CN116658939B - A combined pulse detonation engine ceramic matrix composite combustion chamber - Google Patents

A combined pulse detonation engine ceramic matrix composite combustion chamber Download PDF

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Publication number
CN116658939B
CN116658939B CN202310729473.4A CN202310729473A CN116658939B CN 116658939 B CN116658939 B CN 116658939B CN 202310729473 A CN202310729473 A CN 202310729473A CN 116658939 B CN116658939 B CN 116658939B
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Prior art keywords
cmc
combustion chamber
flange
pulse detonation
cylinder
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CN116658939A (en
Inventor
张禄
陈贤清
葛海浪
吴涛
高希光
龚昕
彭畅新
宋迎东
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R7/00—Intermittent or explosive combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/52—Toroidal combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Connection Of Plates (AREA)

Abstract

A combined type pulse detonation engine ceramic matrix composite combustion chamber is composed of a superalloy cylinder, a bolt, a nut, a CMC cylinder and a sleeve, wherein the combined type structure of the superalloy cylinder and the ceramic matrix composite combustion chamber enables the pulse detonation engine combustion chamber to work for a long time in a high temperature environment, a cooling device is arranged at a flange joint of the superalloy cylinder and the CMC cylinder, the temperature of a flange joint area can be reduced, the height Wen Jianxi of the flange joint is reduced as much as possible, meanwhile, the sleeve is added on the bolt which is fastened with the flange joint, the sleeve has the characteristic of large thermal expansion coefficient, the high Wen Jianxi caused by low thermal expansion coefficient of CMC materials can be effectively counteracted by the bolt-nut joint, and the flange joint structure of the combustion chamber is prevented from loosening due to a high temperature gap. The combined combustion chamber structure can increase the working durability of the combustion chamber of the pulse detonation engine, and has good application prospect on various pulse detonation engines of aerospace aircrafts.

Description

Ceramic matrix composite combustion chamber of combined pulse detonation engine
Technical Field
The invention relates to a pulse detonation engine, in particular to a ceramic matrix composite combustion chamber of a combined pulse detonation engine.
Background
The pulse detonation engine is a brand new engine for generating thrust by utilizing detonation waves, has great difference with the traditional working mode of the gas turbine engine, and has the advantages of simple structure, small size, wide application range, low cost, capability of being used at zero speed, high combustion efficiency, excellent high-speed performance and the like. However, the thermal environment of the pulse detonation engine combustion chamber is very complex and severe, especially the high temperature environment makes the temperature resistance of the pulse detonation engine combustion chamber put forward higher requirements, the traditional common combustion chamber cannot meet the high temperature load of the pulse detonation engine combustion chamber, various active and passive cooling systems and composite material combustion chamber structures are put forward in order to meet the high temperature environment requirements of the pulse detonation engine combustion chamber, various structures face certain structural defects and challenges, or the temperature resistance is poor, or the ablation rate is too high, so that the combustion chamber structure which can meet the long-time use requirements of the pulse detonation engine combustion chamber is little, and the weight of the pulse detonation engine combustion chamber which can meet the temperature requirements can be increased and the structure is complex.
Disclosure of Invention
Aiming at various defects of the pulse detonation engine combustion chamber in the prior art, the invention provides the ceramic matrix composite combustion chamber of the combined pulse detonation engine, which has the advantages of simple structure, good sealing performance and reliable flange connection, and can effectively improve the temperature resistance of the pulse detonation engine combustion chamber and improve the efficiency and durability of the pulse detonation engine.
In order to achieve the technical purpose, the technical scheme of the invention is as follows:
The utility model provides a combination formula pulse detonation engine ceramic matrix combined material combustion chamber, comprises superalloy section of thick bamboo and CMC section of thick bamboo, the flange dish one of superalloy section of thick bamboo one end, the flange dish two is the entry end of combination formula pulse detonation engine ceramic matrix combined material combustion chamber, flange dish two be connected with the CMC flange dish of CMC section of thick bamboo one end, flange dish two pass through bolt and nut fixed connection with the CMC flange dish, superalloy section of thick bamboo be the entry and the intermediate region of combustion chamber, CMC section of thick bamboo be the intermediate and the exit area of combination formula pulse detonation engine ceramic matrix combined material combustion chamber.
In order to optimize the technical scheme, the measures adopted further comprise:
The flange plate II and the CMC flange plate are provided with corresponding bolt holes, the bolts penetrate through the bolt holes of the CMC flange plate, penetrate out of the bolt holes of the flange plate II and are screwed with nuts, a sleeve is further arranged between the nuts and the flange plate II, and the sleeve is sleeved on the studs of the bolts.
Sleeve flanges are arranged at two ends of the sleeve, the thermal expansion coefficient of the sleeve is larger than that of the high-temperature alloy cylinder, the length of the sleeve is set to be that when the pulse detonation engine works, the axial elongation of high-temperature expansion of the bolt is equal to the sum of the axial elongation of the flange II, the CMC flange and the sleeve, and the formula is as follows:
Wherein x is the axial length of the sleeve, a 0 is the thermal expansion coefficient of the bolt, x 0 is the axial length of the bolt, a 1 is the thermal expansion coefficient of the flange plate II, x 1 is the axial length of the flange plate II, a 2 is the thermal expansion coefficient of the CMC flange plate, x 2 is the axial length of the CMC flange plate, and a 3 is the thermal expansion coefficient of the sleeve.
The second flange plate is provided with a cooling groove along the circumferential direction, a cooling pipe is arranged in the cooling groove, the cooling pipe is provided with a cooling pipe inlet and a cooling pipe outlet, cooling liquid flows into the cooling pipe through the cooling pipe inlet and is led out through the cooling pipe outlet, and the cooling liquid cools the superalloy tube and the CMC tube when flowing in the cooling pipe.
The cooling liquid is liquid fuel of a pulse detonation engine or externally connected cooling water.
The CMC cylinder is made of ceramic matrix composite, and a chamfer is arranged in a structure mutation area where the cylindrical structure of the CMC cylinder is connected with the CMC flange, and the chamfer is more than or equal to R5.
The ceramic matrix composite of CMC section of thick bamboo weave the mode for 2.5D or 3D, weave the warp direction of structure and the axial of combination formula pulse detonation engine ceramic matrix composite combustion chamber the same, the weft direction is the same with the circumference of combination formula pulse detonation engine ceramic matrix composite combustion chamber, CMC section of thick bamboo thickness be 5mm-10mm.
And a graphite gasket is further arranged between the second flange plate and the CMC flange plate, and the graphite gasket is provided with bolt holes identical to the second flange plate and the CMC flange plate.
The superalloy tube is made of a superalloy material GH3536.
The ceramic matrix composite is specifically a C/SiC material.
The beneficial effects of the invention are as follows:
1. The cooling liquid can use liquid fuel of the pulse detonation engine, such as kerosene, gasoline and the like, on one hand, the temperature of a flange connection area can be reduced, the too large gap caused by the uncomfortableness of high-temperature thermal expansion of bolt and nut connection is reduced, the connection strength of the flange is improved, and on the other hand, no additional cooling liquid is needed, and the weight of the pulse detonation engine is reduced.
2. The CMC cylinder is provided with the chamfer angles in the structure abrupt change areas, so that the weaving structure arrangement of the ceramic matrix composite is more reasonable, the integral structural strength of the CMC cylinder cannot be reduced due to overlarge rotation angles, and the integral structural strength of the CMC cylinder can be effectively improved.
3. The graphite gasket has high temperature resistance, so that the sealing connection effect of the high Wen Gaojin cylinder and the CMC cylinder is effectively improved, and the long-time operation of the combustion chamber is ensured.
4. The sleeve is arranged at the bolt and nut positions of the connecting flange, so that the gap caused by high-temperature expansion of the bolt and nut connection is reduced, the reliability and stability of the bolt and nut connection are improved, meanwhile, the sleeve flange plates are arranged at the two ends of the sleeve, the contact area of the two ends of the sleeve is increased by the sleeve flange plates, the stress concentration is reduced, and the tightness of the flange plate connection is improved.
5. The length ratio of the high Wen Gaojin cylinder and the CMC cylinder can be adjusted according to the temperature of the combustion chamber of the pulse detonation engine so as to achieve better effect.
6. The CMC material is selected, so that the weight of the engine can be reduced, the method has good beneficial effects on improving various performances of the pulse detonation engine, and has extremely high application value on the application of the pulse detonation engine to various aircrafts in aerospace.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a diagram showing the connection between the second flange and the CMC flange;
FIG. 3 is a schematic view of a high Wen Gaojin cartridge;
FIG. 4 is a schematic illustration of a CMC cylinder structure;
FIG. 5 is a schematic view of a 2.5D weave of a C/SiC material;
The high-temperature alloy cylinder, the first 101-flange, the second 102-flange, the 103-bolt hole, the 104-cooling groove, the 105-cooling pipe, the 106-cooling pipe inlet, the 107-cooling pipe outlet, the 2-CMC cylinder, the 3-bolt, the 4-nut, the 201-CMC flange, the 202-chamfer, the 203-graphite gasket and the 5-sleeve.
Detailed Description
The invention is described in further detail below with reference to the attached drawings and examples:
referring to fig. 1,2,3, 4 and 5, an embodiment of the present invention includes:
A ceramic matrix composite combustion chamber of a combined pulse detonation engine comprises a superalloy cylinder 1, a bolt 3, a nut 4, a CMC cylinder 2 and a sleeve 5. The first flange plate 101 is connected with a combustion chamber inlet device, the second flange plate 102 is connected with a CMC flange plate 201 at one end of the CMC cylinder 2, and the high-temperature alloy cylinder 1 and the CMC cylinder 2 are connected through flanges to form a ceramic matrix composite combustion chamber of the combined pulse detonation engine, so that the ceramic matrix composite combustion chamber has high temperature resistance.
The high-temperature alloy cylinder 1 is made of high-temperature alloy materials, GH3536 can be selected, high-temperature mechanical stability is good, the second flange plate 102 on the high-temperature alloy cylinder 1 is provided with the cooling groove 104, the cooling pipe 105 is embedded in the cooling groove 104, cooling liquid is introduced into the cooling pipe inlet 106 and flows out of the cooling pipe outlet 107 through the cooling pipe 105 in the cooling groove 104, the cooling liquid adopts liquid fuel of the pulse detonation engine, the temperature of a flange connection area can be effectively reduced by introducing the cooling liquid, the gap of connection of bolts 3 and nuts 4 caused by different high-temperature thermal expansion performance is effectively reduced, the stability and the sealing performance of flange connection of a combined combustion chamber of the pulse detonation engine are effectively improved, and the strength of a flange connection structure is improved.
Because CMC cylinder 2, high temperature alloy cylinder 1 and material high temperature expansion coefficient of bolt 3 are different, the elongation of ring flange two 102, CMC ring flange 201 and bolt 3 is different when the pulse detonation engine works, high temperature expansion coefficient of high temperature alloy cylinder 1 and bolt 3 is big, CMC cylinder 2's high temperature expansion coefficient is little, can lead to the axial elongation of bolt 3 to be greater than the axial elongation of ring flange two 102 and CMC ring flange 201, the flange joint can produce the clearance, lead to the combustion chamber leakproofness to become poor, in order to reduce the production of clearance as far as possible, design and add the sleeve 5 that the material expansion rate is great, place sleeve 5 between ring flange 4 and ring flange two 102, sleeve 5 both ends all set up the sleeve ring flange, thereby reduce stress concentration, increase the leakproofness of ring flange two 102 simultaneously. The length of the sleeve 5 can be determined according to the following manner, so that the axial elongation of the high-temperature expansion of the bolt 3 is equal to the sum of the axial elongation of the second flange 102, the CMC flange 201 and the sleeve 5 when the pulse detonation engine works, the gap of flange connection can be effectively reduced, and the tightness and the stability of the flange connection of the combustion chamber are improved.
The CMC cylinder 2 comprises a CMC flange 201 and a chamfer 202 in the structure, the CMC cylinder 2 is made of ceramic matrix composite material, the weaving mode is 2.5D or 3D, the warp direction of the weaving structure is the same as the axial direction of the combustion chamber, the weft direction is the same as the circumferential direction of the combustion chamber, the material has good high temperature resistance and mechanical property, the thickness of the CMC cylinder 2 is between 5mm and 10mm, the material has good ablation resistance, and the material can greatly improve the temperature resistance of the combustion chamber, reduce the cooling air quantity, reduce the weight of the detonation engine and improve the efficiency and the thrust-weight ratio of the detonation engine when being applied to the combustion chamber of the pulse detonation engine.
And a graphite gasket 203 is placed between the CMC flange 201 and the second flange 102, and then the flange is fixedly connected through bolts 3 and nuts 4, so that the graphite gasket 203 has good high-temperature stability, and the flange connection part of the combustion chamber has good temperature resistance and sealing property.
The cylindrical structure on the CMC cylinder 2 and the CMC flange 201 structure mutation area are designed to be chamfer 202, and the chamfer 202 is fixed to be more than or equal to R5, so that the arrangement of the weaving structure of the CMC cylinder 2 is more reasonable, the integral structural strength of the CMC cylinder 2 is not reduced due to overlarge rotation angle, and the integral structural strength of the pulse detonation combustion chamber can be effectively improved.
The first flange plate 101 on the superalloy tube 1 is an inlet end of a pulse detonation combustion chamber, the CMC tube 2 is close to an outlet end of the combustion chamber, the design enables the superalloy tube 1 to be positioned in an inlet and middle area of the combustion chamber, the CMC tube 2 is positioned in the middle and outlet areas of the combustion chamber, and the length ratio of the superalloy tube 1 to the CMC tube 2 can be determined according to the temperature of the combustion chamber on the basis of the characteristics of low temperature of the inlet area and high temperature of the outlet area of the combustion chamber.
Pulse detonation engines utilize high temperature, high pressure fuel gas generated by gap detonation waves to generate thrust. When the pulse detonation combustion chamber operates, explosive fuel and oxidant are mixed and filled into the combustion chamber, namely, the inlet of the superalloy tube 1 is ignited and detonated, generated detonation waves propagate to the open end and are discharged out of the combustion chamber, most of gas is discharged, and after the gas is discharged out, the expansion waves reflected from the closed end are discharged out of the combustion chamber, the combustion chamber is in a low-pressure state, and the residual gas is blown off by filling isolation gas, then the explosive mixture is replenished, and a new cycle is started. The whole working process is carried out intermittently and periodically, namely the pulse detonation engine is in unsteady state working. When the detonation frequency is high, the operation is approximately considered continuous, and continuous thrust can be provided to propel the aircraft. The average temperature of the high-temperature fuel gas in the combustion chamber is different, the temperature of the inlet is the lowest, and the temperature is higher as the temperature approaches to the outlet, so the invention adopts a combined combustion chamber structure, the high-temperature alloy cylinder 1 is arranged in the inlet area, and the CMC cylinder 2 is arranged in the outlet area of the combustion chamber, thus being capable of effectively resisting the high-temperature impact and ablation of the fuel gas in the combustion chamber.
In order to ensure the sealing performance of the flange connection area of the pulse detonation combustion chamber, a graphite gasket 203 is added at the connection position of the CMC flange 201 and the flange plate II 102, and the sealing performance and the temperature resistance of the flange connection can be effectively improved due to the good high-temperature stability of graphite. The cooling fluid is introduced from the cooling tube inlet 106 when the combustion chamber begins to operate, and the cooling fluid is liquid fuel such as kerosene, gasoline and the like required by the combustion chamber of the pulse detonation engine, so that the weight of the pulse detonation engine is reduced without additional cooling fluid. The cooling liquid flows into the cooling pipe 105 from the cooling pipe inlet 106, passes through the second flange 102 and then flows out from the cooling pipe outlet 107, and the flowing cooling liquid is introduced into the fuel inlet of the pulse detonation engine and is injected into the combustion chamber. The problem of expansion clearance caused by high temperature of flange connection is effectively reduced, the strength of the flange is improved, and meanwhile, no extra cooling liquid is needed, so that the overall quality of the engine is reduced.
The length of the sleeve 5 is selected according to the following, when the pulse detonation engine works, the axial elongation of the high-temperature expansion of the bolt 3 is equal to the sum of the axial elongation of the high-temperature expansion of the flange plate II102, the CMC flange plate 201 and the sleeve 5, so that the gap of flange connection can be effectively reduced, and the tightness and the stability of the flange connection of the combined combustion chamber of the pulse detonation engine are improved. The length of the sleeve 5 is x, and the calculation process is as follows:
Wherein a 0 is the thermal expansion coefficient of the bolt 3, x 0 is the axial length of the bolt 3, a 1 is the thermal expansion coefficient of the second flange 102, x 1 is the axial length of the second flange 102, a 2 is the thermal expansion coefficient of the CMC flange 201, x 2 is the axial length of the CMC flange 201, and a 3 is the thermal expansion coefficient of the sleeve 5.
The lengths of the superalloy tube 1 and the CMC tube 2 are determined according to the temperature distribution of the pulse detonation combustion chamber, the temperature of the combustion chamber is the lowest temperature of an inlet area, the highest temperature of an outlet area, the temperatures of all areas of the combustion chamber are ensured to be lower than the temperature resistant temperatures of the superalloy tube 1 and the CMC tube 2, if the temperatures are too high, the length of the CMC tube 2 is lengthened, and if the temperatures are not high, the length of the superalloy tube 1 is lengthened.
The CMC cylinder 2 is made of a ceramic matrix composite material, and the ceramic matrix composite material is various, wherein a 2.5-dimensional braided C/SiC material is selected, so that the CMC cylinder has good mechanical properties in an ultra-high temperature environment, can work at 2500K in a short time and can work below 1932K for a long time, the cooling air quantity of a pulse detonation engine can be reduced, the weight of the detonation engine is reduced, and the efficiency and the thrust-weight ratio of the detonation engine are improved.
The invention can improve the durability of the combustion chamber of the pulse detonation engine, improve the temperature resistance of the combustion chamber, has simple integral structure, good sealing property and high-temperature stability, can effectively improve the working temperature of the detonation engine, has good beneficial effects on improving various performances of the pulse detonation engine, and has good application prospect on various aircrafts in aerospace.
The foregoing description is only illustrative of the present invention and is not intended to limit the scope of the invention, and all equivalent structures or equivalent processes or direct or indirect application in other related technical fields are included in the scope of the present invention.

Claims (7)

1. The ceramic matrix composite combustion chamber of the combined pulse detonation engine is characterized by comprising a superalloy cylinder (1) and a CMC cylinder (2), wherein one end of the superalloy cylinder (1) is connected with a first flange plate (101), the other end of the superalloy cylinder is connected with a second flange plate (102), the first flange plate (101) is an inlet end of the ceramic matrix composite combustion chamber of the combined pulse detonation engine, the second flange plate (102) is connected with a CMC flange plate (201) at one end of the CMC cylinder (2), the second flange plate (102) is fixedly connected with the CMC flange plate (201) through bolts (3) and nuts (4), the superalloy cylinder (1) is an inlet and a middle area of the combustion chamber, and the CMC cylinder (2) is a middle and outlet area of the ceramic matrix composite combustion chamber of the combined pulse detonation engine;
The flange plate II (102) and the CMC flange plate (201) are provided with corresponding bolt holes (103), the bolts (3) penetrate through the bolt holes (103) of the CMC flange plate (201), penetrate out of the bolt holes (103) on the flange plate II (102) and are screwed with nuts (4), a sleeve (5) is further arranged between the nuts (4) and the flange plate II (102), and the sleeve (5) is sleeved on the bolts of the bolts (3);
Sleeve flanges are arranged at two ends of the sleeve (5), the thermal expansion coefficient of the sleeve (5) is larger than that of the high-temperature alloy cylinder (1), the length of the sleeve (5) is set to be equal to the sum of the flange two (102), the CMC flange (201) and the high-temperature expansion axial elongation of the sleeve (5) when the pulse detonation engine works, and the formula is as follows:
Wherein x is the axial length of the sleeve (5), a 0 is the thermal expansion coefficient of the bolt (3), x 0 is the axial length of the bolt (3), a 1 is the thermal expansion coefficient of the flange two (102), x 1 is the axial length of the flange two (102), a 2 is the thermal expansion coefficient of the CMC flange (201), x 2 is the axial length of the CMC flange (201), and a 3 is the thermal expansion coefficient of the sleeve (5);
A cooling groove (104) is formed in the second flange plate (102) along the circumferential direction, a cooling pipe (105) is arranged in the cooling groove (104), the cooling pipe (105) is provided with a cooling pipe inlet (106) and a cooling pipe outlet (107), cooling liquid flows into the cooling pipe (105) through the cooling pipe inlet (106) and is led out through the cooling pipe outlet (107), and the cooling liquid cools the superalloy cylinder (1) and the CMC cylinder (2) when flowing in the cooling pipe (105);
The high-temperature high-gold cylinder (1) and the CMC cylinder (2) can be used for adjusting the length ratio according to the temperature of the combustion chamber of the pulse detonation engine.
2. The ceramic matrix composite combustion chamber of a combined pulse detonation engine of claim 1, wherein the cooling fluid is a liquid fuel or an externally-connected cooling water of the pulse detonation engine.
3. A ceramic matrix composite combustion chamber of a combined pulse detonation engine as claimed in claim 1, wherein the CMC cylinder (2) is made of ceramic matrix composite, and a chamfer (202) is arranged at a structural abrupt change region where a cylindrical structure of the CMC cylinder (2) is connected with the CMC flange (201), and the chamfer (202) is greater than or equal to R5.
4. A combined pulse detonation engine ceramic matrix composite combustion chamber as claimed in claim 1, wherein the ceramic matrix composite of the CMC barrel (2) is woven in a 2.5D or 3D manner, the warp direction of the woven structure is the same as the axial direction of the combined pulse detonation engine ceramic matrix composite combustion chamber, the weft direction is the same as the circumferential direction of the combined pulse detonation engine ceramic matrix composite combustion chamber, and the thickness of the CMC barrel (2) is 5mm-10mm.
5. A ceramic matrix composite combustion chamber of a combined pulse detonation engine as claimed in claim 1 wherein a graphite gasket (203) is further arranged between the second flange (102) and the CMC flange (201), and the graphite gasket (203) is provided with bolt holes (103) identical to the second flange (102) and the CMC flange (201).
6. A combined pulse detonation engine ceramic matrix composite combustion chamber as claimed in claim 1 wherein the superalloy tube (1) is of superalloy material GH3536.
7. A combined pulse detonation engine ceramic matrix composite combustion chamber as claimed in claim 1 wherein said ceramic matrix composite is in particular a C/SiC material.
CN202310729473.4A 2023-06-20 2023-06-20 A combined pulse detonation engine ceramic matrix composite combustion chamber Active CN116658939B (en)

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CN117553324A (en) * 2023-11-13 2024-02-13 南京航空航天大学 A combined rotary detonation engine combustion chamber structure

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