Variable cycle propulsion system with compressed air tapping for a supersonic airplane
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0167419
(2002-06-13)
|
우선권정보 |
FR-0007773 (2001-06-14) |
§371/§102 date |
20030910
(20030910)
|
발명자
/ 주소 |
- Franchet, Michel
- Laugier, Yann
- Loisy, Jean
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier &
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
5 |
초록
▼
A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said engine, and capable of generating ad
A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said engine, and capable of generating additional thrust for takeoff, landing, and subsonic cruising speeds, at least one pipe connecting the engine to the auxiliary propulsion assembly to convey thereto compressed air produced by the compressor so as to enable the auxiliary propulsion assembly to generate additional thrust for takeoff, landing, and subsonic cruising flight, there being at least one valve enabling the pipe to be closed off for supersonic cruising flight.
대표청구항
▼
1. A variable cycle propulsion system for a supersonic airplane, the system comprising:at least one low-bypass ratio engine having at least one compressor and configured to generate thrust for supersonic flight speeds; at least one high-bypass ratio auxiliary propulsion assembly separate from said e
1. A variable cycle propulsion system for a supersonic airplane, the system comprising:at least one low-bypass ratio engine having at least one compressor and configured to generate thrust for supersonic flight speeds; at least one high-bypass ratio auxiliary propulsion assembly separate from said engine, and configured to generate additional horizontal thrust for takeoff, landing, and subsonic cruising speeds; and at least one pipe connecting the engine to the auxiliary propulsion assembly to convey thereto compressed air produced by the compressor to enable the auxiliary propulsion assembly to generate additional horizontal thrust for takeoff, landing, and subsonic cruising flight and to reduce noise during takeoff, landing, and subsonic cruising flight by increasing a bypass ratio of said propulsion system, at least one valve provided for enabling the at least one pipe to be closed off for supersonic cruising flight, wherein the at least one auxiliary propulsion assembly is housed in an airplane fuselage, wherein louvers are provided in the fuselage, wherein said louvers are open as to feed air to the at least one auxiliary propulsion assembly during takeoff, landing, and subsonic cruising flight, and said louvers are closed for supersonic cruising flight, and wherein retractable exhaust nozzles are provided to exhaust the thrust-producing gas during stages of flight. 2. A system according to claim 1, wherein the auxiliary propulsion assembly includes a combustion chamber fed with compressed air during takeoff, landing, and subsonic cruising flight, a turbine through which a combustion gas produced by said combustion chamber passes, and a fan rotated by said turbine.3. A system according to claim 1, wherein the pipe conveys about 20% to 40% of air coming from a last stage of the compressor of the engine.4. A system according to claim 1, having at least two engines feeding compressed air to a single propulsion assembly.5. A system according to claim 1, comprising at least two engines feeding compressed air independently to two propulsion assemblies to improve safety in an event one of said propulsion assemblies fails.6. A system according to claim 5, wherein the two propulsion assemblies are offset one behind the other along a main axis of the airplane to optimize a volume occupied therein.
이 특허에 인용된 특허 (5)
-
Johnson James E. (Hamilton OH) Castells Onofre T. M. (Fairfield OH) Rundell Dan J. (Madeira OH), Auxiliary lift propulsion system with oversized front fan.
-
Snell Leonard S. (Bristol GB2), Gas turbine engines.
-
Bollinger Robert S. (Newhall CA) Nicolai Leland M. (Castaic CA), Propulsion system for a V/STOL aircraft.
-
Rudolph Peter K. C. (Seattle WA), Supersonic airplane with subsonic boost engine means and method of operating the same.
-
Zimmermann Vincent H. (Olivette MO) DEGarcia ; Jr. Horacio J. (Maryland Heights MO) Pierson Harlan K. (Hazelwood MO), Trifan powered VSTOL aircraft.
이 특허를 인용한 특허 (3)
-
Hutterer, Joseph A., Fuel efficient fixed wing aircraft.
-
Suciu, Gabriel L.; Chandler, Jesse M., Gas turbine engine having fan rotor driven by turbine exhaust and with a bypass.
-
Tafoya, Samuel Barran, Stealth bomber, transporter, air-to-air fueling tanker, and space plane.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.