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RU2011110642A - METHOD FOR WORKING A COMPRESSOR AIR-REACTIVE ENGINE - Google Patents

METHOD FOR WORKING A COMPRESSOR AIR-REACTIVE ENGINE Download PDF

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Publication number
RU2011110642A
RU2011110642A RU2011110642/06A RU2011110642A RU2011110642A RU 2011110642 A RU2011110642 A RU 2011110642A RU 2011110642/06 A RU2011110642/06 A RU 2011110642/06A RU 2011110642 A RU2011110642 A RU 2011110642A RU 2011110642 A RU2011110642 A RU 2011110642A
Authority
RU
Russia
Prior art keywords
engine
chamber
fuel
nozzle
combustion
Prior art date
Application number
RU2011110642/06A
Other languages
Russian (ru)
Other versions
RU2495269C2 (en
Inventor
Михаил Зеликович Боярер (RU)
Михаил Зеликович Боярер
Original Assignee
Михаил Зеликович Боярер (RU)
Михаил Зеликович Боярер
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 Михаил Зеликович Боярер (RU), Михаил Зеликович Боярер filed Critical Михаил Зеликович Боярер (RU)
Priority to RU2011110642/06A priority Critical patent/RU2495269C2/en
Publication of RU2011110642A publication Critical patent/RU2011110642A/en
Application granted granted Critical
Publication of RU2495269C2 publication Critical patent/RU2495269C2/en

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  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Способ работы компрессорного воздушно-реактивного двигателя, включающий вращение камеры сгорания топлива и сверхзвукового реактивного сопла двигателя на конце полой лопасти воздушного винта центробежного компрессора с окружной скоростью конца лопасти >300 м/с, отличающийся тем, что посредством камеры смешения газов газ, вытекающий из камеры сгорания топлива в сверхзвуковое реактивное сопло, перед поступлением в сопло, предварительно смешивают, в камере смешения газов, с атмосферным воздухом, имеющим степень сжатия >40. The method of operation of a compressor jet engine, including the rotation of the combustion chamber of the fuel and the supersonic jet nozzle of the engine at the end of a hollow blade of a centrifugal compressor propeller with a peripheral speed of the tip of the blade> 300 m / s, characterized in that the gas flowing out of the chamber through the gas mixing chamber the combustion of fuel into a supersonic jet nozzle, before entering the nozzle, is pre-mixed, in a gas mixing chamber, with atmospheric air having a compression ratio> 40.

Claims (1)

Способ работы компрессорного воздушно-реактивного двигателя, включающий вращение камеры сгорания топлива и сверхзвукового реактивного сопла двигателя на конце полой лопасти воздушного винта центробежного компрессора с окружной скоростью конца лопасти >300 м/с, отличающийся тем, что посредством камеры смешения газов газ, вытекающий из камеры сгорания топлива в сверхзвуковое реактивное сопло, перед поступлением в сопло, предварительно смешивают, в камере смешения газов, с атмосферным воздухом, имеющим степень сжатия >40. The method of operation of a compressor jet engine, including the rotation of the combustion chamber of the fuel and the supersonic jet nozzle of the engine at the end of a hollow blade of a centrifugal compressor propeller with a peripheral speed of the tip of the blade> 300 m / s, characterized in that the gas flowing out of the chamber through the gas mixing chamber the combustion of fuel into a supersonic jet nozzle, before entering the nozzle, is pre-mixed, in a gas mixing chamber, with atmospheric air having a compression ratio> 40.
RU2011110642/06A 2011-03-22 2011-03-22 Compressor air breather RU2495269C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2011110642/06A RU2495269C2 (en) 2011-03-22 2011-03-22 Compressor air breather

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2011110642/06A RU2495269C2 (en) 2011-03-22 2011-03-22 Compressor air breather

Publications (2)

Publication Number Publication Date
RU2011110642A true RU2011110642A (en) 2012-09-27
RU2495269C2 RU2495269C2 (en) 2013-10-10

Family

ID=47078053

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2011110642/06A RU2495269C2 (en) 2011-03-22 2011-03-22 Compressor air breather

Country Status (1)

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RU (1) RU2495269C2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2656780C2 (en) * 2015-04-28 2018-06-06 Юрий Владимирович Кеппер Reactive helicopter
RU2663194C2 (en) * 2015-06-09 2018-08-02 Леонид Александрович Тарасов Blade multi-phase electromagnetic propulsor

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU761A1 (en) * 1924-03-05 1924-09-15 Б.Н. Юрьев Jet turbo propeller and device for its use
SU45139A1 (en) * 1935-05-21 1935-11-30 И.А. Давыдов Reactive internal combustion turbine
US2972862A (en) * 1958-05-06 1961-02-28 Snecma Pulse reactor
US3699771A (en) * 1970-01-29 1972-10-24 Stephen V Chelminski Rotary wing aircraft lift and propulsion method and systems
RU2362707C2 (en) * 2007-10-29 2009-07-27 Общество с ограниченной ответственностью ООО МУЛЬТИКАР Jet slot blade (versions)
RU2382896C9 (en) * 2008-02-06 2010-05-10 Михаил Зеликович Боярер Device to transfer mechanical power from internal combustion engine to thermal electric power station generator

Also Published As

Publication number Publication date
RU2495269C2 (en) 2013-10-10

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

Effective date: 20150323