UA86966C2 - Method for afterburning of EXHAUST generator gas of turbine of turbo-pump unit of liquid rocket engine and DEVICE for its realization - Google Patents

Method for afterburning of EXHAUST generator gas of turbine of turbo-pump unit of liquid rocket engine and DEVICE for its realization

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Publication number
UA86966C2
UA86966C2 UAA200610599A UAA200610599A UA86966C2 UA 86966 C2 UA86966 C2 UA 86966C2 UA A200610599 A UAA200610599 A UA A200610599A UA A200610599 A UAA200610599 A UA A200610599A UA 86966 C2 UA86966 C2 UA 86966C2
Authority
UA
Ukraine
Prior art keywords
nozzle
fuel
turbine
gas
combustion chamber
Prior art date
Application number
UAA200610599A
Other languages
Russian (ru)
Ukrainian (uk)
Inventor
Николай Дмитриевич Коваленко
Геннадий Афанасьевич Стрельников
Галина Николаевна Коваленко
Александр Владимирович Хоменко
Тит Александрович Коваленко
Наталья Петровна Сироткина
Original Assignee
Институт Технической Механики Нану И Нкау
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 Институт Технической Механики Нану И Нкау filed Critical Институт Технической Механики Нану И Нкау
Priority to UAA200610599A priority Critical patent/UA86966C2/en
Publication of UA86966C2 publication Critical patent/UA86966C2/en

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Abstract

Disclosed is a method for afterburning of exhaust generator gas of turbine of turbo-pump unit of liquid rocket engine and a rocket engine for its realization. The rocket engine has a combustion chamber with supersonic nozzle, turbo-pump system for supply of fuel components to combustion chamber, this includes gas generator, turbine, pumps of oxidizer and fuel. Fuel components are supplied to combustion chamber and to gas generator by pipelines of oxidizer and fuel. Exhaust collector of turbine is connected to circular collector of injection to nozzle of exhaust gas on turbine generator, this is placed in supersonic section of the nozzle and is connected by circular slot to flow-through (inner) section of the nozzle. To provide uniformity and stability of geometrical characteristics of circular slot its walls are connected by rigidity ribs that are uniformly placed in perimeter of the slot. Inlet fuel collectors of oxidizer and fuel are connected by fuel pipelines to cooling sections of combustion chamber of the engine. Inlet collectors of cooling sections of chamber are connected to jet head of combustion chamber. From circular collector for injection gas is blown in through circular slot of the nozzle that connects inner cavity of collector to supersonic flow of the nozzle. Simultaneously with circular injection of generator gas to supersonic section of nozzle one supplies uniformly distributed in perimeter of nozzle oxidation component of fuel. In supersonic section of the nozzle oxidizer interacts with blown-in generator gas that has large excess of fuel, this in such way id after-burned, this increases reaction engine thrust.
UAA200610599A 2006-10-06 2006-10-06 Method for afterburning of EXHAUST generator gas of turbine of turbo-pump unit of liquid rocket engine and DEVICE for its realization UA86966C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
UAA200610599A UA86966C2 (en) 2006-10-06 2006-10-06 Method for afterburning of EXHAUST generator gas of turbine of turbo-pump unit of liquid rocket engine and DEVICE for its realization

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
UAA200610599A UA86966C2 (en) 2006-10-06 2006-10-06 Method for afterburning of EXHAUST generator gas of turbine of turbo-pump unit of liquid rocket engine and DEVICE for its realization

Publications (1)

Publication Number Publication Date
UA86966C2 true UA86966C2 (en) 2009-06-10

Family

ID=50631597

Family Applications (1)

Application Number Title Priority Date Filing Date
UAA200610599A UA86966C2 (en) 2006-10-06 2006-10-06 Method for afterburning of EXHAUST generator gas of turbine of turbo-pump unit of liquid rocket engine and DEVICE for its realization

Country Status (1)

Country Link
UA (1) UA86966C2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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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