[특허]Combination turbojet-ramjet-rocket propulsion system

[미국특허] Combination turbojet-ramjet-rocket propulsion system 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/00 F02K-003/10
출원번호	US-0413379 (1989-09-27)
우선권정보	FR-0012645 (1988-09-28); FR-0012646 (1988-09-28); FR-0012647 (1988-09-28)
발명자 / 주소	Labatut Josiane M. F. (Yerres FRX) Marlin Francois M. P. (Melun FRX) Mazeaud Georges (Yerres FRX) Mirville Francois J. (Melun FRX)
출원인 / 주소	Societe Nationale d\Etude et de Construction de Moteurs d\Aviation (Paris FRX 07)
인용정보	피인용 횟수 : 20 인용 특허 : 0

초록 ▼

A propulsion system for a reusable spacecraft is disclosed having turbojet, ramjet and rocket modes of operation. Hydrogen or exhaust gases from a gas generator drives a gas turbine which powers an air compressor in the turbojet mode. An injection device injects hydrogen and exhaust from the gas driven turbine in the combustion chamber in the turbojet mode. In the ramjet mode, only hydrogen is injected into the combustion chamber. In the ramjet mode, hydrogen and oxygen are supplied to the rocket motor. An adjustable nozzle is provided to form a variable throat convergent-divergent nozzle in the turbojet and ramjet modes and to form a divergent nozzle in the rocket mode.

대표청구항 ▼

A combination turbojet-ramjet-rocker propulsion system having a combustion chamber and an air intake duct means to direct air into the combustion chamber defined between a central body and an external housing comprising: a) air compressor means located in the air intake duct upstream of the combustion chamber to generate a compressed air stream passing into the combustion chamber; b) gas driven turbine means located in the central body and operatively connected to the air compressor to drive the air compressor and having the exhaust means; c) means to supply a pressurized gas to drive the gas driven turbine; d) a source of combustible fuel; e) injection means located in the combustion chamber downstream of the air compressor means in communication with the source of combustible fuel and the exhaust means of the gas driven turbine means to inject at least one of the combustible fuel and the exhaust from the gas driven turbine means into the compressed air stream when the system is operated in the turbojet and ramjet modes wherein the injection means comprises; i) an injection device comprising a plurality of arms extending generally radially between the central body and the external housing having an aerodynamic cross-section with an extrados and an intrados extending between a leading edge and a trailing edge, each arm defining at least one interior radially extending cavity in communication with the gas driven turbine to allow exhaust gases from the gas driven turbine to pass into the cavity; and ii) a plurality of injection orifices defined in the intrados and communicating with the at least one internal cavity to inject the exhaust gases in the cavity into the air stream passing into the combustion chamber; f) rocket motor means located in a downstream portion of the central body; g) adjustable exhaust nozzle means in communication with the combustion chamber and the rocket motor; and, h) adjustment means operatively associated with the exhaust nozzle means to adjust the nozzle between a variable throat convergent-divergent nozzle in the turbojet and ramjet modes and a divergent nozzle in the rocket mode.

이 특허를 인용한 특허 (20) 인용/피인용 타임라인 분석

Bunker, Ronald Scott, Aerodynamic pylon fuel injector system for combustors.
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George R. Schmidt, Atomic-based combined cycle propulsion system and method.
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Conrardy, Jean-Marie; Soulier, Nicolas, Combined turbojet and ramjet engine.
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Kohn, Aryeh Yaakov, Deployable rocket engine in a combination jet and rocket engine.
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Trefny, Charles J; Dippold, Vance F, Dual-mode combustor.
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Bond, Alan; Varvill, Richard, Engine.
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Bulman, Melvin J.; Billig, Frederick S.; Baumler, legal representative, Linda A., Integrated air inlet system for multi-propulsion aircraft engines.
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Bulman,Melvin J.; Billig,Frederick S., Integrated air inlet system for multi-propulsion aircraft engines.
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Jahnsen, Eric, Integrated airbreathing and non-airbreathing engine system.
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Pomerleau, Daniel, Jet turbine utilizing a cryogenic fuel.
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Erickson,Christopher M; Lobitz,James R; Bissell,William, Method and apparatus for a rocket engine power cycle.
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Rice, Edward Claude; Ress, Jr., Robert Anthony; Williams, Reginald Guy, Method and apparatus for spraying fuel within a gas turbine engine.
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Wilson, Donald R.; Lu, Frank K., Multi-mode pulsed detonation propulsion system.
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Breugelmans, Frans; Hendrick, Patrick; Marquet, Benoit; Strengnart, Marc, Process and device for collecting air, and engine associated therewith.
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Trefny, Charles J.; Dippold, Vance F., Process for operating a dual-mode combustor.
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Clapp Mitchell B. ; Zubrin Robert M., Reusable rocket-propelled high altitude airplane and method and apparatus for mid-air oxidizer transfer to said airplane.
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Erickson, Christopher M.; Lobitz, James R.; Bissell, William R.; Hanks, David E.; Brown, Corey D., Rocket engine power cycle.
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Fisher, Steven C.; Brodeur, Tim, Sequence diagram system.
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Ronnie J. Duncan, Shaped charged engine.
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Pederson, Robert J.; Schmotolocha, Stephen N.; Follett, William W., Single-stage hypersonic vehicle featuring advanced swirl combustion.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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[미국특허] Combination turbojet-ramjet-rocket propulsion system 원문보기