Combustion chamber with ceramic matrix composite flame tube

Abstract

The combustion chamber comprises a casing outer ring and a casing inner ring, a radial diffuser with an air inlet is fixed to the head of the casing outer ring, and the head end of the casing inner ring is connected with the inner side of the radial diffuser in the axial direction. An annular mounting cavity is formed among the inner wall of the casing outer ring, the inner side of the radial diffuser in the axial direction and the outer wall of the casing outer ring, and a flame tube is connected into the annular mounting cavity and comprises a first annular flame tube body and a second annular flame tube body. The first flame tube body and the second flame tube body are arranged at an interval in the axial direction and are both made of a ceramic matrix composite material, a main combustion hole and a mixing hole are formed in the first flame tube body, and the flame tube is in floating connection with the casing outer ring and the casing inner ring; the flame tube made of the ceramic matrix composite material is in floating connection with the casing inner ring and the casing outer ring, the flame tube has a free space for thermal expansion, and the problem that thermal expansion of the composite material and thermal expansion of a metal material are not matched is solved.

Description

Technical Field

[0001] The invention relates to the technical field of aviation engines, in particular to a combustion chamber with a ceramic-based composite flame tube. Background Art

[0002] The demand for engine performance in high-performance aircraft is constantly increasing. Increasing the combustion chamber outlet temperature and reducing the structural weight are the main ways to improve the engine thrust-to-weight ratio. The combustion chamber is the core component of the engine that converts chemical energy into thermal energy. It heats the high-pressure air after the compressor is pressurized to the allowable temperature before the turbine so that it can enter the turbine to expand and do work. In order to increase the combustion chamber outlet temperature, the proportion of combustion air needs to be greatly increased and the proportion of cooling air needs to be reduced. At the same time, under the conditions of reduced cooling air distribution and reduced cooling air quality, the combustion chamber is also required to further maintain or even improve the durability of the flame tube. In order to meet the above requirements, the use of new high-temperature resistant, low-density, high-strength and toughness structural materials has become an inevitable trend. This is not only the need for the continuous improvement of engine performance, but also the key to improving the thrust-to-weight ratio of aircraft engines.

[0003] SiC fiber reinforced ceramic matrix composites (CMC-SiC) have the characteristics of high specific strength, high specific modulus, high temperature resistance, ablation resistance, oxidation resistance and low density. Ceramic matrix composites can become the most promising material for replacing high-temperature alloys in high-temperature engine components. However, the linear expansion coefficient between the composite parts and the high-temperature alloy connectors to which they are connected is very different. The thermal expansion coefficient of ceramic matrix composites at high temperatures is only about 1 / 3 of that of metal materials. During the use of the engine, due to temperature changes, large residual thermal stress will be generated at the interface of the two materials, seriously affecting the bearing capacity of the composite material. The flame tube is the component with the highest temperature in the engine, and the influence of residual thermal stress caused by the difference in linear expansion coefficient is more obvious. For example, the mismatch of cold and hot structures can easily lead to component failure. When ceramic matrix composite components are connected to metal material components, the problem of thermal expansion mismatch between the two materials is a problem that needs to be solved in this application. Summary of the invention

[0004] The purpose of this section is to summarize some aspects of embodiments of the present invention and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the specification abstract and the invention title of this application to avoid blurring the purpose of this section, the specification abstract and the invention title, and such simplifications or omissions cannot be used to limit the scope of the present invention.

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

[0006] Therefore, the purpose of the present invention is to provide a combustion chamber with a ceramic-based composite flame tube. In the present invention, the flame tube made of ceramic-based composite materials is floatingly connected to the inner ring and the 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] In order to solve the above technical problems, the present invention provides the following technical solutions: a ceramic-based composite material The combustion chamber of the material flame tube comprises an outer ring of the casing and an inner ring of the casing arranged inside the outer ring of the casing, the head of the outer ring of the casing is provided with an air inlet, a radial diffuser is fixedly connected to the inner side of the outer ring of the casing near the air inlet, the head end of the inner ring of the casing is connected to the inner side of the radial diffuser in the axial direction, an annular installation cavity is formed between the inner wall of the outer ring of the casing, the inner side of the radial diffuser in the axial direction and the outer wall of the outer ring of the casing, a flame tube is connected in the annular installation cavity, the flame tube comprises an annular first flame tube body and a second flame tube body, the first The flame tube body and the second flame tube body are spaced apart in the axial direction and are both made of ceramic-based composite materials. 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 is provided with a main combustion hole and a mixing hole. The main combustion hole is arranged close to the outer ring of the casing, and the mixing hole is arranged 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 and the inner ring of the casing, and a ventilation flow passage is formed between the first flame tube body, the second flame tube body and the outer side of the inner ring of the casing.

[0008] As a preferred solution of the combustion chamber with a ceramic-based composite flame tube in the present invention, the ends of the casing outer ring and the casing inner ring are fixedly connected with a high-pressure turbine hollow guide, and the high-pressure turbine hollow guide is provided with an outlet connected to the air flow channel.

[0009] As a preferred solution of the combustion chamber with a ceramic-based composite flame tube in the present invention, the end of the first flame tube body and the end of the second flame tube body are both detachably connected to the high-pressure turbine hollow guide.

[0010] As a preferred solution of the combustion chamber with a ceramic-based composite flame tube in the present invention, an outer connecting ring and an inner connecting ring inside the outer connecting ring are fixed on the side of the high-pressure turbine hollow guide opposite to the flame tube, the end of the first flame tube body and the inner end of the outer connecting ring in the axial direction are detachably connected together, and the end of the second flame tube body and the inner end of the inner connecting ring in the axial direction are detachably connected together.

[0011] As a preferred solution of the combustion chamber with a ceramic-based composite flame tube in the present invention, wherein: a plurality of first positioning bosses are arranged on the inner side of the first positioning ring, a plurality of first grooves corresponding to the first positioning bosses are arranged on the outer periphery of the casing inner ring, a plurality of first through grooves through which the first positioning bosses can pass are arranged on the outer periphery of the casing inner ring at the end of the first groove, the first positioning boss is engaged in the first groove after passing through the first through groove, an annular groove is provided at the inner end of the outer connecting ring 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 clamping groove corresponding to the first limiting boss is also provided on the outer connecting ring, the outer connecting ring is clamped on the first limiting boss through the first clamping groove, and after the first flame tube body is rotated to misalign the first positioning boss and the first through groove, the high-pressure turbine guide is fixedly connected to the casing outer ring and the end of the casing inner ring.

[0012] As a preferred solution of the combustion chamber with a ceramic-based composite flame tube in the present invention, wherein: the head end of the second flame tube body is fixedly connected to a second locating ring made of a ceramic-based composite material, a plurality of second locating bosses are arranged on the inner side of the second locating ring, a plurality of second grooves corresponding to the second locating bosses are arranged on the outer periphery of the casing inner ring, and a plurality of second through grooves that allow the second locating bosses to pass through are arranged on the outer periphery of the casing inner ring at both ends in the axial direction of the second groove, the second locating bosses are engaged in the second grooves after passing through the second through grooves, and the end of the second flame tube body is fixed A damping ring is fixedly connected, and a snap-in groove is opened at one end of the damping ring relative to the high-pressure turbine guide, a supporting ring is fixed on the damping ring on the inner side of the snap-in groove, and an annular plug-in groove is opened at one end of the inner connecting ring relative to the damping ring, the inner connecting ring is supported on the supporting ring through the plug-in groove, a second snap-in groove is opened on the inner connecting ring outside the plug-in groove, a second limiting boss is fixed on the outer side of the support ring, and the inner connecting ring is snapped on the second limiting boss through the second snap-in groove; after the second flame tube body is rotated to misalign the second positioning boss and the second through groove, the high-pressure turbine guide is fixedly connected to the outer ring of the casing and the end of the inner ring of the casing.

[0013] As a preferred solution for the combustion chamber with a ceramic-based composite flame tube in the present invention, the first positioning ring is made of a ceramic-based composite material, both ends of the first positioning boss in the axial direction and both ends of the first groove in the axial direction have a first gap, a second gap is provided between the end of the second flame tube body and the annular groove, and a third gap is provided between the first limiting boss and the first slot.

[0014] As a preferred solution of the combustion chamber with a ceramic-based composite flame tube in the present invention, the second positioning ring is made of a ceramic-based composite material, there is a fourth gap between the second positioning boss and the outer edge of the second groove, there is a fifth gap between the support ring and the plug-in groove, and there is a sixth gap between the second limiting boss and the second slot.

[0015] As a preferred solution of the combustion chamber with a ceramic-based composite flame tube in the present invention, the end of the radial diffuser in the axial direction is fixedly connected to an annular axial diffuser and an intermediate connecting ring arranged in the axial diffuser, 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.

[0016] Compared with the prior art, the present invention has the following technical effects: 1. The first flame tube body and the second flame tube body adopt an indirect positioning structure of floating connection, and the groove and the positioning boss are used for concave-convex matching. The clamping groove and the limiting boss are engaged with each other, so that the flame tube has a certain free space in the axial, radial and circumferential directions to prevent the rigid connection between it and the metal material component from causing damage to the flame tube; 2. The linear expansion coefficients of ceramic-based composite materials and high-temperature alloy components are very different. Due to temperature changes, large thermal stress will be generated at the interface of the two materials. This application adopts a reserved gap method to solve the problem of thermal expansion mismatch between ceramic-based composite materials and metal materials; 3. The weight of the flame tube structure involved in this application is significantly less than the weight 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, is beneficial to improving engine performance and increasing the engine thrust-to-weight ratio. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative labor. Among them: Figure 1 It is the internal structure diagram of the present invention.

[0018] Figure 2 It is a side view of the first locating ring and the inner ring of the casing when they are matched in a concave and convex manner.

[0019] Figure 3 A partial structural diagram of the first positioning ring and the first flame tube body connected together and installed on the inner ring of the casing.

[0020] Figure 4It is a partial structural diagram of the first limiting boss in the first clamping groove of the outer connecting ring.

[0021] Figure 5 A partial structural diagram of the second positioning ring and the second flame tube body connected together and installed on the inner ring of the casing.

[0022] Figure 6 This is the structural diagram of the damping ring.

[0023] Figure 7 It is a partial structural diagram of the second limiting boss in the second groove of the inner connecting ring.

[0024] Figure 8 It is a side view of the concave-convex fit between the second locating ring and the inner ring of the receiver.

[0025] In the figure: 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 clamping sink groove, 105b support ring, 105c second limiting boss, 200 intermediate connecting ring, 300 axial diffuser, 400 casing outer ring, 401 inlet Air inlet, 500 high-pressure turbine guide vane, 501 external connecting ring, 501a ring groove, 501b first slot, 502 internal connecting ring, 502a plug-in groove, 502b second slot, 503 air outlet, 600 casing inner ring, 601 first through groove, 602 first groove, 603 second groove, 604 second through groove, 700 fixing bolt, 800 radial diffuser, M first gap, N second gap, J third gap, X fourth gap, P fifth gap, S sixth gap. DETAILED DESCRIPTION

[0026] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0027] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0028] 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 term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0029] Example 1 Reference Figure 1 , which is the first embodiment of the present invention, provides a combustion chamber with a ceramic-based composite flame tube, which can extend the service life of the combustion chamber.

[0030] A combustion chamber with a ceramic matrix composite flame tube 100, comprising a casing outer ring 400 and a casing inner ring 600 arranged inside the casing outer ring 400, the head of the casing outer ring 400 having an air inlet 401, a radial diffuser 800 fixedly connected inside the casing outer ring 400 near the air inlet 401, a head end of the casing inner ring 600 and the inner side of the radial diffuser 800 connected in the axial direction, and an annular axial diffuser 3 fixedly connected to the end of the radial diffuser 800 in the axial direction 00 and the intermediate connecting ring 200 disposed in the axial diffuser 300. During implementation, the axial diffuser 300 is 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 casing inner ring 600 using fixing bolts 700. The inner wall of the casing outer ring 400, the inner side of the radial diffuser 800 in the axial direction and An annular installation cavity is formed between the outer walls of the casing outer ring 400, and a flame tube 100 is connected in the annular installation 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-based composite materials. The first flame tube body 104 is close to the radial diffuser 800, and the second flame tube body 101 is far away from the radial diffuser 800. The first flame tube body 104 A main combustion hole 104b and a mixing hole 104a are opened on it. The main combustion hole 104b is arranged near the outer ring 400 of the casing, and the mixing hole 104a is arranged near the inner ring 600 of the casing. A plurality of mixing holes 104a are opened on the second flame tube body 101. 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, and a ventilation flow 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.

[0031] The combustion chamber is the core component of the engine. It heats the high-pressure air after the compressor is boosted to the allowable temperature before the turbine so that it can enter the turbine to expand and do work. Figure 1 It can be seen that the combustion chamber in the present application is a baffled annular combustion chamber, that is, the combustion chamber has a plurality of curved ventilation channels. After the high-pressure air entering the combustion chamber is decelerated and diffused by the radial diffuser 800 and the axial diffuser 300, the air enters the ventilation channel through the main combustion hole 104b and the mixing hole 104a, mixes with the fuel and burns before flowing out.

[0032] A floating connection is adopted between the flame tube 100 and components made of metal materials such as the casing outer ring 400, the casing inner ring 600, and the radial diffuser 800. 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, thereby achieving coordination of cold and hot dimensions between the flame tube 100 made of ceramic-based composite materials and the corresponding metal material components, thereby preventing the flame tube 100 from being damaged.

[0033] Example 2 Reference Figures 1 to 8 This embodiment provides a combustion chamber with a ceramic-based composite flame tube 100, which is different from Example 1 in 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.

[0034] Specifically, the ends of the casing outer ring 400 and the casing inner ring 600 are fixedly connected with a high-pressure turbine hollow guide, and an outlet 503 connected to the air flow channel is opened on the high-pressure turbine hollow guide. An outer connecting ring 501 and an inner connecting ring 502 inside the outer connecting ring 501 are fixed on 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 in the axial direction are detachably connected together, and the end of the second flame tube body 101 and the inner end of the inner connecting ring 502 in the axial direction are detachably connected together.

[0035] Specifically, the head end of the first flame tube body 104 is fixedly connected with a first positioning ring 103 made of a ceramic-based composite material, a plurality of first positioning bosses 103a are arranged on the inner side of the first positioning ring 103, a plurality of first grooves 602 corresponding to the first positioning bosses 103a are arranged on the outer periphery of the casing inner ring 600, a plurality of first through grooves 601 that allow the first positioning bosses 103a to pass through are arranged on the outer periphery of the casing inner ring 600 at both ends in the axial direction of the first grooves 602, a plurality of first through grooves 601 corresponding to the first positioning bosses 103a are also opened on the limiting step of the head of the casing inner ring 600, and the first positioning bosses 103a are engaged in the first grooves 602 after passing through the first through grooves 601, and an annular groove 501a is opened on the inner end of the outer connecting ring 501 in the axial direction, and the outer connecting ring 501 is connected to the casing inner ring 600 through the annular groove 501a. 01a is sleeved on the end of the first flame tube body 104, and a first limiting boss 104c is fixed on the outer periphery of the end of the first flame tube body 104. A first clamping groove corresponding to the first limiting boss 104c is also opened on the outer connecting ring 501, and the outer connecting ring 501 is clamped on the first limiting boss 104c through the first clamping groove. After the first flame tube body 104 is rotated 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 casing outer ring 400 and the casing inner ring 600. 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 annular groove 501a, and there is a third gap J between the first limiting boss 104c and the first clamping groove.

[0036] Specifically, a second positioning ring 102 made of a ceramic-based composite material is fixedly connected to the head end of the second flame tube body 101, and a plurality of second positioning bosses 102a are arranged inside the second positioning ring 102. A plurality of second grooves 603 corresponding to the second positioning bosses 102a are arranged on the outer periphery of the casing inner ring 600. A plurality of second through grooves 604 that allow the second positioning bosses 102a to pass through are arranged on the outer periphery of the casing inner ring 600 at both ends in the axial direction of the second grooves 603. The second positioning bosses 102a are engaged in the second grooves 603 after passing through the second through grooves 604. A damping ring 105 is fixedly connected to the end of the second flame tube body 101. A clamping groove 105a is opened at one end of the damping ring 105 relative to the high-pressure turbine guide vane 500. A support ring 105b is fixed to the damping ring 105 inside the clamping groove 105a. An annular plug-in groove 502a is provided at one end of the connecting ring 502 relative to the damping ring 105, and the inner connecting ring 502 is supported on the supporting ring 105b via the plug-in groove 502a. A second clamping groove 501b is provided on the inner connecting ring 502 outside the plug-in groove 502a, and a second limiting boss is fixed on the outer side of the supporting ring 105b, and the inner connecting ring 502 is clamped on the second limiting boss via the second clamping groove 501b; after the second flame tube body 101 is rotated to misalign the second positioning boss 102a and the second through groove 604, the high-pressure turbine guide 500 is fixedly connected to the ends of the casing outer ring 400 and the casing inner ring 600; there is a fourth gap X between the outer edge of the second positioning boss 102a and the second groove 603, there is a fifth gap P between the supporting ring 105b and the plug-in groove 502a, and there is a sixth gap S between the second limiting boss and the second clamping groove 501b.

[0037] After the high-pressure air entering the combustion chamber is decelerated and diffused by the radial diffuser 800 and the axial diffuser 300, the air is divided into two paths (such as Figure 1 As shown in the figure, one path passes through the main combustion hole 104b and the mixing hole 104a on the first flame tube body 104 and then enters the ventilation flow channel, and the other path passes through the hollow groove of the high-pressure turbine guide 500 and the flow hole opened on the second flame tube body 101 and also enters the ventilation flow channel. The jet forms a reflow zone, mixes with the fuel and burns, and then flows out from the outlet 503 on the high-pressure turbine guide 500.

[0038] The connection part between the first flame tube body 104 and the inner ring 600 of the casing via the first positioning ring 103 has gaps in the axial and circumferential directions, and the connection part between the second flame tube body 101 and the inner ring 600 of the casing via the second positioning ring 102 has gaps in the axial and circumferential directions; so that the flame tube 100 has a certain amount of free space in the axial and circumferential directions, and the cold and hot dimensions between the wall of the ceramic-based composite flame tube 100 and the metal casing are coordinated, and the flame tube 100 is prevented from being damaged. When the engine is in working condition, the corresponding wall gaps of the front wall and the rear wall of the flame tube 100 in the axial and circumferential directions become smaller, which can reduce the leakage of the airflow in each flow channel.

[0039] The ends of the first flame tube body 104 and the second flame tube body 101 are overlapped with the outer connecting ring 501 and the inner connecting ring 502 respectively. Annular gaps are left in the connecting 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 respectively. The reserved annular groove 501a gap can meet the space requirement for radial thermal expansion of the ceramic-based composite flame tube 100. At the same time, the annular groove 501a can also play a role in auxiliary support of the wall of the flame tube 100, which is very beneficial to the long-term, reliable and stable operation of the flame tube 100.

[0040] Example 3 The difference between this embodiment and embodiment 2 is that this embodiment provides 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.

[0041] A method for installing a flame tube 100 comprises the following steps: S1: The first flame tube body 104 is sleeved on 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. S2: The second flame body is sleeved on the end of the second positioning ring 102 away from the first positioning ring 103 and is made to abut against the second step of the second positioning ring 102, and the second flame tube body 101 and the second positioning ring 102 are fixedly connected together by rivets made of composite materials, and the damping ring 105 is fixedly connected to the end of the second positioning ring 102 by rivets made of composite materials; S3: The first positioning ring 103 slides along the outer side of the casing inner ring 600, and the first positioning boss 103a passes through the two second through grooves 604 and one first through groove 601 in sequence and then snaps into the first groove 602, and the first flame tube body 104 is rotated to displace the first positioning boss 103a and the first through groove 601, thereby limiting the axial displacement of the first flame tube body 104; S4: the second positioning ring 102 slides along the outer side of the casing inner ring 600, the second positioning boss 102a is inserted into the second groove 603 through the second through groove 604, and the second flame tube body 101 is rotated to displace the second positioning boss 102a and the second through groove 604, thereby limiting the axial displacement of the second flame tube body 101; S5: Align the first clamping groove on the outer connecting ring 501 and the second clamping groove 501b on the inner connecting ring 502 with the first limiting boss 104c and the second limiting boss respectively, the outer connecting ring 501 is clamped on the first limiting boss 104c through the first clamping groove, and the inner connecting ring 502 is clamped on the second limiting boss through the second clamping groove 501b, so as to limit the circumferential displacement of the first flame tube body 104 and the second flame tube body 101; S6: Use a plurality of fixing bolts 700 to fix the high-pressure turbine guide vane 500 to the casing outer ring 400 and the casing inner ring 600 .

[0042] Taking the direction of the air inlet 401 as a reference, the direction of the gas from the air inlet 401 to the air outlet 503 is from the beginning to the end, and the beginning and the end mentioned in this application are all based on the above direction.

[0043] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in 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 invention comprises a casing outer ring (400) and a casing inner ring (600) arranged inside the casing outer ring (400), wherein the head of the casing outer ring (400) has an air inlet (401), and a radial diffuser (800) is fixedly connected inside the casing outer ring near the air inlet (401), the head end of the casing inner ring (600) is connected to the inner side of the radial diffuser (800) in the axial direction, and an annular installation cavity is formed between the inner wall of the casing outer ring (400), the inner side of the radial diffuser (800) in the axial direction, and the outer wall of the casing outer ring (400), and a flame tube (100) is connected inside the annular installation cavity, and the flame tube (100) comprises an annular first flame tube body (104) and a second flame tube body (101), and the first flame tube body (104) and the second flame tube body (101) are connected to each other. The main bodies (101) are arranged at intervals in the axial direction and are both made of ceramic-based composite materials. The first flame tube body (104) is close to the radial diffuser (800), and the second flame tube body (101) is far away from the radial diffuser (800). The first flame tube body (104) is provided with a main combustion hole (104b) and a mixing hole (104a). The main combustion hole (104b) is arranged close to the outer ring (400) of the casing, and the mixing hole (104a) is arranged 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, and a flow passage is formed between the first flame tube body (104), the second flame tube body (101) and the outer sides of the inner ring (600) of the casing.

2. The combustion chamber with a ceramic matrix composite flame tube according to claim 1, characterized in that: The ends of the casing outer ring (400) and the casing inner ring (600) are fixedly connected with a high-pressure turbine hollow guide, and the high-pressure turbine hollow guide is provided with an air outlet (503) that is in communication with the air flow channel.

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

4. The combustion chamber with a ceramic matrix composite flame tube as claimed in claim 3, characterized in that: An outer connecting ring (501) and an inner connecting ring (502) inside the outer connecting ring (501) are fixed to the side of the high-pressure turbine hollow guide device 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) in the axial direction are detachably connected together, and the end of the second flame tube body (101) and the inner end of the inner connecting ring (502) in the axial direction are detachably connected together.

5. The combustion chamber with a ceramic matrix composite flame tube according to claim 4, characterized in that: The head end of the first flame tube body (104) is fixedly connected with a first positioning ring (103) made of a ceramic-based composite material, a plurality of first positioning bosses (103a) are arranged inside the first positioning ring (103), a plurality of first grooves (602) corresponding to the first positioning bosses (103a) are arranged on the outer periphery of the casing inner ring (600), a plurality of first through grooves (601) through which the first positioning bosses (103a) pass are arranged on the outer periphery of the casing inner ring (600) at the end of the first grooves (602), and the first positioning bosses (103a) are engaged in the first grooves (602) after passing through the first through grooves (601), and the outer connecting ring (501) is axially inner and outer. An annular groove (501a) is opened at the end of the first flame tube body (104), 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), and a first clamping groove corresponding to the first limiting boss (104c) is opened on the outer connecting ring (501), the outer connecting ring (501) is clamped on the first limiting boss (104c) through the first clamping groove, and after the first flame tube body (104) is rotated to make the first positioning boss (103a) and the first through groove (601) misaligned, the high-pressure turbine guide (500) is fixedly connected to the ends of the casing outer ring (400) and the casing inner ring (600).

6. The combustion chamber with a ceramic matrix composite flame tube according to claim 5, characterized in that: A second positioning ring (102) made of a ceramic-based composite material is fixedly connected to the head end of the second flame tube body (101), and a plurality of second positioning bosses (102a) are arranged inside the second positioning ring (102). A plurality of second grooves (603) corresponding to the second positioning bosses (102a) are arranged on the outer periphery of the casing inner ring (600). A plurality of second through grooves (604) for allowing the second positioning bosses (102a) to pass through are arranged on the outer periphery of the casing inner ring (600) at both ends in the axial direction of the second grooves (603). After the second positioning bosses (102a) pass through the second through grooves (604), they are engaged in the second grooves (603). A damping ring (105) is fixedly connected to the end of the second flame tube body (101), and a clamping ring (105) is provided at one end of the damping ring (105) relative to the high-pressure turbine guide vane (500). The damping ring (105a) is fixed with a support ring (105b) on the inner side of the clamping groove (105a); an annular plug-in groove (502a) is formed on one end of the inner connecting ring (502) opposite to the damping ring (105); the inner connecting ring (502) is supported on the support ring (105b) via the plug-in groove (502a); and a second plug-in groove (502a) is formed on the inner connecting ring (502) outside the plug-in groove (502a). A second limiting boss is fixed on the outer side of the support ring (105b), and the inner connecting ring (502) is clamped on the second limiting boss via the second clamping groove (501b); after the second flame tube body (101) is rotated to dislocate the second positioning boss (102a) and the second groove (603), the high-pressure turbine guide (500) is fixedly connected to the ends of the casing outer ring (400) and the casing inner ring (600).

7. The combustion chamber with a ceramic matrix composite flame tube according to claim 5 or 6, characterized in that: The first positioning ring (103) is made of a ceramic-based composite material, a first gap (M) is provided 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, a second gap (N) is provided between the end of the second flame tube body (101) and the annular groove (501a), and a third gap (J) is provided between the first limiting boss (104c) and the first clamping groove.

8. The combustion chamber with a ceramic matrix composite flame tube according to claim 6, characterized in that: The second positioning ring (102) is made of a ceramic-based composite material, a fourth gap (X) is provided between the second positioning boss (102a) and the outer edge of the second groove (603), a fifth gap (P) is provided between the support ring (105b) and the plug-in recess (502a), and a sixth gap (S) is provided between the second limiting boss and the second clamping groove (501b).

9. The combustion chamber with a ceramic matrix composite flame tube according to any one of claims 1 to 6, characterized in that: The radial diffuser (800) is fixedly connected at its end in the axial direction to an annular axial diffuser (300) and an intermediate connecting ring (200) arranged in the axial diffuser (300); 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; and the end of the intermediate connecting ring (200) is fixedly connected to the head end of the casing inner ring (600).

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