramic matrix composite flame tube. Background Technology

[0002] High-performance aircraft place ever-increasing demands on engine performance, making increasing combustor exit temperature and reducing structural weight the primary ways to improve engine thrust-to-weight ratio. The combustor is the core component of the engine that converts chemical energy into heat energy, heating the high-pressure air from the compressor to the allowable temperature before it enters the turbine for expansion and work. To increase the combustor exit temperature, the proportion of combustion air needs to be significantly increased, while the proportion of cooling air needs to be reduced. Simultaneously, under conditions of reduced cooling air volume and decreased cooling air quality, the durability of the combustor tube must be further maintained or even improved. To meet these requirements, the use of new high-temperature resistant, low-density, and high-strength structural materials has become an inevitable trend. This is both a necessity for continuously improving engine performance and a key to increasing the thrust-to-weight ratio of aero-engines.

[0003] Ceramic matrix composites (CMC-SiC) possess characteristics such as high specific strength, high specific modulus, high temperature resistance, ablation resistance, oxidation resistance, and low density, making them the most promising material to replace high-temperature alloys in high-temperature engine components. However, the difference in the coefficients of linear expansion between the composite material and the connected high-temperature alloy connectors is significant. At high temperatures, the coefficient of thermal expansion of ceramic matrix composites is only about one-third that of metallic materials. During engine operation, temperature changes at the interface between the two materials generate substantial residual thermal stress, severely impacting the load-bearing capacity of the composite material. The flame tube is the hottest component in the engine, where the impact of residual thermal stress caused by the difference in coefficients of linear expansion is even more pronounced. Structural mismatch in cold and hot states can easily lead to component failure. The problem of thermal expansion mismatch between ceramic matrix composite components and metallic components is the issue that this application aims to address. Summary of the Invention

[0004] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0005] In view of the problems existing in the above and / or existing engine combustion chambers, the present invention is proposed.

[0006] Therefore, the purpose of this invention is to provide a combustion chamber with a ceramic matrix composite flame tube. In this invention, the flame tube made of ceramic matrix composite material is floatingly connected to the inner ring and outer ring of the casing. The flame tube has free space for thermal expansion, which solves the problem of thermal expansion mismatch between composite materials and metal materials.

[0007] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a ceramic-based composite material

[0008] The combustion chamber of the combustion tube includes an outer casing ring and an inner casing ring disposed within the outer casing ring. The head of the outer casing ring has an air inlet. A radial diffuser is fixedly connected to the inner casing ring near the air inlet. The head end of the inner casing ring is connected to the inner side of the radial diffuser in the axial direction. An annular mounting cavity is formed between the inner wall of the outer casing ring, the inner side of the radial diffuser in the axial direction, and the outer wall of the outer casing ring. A combustion tube is connected within the annular mounting cavity. The combustion tube includes an annular first combustion tube body and a second combustion tube body. The flame tube body and the second flame tube body are spaced apart in the axial direction and are both made of ceramic matrix composite material. The first flame tube body is close to the radial diffuser and the second flame tube body is far away from the radial diffuser. The first flame tube body has a main combustion hole and a mixing hole. The main combustion hole is located close to the outer ring of the casing and the mixing hole is located close to the inner ring of the casing. The first flame tube body and the second flame tube body are both floatingly connected to the outer ring of the casing and the inner ring of the casing. An airflow channel is formed between the first flame tube body, the second flame tube body and the outer side of the inner ring of the casing.

[0009] As a preferred embodiment of the combustion chamber of the ceramic matrix composite flame tube in this invention, wherein: a high-pressure turbine hollow guide is fixedly connected to the ends of the outer ring and the inner ring of the casing, and the high-pressure turbine hollow guide has an air outlet communicating with the air passage.

[0010] As a preferred embodiment of the combustion chamber with ceramic matrix composite flame tube in this invention, the ends of the first flame tube body and the ends of the second flame tube body are detachably connected to the high-pressure turbine hollow guide.

[0011] As a preferred embodiment of the combustion chamber of the ceramic matrix composite flame tube in this invention, wherein: the high-pressure turbine hollow guide is fixed with an outer connecting ring and an inner connecting ring inside the outer connecting ring on one side relative to the flame tube; the end of the first flame tube body and the inner end of the outer connecting ring are detachably connected together in the axial direction; and the end of the second flame tube body and the inner end of the inner connecting ring are detachably connected together in the axial direction.

[0012] As a preferred embodiment of the combustion chamber of the ceramic matrix composite flame tube in this invention, the following features are provided: a plurality of first positioning bosses are arranged on the inner side of the first positioning ring; a plurality of first grooves corresponding one-to-one with the first positioning bosses are arranged on the outer periphery of the inner ring of the casing; a plurality of first through slots that allow the first positioning bosses to pass through are arranged on the outer periphery of the inner ring of the casing at the end of the first groove; the first positioning bosses are engaged in the first grooves after passing through the first through slots; the outer connecting ring has an annular groove at its inner end in the axial direction; the outer connecting ring is sleeved on the end of the first flame tube body through the annular groove; a first limiting boss is fixed on the outer periphery of the end of the first flame tube body; a first slot corresponding to the first limiting boss is also provided on the outer connecting ring; the outer connecting ring is engaged on the first limiting boss through the first slot; after rotating the first flame tube body to misalign the first positioning bosses and the first through slots, the high-pressure turbine guide is fixedly connected to the end of the outer ring and the inner ring of the casing.

[0013] In a preferred embodiment of the combustion chamber of the ceramic matrix composite flame tube in this invention, the head end of the second flame tube body is fixedly connected to a second positioning ring made of ceramic matrix composite material. A plurality of second positioning bosses are arranged on the inner side of the second positioning ring. A plurality of second grooves corresponding one-to-one with the second positioning bosses are also arranged on the outer periphery of the inner ring of the casing. A plurality of second through slots are arranged on the outer periphery of the inner ring of the casing at both ends of the second groove in the axial direction, allowing the second positioning bosses to pass through. After passing through the second through slots, the second positioning bosses engage in the second grooves. The end of the second flame tube body is fixed... A damping ring is fixedly connected to the high-pressure turbine guide. The end of the damping ring relative to the high-pressure turbine guide has a snap-fit ​​groove. A support ring is fixed on the damping ring inside the snap-fit ​​groove. An annular insertion groove is opened on the end of the inner connecting ring relative to the damping ring. The inner connecting ring is supported on the support ring through the insertion groove. A second slot is opened on the inner connecting ring outside the insertion groove. A second limiting boss is fixed on the outside of the support ring. The inner connecting ring is snapped onto the second limiting boss through the second slot. After rotating the second flame tube body to misalign the second positioning boss and the second through groove, the high-pressure turbine guide is fixedly connected to the end of the outer ring and the inner ring of the casing.

[0014] As a preferred embodiment of the combustion chamber of the flame tube with ceramic matrix composite material in this invention, wherein: the first positioning ring is made of ceramic matrix composite material, the two ends of the first positioning boss in the axial direction and the two ends of the first groove in the axial direction have a first gap, the end of the second flame tube body and the ring groove have a second gap, and the first limiting boss and the first slot have a third gap.

[0015] As a preferred embodiment of the combustion chamber of the flame tube with ceramic matrix composite material in this invention, the second positioning ring is made of ceramic matrix composite material, there is a fourth gap between the outer edge of the second positioning boss and the second groove, there is a fifth gap between the support ring and the insertion groove, and there is a sixth gap between the second limiting boss and the second slot.

[0016] As a preferred embodiment of the combustion chamber of the ceramic matrix composite flame tube in this invention, wherein: the radial diffuser is fixedly connected to an annular axial diffuser and an intermediate connecting ring disposed within the axial diffuser at its axial end, the head end of the axial diffuser and the head end of the intermediate connecting ring are both fixedly connected to the inner side of the radial diffuser in the axial direction, and the end of the intermediate connecting ring is fixedly connected to the head end of the inner ring of the casing.

[0017] Compared with the prior art, the present invention has the following technical effects:

[0018] 1. The first flame tube body and the second flame tube body adopt an indirect positioning structure with floating connection. The groove and the positioning boss are used for concave-convex cooperation, and the slot and the limiting boss are engaged with each other, so that the flame tube has a certain amount of free space in the axial, radial and circumferential directions, preventing the flame tube from being damaged due to rigid connection with metal material components.

[0019] 2. The linear expansion coefficients of ceramic matrix composites and high-temperature alloy components differ greatly. Due to temperature changes, large thermal stress will be generated at the interface between the two materials. This application adopts a reserved gap method to solve the problem of thermal expansion mismatch between ceramic matrix composites and metal materials.

[0020] 3. The weight of the flame tube structure involved in this application is significantly less than that of the flame tube made of metal materials in the prior art, which has a significant effect on reducing the weight of the engine combustion chamber, and is conducive to improving engine performance and increasing the engine thrust-to-weight ratio. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein:

[0022] Figure 1 This is a diagram of the internal structure of the present invention.

[0023] Figure 2 This is a side view of the first positioning ring and the inner ring of the casing when they are in a concave-convex fit.

[0024] Figure 3A partial structural diagram showing the first positioning ring and the first flame tube body connected together and mounted on the inner ring of the casing.

[0025] Figure 4 This is a partial structural diagram of the first limiting boss within the first slot of the outer connecting ring.

[0026] Figure 5 A partial structural diagram showing the second positioning ring and the second flame tube body connected together and mounted on the inner ring of the casing.

[0027] Figure 6 This is a structural diagram of the damping ring.

[0028] Figure 7 This is a partial structural diagram of the second limiting boss within the second slot of the inner connecting ring.

[0029] Figure 8 This is a side view of the second positioning ring and the inner ring of the casing when they are in a concave-convex fit.

[0030] In the diagram: 100 Flame tube, 101 Second flame tube body, 102 Second positioning ring, 102a Second positioning boss, 103 First positioning ring, 103a First positioning boss, 104 First flame tube body, 104a Mixing hole, 104b Main combustion hole, 104c First limiting boss, 105 Damping ring, 105a Snap-fit ​​groove, 105b Support ring, 105c Second limiting boss, 200 Intermediate connecting ring, 300 Axial diffuser, 400 Outer ring of casing, 401 Inlet Air inlet, 500 high-pressure turbine guide, 501 outer connecting ring, 501a ring groove, 501b first slot, 502 inner connecting ring, 502a insertion groove, 502b second slot, 503 air outlet, 600 casing inner ring, 601 first through groove, 602 first recess, 603 second recess, 604 second through groove, 700 fixing bolt, 800 radial diffuser, M first clearance, N second clearance, J third clearance, X fourth clearance, P fifth clearance, S sixth clearance. Detailed Implementation

[0031] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0032] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0033] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0034] Example 1

[0035] Reference Figure 1 This is the first embodiment of the present invention, which provides a combustion chamber with a ceramic matrix composite flame tube, which can extend the service life of the combustion chamber.

[0036] A combustion chamber of a ceramic matrix composite flame tube 100 includes an outer casing ring 400 and an inner casing ring 600 disposed within the outer casing ring 400. The head of the outer casing ring 400 has an air inlet 401. A radial diffuser 800 is fixedly connected inside the outer casing ring 400 near the air inlet 401. The head end of the inner casing ring 600 is connected to the inner side of the radial diffuser 800 in the axial direction. An annular axial diffuser 3 is fixedly connected to the end of the radial diffuser 800 in the axial direction. The axial diffuser 300 and the intermediate connecting ring 200 disposed within the axial diffuser 300 are, in practice, welded to the radial diffuser 800. The head end of the axial diffuser 300 and the head end of the intermediate connecting ring 200 are both fixedly connected to the inner side of the radial diffuser 800 in the axial direction. The end of the intermediate connecting ring 200 is fixedly connected to the head end of the inner ring 600 of the casing using fixing bolts 700. The inner wall of the outer ring 400 of the casing, the inner side of the radial diffuser 800 in the axial direction, and... An annular mounting cavity is formed between the outer walls of the outer ring 400 of the casing. A flame tube 100 is connected within the annular mounting cavity. The flame tube 100 includes an annular first flame tube body 104 and a second flame tube body 101. The first flame tube body 104 and the second flame tube body 101 are spaced apart in the axial direction and are both made of ceramic matrix composite material. The first flame tube body 104 is close to the radial diffuser 800, and the second flame tube body 101 is away from the radial diffuser 800. The first flame tube body 104 and the second flame tube body 101 are provided with a main combustion port 104b and a mixing port 104a. The main combustion port 104b is located near the outer ring 400 of the casing, and the mixing port 104a is located near the inner ring 600 of the casing. The second flame tube body 101 is provided with a number of mixing ports 104a. The first flame tube body 104 and the second flame tube body 101 are both floatingly connected to the outer ring 400 and the inner ring 600 of the casing. An air passage is formed between the first flame tube body 104, the second flame tube body 101 and the outer side of the inner ring 600 of the casing.

[0037] The combustion chamber is a core component of the engine. It heats the high-pressure air, boosted by the compressor, to the allowable temperature before the turbine, allowing it to expand and perform work inside the turbine. Figure 1As can be seen from the above, the combustion chamber in this application is a baffled annular combustion chamber, that is, the combustion chamber has multiple tortuous air passages. The high-pressure air entering the combustion chamber is decelerated and diffused by the radial diffuser 800 and the axial diffuser 300. The air then enters the air passage through the main combustion hole 104b and the mixing hole 104a, mixes with fuel and burns, and then flows out.

[0038] The flame tube 100 and the components made of metal materials, such as the outer ring 400 of the casing, the inner ring 600 of the casing, and the radial diffuser 800, are connected by a floating connection. A certain expansion gap is reserved between the flame tube 100 and the metal material components, so that the flame tube 100 has a certain free space in all directions. This achieves cold and hot dimensional coordination between the flame tube 100 made of ceramic matrix composite material and the corresponding metal material components, and prevents the flame tube 100 from being damaged.

[0039] Example 2

[0040] Reference Figures 1 to 8 This embodiment provides a combustion chamber for a flame tube 100 with ceramic matrix composite material. The difference between this embodiment and Embodiment 1 is that it can improve the cooling efficiency of the cooling air of the flame tube 100 and reduce the overall temperature of the wall of the flame tube 100, thereby extending the service life of the flame tube 100.

[0041] Specifically, a high-pressure turbine hollow guide is fixedly connected to the ends of the outer ring 400 and the inner ring 600 of the casing. The high-pressure turbine hollow guide has an outlet 503 that communicates with the air passage. An outer connecting ring 501 and an inner connecting ring 502 are fixed to the side of the high-pressure turbine hollow guide opposite to the flame tube 100. The end of the first flame tube body 104 and the inner end of the outer connecting ring 501 are detachably connected together in the axial direction. The end of the second flame tube body 101 and the inner end of the inner connecting ring 502 are detachably connected together in the axial direction.

[0042] Specifically, a first positioning ring 103 made of ceramic matrix composite material is fixedly connected to the head end of the first flame tube body 104. Several first positioning bosses 103a are arranged on the inner side of the first positioning ring 103. Several first grooves 602 corresponding to the first positioning bosses 103a are arranged on the outer periphery of the inner ring 600 of the casing. Several first through slots 601 that allow the first positioning bosses 103a to pass through are arranged on the outer periphery of the inner ring 600 at both ends of the first grooves 602 in the axial direction. Several first through slots 601 corresponding to the first positioning bosses 103a are also opened on the limiting step at the head of the inner ring 600 of the casing. After the first positioning bosses 103a pass through the first through slots 601, they engage in the first grooves 602. An annular groove 501a is opened at the inner end of the outer connecting ring 501 in the axial direction. The outer connecting ring 501 is sleeved on the outer ring 501 through the annular groove 501a. At the end of the first flame tube body 104, a first limiting boss 104c is fixed on the outer periphery of the end of the first flame tube body 104. The outer connecting ring 501 also has a first slot 501b corresponding to the first limiting boss 104c. The outer connecting ring 501 is engaged with the first limiting boss 104c through the first slot 501b. After rotating the first flame tube body 104 to misalign the first positioning boss 103a and the first through groove 601, the high-pressure turbine guide 500 is fixedly connected to the end of the outer ring 400 and the inner ring 600 of the casing. There is a first gap M between the two ends of the first positioning boss 103a in the axial direction and the two ends of the first groove 602 in the axial direction. There is a second gap N between the end of the second flame tube body 101 and the ring groove 501a. There is a third gap J between the first limiting boss 104c and the first slot 501b.

[0043] Specifically, a second positioning ring 102 made of ceramic matrix composite material is fixedly connected to the head end of the second flame tube body 101. Several second positioning bosses 102a are arranged inside the second positioning ring 102. Several second grooves 603 corresponding to the second positioning bosses 102a are arranged on the outer periphery of the inner ring 600 of the casing. Several second through slots 604 that allow the second positioning bosses 102a to pass through are arranged on the outer periphery of the inner ring 600 at both ends of the second grooves 603 in the axial direction. After passing through the second through slots 604, the second positioning bosses 102a are engaged in the second grooves 603. A damping ring 105 is fixedly connected to the end of the second flame tube body 101. A snap-fit ​​groove 105a is opened at one end of the damping ring 105 relative to the high-pressure turbine guide 500. A support ring 105b is fixed on the damping ring 105 inside the snap-fit ​​groove 105a. One end of the connecting ring 502 relative to the damping ring 105 has an annular insertion groove 502a. The inner connecting ring 502 is supported on the support ring 105b via the insertion groove 502a. A second slot 502b is opened on the inner connecting ring 502 outside the insertion groove 502a. A second limiting boss is fixed on the outer side of the support ring 105b. The inner connecting ring 502 is engaged with the second limiting boss via the second slot 502b. After rotating the second flame tube body 101 to misalign the second positioning boss 102a and the second through groove 604, the high-pressure turbine guide 500 is fixedly connected to the outer ring 400 of the casing and the end of the inner ring 600 of the casing. There is a fourth gap X between the outer edges of the second positioning boss 102a and the second groove 603, a fifth gap P between the support ring 105b and the insertion groove 502a, and a sixth gap S between the second limiting boss and the second slot 502b.

[0044] The high-pressure air entering the combustion chamber is decelerated and diffused by the radial diffuser 800 and the axial diffuser 300, and then the air is divided into two paths (such as...). Figure 1 As shown, one stream enters the air passage after passing through the main combustion hole 104b and mixing hole 104a on the first flame tube body 104, while the other stream enters the air passage through the hollow groove of the high-pressure turbine guide 500 and the flow hole on the second flame tube body 101. The jet forms a backflow zone, mixes and burns with the fuel, and then flows out through the outlet 503 on the high-pressure turbine guide 500.

[0045] The first flame tube body 104 has gaps in both the axial and circumferential directions at the connection between the first positioning ring 103 and the inner ring 600 of the casing. The second flame tube body 101 also has gaps in both the axial and circumferential directions at the connection between the second positioning ring 102 and the inner ring 600 of the casing. This allows the flame tube 100 to have a certain amount of free space in both the axial and circumferential directions, achieving dimensional coordination between the ceramic matrix composite flame tube 100 wall and the metal casing in both hot and cold states, preventing damage to the flame tube 100. When the engine is running, the corresponding wall surface gaps of the front and rear walls of the flame tube 100 decrease in both the axial and circumferential directions, which can reduce the leakage of airflow in each flow channel.

[0046] The ends of the first flame tube body 104 and the second flame tube body 101 overlap with the outer connecting ring 501 and the inner connecting ring 502, respectively. The connection sections of the first flame tube body 104 and the second flame tube body 101 with the outer connecting ring 501 and the inner connecting ring 502 are all left with annular gaps. The gaps of the reserved annular grooves 501a can meet the space requirements of the ceramic matrix composite flame tube 100 for radial thermal expansion. At the same time, the annular grooves 501a can also play a role in providing auxiliary support for the wall of the flame tube 100, which is very beneficial to the long-term reliable and stable operation of the flame tube 100.

[0047] Example 3

[0048] The difference between this embodiment and embodiment 2 is that this embodiment improves a method for installing the flame tube 100, which can realize the installation of the flame tube 100 and various metal material components, and is easy to assemble and disassemble.

[0049] A method for installing a flame tube 100 includes the following steps:

[0050] S1: The first flame tube body 104 is fitted onto the first positioning ring 103 so that it abuts against the first step of the first positioning ring 103, and the first flame tube body 104 and the first positioning ring 103 are fixedly connected together using rivets made of composite materials.

[0051] S2: The second flame body is fitted onto the end of the second positioning ring 102 away from the first positioning ring 103 and abuts against the second step of the second positioning ring 102. The second flame tube body 101 and the second positioning ring 102 are fixedly connected together using rivets made of composite materials. The damping ring 105 is fixedly connected to the end of the second positioning ring 102 using rivets made of composite materials.

[0052] S3: The first positioning ring 103 slides along the outer side of the inner ring 600 of the casing. The first positioning boss 103a passes through two second through slots 604 and one first through slot 601 in sequence and then gets stuck in the first groove 602. The first flame tube body 104 is rotated to make the first positioning boss 103a and the first through slot 601 misaligned, thus restricting the axial displacement of the first flame tube body 104.

[0053] S4: The second positioning ring 102 slides along the outer side of the inner ring 600 of the casing, and the second positioning boss 102a is inserted into the second groove 603 through the second through groove 604. The second flame tube body 101 is rotated to make the second positioning boss 102a and the second through groove 604 misaligned, thereby restricting the axial displacement of the second flame tube body 101.

[0054] S5: Align the first slot 501b on the outer connecting ring 501 and the second slot 502b on the inner connecting ring 502 with the first limiting boss 104c and the second limiting boss respectively. The outer connecting ring 501 is engaged with the first limiting boss 104c via the first slot 501b, and the inner connecting ring 502 is engaged with the second limiting boss via the second slot 502b, thereby restricting the circumferential displacement of the first flame tube body 104 and the second flame tube body 101.

[0055] S6: Use several fixing bolts 700 to fix the high-pressure turbine guide 500 to the outer ring 400 and the inner ring 600 of the casing.

[0056] With reference to the direction of the air inlet 401, the direction of the gas from the air inlet 401 to the air outlet 503 is from the beginning to the end. The beginning and end mentioned in this application are both based on the above direction.

[0057] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A combustion chamber with a ceramic matrix composite flame tube, characterized in that: The device includes an outer casing ring (400) and an inner casing ring (600) disposed within the outer casing ring (400). The head of the outer casing ring (400) has an air inlet (401). A radial diffuser (800) is fixedly connected to the inner side of the outer casing ring near the air inlet (401). The head end of the inner casing ring (600) is connected to the inner side of the radial diffuser (800) in the axial direction. An annular mounting cavity is formed between the inner wall of the outer casing ring (400), the inner side of the radial diffuser (800) in the axial direction, and the outer wall of the outer casing ring (400). A flame tube (100) is connected within the annular mounting cavity. The flame tube (100) includes an annular first flame tube body (104) and a second flame tube body (101). The first flame tube body (104) and the second flame tube body (101) are spaced apart in the axial direction and are both made of ceramic matrix composite material. The first flame tube body (104) is close to the radial diffuser (800), and the second flame tube body (101) is far from the radial diffuser (800). The first flame tube body (104) has a main combustion port (104b) and a mixing port (104a). The main combustion port (104b) is located close to the outer ring (400) of the casing, and the mixing port (104a) is located close to the inner ring (600) of the casing. The first flame tube body (104) and the second flame tube body (101) are both floatingly connected to the outer ring (400) and the inner ring (600) of the casing. An air passage is formed between the flame tube body (101) and the outer side of the inner ring (600) of the casing; a high-pressure turbine hollow guide is fixedly connected to the ends of the outer ring (400) and the inner ring (600) of the casing, and an air outlet (503) communicating with the air passage is opened on the high-pressure turbine hollow guide. An outer connecting ring (501) is fixed to one side of the high-pressure turbine hollow guide opposite to the flame tube (100). A first positioning ring (103) made of ceramic matrix composite material is fixedly connected to the head end of the first flame tube body (104). A plurality of first positioning bosses (103a) are arranged on the inner side of the first positioning ring (103), and a plurality of first positioning bosses (103a) are arranged on the outer periphery of the inner ring (600) to correspond one-to-one with the first positioning bosses (103a). The first groove (602) has a first through groove (601) arranged around the outer periphery of the inner ring (600) of the casing at the end of the first groove (602), allowing the first positioning boss (103a) to pass through. After passing through the first through groove (601), the first positioning boss (103a) is engaged in the first groove (602). The outer connecting ring (501) has an annular groove (501a) at its inner end in the axial direction. The outer connecting ring (501) is sleeved on the end of the first flame tube body (104) through the annular groove (501a). A first limiting boss (104c) is fixed on the outer periphery of the end of the first flame tube body (104). The outer connecting ring (501) also has a first slot corresponding to the first limiting boss (104c).The outer connecting ring (501) is engaged with the first limiting boss (104c) via the first slot. After rotating the first flame tube body (104) to misalign the first positioning boss (103a) and the first through groove (601), the high-pressure turbine guide (500) is fixedly connected to the ends of the outer ring (400) and the inner ring (600) of the casing. The head end of the second flame tube body (101) is fixedly connected to a second positioning ring (102) made of ceramic matrix composite material. Several second positioning bosses (103a) are arranged on the inner side of the second positioning ring (102). 02a) The outer periphery of the inner ring (600) of the casing is also provided with a plurality of second grooves (603) corresponding one-to-one with the second positioning boss (102a). The outer periphery of the inner ring (600) of the casing at both ends of the second groove (603) in the axial direction is provided with a plurality of second through slots (604) that allow the second positioning boss (102a) to pass through. After the second positioning boss (102a) passes through the second through slot (604), it is engaged in the second groove (603). The end of the second flame tube body (101) is fixedly connected with a damping ring (105). The damping ring (105) has a snap-fit ​​groove (105a) at one end relative to the high-pressure turbine guide (500). A support ring (105b) is fixed on the damping ring (105) inside the snap-fit ​​groove (105a). An inner connecting ring (502) is fixed on one side of the high-pressure turbine hollow guide relative to the flame tube (100) within the outer connecting ring (501). An annular insertion groove (502a) is opened at one end of the inner connecting ring (502) relative to the damping ring (105). The inner connecting ring (502) is supported by the insertion groove (502a). The inner connecting ring (502), which rests on the support ring (105b) and is inserted into the outer side of the recess (502a), has a second slot (501b). A second limiting boss is fixed to the outer side of the support ring (105b), and the inner connecting ring (502) is engaged with the second limiting boss via the second slot (501b). After rotating the second flame tube body (101) to misalign the second positioning boss (102a) and the second groove (603), the high-pressure turbine guide (500) is fixedly connected to the ends of the outer ring (400) and the inner ring (600) of the casing.

2. The combustion chamber of the ceramic matrix composite flame tube as described in claim 1, characterized in that: The ends of the first flame tube body (104) and the second flame tube body (101) are detachably connected to the high-pressure turbine hollow guide.

3. The combustion chamber of the ceramic matrix composite flame tube as described in claim 1, characterized in that: The end of the first flame tube body (104) and the inner end of the outer connecting ring (501) are detachably connected together in the axial direction, and the end of the second flame tube body (101) and the inner end of the inner connecting ring (502) are detachably connected together in the axial direction.

4. The combustion chamber of the ceramic matrix composite flame tube as described in claim 1, characterized in that: The first positioning ring (103) is made of ceramic matrix composite material. The first positioning boss (103a) and the first groove (602) have a first gap (M) between their two ends in the axial direction. The second flame tube body (101) and the ring groove (501a) have a second gap (N). The first limiting boss (104c) and the first slot have a third gap (J).

5. The combustion chamber of the ceramic matrix composite flame tube as described in claim 1, characterized in that: The second positioning ring (102) is made of ceramic matrix composite material. There is a fourth gap (X) between the outer edges of the second positioning boss (102a) and the second groove (603), a fifth gap (P) between the support ring (105b) and the insertion groove (502a), and a sixth gap (S) between the second limiting boss and the second slot (501b).

6. The combustion chamber of the ceramic matrix composite flame tube as described in any one of claims 1 to 5, characterized in that: The radial diffuser (800) has an annular axial diffuser (300) and an intermediate connecting ring (200) disposed inside the axial diffuser (300) fixedly connected to its axial end. The head end of the axial diffuser (300) and the head end of the intermediate connecting ring (200) are both fixedly connected to the inner side of the radial diffuser (800) in the axial direction. The end of the intermediate connecting ring (200) is fixedly connected to the head end of the inner ring (600) of the casing.

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