CN107620654B - Coaxial jet mixer of hydrogen-oxygen expansion cycle rocket engine - Google Patents
Coaxial jet mixer of hydrogen-oxygen expansion cycle rocket engine Download PDFInfo
- Publication number
- CN107620654B CN107620654B CN201610554818.7A CN201610554818A CN107620654B CN 107620654 B CN107620654 B CN 107620654B CN 201610554818 A CN201610554818 A CN 201610554818A CN 107620654 B CN107620654 B CN 107620654B
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- Prior art keywords
- hydrogen
- gas
- shell
- injection pipe
- oxygen
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- 239000001301 oxygen Substances 0.000 title claims abstract description 21
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 21
- 239000001257 hydrogen Substances 0.000 claims abstract description 106
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 106
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 79
- 239000007788 liquid Substances 0.000 claims abstract description 24
- 238000002347 injection Methods 0.000 claims abstract description 23
- 239000007924 injection Substances 0.000 claims abstract description 23
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 11
- 125000004122 cyclic group Chemical group 0.000 claims 3
- 239000007789 gas Substances 0.000 abstract description 21
- 150000002431 hydrogen Chemical class 0.000 description 5
- 239000002737 fuel gas Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 125000004435 hydrogen atom Chemical group [H]* 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Landscapes
- Jet Pumps And Other Pumps (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention belongs to the technical field of aerospace propulsion, and particularly relates to a coaxial jet mixer of an oxyhydrogen expansion cycle rocket engine. Comprises a shell and an injection pipe; the injection pipe is connected in the shell, the gas-hydrogen speed nozzle is arranged at the gas-hydrogen inlet of the shell, and the gas-hydrogen speed nozzle is contacted with the end part of the injection pipe; the gas-hydrogen inlet, the injection pipe and the shell outlet are positioned on the same axis; an annular gap is formed between the outlet of the injection pipe and the shell; the liquid hydrogen inlet of the shell is connected with an outlet pipeline of the hydrogen pump; the outlet pipeline of the hydrogen pump is provided with a liquid hydrogen cavitation pipe, and the outlet pipeline of the oxygen turbine is provided with a gas hydrogen sonic nozzle; the hydrogen pump and the hydrogen turbine are respectively connected with the thrust chamber, and the oxygen turbine is connected with the thrust chamber. The invention fully mixes the liquid hydrogen after the engine hydrogen pump with the gas hydrogen heated by the thrust chamber, and the mixed gas hydrogen is used for pressurizing the rocket body hydrogen storage tank.
Description
Technical Field
The invention belongs to the technical field of aerospace propulsion, and particularly relates to a coaxial jet mixer of an oxyhydrogen expansion cycle rocket engine.
Background
In order to meet the inlet parameters of the hydrogen pump of the hydrogen-oxygen expansion cycle rocket engine and enable the engine to start smoothly, hydrogen at a specified temperature for pressurization needs to be provided for the rocket body hydrogen storage tank. The domestic hydrogen-oxygen engine working circulation mode mainly uses the circulation of a gas generator, and the hydrogen for providing pressurization for the rocket body hydrogen storage tank is obtained by heating liquid hydrogen in a spiral pipe by using high-temperature fuel gas output by the engine gas generator. Vinci is a high-performance hydrogen-oxygen expansion cycle upper-level engine developed by European multi-country combination, and a stream of gas hydrogen is led out in front of a hydrogen main valve to pressurize a hydrogen storage tank. The first 8-ton expansion cycle engine developed for the new generation of carrier rockets in China has no high-temperature fuel gas in the engine, and the temperature of the gas hydrogen directly led out from the front of a hydrogen main valve cannot meet the overall requirement, so that a mixer is adopted to fully mix the liquid hydrogen pumped by the engine with the gas hydrogen heated by a thrust chamber, and the mixed gas hydrogen is used for pressurizing an rocket body hydrogen storage tank.
Disclosure of Invention
The invention aims to provide a coaxial jet mixer of an oxyhydrogen expansion cycle rocket engine, which is used for fully mixing liquid hydrogen after an engine hydrogen pump and gas hydrogen heated by a thrust chamber, wherein the mixed gas hydrogen is used for pressurizing an rocket body hydrogen storage tank.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
A coaxial jet mixer of an oxyhydrogen expansion cycle rocket engine comprises a shell and an ejector tube; the injection pipe is connected in the shell, the gas-hydrogen speed nozzle is arranged at the gas-hydrogen inlet of the shell, and the gas-hydrogen speed nozzle is contacted with the end part of the injection pipe; the gas-hydrogen inlet, the injection pipe and the shell outlet are positioned on the same axis; an annular gap is formed between the outlet of the injection pipe and the shell; the liquid hydrogen inlet of the shell is connected with an outlet pipeline of the hydrogen pump; the outlet pipeline of the hydrogen pump is provided with a liquid hydrogen cavitation pipe, and the outlet pipeline of the oxygen turbine is provided with a gas hydrogen sonic nozzle; the hydrogen pump and the hydrogen turbine are respectively connected with the thrust chamber, and the oxygen turbine is connected with the thrust chamber.
The injection pipe is connected in the shell through threads.
The gas-hydrogen sonic nozzle is arranged at the gas-hydrogen inlet of the shell through threads.
The injection pipe is provided with a groove.
The hydrogen pump and the hydrogen turbine are respectively connected with the thrust chamber through bolts.
The oxygen turbine is connected with the thrust chamber through bolts.
The beneficial effects obtained by the invention are as follows:
the invention fully utilizes the characteristics of an expansion cycle engine, adopts the mixture of gas hydrogen and liquid hydrogen after heat exchange of a thrust chamber jacket to obtain hydrogen for pressurizing an arrow hydrogen storage tank, is provided with a liquid hydrogen cavitation tube behind a hydrogen pump to control the flow of the liquid hydrogen, and is provided with a hydrogen sonic nozzle behind an oxygen turbine to control the flow of the gas hydrogen, thereby breaking the mode that the prior oxyhydrogen engine heats the liquid hydrogen by using high-temperature fuel gas to obtain hydrogen, and belongs to the first example in the engine taking oxyhydrogen as a propellant in China. The invention is applied to the engineering development of the first 8-ton expansion cycle oxyhydrogen engine in China, and can realize the full mixing of liquid hydrogen and gas hydrogen through multiple engine test runs and verification, and has stable performance.
Drawings
FIG. 1 is a diagram of a mixer arrangement on an expansion cycle engine system;
FIG. 2 is a schematic illustration of a coaxial jet mixer;
In the figure: 1. a hydrogen pump; 2. a liquid hydrogen cavitation tube; 3. a mixer; 4. a gas-hydrogen sonic nozzle; 5. an oxygen turbine; 6. a thrust chamber; 7. a hydrogen turbine; 8. a housing; 9. an ejector tube; 10. a gas-hydrogen inlet; 11. a thread; 12. a liquid hydrogen inlet; 13. an annular gap; 14. a housing outlet; 15. a groove.
Detailed Description
The invention will now be described in detail with reference to the drawings and specific examples.
As shown in fig. 1, the coaxial jet mixer 3 of the hydrogen-oxygen expansion cycle rocket engine comprises a shell 8 and an ejector pipe 9; the injection pipe 9 is connected in the shell 8 through threads 11, the gas-hydrogen speed nozzle 4 is arranged at a gas-hydrogen inlet 10 of the shell 8 through threads, and the gas-hydrogen speed nozzle 4 is contacted with the end part of the injection pipe 9; the gas-hydrogen inlet 10, the injection pipe 9 and the shell outlet 14 are positioned on the same axis; an annular gap 13 is formed between the outlet of the injection pipe 9 and the shell 8, so that liquid hydrogen and gas hydrogen form coaxial injection at the outlet 14 of the shell, and a coaxial jet type structure mixer is realized; the liquid hydrogen inlet 12 of the housing 8 is connected to the outlet line of the hydrogen pump 1. The outlet pipeline of the hydrogen pump 1 is provided with a liquid hydrogen cavitation pipe 2 for controlling the flow of liquid hydrogen, and the outlet pipeline of the oxygen turbine 5 is provided with a gas hydrogen sonic nozzle 4 for controlling the flow of gas hydrogen so as to obtain hydrogen at a specified temperature for pressurization after being fully mixed; in order to facilitate the installation of the injection pipe 9, a groove 15 is designed on the injection pipe 9. The hydrogen pump 1 and the hydrogen turbine 7 are connected to the thrust chamber 6 by bolts, respectively, and the oxygen turbine 5 is connected to the thrust chamber 6 by bolts. The mixer 3 adopts a structure that gas hydrogen ejects liquid hydrogen from the middle, the gas hydrogen passes through the center of the ejection pipe 9, the liquid hydrogen passes through an annular gap 13 formed by the shell 8 and the ejection pipe 9, and the mixed hydrogen is formed by mixing the liquid hydrogen and the gas hydrogen at the outlet of the mixer 3 by utilizing the entrainment effect of high-speed jet flow.
Claims (4)
1. The utility model provides a coaxial efflux formula blender of hydrogen-oxygen expansion cycle rocket engine which characterized in that: the mixer (3) comprises a shell (8) and an injection pipe (9); the ejector tube (9) is connected in the shell (8), the gas-hydrogen speed nozzle (4) is arranged at a gas-hydrogen inlet (10) of the shell (8), and the gas-hydrogen speed nozzle (4) is contacted with the end part of the ejector tube (9); the gas-hydrogen inlet (10), the injection pipe (9) and the shell outlet (14) are positioned on the same axis; an annular gap (13) is formed between the outlet of the injection pipe (9) and the shell (8); the liquid hydrogen inlet (12) of the shell (8) is connected with an outlet pipeline of the hydrogen pump (1); the outlet pipeline of the hydrogen pump (1) is provided with a liquid hydrogen cavitation tube (2); the hydrogen pump (1) and the hydrogen turbine (7) are respectively connected with the thrust chamber (6), and the oxygen turbine (5) is connected with the thrust chamber (6); the injection pipe (9) is connected in the shell (8) through threads (11); the injection pipe (9) is provided with a groove (15).
2. The hydrogen-oxygen expansion cyclic rocket engine coaxial jet mixer of claim 1, wherein: the gas-hydrogen sonic nozzle (4) is arranged at a gas-hydrogen inlet (10) of the shell (8) through threads.
3. The hydrogen-oxygen expansion cyclic rocket engine coaxial jet mixer of claim 1, wherein: the hydrogen pump (1) and the hydrogen turbine (7) are respectively connected with the thrust chamber (6) through bolts.
4. The hydrogen-oxygen expansion cyclic rocket engine coaxial jet mixer of claim 1, wherein: the oxygen turbine (5) is connected with the thrust chamber (6) through bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610554818.7A CN107620654B (en) | 2016-07-14 | 2016-07-14 | Coaxial jet mixer of hydrogen-oxygen expansion cycle rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610554818.7A CN107620654B (en) | 2016-07-14 | 2016-07-14 | Coaxial jet mixer of hydrogen-oxygen expansion cycle rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107620654A CN107620654A (en) | 2018-01-23 |
| CN107620654B true CN107620654B (en) | 2024-05-17 |
Family
ID=61087397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610554818.7A Active CN107620654B (en) | 2016-07-14 | 2016-07-14 | Coaxial jet mixer of hydrogen-oxygen expansion cycle rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107620654B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2171427C2 (en) * | 1999-09-20 | 2001-07-27 | Федеральное государственное унитарное предприятие Конструкторское бюро химавтоматики | Coaxial spray injector |
| CN102536511A (en) * | 2011-03-28 | 2012-07-04 | 摩尔动力(北京)技术股份有限公司 | High thrust aircraft engine |
| CN103982332A (en) * | 2014-06-06 | 2014-08-13 | 葛明龙 | Rocket thrust chamber with fuel switching function and supply system of rocket thrust chamber |
| CN203796471U (en) * | 2014-03-31 | 2014-08-27 | 北京航天动力研究所 | Nozzle with internal flow equalizing chamber |
| CN105114353A (en) * | 2015-08-21 | 2015-12-02 | 北京航天动力研究所 | Rayleigh groove type floating ring sealing device for hydrogen oxygen engine turbopump |
| CN205876542U (en) * | 2016-07-14 | 2017-01-11 | 北京航天动力研究所 | Oxyhydrogen inflation circulation rocket engine coaxial jets formula blender |
-
2016
- 2016-07-14 CN CN201610554818.7A patent/CN107620654B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2171427C2 (en) * | 1999-09-20 | 2001-07-27 | Федеральное государственное унитарное предприятие Конструкторское бюро химавтоматики | Coaxial spray injector |
| CN102536511A (en) * | 2011-03-28 | 2012-07-04 | 摩尔动力(北京)技术股份有限公司 | High thrust aircraft engine |
| CN203796471U (en) * | 2014-03-31 | 2014-08-27 | 北京航天动力研究所 | Nozzle with internal flow equalizing chamber |
| CN103982332A (en) * | 2014-06-06 | 2014-08-13 | 葛明龙 | Rocket thrust chamber with fuel switching function and supply system of rocket thrust chamber |
| CN105114353A (en) * | 2015-08-21 | 2015-12-02 | 北京航天动力研究所 | Rayleigh groove type floating ring sealing device for hydrogen oxygen engine turbopump |
| CN205876542U (en) * | 2016-07-14 | 2017-01-11 | 北京航天动力研究所 | Oxyhydrogen inflation circulation rocket engine coaxial jets formula blender |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107620654A (en) | 2018-01-23 |
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