[특허]Thrust augmentation in plug nozzles and expansion-deflection nozzles

Thrust augmentation in plug nozzles and expansion-deflection nozzles 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/00 B63H-025/46
출원번호	UP-0226127 (2005-09-13)
등록번호	US-7823376 (2010-11-22)
발명자 / 주소	Lausten, Merlyn Bulman, Melvin J.
출원인 / 주소	Aerojet-General Corporation
대리인 / 주소	Townsend and Townsend and Crew LLP
인용정보	피인용 횟수 : 0 인용 특허 : 27

초록 ▼

Thrust augmentation in a rocket nozzle is achieved by incorporating injectors for the introduction of unburnt fuel and oxidizer into a nozzle to combust in the nozzle and thereby supplement the primary thrust that is supplied by fuel and oxidizer that are combusted prior to entry into the nozzle. These secondary injectors are incorporated into the design of expansion-deflection nozzles and plug nozzles. In expansion-deflection nozzles, the injectors are either in the flow deflector itself or in the wall of the divergent section of the nozzle. In plug nozzles, the injectors are either in a shell of the nozzle surrounding the forward end of the centerbody or in the centerbody itself.

대표청구항 ▼

What is claimed is: 1. A propulsion system comprising: a rocket nozzle comprising a combustion zone, a throat, and a divergent section disposed along a longitudinal axis to define a serially axial direction of flow extending from said combustion zone, through said throat, and then through said divergent section; a flow deflector disposed in said divergent section, said flow deflector having a flared end flaring outward along said direction of flow to deflect combustion gas emerging from said throat away from said longitudinal axis; and separate flow passages extending through said flow deflector, said flow passages parallel to said longitudinal axis and terminating at said flared end to separately inject said fluid fuel and oxidizer into said core. 2. The propulsion system of claim 1 wherein said rocket nozzle is an overexpanded nozzle. 3. The propulsion system of claim 1 wherein said rocket nozzle and said flow deflector are axisymmetrical about said longitudinal axis. 4. The propulsion system of claim 1 wherein said rocket nozzle has an area ratio of at least about 25:1. 5. The propulsion system of claim 1 wherein said rocket nozzle has an area ratio within the range of from about 25:1 to about 150:1. 6. The propulsion system of claim 1 wherein said rocket nozzle has an area ratio within the range of from about 65:1 to about 85:1. 7. The propulsion system of claim 1 wherein said combustion gas deflected by said flow deflector is defined as a primary combustion gas, said rocket nozzle creating a volumetric flow rate of said primary combustion gas through said divergent section, and said passages within said flow deflector are sufficiently large relative to said rocket nozzle to produce, upon combustion of said fuel and oxidizer in said divergent section, a secondary combustion gas at a volumetric flow rate equal to from about 25% to about 75% of said volumetric flow rate of said primary combustion gas. 8. The propulsion system of claim 1 wherein said flow deflector has an aft face that is planar. 9. The propulsion system of claim 1 wherein said rocket nozzle and said flow deflector are axisymmetrical about said longitudinal axis, and said flow deflector has an aft face that is planar and perpendicular to said longitudinal axis. 10. The propulsion system of claim 1 wherein flow deflector is mounted to an aft end of a shaft passing through said combustion zone to define an annular passage within said combustion zone around said shaft, said annular passage having a cross section that constitutes from about 20% to about 90% of the combined cross sections of said annular passage and said shaft. 11. The propulsion system of claim 10 wherein said annular passage has a cross section that constitutes from about 20% to about 50% of the combined cross sections of said annular passage and said flow deflector.

이 특허에 인용된 특허 (27)

Speir Donald W. (Cincinnati OH) McHugh Donald P. (Cincinnati OH), Articulated plug nozzle.
상세보기
Janeke Charl E.,ZAX, Asonic aerospike engine.
상세보기
Cherry Charles C. (McGregor TX) King Lewis C. (Dallas TX), Axisymmetrical annular plug nozzle.
상세보기
Corson ; Jr. Blake W. (Newport News VA), Cascade plug nozzle.
상세보기
Rabone George R. (Cincinnati OH), Convergent-divergent plug nozzle.
상세보기
Thayer Edward B. (Palm Beach Gardens FL), Convertible plug nozzle.
상세보기
Hermant Eric (Vernon FRX), Diverging portion of discontinuous curvature for a rocket engine nozzle.
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Beichel Rudi (Sacramento CA), Dual expander rocket engine.
상세보기
Bornstein Lawrence J. (Sacramento CA), Dual thrust rocket motor.
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Klees Garry W. (Mercer Island WA) Wright Charles P. (Seattle WA), Internally ventilated noise suppressor with large plug nozzle.
상세보기
Mayer Wolfgang,DEX, Method of injecting a first and a second fuel component and injection head for a rocket.
상세보기
Bornstein Lawrence J. (Sacramento CA), Method of making dual-thrust rocket motor.
상세보기
Dusa Donald J. (Cincinnati OH), Multiple bypass-duct turbofan with annular flow plug nozzle and method of operating same.
상세보기
Dressler, Gordon A.; Mueller, Thomas J.; Rotenberger, Scott J., Pintle injector rocket with expansion-deflection nozzle.
상세보기
Lovelace Donald E. (Huntsville AL) Schexnayder Michael C. (Huntsville AL) Snyder George W. (Huntsville AL), Plug nozzle kinetic energy penetrator rocket.
상세보기
Marguet Roger (Issy les Moulineaux FRX) Petit Bernard (Les Ulis Bures FRX) Naduad Lionel (Massy FRX) Borton Pierre (Boulogne Billancourt FRX), Power units of the ram-jet engine type.
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Mango,Frank S., Propellant management system and method for multiple booster rockets.
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Hivert Michel (Merignac FRX) Coleno Raymond (Saint-Aubin De Medoc FRX), Propulsion device comprising a block of propellant provided with a central duct of variable section.
상세보기
Bonniot Claude E. (Gisors FRX), Rocket engine expansion nozzle with complementary annular nozzle.
상세보기
Bulman, Melvin J., Rocket vehicle thrust augmentation within divergent section of nozzle.
상세보기
Bulman Melvin J. (Folsom CA), Scramjet injector.
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Lewis Joseph W. (Edwards Air Force Base CA), Solid rocket motor with nozzle containing aromatic amide fibers.
상세보기
Carter Gregory E. (3120 Kings Lake Blvd. Naples FL 33962), Spin-stabilized missile with plug nozzle.
상세보기
Klees Garry W. (Mercer Island WA), Supersonic jet engine installation and method with sound suppressing nozzle.
상세보기
Wynosky Thomas A. (Madison CT) Campbell Charles A. (Palm Beach Gardens FL) Mischke Robert J. (Middletown CT), Two-dimensional plug nozzle.
상세보기
Lair, Jean-Pierre, Variable area plug nozzle.
상세보기
Wagenknecht Conrad D. (West Chester OH), Variable cycle plug nozzle and flap and method of operating same.
상세보기

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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Thrust augmentation in plug nozzles and expansion-deflection nozzles 원문보기

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