RU95101557A - Plasma-jet engine - Google Patents

Plasma-jet engine

Info

Publication number
RU95101557A
RU95101557A RU95101557/06A RU95101557A RU95101557A RU 95101557 A RU95101557 A RU 95101557A RU 95101557/06 A RU95101557/06 A RU 95101557/06A RU 95101557 A RU95101557 A RU 95101557A RU 95101557 A RU95101557 A RU 95101557A
Authority
RU
Russia
Prior art keywords
plasma
magnetic
engine
field
accelerator
Prior art date
Application number
RU95101557/06A
Other languages
Russian (ru)
Other versions
RU2099572C1 (en
Inventor
Н.С. Козлов
Original Assignee
Н.С. Козлов
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 Н.С. Козлов filed Critical Н.С. Козлов
Priority to RU95101557A priority Critical patent/RU2099572C1/en
Publication of RU95101557A publication Critical patent/RU95101557A/en
Application granted granted Critical
Publication of RU2099572C1 publication Critical patent/RU2099572C1/en

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  • Plasma Technology (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)

Abstract

FIELD: manufacture of aircraft and rocket liquid-propellant engines. SUBSTANCE: engine has vortex combustion chamber, magnetic plasma accelerator and gas dynamic nozzle connected coaxially and engageable by their torous surfaces which hold water (steam) supply injectors and corona- forming electrodes. Magnetic ion radiation plasma accelerator creates rotary magnetic field and separation of ionized gases of plasma by spectral mass; nozzle terminates in probes for concentration and flow of ionized gases. EFFECT: increased power of engine; enhanced economical efficiency and ecological safety. 7 dwg

Claims (1)

Изобретение относится к области авиационного и ракетного двигателестроения на жидком топливе и позволяет создать более мощный, высокоэкономичный и более экологичный двигатель с использованием новых физико-энергетических принципов. Двигатель состоит из вихревой камеры воспламенения и сжигания топлива, магнитного ускорителя плазмы и газодинамического сопла, соединенных соосно и сопряженных торцовыми поверхностями, на которых размещены форсунки для подачи воды (пара) и коронирующие электроды. Причем магнитный ускоритель ионно-радиационной плазмы обеспечивает создание вращающегося магнитного поля и разделение ионизированных газов плазмы по спектральной массе, а сопло заканчивается зондами для концентрации и стечения ионизированных газов.The invention relates to the field of aircraft and rocket engines using liquid fuel and allows you to create a more powerful, highly economical and more environmentally friendly engine using new physical and energy principles. The engine consists of a vortex chamber for igniting and burning fuel, a magnetic plasma accelerator and a gas-dynamic nozzle connected coaxially and mated with end surfaces, on which nozzles for supplying water (steam) and corona electrodes are placed. Moreover, the magnetic accelerator of ion-radiation plasma provides the creation of a rotating magnetic field and the separation of ionized plasma gases by spectral mass, and the nozzle ends with probes for the concentration and confluence of ionized gases.
RU95101557A 1995-01-16 1995-01-16 Plasma-jet engine RU2099572C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU95101557A RU2099572C1 (en) 1995-01-16 1995-01-16 Plasma-jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU95101557A RU2099572C1 (en) 1995-01-16 1995-01-16 Plasma-jet engine

Publications (2)

Publication Number Publication Date
RU95101557A true RU95101557A (en) 1997-02-10
RU2099572C1 RU2099572C1 (en) 1997-12-20

Family

ID=20164514

Family Applications (1)

Application Number Title Priority Date Filing Date
RU95101557A RU2099572C1 (en) 1995-01-16 1995-01-16 Plasma-jet engine

Country Status (1)

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RU (1) RU2099572C1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009028977A1 (en) * 2007-08-29 2009-03-05 Rudolf Klavdievich Katargin Hydrogen-gas engine
AT507156B1 (en) 2008-07-22 2011-12-15 Ge Jenbacher Gmbh & Co Ohg DEVICE FOR IGNITING A FUEL / AIR MIXTURE
RU2443905C2 (en) * 2010-05-24 2012-02-27 ФГУ "46 ЦНИИ Минобороны России" Draft unit
RU2458248C1 (en) * 2011-05-04 2012-08-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) Laser rocket engine and method of its operation
FR2997462B1 (en) * 2012-10-30 2018-09-14 Safran Aircraft Engines SUPPLYING AN ION PROPELLANT IN PROPULSIVE GAS
RU173324U1 (en) * 2016-11-15 2017-08-22 Дмитрий Николаевич Харитонов MEMBRANE ION ENGINE
RU2733076C1 (en) * 2019-12-16 2020-09-29 Николай Борисович Болотин Plasma-rocket engine
RU2738136C1 (en) * 2019-12-23 2020-12-08 Николай Борисович Болотин Ionic rocket engine and method of operation thereof
RU2724375C1 (en) * 2019-12-24 2020-06-23 Николай Борисович Болотин Ionic rocket engine and method of its operation
RU2738522C1 (en) * 2019-12-30 2020-12-14 Николай Борисович Болотин Ionic rocket engine and method of operation thereof
RU2745180C1 (en) * 2020-05-12 2021-03-22 Николай Борисович Болотин Combined ion rocket engine and coroning electrode
RU2735043C1 (en) * 2020-05-20 2020-10-27 Николай Борисович Болотин Plasma-ion rocket engine
RU2747067C1 (en) * 2020-06-03 2021-04-23 Николай Борисович Болотин Ion propulsion engine, method for operation thereof and corona forming electrode
RU2761693C1 (en) * 2020-08-04 2021-12-13 Николай Борисович Болотин Ion rocket engine, method of its operation and coroning electrode
US11795879B2 (en) 2021-12-20 2023-10-24 General Electric Company Combustor with an igniter provided within at least one of a fuel injector or a compressed air passage

Also Published As

Publication number Publication date
RU2099572C1 (en) 1997-12-20

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