UA95643C2 - Liquid rocket thrust chamber with afterburning of oxidation gas - Google Patents

Liquid rocket thrust chamber with afterburning of oxidation gas

Info

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
Application number
UAA200901171A
Other languages
Russian (ru)
Ukrainian (uk)
Inventor
Иван Максимович Кучма
Владимир Николаевич Шнякин
Галина Григорьевна Божко
Андрей Владимирович Родькин
Original Assignee
Государственное Предприятие "Конструкторское Бюро "Южное" Им. М.К.Янгеля
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Государственное Предприятие "Конструкторское Бюро "Южное" Им. М.К.Янгеля filed Critical Государственное Предприятие "Конструкторское Бюро "Южное" Им. М.К.Янгеля
Priority to UAA200901171A priority Critical patent/UA95643C2/en
Publication of UA95643C2 publication Critical patent/UA95643C2/en

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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.
UAA200901171A 2009-02-13 2009-02-13 Liquid rocket thrust chamber with afterburning of oxidation gas UA95643C2 (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (7)

* Cited by examiner, † Cited by third party
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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