UA95643C2 - Liquid rocket thrust chamber with afterburning of oxidation gas - Google Patents
Liquid rocket thrust chamber with afterburning of oxidation gasInfo
- Publication number
- UA95643C2 UA95643C2 UAA200901171A UAA200901171A UA95643C2 UA 95643 C2 UA95643 C2 UA 95643C2 UA A200901171 A UAA200901171 A UA A200901171A UA A200901171 A UAA200901171 A UA A200901171A UA 95643 C2 UA95643 C2 UA 95643C2
- Authority
- UA
- Ukraine
- Prior art keywords
- afterburning
- gas
- oxidation gas
- liquid
- honeycomb
- Prior art date
Links
Landscapes
- Testing Of Engines (AREA)
Abstract
The invention relates to rocket building and can be used for formation of traction of liquid engine with afterburning of oxidation gas. A liquid rocket thrust chamber with afterburning of oxidation gas has a gas duct as a divergent cone, with honeycomb, a body with medium and fire bottoms and gas-liquid jets. The honeycomb is installed at distance from the medium bottom that is equal to 0.3÷0.45 of diameter of combustion chamber cylinder, at that the inlet ends of the jets are placed from the honeycomb at distance that is 0.35÷0.65 of the distance from it to the medium bottom. New technical result is in exclusion of high-frequency instability of the burning process in combustion chamber and increase of reliability of operation of the liquid engine with afterburning of oxidation gas at starting cycle due to arrangement of inlet edges of gas passages of the jets in pre-jet cavity with minimal acoustic resistance.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
UAA200901171A UA95643C2 (en) | 2009-02-13 | 2009-02-13 | Liquid rocket thrust chamber with afterburning of oxidation gas |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
UAA200901171A UA95643C2 (en) | 2009-02-13 | 2009-02-13 | Liquid rocket thrust chamber with afterburning of oxidation gas |
Publications (1)
Publication Number | Publication Date |
---|---|
UA95643C2 true UA95643C2 (en) | 2011-08-25 |
Family
ID=50836653
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
UAA200901171A UA95643C2 (en) | 2009-02-13 | 2009-02-13 | Liquid rocket thrust chamber with afterburning of oxidation gas |
Country Status (1)
Country | Link |
---|---|
UA (1) | UA95643C2 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
CN107676194A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
CN107676195A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of cover plate connection |
CN112628020A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | Low-temperature afterburning thrust chamber cooling flow path and control method |
-
2009
- 2009-02-13 UA UAA200901171A patent/UA95643C2/en unknown
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
CN107676194A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
CN107676195A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of cover plate connection |
CN107676194B (en) * | 2017-09-12 | 2019-07-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
CN107676196B (en) * | 2017-09-12 | 2019-07-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of connection of cover board can blocking type rocket engine propellant bias spray panel |
CN112628020A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | Low-temperature afterburning thrust chamber cooling flow path and control method |
CN112628020B (en) * | 2020-12-18 | 2022-04-12 | 西安航天动力研究所 | Low-temperature afterburning thrust chamber cooling flow path and control method |
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