CN113217949A - Combustion chamber diverging and cooling structure and ramjet combustion chamber - Google Patents
Combustion chamber diverging and cooling structure and ramjet combustion chamber Download PDFInfo
- Publication number
- CN113217949A CN113217949A CN202110552219.2A CN202110552219A CN113217949A CN 113217949 A CN113217949 A CN 113217949A CN 202110552219 A CN202110552219 A CN 202110552219A CN 113217949 A CN113217949 A CN 113217949A
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- Prior art keywords
- flame tube
- combustion chamber
- cooling
- combustor
- temperature
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Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 61
- 238000001816 cooling Methods 0.000 title claims abstract description 56
- 239000000463 material Substances 0.000 claims abstract description 26
- 239000000112 cooling gas Substances 0.000 claims abstract description 22
- 239000007789 gas Substances 0.000 claims abstract description 13
- 230000001681 protective effect Effects 0.000 claims abstract description 7
- 230000009471 action Effects 0.000 claims abstract description 5
- 239000007921 spray Substances 0.000 claims description 9
- 239000000956 alloy Substances 0.000 claims description 5
- 229910045601 alloy Inorganic materials 0.000 claims description 5
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 238000005096 rolling process Methods 0.000 claims description 5
- 238000005245 sintering Methods 0.000 claims description 5
- 239000003381 stabilizer Substances 0.000 claims description 5
- 238000009941 weaving Methods 0.000 claims description 5
- 230000005068 transpiration Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 239000003921 oil Substances 0.000 description 3
- 230000035900 sweating Effects 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000008520 organization Effects 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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 combustion chamber divergent cooling structure and a ramjet combustion chamber, which comprise a flame tube made of high-temperature-resistant loose materials, wherein an annular crack formed between a combustion chamber outer shell and the flame tube is used for taking partial air from airflow at an inlet of the combustion chamber as cooling air; the cooling gas flows in the annular crack along the axial direction of the combustion chamber, and is in heat convection with the outer side wall surface of the flame tube, meanwhile, under the action of pressure difference, the cooling gas in the annular crack enters the flame tube through the divergent cooling holes on the wall surface of the flame tube, radial heat exchange is realized with the inside of the flame tube, and a continuous protective gas film is formed on the inner side wall of the flame tube. The cooling structure reduces the required cooling air quantity on one hand, improves the specific impulse and thrust performance of the engine, reduces the mass of the thermal protection structure of the combustion chamber on the other hand, and improves the load mass of the aircraft or increases the range.
Description
Technical Field
The invention designs a cooling structure, and particularly relates to a combustion chamber divergent cooling structure and a ramjet combustion chamber.
Background
During supersonic flight of the ramjet, the hot parts are subjected to high heat flux density, and the heat protection technology is one of the key technologies for failure. The ramjet combustion chamber is one of the key points of thermal protection, the temperature of air flow in the combustion chamber is high, the thermal protection area is large, the air quantity for cooling the wall surface of the combustion chamber is increased continuously along with the increase of the flying speed, and a light and efficient mode is necessary to be adopted for thermal protection of the combustion chamber.
The conventional heat protection mode of the combustion chamber of the ramjet engine is air film cooling, and the specific scheme is as follows: the air in the inlet edge of the combustor is sprayed through a series of annular slots or discrete holes to the inner wall of the flame tube to form a cooling film between the wall and the hot combustion gas to protect the flame tube. However, as the flying speed of the ramjet increases, the amount of air used for cooling the combustion chamber needs to be increased continuously to ensure the thermal protection effect, so that a large amount of air is used for cooling and does not participate in combustion, and the specific impulse and thrust performance of the ramjet are obviously reduced.
Disclosure of Invention
The invention provides a divergent cooling structure of a combustion chamber, aiming at solving the problems that after the flying speed of an engine is improved, the air quantity participating in cooling is continuously increased when air film cooling is adopted, so that a large amount of air is used for cooling but does not participate in combustion, and the specific impulse and thrust performance of the engine are obviously reduced.
In order to achieve the purpose, the specific technical scheme of the invention is as follows:
a divergent cooling structure of a combustion chamber comprises a flame tube made of high-temperature-resistant loose materials, wherein an annular crack formed between an outer shell of the combustion chamber and the flame tube is used for taking partial air from airflow at an inlet of the combustion chamber as cooling air; the cooling gas flows in the annular crack along the axial direction of the combustion chamber, and is in heat convection with the outer side wall surface of the flame tube, meanwhile, under the action of pressure difference, the cooling gas in the annular crack enters the flame tube through the divergent cooling holes on the wall surface of the flame tube, radial heat exchange is realized with the inside of the flame tube, and a continuous protective gas film is formed on the inner side wall of the flame tube.
The principle of the cooling structure is as follows: firstly, the heat can be taken away by cooling gas flowing along the axial path of the annular crack and the flow of a protective gas film on the inner wall of the flame tube; secondly, radial heat exchange is formed between cooling gas in the annular crack and the flame tube, so that the cooling effect can be further improved, and the thermal protection performance is ensured.
Further, the high-temperature-resistant loose material is formed by weaving, sintering and rolling a high-temperature alloy wire mesh with the diameter of 10-100 mu m.
Furthermore, the flame tube is made of high-temperature-resistant loose material plates through sheet metal forming.
Further, in order to increase the rigidity of the flame tube, the flame tube is pressed into a corrugated structure.
Further, the flame tube is fixed inside the combustion chamber in a screw connection mode.
Meanwhile, the invention also provides a ramjet combustion chamber, which comprises an oil injection device, a flame stabilizer, a combustion chamber outer shell and a spray pipe; the improvement is that: the combustor comprises a combustor outer shell and a combustor liner, wherein the combustor liner is coaxially arranged in the combustor outer shell and is made of high-temperature-resistant loose materials, and an annular crack formed between the combustor outer shell and the combustor liner is used for taking partial air from airflow at an inlet of a combustor as cooling air; the cooling gas flows in the annular crack along the axial direction of the combustion chamber, and is in heat convection with the outer side wall surface of the flame tube, meanwhile, under the action of pressure difference, the cooling gas in the annular crack enters the flame tube through the divergent cooling holes on the wall surface of the flame tube, radial heat exchange is realized with the inside of the flame tube, and a continuous protective gas film is formed on the inner side wall of the flame tube.
Further, the high-temperature-resistant loose material is formed by weaving, sintering and rolling a high-temperature alloy wire mesh with the diameter of 10-100 mu m.
Furthermore, the flame tube is made of high-temperature-resistant loose material plates through sheet metal forming.
Further, in order to increase the rigidity of the flame tube, the flame tube is pressed into a corrugated structure.
Further, the flame tube is fixed inside the combustion chamber in a screw connection mode.
Compared with the prior art, the invention has the following advantages:
1. the invention adopts the flame tube made of high-temperature resistant loose materials arranged in the combustion chamber shell and forms the annular crack, thereby forming a cooling structure with the functions of air film cooling and sweating cooling. The transpiration cooling is suitable for ramjet combustion chamber thermal protection. This is because the heat exchange area between the air and the flame tube is increased by the divergent cooling, and the temperature gradient of the flame tube is reduced; the cooling structure can realize the directional flow of cooling air in the loose material, and improve the heat exchange efficiency; and on the hot side of the flame tube, full-gas film protection can be formed.
2. According to the invention, the high-temperature-resistant loose material is used as the material of the flame tube, cooling gas can flow directionally in the loose material, the heat exchange area in the structure is greatly increased, the cooling effect is good, and the heat exchange efficiency is high; the flow resistance and the divergence of the cooling air can be controlled by the wire mesh gaps and the directional sweating holes; the inner wall of the flame tube can form continuous full-gas film protection, and the gas film is not easily disturbed by the flow in the combustion chamber.
3. The invention adopts high temperature resistant loose material to cool, which improves the heat exchange capability of the cooling gas, reduces the cooling gas consumption, increases the air for the combustion chamber organization, and has high engine performance; under the condition of the same cooling air intake ratio, the engine can work under the conditions of higher Mach number and worse thermal environment.
Drawings
Fig. 1 is a schematic view showing an embodiment of applying the cooling structure of the present invention to a combustion chamber of a ramjet engine.
1-oil injection device, 2-flame stabilizer, 3-flame tube, 4-combustion chamber outer shell, 5-spray pipe and 6-annular crack.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The present embodiment gives a concrete structure of applying the transpiration cooling structure to the ram engine combustion chamber. As shown in fig. 1, the ramjet combustion chamber comprises: oil injection device 1, flame holder 2, flame tube 3, combustion chamber shell 4 and spray tube 5.
The fuel injection device 1 plays a role in injecting fuel, so that the fuel is effectively mixed with air;
the flame stabilizer 2 establishes a proper backflow area in airflow to provide conditions for further mixing and organizing stable combustion of fuel oil; the combustion of the fuel oil and the air is organized downstream of the flame stabilizer 2 to form high-temperature combustion gas.
The flame tube 3 is made of high-temperature-resistant loose materials, and an annular crack 6 is formed between the outer shell 4 of the combustion chamber and the flame tube 3 and used for taking part of air from airflow at the inlet of the combustion chamber as cooling air; specifically, the leading edge of the liner 3 is arranged at the inlet of the combustion chamber 4 where air is not mixed with fuel and the air temperature is low; the rear edge of the flame tube 3 is arranged at the inlet position of the spray pipe 5, and cooling air discharged from the rear edge of the flame tube 3 flows downstream along the wall surface of the spray pipe 5 to form an air film, so that the thermal protection effect on the spray pipe is achieved;
the cooling gas flows in the annular crack 6 along the axial direction of the combustion chamber and is in heat convection with the outer side wall surface of the flame tube 3, radial heat exchange is formed between the cooling gas in the annular crack 6 and the flame tube 3 (specifically, the cooling gas is forced to pass through the loose wall surface of the flame tube by the pressure difference between the annular crack and the flame tube to form radial heat exchange), and a continuous protective gas film is formed on the inner wall of the flame tube. The cooling gas flows in the annular crack 6 along the axial direction and the gas film flows to take away the heat of the flame tube, thereby playing a role in thermal protection; the cooling air discharged from the rear edge of the flame tube flows downstream along the wall surface of the spray pipe 5 to form an air film, so that the spray pipe is protected thermally.
In the embodiment, the high-temperature-resistant loose material used by the flame tube 3 is formed by weaving, sintering and rolling a high-temperature alloy wire mesh with the diameter of 10-100 μm; the direction and flow resistance of the airflow passing through the loose material are specifically designed according to the thermal environment, the cooling air quantity, the cooling air circulation distribution and the like, and the production process is adopted to realize the purpose. The flame tube 3 can be formed by sheet metal process using plate material, and the flame tube 3 can be pressed into a corrugated structure to increase rigidity. The flame tube 3 can be connected with the outer shell of the combustion chamber by welding the structures such as the mounting seat, and the embodiment adopts screw connection.
In summary, the ram combustor of the present embodiment has the following advantages:
1. high-temperature-resistant loose materials (such as large-size directional diffusion cooling panels rolled by wire materials) are used as flame tube materials, cooling gas can flow in the annular crack along the axial direction, and the mode of radial heat exchange through pressure difference is combined, so that the heat exchange area of the structure is increased, the cooling effect is good, and the heat exchange efficiency is high; the flow resistance and the divergence of the cooling air can be controlled by the wire mesh gaps and the directional sweating holes; the inner wall of the flame tube can form continuous full-gas film protection, and the gas film is not easily disturbed by the flow in the combustion chamber.
2. Because the high-temperature resistant loose material is adopted for cooling, the heat exchange capacity of the cooling gas is improved, the consumption of the cooling gas is reduced, the air which can be used for the organization of a combustion chamber is increased, and the performance of the engine is high; under the condition of the same cooling air intake ratio, the engine can work under the conditions of higher Mach number and worse thermal environment.
Claims (10)
1. A combustion chamber divergent cooling structure is characterized in that: the annular crack formed between the outer shell of the combustion chamber and the flame tube is used for taking partial air from airflow at the inlet of the combustion chamber as cooling air; the cooling gas flows in the annular crack along the axial direction of the combustion chamber, and is in heat convection with the outer side wall surface of the flame tube, meanwhile, under the action of pressure difference, the cooling gas in the annular crack enters the flame tube through the divergent cooling holes on the wall surface of the flame tube, radial heat exchange is realized with the inside of the flame tube, and a continuous protective gas film is formed on the inner side wall of the flame tube.
2. The combustor transpiration cooling structure of claim 1, wherein: the high-temperature-resistant loose material is formed by weaving, sintering and rolling a high-temperature alloy wire mesh with the diameter of 10-100 mu m.
3. The combustor transpiration cooling structure of claim 2, wherein: the flame tube is made of high-temperature-resistant loose material plates through sheet metal forming.
4. The combustor divergent cooling structure as claimed in claim 3, wherein: the flame tube is pressed into a corrugated structure.
5. The combustor divergent cooling structure as claimed in claim 4, wherein: the flame tube is fixed inside the combustion chamber in a screw connection mode.
6. A ramjet combustion chamber comprises an oil injection device, a flame stabilizer, a combustion chamber outer shell and a spray pipe; the method is characterized in that: the combustor comprises a combustor outer shell and a combustor liner, wherein the combustor liner is coaxially arranged in the combustor outer shell and is made of high-temperature-resistant loose materials, and an annular crack formed between the combustor outer shell and the combustor liner is used for taking partial air from airflow at an inlet of a combustor as cooling air; the cooling gas flows in the annular crack along the axial direction of the combustion chamber, and is in heat convection with the outer side wall surface of the flame tube, meanwhile, under the action of pressure difference, the cooling gas in the annular crack enters the flame tube through the divergent cooling holes on the wall surface of the flame tube, radial heat exchange is realized with the inside of the flame tube, and a continuous protective gas film is formed on the inner side wall of the flame tube.
7. The ramjet combustion chamber of claim 6, wherein: the high-temperature-resistant loose material is formed by weaving, sintering and rolling a high-temperature alloy wire mesh with the diameter of 10-100 mu m.
8. The ramjet combustion chamber of claim 7, wherein: the flame tube is made of high-temperature-resistant loose material plates through sheet metal forming.
9. The ramjet combustion chamber of claim 8, wherein: the flame tube is pressed into a corrugated structure.
10. The ramjet combustion chamber of claim 9, wherein: the flame tube is fixed inside the combustion chamber in a screw connection mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110552219.2A CN113217949A (en) | 2021-05-20 | 2021-05-20 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110552219.2A CN113217949A (en) | 2021-05-20 | 2021-05-20 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113217949A true CN113217949A (en) | 2021-08-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110552219.2A Pending CN113217949A (en) | 2021-05-20 | 2021-05-20 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115111603A (en) * | 2022-05-31 | 2022-09-27 | 哈尔滨工程大学 | Double-wall structure combustion chamber flame tube of micro gas turbine with cooling structure |
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
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2021
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115111603A (en) * | 2022-05-31 | 2022-09-27 | 哈尔滨工程大学 | Double-wall structure combustion chamber flame tube of micro gas turbine with cooling structure |
| CN115111603B (en) * | 2022-05-31 | 2023-09-29 | 哈尔滨工程大学 | Combustion chamber flame tube with cooling structure for miniature gas turbine and double-layer wall structure |
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
| CN115493163B (en) * | 2022-09-06 | 2024-02-20 | 清华大学 | Combustion chamber flame tube and high-efficiency cooling method thereof |
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Application publication date: 20210806 |