CN115585480B - Wide-adaptability supersonic combustion chamber with adjustable concave cavity structure - Google Patents
Wide-adaptability supersonic combustion chamber with adjustable concave cavity structure Download PDFInfo
- Publication number
- CN115585480B CN115585480B CN202211035036.4A CN202211035036A CN115585480B CN 115585480 B CN115585480 B CN 115585480B CN 202211035036 A CN202211035036 A CN 202211035036A CN 115585480 B CN115585480 B CN 115585480B
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- cavity
- combustion chamber
- adjustable
- adjusting module
- depth
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 97
- 238000002955 isolation Methods 0.000 claims abstract description 21
- 238000007789 sealing Methods 0.000 claims description 19
- 230000006835 compression Effects 0.000 claims description 16
- 238000007906 compression Methods 0.000 claims description 16
- 230000009471 action Effects 0.000 claims description 6
- 238000006073 displacement reaction Methods 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 6
- 230000008859 change Effects 0.000 claims description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
Classifications
-
- 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
Abstract
The invention discloses a wide-adaptability supersonic combustion chamber with an adjustable concave cavity structure, which comprises: the device comprises a combustion chamber isolation section, an air guide pipe, a concave cavity depth adjusting module, a communicating pipe, a concave cavity length adjusting module and a combustion chamber expansion section; the combustion chamber isolation section is communicated with the combustion chamber expansion section; the cavity depth adjusting module and the cavity length adjusting module are positioned below the expansion section of the combustion chamber to form an adjustable cavity, and the depth and the length of the adjustable cavity are adjusted; the combustion chamber isolation section is communicated with the concave cavity depth adjusting module through a bleed air pipe; the cavity depth adjusting module is communicated with the cavity length adjusting module through a communicating pipe. The adjustable concave cavity of the supersonic combustion chamber is adjustable in length and depth, and the requirements of different flight conditions on the performance of the supersonic combustion chamber can be met by adjusting the length and depth of the adjustable concave cavity.
Description
Technical Field
The invention belongs to the technical field of supersonic combustion chambers, and particularly relates to a wide-adaptability supersonic combustion chamber with an adjustable concave cavity structure.
Background
The excellent performance of the scramjet engine under the condition of high flight Mach number obtains the favor of hypersonic aircrafts, becomes one of the most ideal propulsion system choices, and the supersonic combustion chamber is a key technology of the scramjet engine design. For supersonic combustors, the incoming flow is fast, the residence time of the fuel is in the order of milliseconds, and it is conceivable to achieve efficient mixing of the fuel and stable combustion difficulties in a limited time and space. Thus, supersonic combustion chamber mixing and stable combustion technologies represented by cavities have been developed.
With the development of technology, aircraft are placing higher demands on power plants and are also more demanding. The supersonic combustion chamber can stably operate under a single hypersonic working condition, can be operated under a wide inflow condition, is suitable for a wide-speed-domain working condition, and cannot meet the working requirement of the wide-speed domain due to a single structure. However, in the prior art, the structure of the concave cavity cannot be changed, and once the design of the combustion chamber is completed, the length-depth ratio of the concave cavity cannot be adjusted, so that the supersonic combustion chamber has better performance only under the designed flight working condition.
Disclosure of Invention
The technical solution of the invention is as follows: the defect of the prior art is overcome, and the wide adaptability supersonic combustion chamber with the adjustable cavity structure is provided, and the requirements of different flight conditions on the performance of the supersonic combustion chamber are met by adjusting the length and the depth of the adjustable cavity.
In order to solve the technical problems, the invention discloses a wide-adaptability supersonic combustion chamber with an adjustable concave cavity structure, which comprises: the device comprises a combustion chamber isolation section, an air guide pipe, a concave cavity depth adjusting module, a communicating pipe, a concave cavity length adjusting module and a combustion chamber expansion section;
the combustion chamber isolation section is communicated with the combustion chamber expansion section;
the cavity depth adjusting module and the cavity length adjusting module are positioned below the expansion section of the combustion chamber to form an adjustable cavity, and the depth and the length of the adjustable cavity are adjusted;
the combustion chamber isolation section is communicated with the concave cavity depth adjusting module through a bleed air pipe;
the cavity depth adjusting module is communicated with the cavity length adjusting module through a communicating pipe.
In the wide adaptability supersonic combustion chamber with the adjustable cavity structure, the cavity depth adjusting module comprises: the device comprises a depth adjusting driving motor base, a depth adjusting driving motor, a depth adjusting screw rod, a concave cavity bottom sealing sliding block, a compression spring and a spring fixing seat;
the spring fixing seat, the compression spring and the concave cavity bottom sealing sliding block are sequentially connected and horizontally arranged to serve as the bottom of the adjustable concave cavity; the sealing sliding block at the bottom of the concave cavity can move in the horizontal direction under the action of the compression spring; the spring fixing seat is tightly attached to the side wall of the depth adjusting module shell under the action of the compression spring;
the depth adjusting driving motor is arranged on a depth adjusting driving motor base, and the depth adjusting driving motor base is fixed on the bottom surface of the depth adjusting module shell;
the depth adjusting screw rod is vertically arranged and connected with the depth adjusting driving motor and is used for adjusting the vertical displacement of the bottom of the adjustable concave cavity under the driving of the depth adjusting driving motor;
a depth adjusting module balance cavity is formed between the depth adjusting module shell and the bottom of the adjustable concave cavity, and the combustion chamber isolation section is communicated with the depth adjusting module balance cavity through a bleed air pipe.
In the wide adaptability supersonic combustion chamber with the adjustable cavity structure, the cavity length adjusting module comprises: the device comprises a length adjusting driving motor base, a length adjusting driving motor, a length adjusting screw rod, an adjustable concave cavity tail edge and a length adjusting module shell;
the length adjusting driving motor base is fixed on the bottom surface of the length adjusting module shell;
the length adjusting driving motor is arranged on the length adjusting driving motor base;
the length adjusting screw rod is horizontally arranged and connected with the length adjusting driving motor and is used for adjusting the horizontal displacement of the tail edge of the adjustable concave cavity under the driving of the length adjusting driving motor;
the inclined plane of the tail edge of the adjustable concave cavity is attached to the inclined plane of the end part of the sealing sliding block at the bottom of the concave cavity;
a length adjusting module balance cavity is formed among the tail edge of the adjustable concave cavity, the length adjusting module shell and the lower wall surface of the expansion section of the combustion chamber, and the depth adjusting module balance cavity is communicated with the length adjusting module balance cavity through a communicating pipe; wherein, the ratio of the diameters of the air entraining pipe and the communicating pipe is 0.8-0.95, so as to ensure that the air flow smoothly enters the balance cavity of the length adjusting module.
In the wide adaptability supersonic combustion chamber with the adjustable concave cavity structure,
the front end opening of the isolation section of the combustion chamber is an inlet of the combustion chamber;
the tail end of the combustion chamber isolation section is provided with an air vent; one end of the air entraining pipe is connected with the air entraining hole, and the other end of the air entraining pipe is communicated with the balance cavity of the depth adjusting module;
the ratio of the areas of the bleed holes to the inlet of the combustion chamber is 0.001-0.003, and the interference of bleed air to the main flow is reduced under the condition that the requirements of the balance cavity of the depth adjusting module and the balance cavity of the length adjusting module on the gas flow are met.
In the wide-adaptability supersonic combustion chamber with the adjustable concave cavity structure, the lower wall surface of the expansion section of the combustion chamber, the tail edge of the adjustable concave cavity, the sealing sliding block at the bottom of the concave cavity and the spring fixing seat all adopt a streamline transition mode so as to reduce flow abrupt change caused by wall surface change.
In the wide-adaptability supersonic combustion chamber with the adjustable concave cavity structure, the rotating speeds of the depth adjusting driving motor and the length adjusting driving motor are 10-500 rad/s so as to meet the requirements of different working conditions on the deformation rate of the adjustable concave cavity.
In the wide-adaptability supersonic combustion chamber with the adjustable concave cavity structure, the rigidity of the compression spring is 20.95-36.30N/mm so as to ensure that the sealing sliding block at the bottom of the concave cavity is always contacted and tightly attached to the tail edge of the adjustable concave cavity, and the spring fixing seat is always contacted and tightly attached to the side wall of the depth adjusting module shell.
In the wide-adaptability supersonic combustion chamber with the adjustable concave cavity structure, the ratio of the pressure of the balance cavity of the depth adjusting module and the pressure of the expansion section of the combustion chamber is 1.01-1.10, so that the pressure in the balance cavity is higher than the pressure of the expansion section of the combustion chamber, and the tightness of the adjustable concave cavity is ensured.
In the wide-adaptability supersonic combustion chamber with the adjustable cavity structure, the ratio of the length to the depth of the adjustable cavity is 5-15, and the requirements of the open cavity, the transition cavity and the closed cavity on the length-depth ratio are met.
In the wide-adaptability supersonic combustion chamber with the adjustable concave cavity structure, the flight Mach number range suitable for the supersonic combustion chamber is 2.0-8.0.
The invention has the following advantages:
(1) The invention discloses a wide-adaptability supersonic combustion chamber with an adjustable concave cavity structure, which can adjust the length and depth of an adjustable concave cavity and greatly broaden the applicable working conditions of the combustion chamber.
(2) The invention discloses a wide-adaptability supersonic combustion chamber with an adjustable concave cavity structure, which adopts two independent driving motors and a screw rod mode, and has stable mechanical structure and various adjustment modes.
(3) The invention discloses a wide-adaptability supersonic combustion chamber with an adjustable concave cavity structure, which adopts a mode of a balance cavity to realize the tightness of the concave cavity adjusting process without introducing a complex structure and has a simple structure.
Drawings
FIG. 1 is a schematic three-dimensional structure of a wide-adaptability supersonic combustor with an adjustable cavity structure according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a cavity structure adjustable wide adaptability supersonic combustor in accordance with an embodiment of the invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the embodiments of the present invention disclosed herein will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1 and 1, in this embodiment, the cavity structure-adjustable wide-adaptability supersonic combustion chamber includes: the device comprises a combustion chamber isolation section 1, a bleed air pipe 2, a cavity depth adjusting module 3, a communicating pipe 4, a cavity length adjusting module 5 and a combustion chamber expansion section 6. Wherein the combustion chamber isolation section 1 is communicated with the combustion chamber expansion section 6; the cavity depth adjusting module 3 and the cavity length adjusting module 5 are positioned below the combustion chamber expansion section 6 to form an adjustable cavity 22, and the depth and the length of the adjustable cavity 22 are adjusted; the combustion chamber isolation section 1 is communicated with the concave cavity depth adjusting module 3 through an air guide pipe 2; the cavity depth adjusting module 3 is communicated with the cavity length adjusting module 5 through a communicating pipe 4.
In this embodiment, as shown in fig. 2, the cavity depth adjusting module 3 may specifically include: the depth adjusting driving motor comprises a depth adjusting driving motor base 10, a depth adjusting driving motor 11, a depth adjusting screw rod 12, a concave cavity bottom sealing sliding block 19, a compression spring 20 and a spring fixing seat 21. The spring fixing seat 21, the compression spring 20 and the concave cavity bottom sealing sliding block 19 are sequentially connected and horizontally arranged to serve as the bottom of the adjustable concave cavity 22; the concave cavity bottom sealing slide block 19 can move in the horizontal direction under the action of the compression spring 20; the spring fixing seat 21 is tightly attached to the side wall of the depth adjusting module shell 23 under the action of the compression spring 20; the depth adjustment driving motor 11 is mounted on the depth adjustment driving motor base 10, and the depth adjustment driving motor base 10 is fixed on the bottom surface of the depth adjustment module housing 23; the depth adjusting screw rod 12 is vertically arranged and connected with the depth adjusting driving motor 11, and is used for realizing the adjustment of the vertical displacement of the bottom of the adjustable concave cavity 22 under the driving of the depth adjusting driving motor 11; a depth adjusting module balance cavity 9 is formed between the depth adjusting module shell 23 and the bottom of the adjustable concave cavity 22, and the combustion chamber isolation section 1 is communicated with the depth adjusting module balance cavity 9 through an air guide pipe 2.
In this embodiment, as shown in fig. 2, the cavity length adjustment module 5 may specifically include: a length adjustment drive motor base 14, a length adjustment drive motor 16, a length adjustment screw 17, an adjustable cavity trailing edge 18, and a length adjustment module housing 24. Wherein the length adjustment drive motor base 14 is fixed on the bottom surface of the length adjustment module housing 24; the length adjustment drive motor 16 is mounted on the length adjustment drive motor base 14; the length adjusting screw rod 17 is horizontally arranged and connected with the length adjusting driving motor 16, and is used for realizing the adjustment of the horizontal displacement of the tail edge 18 of the adjustable concave cavity under the driving of the length adjusting driving motor 16; the inclined plane of the tail edge 18 of the adjustable concave cavity is attached to the inclined plane of the end part of the sealing slide block 19 at the bottom of the concave cavity; the tail edge 18 of the adjustable concave cavity, the length adjusting module shell 24 and the lower wall surface 15 of the expansion section of the combustion chamber form a length adjusting module balancing cavity 13, and the depth adjusting module balancing cavity 9 and the length adjusting module balancing cavity 13 are communicated through a communicating pipe 4.
In the embodiment, the front end of the combustion chamber isolation section 1 is open and is an inlet 7 of the combustion chamber; the tail end of the combustion chamber isolation section 1 is provided with an air vent 8. One end of the air entraining pipe 2 is connected with the air entraining hole 8, and the other end of the air entraining pipe is communicated with the balancing cavity 9 of the depth adjusting module, namely, the air entraining pipe 2 is arranged at the tail end of the isolating section 1 of the combustion chamber, so that the air flow introduced into the balancing cavity 9 of the depth adjusting module can be ensured to have enough pressure. The ratio of the diameters of the air-inducing pipe 2 and the communicating pipe 4 is 0.8-0.95 so as to ensure that the air flow can smoothly enter the length adjusting module balance cavity 13. Because the depth and the length of the adjustable concave cavity are adjustable, the flight Mach number range suitable for the supersonic combustion chamber is 2.0-8.0.
In this embodiment, the ratio of the length L2 to the depth L1 of the adjustable cavity 22 is 5-15 to meet the requirements of the open cavity, the transition cavity and the closed cavity for the depth-to-length ratio. The lower wall surface 15 of the expansion section of the combustion chamber, the tail edge 18 of the adjustable concave cavity, the sealing sliding block 19 at the bottom of the concave cavity and the spring fixing seat 21 all adopt a streamline transition mode, so that flow abrupt changes caused by wall surface changes are reduced to the greatest extent. The rotation speed of the depth adjusting driving motor 11 and the length adjusting driving motor 16 is 10-500 rad/s so as to meet the requirements of different working conditions on the deformation rate of the adjustable concave cavity 22. The rigidity of the compression spring 20 is 20.95-36.30N/mm so as to ensure that the cavity bottom sealing slide block 19 is always contacted and tightly attached to the tail edge 18 of the adjustable cavity, and the spring fixing seat 21 is always contacted and tightly attached to the side wall of the depth adjusting module shell 23. The ratio of the areas of the bleed holes 8 and the combustor inlet 7 is 0.001-0.003, and the interference of bleed air on the main flow is reduced to the greatest extent under the condition that the requirements of the depth adjusting module balance cavity 9 and the length adjusting module balance cavity 13 on the gas flow are met. The ratio of the pressure of the balancing cavity 9 of the depth adjusting module and the balancing cavity 13 of the length adjusting module to the pressure of the expansion section 6 of the combustion chamber is 1.01-1.10, so that the pressure in the balancing cavity is slightly larger than the pressure of the expansion section 6 of the combustion chamber, and the tightness of the adjustable concave cavity 22 is ensured.
In this embodiment, the working principle of the wide-adaptability supersonic combustion chamber with the adjustable cavity structure is as follows: the depth adjusting driving motor 11 drives the depth adjusting screw rod 12 to drive the spring fixing seat 21 to move up and down, so that the depth of the adjustable concave cavity 22 is changed; the length adjusting driving motor 16 drives the length adjusting screw rod 17 to drive the tail edge 18 of the adjustable concave cavity to move back and forth, so that the length of the adjustable concave cavity 22 is changed; in the adjusting process, the compression spring 20 ensures that the sealing sliding block 19 at the bottom of the concave cavity is always in close contact with the tail edge 19 of the adjustable concave cavity, so that the tightness is ensured. Therefore, the invention changes the strokes of the depth adjusting screw rod 12 and the length adjusting screw rod 17 by controlling the depth adjusting driving motor 11 and the length adjusting driving motor 16, realizes the adjustment of the length and the depth of the adjustable concave cavity, further changes the wave system and the vortex system structure of the flow of the supersonic combustion chamber, and realizes the performance adjustment of the supersonic combustion chamber so as to adapt to the performance requirements of different flight working conditions on the supersonic combustion chamber.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
What is not described in detail in the present specification belongs to the known technology of those skilled in the art.
Claims (8)
1. A wide adaptability supersonic combustion chamber with an adjustable concave cavity structure, which is characterized by comprising: the device comprises a combustion chamber isolation section (1), an air entraining pipe (2), a cavity depth adjusting module (3), a communicating pipe (4), a cavity length adjusting module (5) and a combustion chamber expansion section (6);
the combustion chamber isolation section (1) is communicated with the combustion chamber expansion section (6);
the cavity depth adjusting module (3) and the cavity length adjusting module (5) are positioned below the combustion chamber expansion section (6) to form an adjustable cavity (22), and the depth and the length of the adjustable cavity (22) are adjusted;
the combustion chamber isolation section (1) is communicated with the concave cavity depth adjusting module (3) through an air guide pipe (2);
the cavity depth adjusting module (3) is communicated with the cavity length adjusting module (5) through a communicating pipe (4);
wherein:
a cavity depth adjustment module (3), comprising: the device comprises a depth adjusting driving motor base (10), a depth adjusting driving motor (11), a depth adjusting screw rod (12), a concave cavity bottom sealing sliding block (19), a compression spring (20) and a spring fixing seat (21); the spring fixing seat (21), the compression spring (20) and the concave cavity bottom sealing sliding block (19) are sequentially connected and horizontally arranged to serve as the bottom of the adjustable concave cavity (22); wherein, the sealing slide block (19) at the bottom of the concave cavity can move in the horizontal direction under the action of the compression spring (20); the spring fixing seat (21) is tightly attached to the side wall of the depth adjusting module shell (23) under the action of the compression spring (20); the depth adjusting driving motor (11) is arranged on the depth adjusting driving motor base (10), and the depth adjusting driving motor base (10) is fixed on the bottom surface of the depth adjusting module shell (23); the depth adjusting screw rod (12) is vertically arranged and connected with the depth adjusting driving motor (11) and is used for adjusting the vertical displacement of the bottom of the adjustable concave cavity (22) under the driving of the depth adjusting driving motor (11); a depth adjusting module balance cavity (9) is formed between the depth adjusting module shell (23) and the bottom of the adjustable concave cavity (22), and the combustion chamber isolation section (1) is communicated with the depth adjusting module balance cavity (9) through an air guide pipe (2);
a cavity length adjustment module (5) comprising: a length adjusting driving motor base (14), a length adjusting driving motor (16), a length adjusting screw rod (17), an adjustable concave cavity tail edge (18) and a length adjusting module shell (24); wherein the length adjustment driving motor base (14) is fixed on the bottom surface of the length adjustment module shell (24); the length adjusting driving motor (16) is arranged on the length adjusting driving motor base (14); the length adjusting screw rod (17) is horizontally arranged and connected with the length adjusting driving motor (16) and is used for adjusting the horizontal displacement of the tail edge (18) of the adjustable concave cavity under the driving of the length adjusting driving motor (16); the inclined plane of the tail edge (18) of the adjustable concave cavity is attached to the inclined plane of the end part of the sealing slide block (19) at the bottom of the concave cavity; a length adjusting module balance cavity (13) is formed among the tail edge (18) of the adjustable concave cavity, the length adjusting module shell (24) and the lower wall surface (15) of the expansion section of the combustion chamber, and the depth adjusting module balance cavity (9) is communicated with the length adjusting module balance cavity (13) through a communicating pipe (4); wherein, the diameter ratio of the air entraining pipe (2) and the communicating pipe (4) is 0.8-0.95, so as to ensure that the air flow smoothly enters the length adjusting module balance cavity (13).
2. The cavity structure adjustable wide adaptability supersonic combustion chamber according to claim 1, wherein,
the front end of the combustion chamber isolation section (1) is provided with an opening, which is a combustion chamber inlet (7);
the tail end of the combustion chamber isolation section (1) is provided with an air vent (8); one end of the air entraining pipe (2) is connected with the air entraining hole (8), and the other end of the air entraining pipe is communicated with the depth adjusting module balance cavity (9);
the ratio of the areas of the air guiding holes (8) and the combustion chamber inlet (7) is 0.001-0.003, and the interference of air guiding on the main flow is reduced under the condition that the requirements of the depth adjusting module balance cavity (9) and the length adjusting module balance cavity (13) on the gas flow are met.
3. The cavity structure adjustable wide adaptability supersonic combustion chamber according to claim 1, wherein the combustion chamber expansion section lower wall surface (15) and the adjustable cavity tail edge (18), the cavity bottom sealing slide block (19) and the spring fixing seat (21) all adopt a streamline transition mode so as to reduce flow abrupt change caused by wall surface change.
4. The adjustable wide-adaptability supersonic combustion chamber with the cavity structure according to claim 1, wherein the rotating speeds of the depth adjusting driving motor (11) and the length adjusting driving motor (16) are 10-500 rad/s so as to meet the requirements of different working conditions on the deformation rate of the adjustable cavity (22).
5. The cavity structure adjustable wide adaptability supersonic combustion chamber according to claim 1, wherein the rigidity of the compression spring (20) is 20.95-36.30N/mm, so as to ensure that the cavity bottom sealing slide block (19) is always contacted and tightly fitted with the tail edge (18) of the adjustable cavity, and the spring fixing seat (21) is always contacted and tightly fitted with the side wall of the depth adjusting module shell (23).
6. The cavity structure adjustable wide adaptability supersonic combustion chamber according to claim 1, characterized in that the ratio of the pressure of the depth adjusting module balance chamber (9) and the length adjusting module balance chamber (13) to the pressure of the combustion chamber expansion section (6) is 1.01-1.10, so that the pressure inside the balance chamber is larger than the pressure of the combustion chamber expansion section (6) to ensure the tightness of the adjustable cavity (22).
7. The cavity structure adjustable wide adaptability supersonic combustion chamber according to claim 1, characterized in that the ratio of the length and depth of the adjustable cavity (22) is 5-15, meeting the requirements of open cavity, transition cavity and closed cavity on the depth-to-length ratio.
8. The cavity structure adjustable wide adaptability supersonic combustion chamber according to claim 1, wherein the supersonic combustion chamber is adapted to a flight mach number in the range of 2.0-8.0.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211035036.4A CN115585480B (en) | 2022-08-26 | 2022-08-26 | Wide-adaptability supersonic combustion chamber with adjustable concave cavity structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211035036.4A CN115585480B (en) | 2022-08-26 | 2022-08-26 | Wide-adaptability supersonic combustion chamber with adjustable concave cavity structure |
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| CN115585480A CN115585480A (en) | 2023-01-10 |
| CN115585480B true CN115585480B (en) | 2023-12-29 |
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| CN102374071A (en) * | 2011-09-15 | 2012-03-14 | 西北工业大学 | Center rocket type bimodal ramjet with circular structure |
| CN105180212A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber of supersonic combustion ramjet engine |
| CN112361379A (en) * | 2020-11-18 | 2021-02-12 | 中国人民解放军国防科技大学 | Ignition structure of supersonic concave cavity combustion chamber and scramjet engine |
| CN112413644A (en) * | 2020-12-04 | 2021-02-26 | 中国人民解放军国防科技大学 | Scramjet engine and double-throat combustion chamber thereof |
| CN113137634A (en) * | 2021-06-02 | 2021-07-20 | 厦门大学 | Variable-structure bimodal stamping combustion chamber |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JP6090638B2 (en) * | 2015-01-09 | 2017-03-08 | マツダ株式会社 | Engine combustion chamber structure |
| US10563867B2 (en) * | 2015-09-30 | 2020-02-18 | General Electric Company | CMC articles having small complex features for advanced film cooling |
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2022
- 2022-08-26 CN CN202211035036.4A patent/CN115585480B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102374071A (en) * | 2011-09-15 | 2012-03-14 | 西北工业大学 | Center rocket type bimodal ramjet with circular structure |
| CN105180212A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber of supersonic combustion ramjet engine |
| CN112361379A (en) * | 2020-11-18 | 2021-02-12 | 中国人民解放军国防科技大学 | Ignition structure of supersonic concave cavity combustion chamber and scramjet engine |
| CN112413644A (en) * | 2020-12-04 | 2021-02-26 | 中国人民解放军国防科技大学 | Scramjet engine and double-throat combustion chamber thereof |
| CN113137634A (en) * | 2021-06-02 | 2021-07-20 | 厦门大学 | Variable-structure bimodal stamping combustion chamber |
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| CN115585480A (en) | 2023-01-10 |
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