Pulsejet ejector thrust augmentor
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0245519
(2002-09-16)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
2 인용 특허 :
7 |
초록
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A pulsejet system and method requires no pulsejet internal moving parts. Each pulsejet includes a combustion chamber having an upstream inlet port joined to an inlet diffuser, boundary layer air ports enveloping the combustion chamber, and a downstream exit port joined to a discharge nozzle. Each pu
A pulsejet system and method requires no pulsejet internal moving parts. Each pulsejet includes a combustion chamber having an upstream inlet port joined to an inlet diffuser, boundary layer air ports enveloping the combustion chamber, and a downstream exit port joined to a discharge nozzle. Each pulsejet discharges into an ejector to increase net thrust. Each ejector includes an augmentor cell having side walls and perforated end plates. The perforated end plate between each pair of pulsejets is shared to permit the discharge thrust to equalize across the pulsejet group. Air and fuel mix in the combustion chamber and are detonated by a reflected back-pressure wave. Detonation/deflagration reverse pressure waves compressing boundary layer air flow act as a pneumatic throat to temporarily choke off inlet fresh air at the upstream inlet port. The pneumatic throat replaces the conventional mechanical valve used for this purpose.
대표청구항
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1. A pulsejet system, comprising:a group of pulsejets each having no moving parts and including: (a) a boundary layer air plenum defining a combustion chamber having an upstream inlet port, a plurality of boundary layer air ports enveloping said combustion chamber, and a downstream exit port; (b) sa
1. A pulsejet system, comprising:a group of pulsejets each having no moving parts and including: (a) a boundary layer air plenum defining a combustion chamber having an upstream inlet port, a plurality of boundary layer air ports enveloping said combustion chamber, and a downstream exit port; (b) said combustion chamber being connectably joined to an inlet diffuser at said upstream inlet port; and (c) said combustion chamber being connectably joined at said downstream exit port to a discharge nozzle; and each pulsejet of said group of pulsejets being disposed in one of a plurality of ejectors; wherein each of said plurality of ejectors directs a discharge thrust from one of said group of pulsejets; and wherein each said ejector comprises an augmentor cell having side walls and perforated end plates. 2. The pulsejet system of claim 1, further comprising:each said augmentor cell including at least one movable cowl rotatably attached to one of said side walls; and movement of said movable cowl directably controlling one of an inlet flow into said augmentor cell and an exhaust flow from said augmentor cell. 3. The pulsejet system of claim 1, wherein said group of pulsejets is formed as successive pairs of pulsejets.4. The pulsejet system of claim 3, comprising:at least one of said perforated end plates of said augmentor cell between each said successive pair of pulsejets is a shared perforated end plate; and each said shared perforated end plate having a plurality of apertures permitting said discharge thrust to combine between said successive pairs of pulsejets. 5. The pulsejet system of claim 1, wherein said inlet diffuser, said combustion chamber and said discharge nozzle of each pulsejet of said group of pulsejets are co-aligned on a common longitudinal center-line.6. The pulsejet system of claim 1, further comprising:said inlet diffuser and said combustion chamber of each pulsejet of said group of pulsejets are co-aligned on a common longitudinal centerline; and said discharge nozzle having a nozzle longitudinal center-line aligned approximately perpendicular to said common longitudinal center-line. 7. A pulsejet system, comprising:a boundary layer air plenum defining at least a combustion chamber, an upstream inlet port, and a plurality of boundary layer air ports in communication with said combustion chamber; an air supply in communication with said combustion chamber through said inlet port; a reverse pressure wave created in said combustion chamber upon ignition of a combustion mixture; and a choke point operably formed within said combustion chamber at a location where said reverse pressure wave contacts said air supply; wherein said choke point is operable to temporarily block said air supply. 8. The system of claim 7, further comprising:a discharge nozzle in communication with said combustion chamber; and a boundary layer air provided through said plurality of boundary layer air ports operable to stabilize said combustion mixture; wherein said combustion mixture is ignitable in said combustion chamber to operably form each of a forward pressure wave directed toward said discharge nozzle and a discharge nozzle back-pressure wave. 9. The system of claim 7, comprising a pulsejet thrust operably generated when said forward pressure wave exits said discharge nozzle.10. The system of claim 7, comprising an inlet diffuser connectable to said combustion chamber.11. The system of claim 7, wherein said discharge nozzle comprises a plurality of structural members.12. A pulsejet system, comprising:a boundary layer air plenum defining each of a combustion chamber, a combustion chamber upstream inlet port, and a plurality of boundary layer air ports in communication with the combustion chamber; a discharge nozzle in fluid communication with the combustion chamber; an air supply receivable in the combustion chamber through the upstream inlet port; a combustion mixture including the air supply and a fuel; a reverse pressure wave operably created by combustion of the combustion mixture; a forward pressure wave operably created by combustion of the combustion mixture; and a choke point located within the combustion chamber and operably formed at a location defining compressible contact between the air supply and the reverse pressure wave, the choke point being operable to temporarily block the air supply following a detonation stage. 13. The system of claim 12, further comprising:a boundary layer air volume receivable through the plurality of boundary layer air ports operable to stabilize the combustion mixture; and a discharge nozzle back-pressure wave operably formed by combustion of the combustion mixture. 14. The system of claim 13, comprising:a taper section of the boundary layer air plenum; and a high temperature gas component of the discharge nozzle back-pressure wave; wherein the detonation stage is initiated by reflection of the high temperature gas component from both the taper section and the discharge nozzle towards the combustion chamber, the high temperature gas component being operable to ignite the combustion mixture. 15. The system of claim 12, wherein the combustion chamber further comprises:a substantially conical shaped section; and a taper section disposed between the conical shaped section and the discharge nozzle. 16. The system of claim 15, wherein the taper section comprises a continuously decreasing diameter between the conical shaped section and the discharge nozzle.17. The system of claim 12, wherein the discharge nozzle comprises a plurality of structural members operable to structurally support the pulsejet engine.18. A pulsejet system, comprising:a boundary layer air plenum defining each of a combustion chamber, a combustion chamber upstream inlet port, a plurality of boundary layer air ports in communication with the combustion chamber, a taper section and a downstream exit port; a discharge nozzle in fluid communication with the combustion chamber; a combustion mixture receivable within the combustion chamber; a discharge nozzle backpressure wave operably created by combustion of the combustion mixture; a high temperature gas component of the discharge nozzle back-pressure wave; and a detonation stage operably created by reflection of the high temperature gas component from both the taper section and the discharge nozzle towards the combustion chamber, the high temperature gas component being operable to ignite the combustion mixture.
이 특허에 인용된 특허 (7)
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Dorris ; III John ; Smith David Michael ; Parekh David Espineli ; Kibens Valdis, Apparatus and methods for active flow control of a nozzle exhaust plume.
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Papsdorf Kurt R. (Florida ZAX), Combustion unit.
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West Bill (Laguna Niguel CA) Trulis Thomas (San Juan Capistrano CA), Exhaust fume energy source and waste combustion apparatus.
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Otto William F. (Huntsville AL) Roberts Thomas G. (Huntsville AL) Jenkins Andrew H. (Huntsville AL) Honeycutt Thomas E. (Somerville AL), Laser effects simulator.
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Catt Jeffrey Alan ; Miller Daniel Nicholas, Method and apparatus of asymmetric injection at the subsonic portion of a nozzle flow.
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Yamaguchi Shigeki (Nagoya JPX) Ohiwa Norio (Nagoya JPX) Ishiguro Katsusuke (Nagoya JPX), Pulse combustion device.
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Oppenheim A. K. (Berkeley CA) Stewart H. E. (Alameda CA) Hom K. (Hercules CA), Pulsed jet combustion generator for premixed charge engines.
이 특허를 인용한 특허 (2)
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Ouellette, Richard P, Acoustic pulsejet helmet.
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Nalim, Razi; Akbari, Pejman, Direct injection of a discrete quantity of fuel into channels of a wave rotor engine.
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