RU2012148273A - LIQUID ROCKET ENGINE ACCORDING TO THE GENERATOR GAS BURNING - Google Patents

LIQUID ROCKET ENGINE ACCORDING TO THE GENERATOR GAS BURNING Download PDF

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Publication number
RU2012148273A
RU2012148273A RU2012148273/06A RU2012148273A RU2012148273A RU 2012148273 A RU2012148273 A RU 2012148273A RU 2012148273/06 A RU2012148273/06 A RU 2012148273/06A RU 2012148273 A RU2012148273 A RU 2012148273A RU 2012148273 A RU2012148273 A RU 2012148273A
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RU
Russia
Prior art keywords
pump
fuel
oxidizer
tna
chambers
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Application number
RU2012148273/06A
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Russian (ru)
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RU2520771C1 (en
Inventor
Петр Сергеевич Лёвочкин
Владимир Константинович Чванов
Вадим Ильич Семенов
Дмитрий Сергеевич Пушкарев
Александр Анатольевич Тюрин
Original Assignee
Открытое акционерное общество "НПО Энергомаш имени академика В.П. Глушко"
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Priority to RU2012148273/06A priority Critical patent/RU2520771C1/en
Publication of RU2012148273A publication Critical patent/RU2012148273A/en
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Publication of RU2520771C1 publication Critical patent/RU2520771C1/en

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Classifications

    • 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
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
    • 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
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • 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
    • F02K9/44—Feeding propellants
    • F02K9/56—Control
    • F02K9/563—Control of propellant feed pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/53—Hydrodynamic or hydrostatic bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Abstract

1. Жидкостный ракетный двигатель по схеме с дожиганием генераторного газа, включающий камеры (не менее двух) с трактами регенеративного охлаждения и смесительные головки; турбонасосную систему питания газогенераторов и камер двигателя; систему управления и регулирования, имеющую пускоотсечные клапаны, регулятор тяги и дроссель соотношения компонентов топлива, отличающийся тем, что турбонасосная система питания двигателя содержит два турбонасосных агрегата, питаемых двумя автономными окислительными газогенераторами, при этом первый и второй ТНА имеют одинаковую конструкцию и включают соосно установленные и последовательно расположенные на одном валу насос горючего, насос окислителя и газовую турбину, причем насос горючего второго ТНА выполнен двухступенчатым, кроме того, выходы из насосов горючего и окислителя первого ТНА соединены трубопроводами со входами насосов горючего и окислителя второго ТНА, насос окислителя второго ТНА соединен со смесительными головками указанных газогенераторов через трубопроводы, в которых установлены пускоотсечные клапаны, а выход из первой ступени насоса горючего второго ТНА соединен со смесительными головками камер двигателя через дроссель соотношения компонентов топлива, пускоотсечные клапаны, трубопроводы и тракты регенеративного охлаждения камер, а выход из второй ступени насоса горючего второго ТНА соединен со смесительными головками газогенераторов через трубопровод и регулятор тяги.2. ЖРД по п.1, отличающийся тем, что при питании турбин двух ТНА генераторным газом с избытком горючего насос окислителя второго ТНА выполнен двухступенчатым, а насос горюче�1. Liquid rocket engine according to the scheme with afterburning of the generator gas, including chambers (at least two) with regenerative cooling paths and mixing heads; turbopump system for powering gas generators and engine chambers; a control and regulation system having start-up shut-off valves, a draft regulator and a fuel ratio throttle, characterized in that the turbopump engine power supply system contains two turbopump units powered by two autonomous oxidation gas generators, while the first and second pump pumps have the same design and include coaxially installed and a fuel pump, an oxidizer pump and a gas turbine are located sequentially on one shaft, and the fuel pump of the second heat pump is made of a two-stage design, in addition, the outputs from the fuel and oxidizer pumps of the first heat pump are connected by pipelines to the inputs of the fuel and oxidizer pumps of the second heat pump, the oxidizer pump of the second heat pump is connected to the mixing heads of the said gas generators through pipelines in which start-up shut-off valves are installed, and the outlet from the first stage of the fuel pump of the second THA is connected to the mixing heads of the engine chambers through the fuel component ratio throttle, start-up shut-off valves, pipelines and regenerative cooling paths of the chambers, and the outlet from the second stage of the pump The fuel supply of the second pump is connected to the mixing heads of the gas generators through a pipeline and a draft regulator.2. Liquid rocket engine according to claim 1, characterized in that when the turbines of two turbocharger pumps are powered by generator gas with excess fuel, the oxidizer pump of the second turbocharger is made of two stages, and the pump is combustible

Claims (2)

1. Жидкостный ракетный двигатель по схеме с дожиганием генераторного газа, включающий камеры (не менее двух) с трактами регенеративного охлаждения и смесительные головки; турбонасосную систему питания газогенераторов и камер двигателя; систему управления и регулирования, имеющую пускоотсечные клапаны, регулятор тяги и дроссель соотношения компонентов топлива, отличающийся тем, что турбонасосная система питания двигателя содержит два турбонасосных агрегата, питаемых двумя автономными окислительными газогенераторами, при этом первый и второй ТНА имеют одинаковую конструкцию и включают соосно установленные и последовательно расположенные на одном валу насос горючего, насос окислителя и газовую турбину, причем насос горючего второго ТНА выполнен двухступенчатым, кроме того, выходы из насосов горючего и окислителя первого ТНА соединены трубопроводами со входами насосов горючего и окислителя второго ТНА, насос окислителя второго ТНА соединен со смесительными головками указанных газогенераторов через трубопроводы, в которых установлены пускоотсечные клапаны, а выход из первой ступени насоса горючего второго ТНА соединен со смесительными головками камер двигателя через дроссель соотношения компонентов топлива, пускоотсечные клапаны, трубопроводы и тракты регенеративного охлаждения камер, а выход из второй ступени насоса горючего второго ТНА соединен со смесительными головками газогенераторов через трубопровод и регулятор тяги.1. A liquid-propellant rocket engine according to a scheme with generator gas afterburning, including chambers (at least two) with regenerative cooling paths and mixing heads; turbopump power supply system for gas generators and engine chambers; a control and regulation system having start-off valves, a draft regulator and a throttle ratio of fuel components, characterized in that the turbopump engine power supply system contains two turbopump units powered by two autonomous oxidizing gas generators, while the first and second heat pumps are of the same design and include coaxially mounted and a fuel pump, an oxidizer pump and a gas turbine sequentially arranged on the same shaft, the fuel pump of the second TNA being made in two stages, Moreover, the exits from the fuel and oxidizer pumps of the first TNA are connected by pipelines to the inlets of the fuel and oxidizer pumps of the second TNA, the oxidizer pump of the second TNA is connected to the mixing heads of these gas generators through pipelines in which shut-off valves are installed, and the exit from the first stage of the fuel pump of the second TNA connected to the mixing heads of the engine chambers through the throttle of the ratio of fuel components, start-off valves, pipelines and paths of regenerative cooling of the chambers, and the output from the second stage of the fuel pump, the second TNA is connected to the mixing heads of the gas generators through a pipeline and a draft regulator. 2. ЖРД по п.1, отличающийся тем, что при питании турбин двух ТНА генераторным газом с избытком горючего насос окислителя второго ТНА выполнен двухступенчатым, а насос горючего второго ТНА одноступенчатым. 2. The liquid propellant rocket engine according to claim 1, characterized in that when the turbines are supplied with two TNAs with generator gas with excess fuel, the oxidizer pump of the second TNA is two-stage, and the fuel pump of the second TNA is single-stage.
RU2012148273/06A 2012-11-14 2012-11-14 Liquid-propellant engine with generator gas staged combustion cycle RU2520771C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2012148273/06A RU2520771C1 (en) 2012-11-14 2012-11-14 Liquid-propellant engine with generator gas staged combustion cycle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2012148273/06A RU2520771C1 (en) 2012-11-14 2012-11-14 Liquid-propellant engine with generator gas staged combustion cycle

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RU2012148273A true RU2012148273A (en) 2014-05-20
RU2520771C1 RU2520771C1 (en) 2014-06-27

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112901353A (en) * 2021-02-01 2021-06-04 中国科学院力学研究所 System and method for starting ramjet engine through active cooling of hydrocarbon fuel and scramjet engine

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RU2692598C1 (en) * 2018-07-31 2019-06-25 Акционерное общество "НПО Энергомаш имени академика В.П.Глушко" Liquid-propellant engine
RU2703076C1 (en) * 2019-07-01 2019-10-16 Акционерное общество "Конструкторское бюро химавтоматики" Multi-chamber liquid-propellant rocket engine with afterburning with controlled thrust vector
RU2742516C1 (en) * 2019-08-08 2021-02-08 Александр Вячеславович Дыбой Propulsion system with a rocket engine
RU2725345C1 (en) * 2019-10-01 2020-07-02 Акционерное общество "Конструкторское бюро химавтоматики" Multi-chamber liquid-propellant rocket engine with afterburning with controlled thrust vector
RU2765219C1 (en) * 2020-11-10 2022-01-26 Акционерное общество "КБхиммаш им. А.М. Исаева" Liquid rocket engine made according to the configuration without afterburning in the chamber

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US1998410A (en) * 1933-10-16 1935-04-16 Gray Telephone Pay Station Com Telephone toll collecting apparatus
DE1626055B1 (en) * 1967-04-05 1970-07-30 Messerschmitt Boelkow Blohm Propulsion unit consisting of several liquid rockets
RU2158839C2 (en) * 1999-01-21 2000-11-10 Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" Liquid-propellant rocket reheat engine
RU2232915C2 (en) * 2002-03-14 2004-07-20 ОАО "НПО Энергомаш им. акад. В.П. Глушко" Reheat liquid-propellant rocket engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112901353A (en) * 2021-02-01 2021-06-04 中国科学院力学研究所 System and method for starting ramjet engine through active cooling of hydrocarbon fuel and scramjet engine

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MM4A The patent is invalid due to non-payment of fees

Effective date: 20210101

NF4A Reinstatement of patent

Effective date: 20211112