CN111456866A - Cooling liquid film forming structure of liquid rocket engine - Google Patents
Cooling liquid film forming structure of liquid rocket engine Download PDFInfo
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- CN111456866A CN111456866A CN202010288944.9A CN202010288944A CN111456866A CN 111456866 A CN111456866 A CN 111456866A CN 202010288944 A CN202010288944 A CN 202010288944A CN 111456866 A CN111456866 A CN 111456866A
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- distribution
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- thrust chamber
- film forming
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a cooling liquid film forming structure of a liquid rocket engine, which comprises an inlet pipe connected to the side wall of a thrust chamber, wherein the end part of the inlet pipe is communicated with a diffusion cavity positioned in the side wall of the thrust chamber, the diffusion cavity is communicated along the circumferential direction of the thrust chamber, and a distribution cavity communicated along the circumferential direction is arranged in the side wall of the thrust chamber; an intermediate partition plate is arranged between the diffusion cavity and the distribution cavity at intervals, communication holes are formed in the intermediate partition plate and are circumferentially arranged at intervals, and distribution holes are formed between the distribution cavity and the inner cavity of the thrust chamber and are circumferentially arranged at intervals. The invention can ensure that the deviation of the coolant flow in each distribution pipe is within 3 percent, effectively ensures the forming thickness uniformity of the cooling liquid film on the wall surface of the thrust chamber, and simultaneously improves the reliability of the engine.
Description
Technical Field
The invention relates to the field of active cooling of liquid rocket engines, in particular to a cooling liquid film forming structure of a liquid rocket engine.
Background
At present, the temperature of fuel gas in a combustion chamber of a rocket engine can reach 3000-4700K, the inner wall of the whole thrust chamber is strongly heated, and the heat flux density of the inner wall surface of the thrust chamber is very high, so that the thrust chamber needs to adopt an effective cooling technology or improve the heat resistance of heated parts to ensure that the heated parts can normally work. The cooling techniques commonly employed are classified into convective cooling, film cooling, transpiration cooling, radiative cooling, and ablative cooling.
In the prior art, a thrust chamber of a liquid rocket engine is generally cooled by liquid films near a throat part of a spray pipe with the highest heat flux density, the cooling effect depends on the circumferential uniformity of the thickness of the cooling liquid film, and the effective measure is important for ensuring that the thickness of the cooling liquid film is uniformly distributed in the circumferential direction. In view of this, it is necessary to develop and design a cooling liquid film forming structure of a liquid rocket engine.
Disclosure of Invention
Aiming at the defects and shortcomings of the prior art, the invention provides a cooling liquid film forming structure of a liquid rocket engine, which can ensure that the deviation of the coolant flow in each distribution pipe is within the range of 3%, effectively ensure the forming thickness uniformity of the cooling liquid film on the wall surface of a thrust chamber, and simultaneously improve the reliability of the engine.
The technical scheme adopted by the invention is as follows:
a cooling liquid film forming structure of a liquid rocket engine comprises an inlet pipe connected to the side wall of a thrust chamber, wherein the end part of the inlet pipe is communicated with a diffusion cavity positioned in the side wall of the thrust chamber, the diffusion cavity is communicated along the circumferential direction of the thrust chamber, and a distribution cavity communicated along the circumferential direction of the thrust chamber is arranged in the side wall of the thrust chamber; intermediate partition plates are arranged between the diffusion cavity and the distribution cavity at intervals, communication holes are formed in the intermediate partition plates and are circumferentially arranged at intervals, and distribution holes are formed between the distribution cavity and the inner cavity of the thrust chamber and are circumferentially arranged at intervals.
Furthermore, the distribution holes are obliquely arranged, and distribution pipes are matched in the distribution holes.
Furthermore, an inlet pipe is connected to the side wall of the thrust chamber.
Furthermore, a middle partition plate is arranged between the lower bottom wall of the diffusion cavity and the adjacent side wall of the distribution cavity, and the communication hole is formed in the middle partition plate.
Still further, the distribution chamber is located below the diffusion chamber, and the distribution hole is located below the distribution chamber.
Further, the communication holes are arranged at equal intervals in the circumferential direction of the intermediate partition, and the distribution holes are arranged at equal intervals in the circumferential direction of the distribution chamber.
Furthermore, the coolant enters the diffusion cavity from the inlet pipe, gradually fills the diffusion cavity, then enters the distribution cavity through the communication holes on the middle partition plate, and gradually fills the distribution cavity, and then enters the inner wall of the thrust chamber through the distribution pipes to form a liquid film.
Further, the diameter of the distribution pipe is smaller than that of the communication hole.
Compared with the prior art, the invention has the following beneficial technical effects:
1. liquid film cooling generally adopts the mode of single import pipe, leads to producing obvious striking effect after the coolant of entrance perpendicularly gets into the ring chamber, and the pressure of striking department is great, and the flow in the distributing pipe of relevant position will be obviously higher than the flow in other pipelines for the thickness of liquid film is very inhomogeneous, influences the formation of liquid film even. Second, a single inlet tube configuration may result in multiple separation zones circumferentially within the annulus, such that the flow parameter distribution varies widely across the circumference of the annulus. If adopt a plurality of import pipe modes, then can increase the connection structure with outside pipeline for overall structure is complicated and the reliability reduces. The cooling liquid film forming device has good feasibility of structural design and assembly, and the cooling agent sequentially passes through the diffusion cavity, the middle partition plate and the distribution cavity based on the design principle of hydrodynamics, so that the problems of most cooling liquid film forming structures in the prior art can be solved.
2. The middle partition plate is arranged between the diffusion cavity and the distribution cavity in an interval mode, so that the impact effect of the coolant fluid at the inlet on the flow distribution in each distribution pipe is greatly weakened, and the nonuniformity of the circumferential flow of the coolant is greatly weakened through the collection and redistribution effects of the diffusion cavity and the distribution cavity. The coolant flow deviation in each distribution pipe can be guaranteed within the range of 3%, the uniformity of the forming thickness of a cooling liquid film on the wall surface of the thrust chamber is effectively guaranteed, and meanwhile the reliability of the engine is improved.
Drawings
Fig. 1 is a schematic view of the internal structure of the present invention.
FIG. 2 is a schematic view of the installation of the intermediate deck of the present invention.
Fig. 3 is an external structural view of the present invention.
Reference numerals: 1. an inlet pipe; 2. a diffusion chamber; 3. a middle partition plate; 4. a communicating hole; 5. a distribution chamber; 6. a distribution pipe; 7. a thrust chamber; 8. the inner wall of the thrust chamber.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to the attached drawings, the cooling liquid film forming structure of the liquid rocket engine disclosed by the invention comprises an inlet pipe 1 connected to the side wall of a thrust chamber 7, wherein the end part of the inlet pipe 1 is communicated with a diffusion cavity 2 positioned in the side wall of the thrust chamber 7, the diffusion cavity 2 is communicated along the circumferential direction of the thrust chamber 7, and a distribution cavity 5 communicated along the circumferential direction is arranged in the side wall of the thrust chamber 7; a middle partition plate 3 is arranged between the diffusion cavity 2 and the distribution cavity 5 at intervals, communication holes 4 which are arranged at equal intervals along the circumferential direction are formed in the middle partition plate 3, distribution holes are formed between the distribution cavity 5 and an inner cavity of the thrust chamber 7, and the distribution holes are arranged at equal intervals along the circumferential direction of the distribution cavity 5.
Referring to fig. 1, the distribution holes are arranged obliquely, an included angle smaller than 90 degrees is formed between the central line of the distribution holes and the central line of the thrust chamber 7, and the distribution pipes 6 are matched in the distribution holes. A middle partition plate 3 is arranged between the lower bottom wall of the diffusion cavity 2 and the adjacent side wall of the distribution cavity 5, a communication hole 4 is formed in the middle partition plate 3, and the communication between the diffusion cavity 2 and the distribution cavity 5 is realized through the communication hole 4; the distribution cavity 5 is positioned below the diffusion cavity 2, the distribution holes are positioned below the distribution cavity 5, and the diameter of the distribution pipe 6 is smaller than that of the communication hole 4.
The implementation principle of the embodiment is as follows: the coolant enters the diffusion cavity 2 from an inlet pipe 1 on the side wall of the thrust chamber 7, gradually fills the diffusion cavity 2, then enters the distribution cavity 5 through the communication holes 4 on the middle partition plate 3, gradually fills the distribution cavity 5, then enters the inner wall 8 of the thrust chamber through the distribution pipes 6 to form a liquid film, and the liquid film cools the inner wall 8 of the thrust chamber. The middle partition plate 3 is arranged between the diffusion cavity 2 and the distribution cavity 5 in an interval mode, so that the impact effect of the coolant fluid at the inlet on the flow distribution in each distribution pipe 6 is greatly weakened, and the nonuniformity of the circumferential flow of the coolant is greatly weakened through the collection and redistribution effects of the diffusion cavity 2 and the distribution cavity 5. In addition, the diameter of the communication hole 4 on the middle partition plate 3 can be adjusted, so that the function of adjusting the whole pressure drop can be realized.
The embodiments of the present invention are preferred embodiments of the present invention, and the scope of the present invention is not limited by these embodiments, so: all equivalent changes made according to the structure, shape and principle of the invention are covered by the protection scope of the invention.
Claims (8)
1. A cooling liquid film forming structure of a liquid rocket engine comprises an inlet pipe (1) connected to the side wall of a thrust chamber (7), and is characterized in that the end part of the inlet pipe (1) is communicated with a diffusion cavity (2) positioned in the side wall of the thrust chamber (7), the diffusion cavity (2) is communicated along the circumferential direction of the thrust chamber (7), and a distribution cavity (5) communicated along the circumferential direction is arranged in the side wall of the thrust chamber (7); intermediate partition plates (3) are arranged between the diffusion cavity (2) and the distribution cavity (5) at intervals, communication holes (4) which are arranged at intervals along the circumferential direction are formed in the intermediate partition plates (3), and distribution holes which are arranged at intervals along the circumferential direction are formed between the distribution cavity (5) and an inner cavity of the thrust chamber (7).
2. The coolant film forming structure of a liquid rocket engine according to claim 1, wherein said distribution holes are obliquely arranged, and distribution pipes (6) are fitted in the distribution holes.
3. The coolant film forming structure of a liquid rocket engine according to claim 1, wherein an inlet pipe (1) is connected to a side wall of said thrust chamber (7).
4. The coolant film forming structure of a liquid rocket engine according to claim 1, wherein a middle partition plate (3) is arranged between the lower bottom wall of the diffusion chamber (2) and the adjacent side wall of the distribution chamber (5), and the communication holes (4) are opened on the middle partition plate (3).
5. The coolant film forming structure of a liquid rocket engine according to claim 4, wherein the distribution chamber (5) is located below the diffusion chamber (2), and the distribution holes are located below the distribution chamber (5).
6. The coolant film forming structure of a liquid rocket engine according to claim 5, wherein the communication holes (4) are arranged at equal intervals in the circumferential direction of the intermediate diaphragm (3), and the distribution holes are arranged at equal intervals in the circumferential direction of the distribution chamber (5).
7. The cooling liquid film forming structure of the liquid rocket engine according to any one of claims 2-6, wherein the coolant enters the diffusion chamber (2) from the inlet pipe (1), gradually fills the diffusion chamber (2), then enters the distribution chamber (5) through each communication hole (4) on the middle partition plate (3), and after gradually filling the distribution chamber (5), enters the inner wall (8) of the thrust chamber through each distribution pipe (6) to form a liquid film.
8. The coolant film forming structure of a liquid rocket engine according to claim 7, wherein the diameter of the distribution pipe (6) is smaller than the diameter of the communication hole (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010288944.9A CN111456866A (en) | 2020-04-14 | 2020-04-14 | Cooling liquid film forming structure of liquid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010288944.9A CN111456866A (en) | 2020-04-14 | 2020-04-14 | Cooling liquid film forming structure of liquid rocket engine |
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| CN111456866A true CN111456866A (en) | 2020-07-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010288944.9A Pending CN111456866A (en) | 2020-04-14 | 2020-04-14 | Cooling liquid film forming structure of liquid rocket engine |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111963339A (en) * | 2020-08-19 | 2020-11-20 | 西安航天动力研究所 | Liquid film cooling rail attitude control engine thrust chamber |
| CN112832928A (en) * | 2021-03-05 | 2021-05-25 | 中国科学院力学研究所 | Method for designing cooling structure with equal inner wall strength for rocket engine |
| CN113006970A (en) * | 2021-02-26 | 2021-06-22 | 陕西蓝箭航天技术有限公司 | Liquid rocket engine cyclone liquid film cooling structure and rocket engine |
| CN113530718A (en) * | 2021-08-31 | 2021-10-22 | 西安航天动力研究所 | Body module for hot test of rocket engine thrust chamber |
| CN115263606A (en) * | 2022-09-23 | 2022-11-01 | 北京星河动力装备科技有限公司 | Engine thrust chamber, rocket engine and liquid rocket |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1187946A (en) * | 1956-11-09 | 1959-09-17 | Armstrong Siddeley Motors Ltd | Combustion chamber |
| US4369920A (en) * | 1979-12-08 | 1983-01-25 | Messerschmitt-Bolkow-Blohm Gmbh | Arrangement to cool the thrust nozzle for a rocket engine |
| JP2012189010A (en) * | 2011-03-11 | 2012-10-04 | Ihi Aerospace Co Ltd | Nozzle for liquid rocket engine |
| CN104948347A (en) * | 2014-03-31 | 2015-09-30 | 北京航天动力研究所 | Thrust chamber collector with flow uniformizing function |
| CN105089852A (en) * | 2014-05-06 | 2015-11-25 | 中国航天科技集团公司第六研究院第十一研究所 | Combustion chamber inner liner cooling structure |
| CN107956601A (en) * | 2017-06-15 | 2018-04-24 | 葛明龙 | One group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate |
-
2020
- 2020-04-14 CN CN202010288944.9A patent/CN111456866A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1187946A (en) * | 1956-11-09 | 1959-09-17 | Armstrong Siddeley Motors Ltd | Combustion chamber |
| US4369920A (en) * | 1979-12-08 | 1983-01-25 | Messerschmitt-Bolkow-Blohm Gmbh | Arrangement to cool the thrust nozzle for a rocket engine |
| JP2012189010A (en) * | 2011-03-11 | 2012-10-04 | Ihi Aerospace Co Ltd | Nozzle for liquid rocket engine |
| CN104948347A (en) * | 2014-03-31 | 2015-09-30 | 北京航天动力研究所 | Thrust chamber collector with flow uniformizing function |
| CN105089852A (en) * | 2014-05-06 | 2015-11-25 | 中国航天科技集团公司第六研究院第十一研究所 | Combustion chamber inner liner cooling structure |
| CN107956601A (en) * | 2017-06-15 | 2018-04-24 | 葛明龙 | One group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111963339A (en) * | 2020-08-19 | 2020-11-20 | 西安航天动力研究所 | Liquid film cooling rail attitude control engine thrust chamber |
| CN111963339B (en) * | 2020-08-19 | 2021-07-20 | 西安航天动力研究所 | Liquid film cooling rail attitude control engine thrust chamber |
| CN113006970A (en) * | 2021-02-26 | 2021-06-22 | 陕西蓝箭航天技术有限公司 | Liquid rocket engine cyclone liquid film cooling structure and rocket engine |
| CN113006970B (en) * | 2021-02-26 | 2022-05-27 | 陕西蓝箭航天技术有限公司 | Liquid rocket engine cyclone liquid film cooling structure and rocket engine |
| CN112832928A (en) * | 2021-03-05 | 2021-05-25 | 中国科学院力学研究所 | Method for designing cooling structure with equal inner wall strength for rocket engine |
| CN112832928B (en) * | 2021-03-05 | 2022-04-22 | 中国科学院力学研究所 | Method for designing cooling structure with equal inner wall strength for rocket engine |
| CN113530718A (en) * | 2021-08-31 | 2021-10-22 | 西安航天动力研究所 | Body module for hot test of rocket engine thrust chamber |
| CN115263606A (en) * | 2022-09-23 | 2022-11-01 | 北京星河动力装备科技有限公司 | Engine thrust chamber, rocket engine and liquid rocket |
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Application publication date: 20200728 |