RU92003195A - AIRCRAFT WITH FLOW LAMINARIZATION SYSTEM - Google Patents

AIRCRAFT WITH FLOW LAMINARIZATION SYSTEM

Info

Publication number
RU92003195A
RU92003195A RU92003195/11A RU92003195A RU92003195A RU 92003195 A RU92003195 A RU 92003195A RU 92003195/11 A RU92003195/11 A RU 92003195/11A RU 92003195 A RU92003195 A RU 92003195A RU 92003195 A RU92003195 A RU 92003195A
Authority
RU
Russia
Prior art keywords
compressor
combustion chamber
aircraft
auxiliary circuit
turbine
Prior art date
Application number
RU92003195/11A
Other languages
Russian (ru)
Other versions
RU2084377C1 (en
Inventor
А.Н. Гришин
Original Assignee
А.Н. Гришин
Filing date
Publication date
Application filed by А.Н. Гришин filed Critical А.Н. Гришин
Priority to RU92003195A priority Critical patent/RU2084377C1/en
Priority claimed from RU92003195A external-priority patent/RU2084377C1/en
Publication of RU92003195A publication Critical patent/RU92003195A/en
Application granted granted Critical
Publication of RU2084377C1 publication Critical patent/RU2084377C1/en

Links

Claims (1)

Изобретение относится к авиастроению, ракетной технике и двигателестроению. Летательный аппарат имеет на аэродинамических поверхностях щели для отсоса воздуха, связанные с компрессором системы ламинаризации. Отсасываемый воздух включен в термодинамический цикл основных двигателей летательного аппарата. Двигатели имеют внутренний контур, включающий компрессор, камеру сгорания и турбину, вспомогательный контур, состоящий из теплообменника, компрессора, камеры сгорания и турбины. Отбор воздуха из внутреннего контура во вспомогательный контур производится за компрессором внутреннего контура через трубопровод, подключенный к теплообменнику. За компрессором вспомогательного контура отбирается часть воздуха из вспомогательного контура, которая после подогрева в дополнительной камере сгорания расширяется в силовой турбине, расположенной на одном валу с компрессором системы ламинаризации. После расширения газ направляется в камеру сгорания внутреннего контура. В эту же камеру сгорания возвращается газ из турбины вспомогательного контура.The invention relates to aircraft manufacturing, rocket technology and engine building. The aircraft has slots on the aerodynamic surfaces for air suction connected with the compressor of the laminarization system. The suction air is included in the thermodynamic cycle of the main engines of the aircraft. Engines have an internal circuit including a compressor, a combustion chamber and a turbine, an auxiliary circuit consisting of a heat exchanger, a compressor, a combustion chamber and a turbine. The air is taken from the internal circuit to the auxiliary circuit after the compressor of the internal circuit through a pipeline connected to the heat exchanger. Behind the auxiliary circuit compressor, part of the air is taken from the auxiliary circuit, which, after heating in the additional combustion chamber, expands in a power turbine located on the same shaft as the compressor of the laminarization system. After expansion, the gas is directed to the combustion chamber of the internal circuit. Gas from the auxiliary circuit turbine is returned to the same combustion chamber.
RU92003195A 1992-11-02 1992-11-02 Power plant of flying vehicle with laminar-flow control system of aerodynamic surfaces RU2084377C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU92003195A RU2084377C1 (en) 1992-11-02 1992-11-02 Power plant of flying vehicle with laminar-flow control system of aerodynamic surfaces

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU92003195A RU2084377C1 (en) 1992-11-02 1992-11-02 Power plant of flying vehicle with laminar-flow control system of aerodynamic surfaces

Publications (2)

Publication Number Publication Date
RU92003195A true RU92003195A (en) 1997-01-27
RU2084377C1 RU2084377C1 (en) 1997-07-20

Family

ID=20131316

Family Applications (1)

Application Number Title Priority Date Filing Date
RU92003195A RU2084377C1 (en) 1992-11-02 1992-11-02 Power plant of flying vehicle with laminar-flow control system of aerodynamic surfaces

Country Status (1)

Country Link
RU (1) RU2084377C1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10361390B4 (en) 2003-12-29 2008-05-08 Airbus Deutschland Gmbh Method and device for extracting the boundary layer
DE102004024057B3 (en) 2004-05-13 2005-09-15 Airbus Deutschland Gmbh Aircraft, has fluid duct system connected to pumping device that is driven, by cabin exhaust air, for production of low pressure for suction of boundary layer though valve, where device is jet pump whose driving jets are generated by air
DE102004024016A1 (en) 2004-05-13 2005-12-22 Airbus Deutschland Gmbh Air suction arrangement for aircraft, has branch line to draw bleed air from high-pressure region of engine so as to drive turbine of turbo-supercharger
CN103184936B (en) * 2011-12-31 2016-08-03 朱晓义 A kind of electromotor and a kind of aircraft
RU2523510C1 (en) * 2013-02-19 2014-07-20 Николай Евгеньевич Староверов Method of gas turbine engine afterburning

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