RU2000111943A - DEVICE FOR IGNITION OF FUEL COMPONENTS IN THE COMBUSTION CHAMBER OF A LIQUID ROCKET ENGINE - Google Patents

DEVICE FOR IGNITION OF FUEL COMPONENTS IN THE COMBUSTION CHAMBER OF A LIQUID ROCKET ENGINE

Info

Publication number
RU2000111943A
RU2000111943A RU2000111943/06A RU2000111943A RU2000111943A RU 2000111943 A RU2000111943 A RU 2000111943A RU 2000111943/06 A RU2000111943/06 A RU 2000111943/06A RU 2000111943 A RU2000111943 A RU 2000111943A RU 2000111943 A RU2000111943 A RU 2000111943A
Authority
RU
Russia
Prior art keywords
combustion chamber
cavity
rocket engine
fuel
sleeve
Prior art date
Application number
RU2000111943/06A
Other languages
Russian (ru)
Other versions
RU2183763C2 (en
Inventor
Анатолий Григорьевич Весноватов
Олег Александрович Барсуков
Анатолий Васильевич Межевов
Original Assignee
Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева"
Filing date
Publication date
Application filed by Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" filed Critical Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева"
Priority to RU2000111943/06A priority Critical patent/RU2183763C2/en
Priority claimed from RU2000111943/06A external-priority patent/RU2183763C2/en
Publication of RU2000111943A publication Critical patent/RU2000111943A/en
Application granted granted Critical
Publication of RU2183763C2 publication Critical patent/RU2183763C2/en

Links

Claims (1)

Устройство для воспламенения компонентов топлива в камере сгорания жидкостного ракетного двигателя, содержащее корпус, в котором центрально установлена электрическая свеча, реакционную полостью, сужающуюся к выходу в камеру сгорания, полость подачи горючего и коллектор подвода окислителя, отличающееся тем, что в него введен смесительный элемент, внутри которого образована реакционная полость, а на наружной поверхности выполнен шнек, на входе в шнек со стороны камеры сгорания размещен коллектор подвода окислителя, причем полость подачи горючего образована во втулке, установленной с образованием подсвечной полости, которая соединена через центральное отверстие, выполненное во втулке, с полостью подачи горючего и сквозными отверстиями, выполненными во втулке вокруг полости подачи горючего, с реакционной полостью смесительного элемента, установленного под втулкой с зазором со стороны камеры сгорания.A device for igniting the components of the fuel in the combustion chamber of a liquid propellant rocket engine, comprising a housing in which a spark plug is centrally mounted, a reaction cavity that tapers towards the exit to the combustion chamber, a fuel supply cavity and an oxidizer supply manifold, characterized in that a mixing element is introduced therein, inside of which a reaction cavity is formed, and on the outer surface a screw is made, at the inlet of the screw from the side of the combustion chamber, an oxidizer supply manifold is placed, and the feed cavity and fuel is formed in the sleeve installed with the formation of the backlight cavity, which is connected through the Central hole made in the sleeve, with the fuel supply cavity and through holes made in the sleeve around the fuel supply cavity, with the reaction cavity of the mixing element mounted under the sleeve with a gap with sides of the combustion chamber.
RU2000111943/06A 2000-05-11 2000-05-11 Device for ignition of propellant components in combustion chamber of liquid-propellant rocket engine RU2183763C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2000111943/06A RU2183763C2 (en) 2000-05-11 2000-05-11 Device for ignition of propellant components in combustion chamber of liquid-propellant rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2000111943/06A RU2183763C2 (en) 2000-05-11 2000-05-11 Device for ignition of propellant components in combustion chamber of liquid-propellant rocket engine

Publications (2)

Publication Number Publication Date
RU2000111943A true RU2000111943A (en) 2002-04-20
RU2183763C2 RU2183763C2 (en) 2002-06-20

Family

ID=20234587

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000111943/06A RU2183763C2 (en) 2000-05-11 2000-05-11 Device for ignition of propellant components in combustion chamber of liquid-propellant rocket engine

Country Status (1)

Country Link
RU (1) RU2183763C2 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2994587B1 (en) * 2012-08-20 2017-07-07 Snecma BIMODAL IGNITER AND BIMODAL INJECTION METHOD FOR ENGINE IGNITER
RU2684765C1 (en) * 2018-02-26 2019-04-12 Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева - КАИ" Method of stabilization of combustion process in its combustion chamber and apparatus for realizing said method
RU2692171C1 (en) * 2018-11-23 2019-06-21 Степан Валентинович Суворов Pulsejet cumulative engine

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