[특허]Low shock strength propulsion system

Gulfstream Aerospace Corporation

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

특허 상세정보

MyON담기

내보내기

Low shock strength propulsion system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/02
미국특허분류(USC)	060/226.1; 137/015.1
출원번호	US-0257982 (2008-10-24)
등록번호	US-8739514 (2014-06-03)
발명자 / 주소	Conners, Timothy R.
출원인 / 주소	Gulfstream Aerospace Corporation
대리인 / 주소	Ingrassia Fisher & Lorenz, P.C.
인용정보	피인용 횟수 : 2 인용 특허 : 87

초록

A supersonic nacelle design is disclosed herein that employs a bypass flow path internal to the nacelle and around the engine. By shaping the nacelle, the nacelle may function to reduce sonic boom strength, cowl drag, and /or airframe interference drag. The nacelle may also function to improve total pressure recovery and/or total thrust of the primary flow path through the engine.

대표
청구항
▼

1. A supersonic nozzle for a supersonic engine, comprising: an outer wall;a bypass wall disposed within the outer wall, the bypass wall having a bypass wall leading edge positioned proximate an outer wall leading edge, the bypass wall being configured to continuously separate an aft directed airflow inside the outer wall into a primary flow portion and a bypass flow portion around the supersonic engine, the primary flow portion passing through the supersonic engine and the bypass flow portion passing through a bypass that bypasses the supersonic engine;a set of struts configured to couple the outer wall with the bypass wall, the set of struts configured to tailor a direction of the bypass flow portion, andan external compression inlet having an external compression surface upstream of the supersonic engine. 2. The supersonic nozzle of claim 1, wherein the set of struts comprises composite or other lightweight material for providing structural stiffness to the supersonic nozzle. 3. The supersonic nozzle of claim 1, wherein a thickness of the struts is configured to control an expansion of an exhaust from the supersonic engine. 4. The supersonic nozzle of claim 1, wherein the set of struts is constructed using linear surfaces. 5. The supersonic nozzle of claim 1, wherein the set of struts controls an amount of airflow depending on local blockage characteristics within the bypass flow portion; andwherein the set of struts shapes the bypass flow portion around internal blockages created by a gearbox of the supersonic engine. 6. The supersonic nozzle of claim 1, wherein the set of struts directs the bypass flow portion into a substantially circumferentially uniform pattern prior to exhaust. 7. The supersonic nozzle of claim 1, wherein the outer wall comprises a trailing edge that defines an exit cross-sectional area of the supersonic nozzle. 8. The supersonic nozzle of claim 1, wherein the supersonic nozzle expands the bypass flow portion to maximize a thrust of the supersonic engine and to minimize a sonic boom signature generated by exhaust of the primary flow portion. 9. The supersonic nozzle of claim 1, wherein the outer wall comprises a thin-wall composite construction. 10. A low shock supersonic nacelle, comprising: an engine;an external compression inlet having an external compression surface upstream of the engine;an outer wall;a bypass wall disposed within the outer wall, the bypass wall having a bypass wall leading edge positioned proximate an outer wall leading edge;a set of struts configured to couple the outer wall with the bypass wall; an inlet module comprising front portions of the outer wall and the bypass wall, the inlet module configured to decelerate an incoming airflow to a speed compatible with the engine; anda nozzle module comprising rear portions of the outer wall and the bypass wall, the nozzle module configured to accelerate an exhaust from the engine and a bypass;wherein the bypass wall continuously divides the incoming aft directed airflow into a primary flow portion directed into the engine and a bypass flow portion directed into the bypass around the engine wherein the bypass flow portion bypasses the engine. 11. The low shock supersonic nacelle of claim 10, wherein the inlet module comprises: a leading edge configured to generate a first shock wave;a compression surface positioned downstream of the leading edge and having at least one curved section configured to generate compression; anda cowl lip on a cowling spatially separated from the compression surface such that the cowl lip and the compression surface define an inlet opening for receiving a supersonic flow;wherein the compression surface is configured to generate a second shock wave that, during operation of the inlet module at a predetermined cruise speed, extends from the compression surface to intersect the first shock wave at a point substantially adjacent to the cowl lip. 12. The low shock supersonic nacelle of claim 11, wherein the compression generated by the curved section is characterized by a series of Mach lines where, during operation of the inlet module at the predetermined cruise speed, at least a plurality of the Mach lines do not focus on the point substantially adjacent to the cowl lip. 13. The low shock supersonic nacelle of claim 10, wherein the bypass flow portion receives and captures a substantial region of flow distortion created by the inlet module. 14. The low shock supersonic nacelle of claim 10, further comprising a diffuser that receives the primary flow portion and delivers a subsonic flow to the engine. 15. The low shock supersonic nacelle of claim 10, wherein the set of struts comprises composite materials configured to provide structural stiffness to the nozzle module. 16. The low shock supersonic nacelle of claim 10, wherein a thickness of the struts is configured to control an expansion of exhaust from the engine. 17. The low shock supersonic nacelle of claim 10, wherein the set of struts is constructed using linear surfaces within the nozzle module. 18. The low shock supersonic nacelle of claim 10, wherein the set of struts controls an amount of airflow depending on local blockage characteristics within the bypass; andwherein the set of struts shapes the bypass flow portion around internal blockages created by a gearbox mounted on and about the engine. 19. The low shock supersonic nacelle of claim 10, wherein the set of struts directs the bypass flow portion into a substantially circumferentially uniform pattern prior to exhaust. 20. The low shock supersonic nacelle of claim 10, wherein the outer wall comprises a trailing edge that defines an exit cross-sectional area of the nozzle module. 21. The low shock supersonic nacelle of claim 10, wherein the nozzle module expands the bypass flow portion to maximize a thrust of the supersonic engine and to minimize a sonic boom signature created by the primary flow portion. 22. The low shock supersonic nacelle of claim 10, wherein the outer wall comprises a thin-wall composite construction. 23. The low shock supersonic nacelle of claim 10, wherein increasing a distance between the outer wall and the engine increases opportunities for localized, tailored, three-dimensional shaping of the outer wall. 24. The low shock supersonic nacelle of claim 10, wherein the bypass attenuates instabilities in the incoming airflow at the inlet opening. 25. The low shock supersonic nacelle of claim 10, wherein the front portions of the outer wall and the bypass wall comprise aerodynamically coupled leading edges at a low flight speeds configured to generate an internal recirculating flow region immediately aft of the leading edge of the outer wall; andwherein the internal recirculating flow region generates a smoothly curved virtual aerodynamic surface that reduces a downstream flow separation and distortion within the primary flow portion leading to the engine. 26. A method of decelerating a supersonic flow for a supersonic propulsion system, the method comprising: cruising at a predetermined supersonic speed;receiving a supersonic flow in an external compression inlet having an external compression surface, a bypass splitter, and a cowl lip, the cowl lip spatially separated from and aft of the external compression surface;splitting a subsonic flow into a primary flow portion and a bypass flow portion around an engine, whereby the bypass flow portion receives and captures a substantial region of a flow distortion created by the inlet;diffusing the primary flow portion with a diffuser to a predetermined speed suitable for an engine;expanding the primary flow portion after the primary flow portion leaves the engine and reaches a nozzle; anddirecting the bypass flow portion into a substantially circumferentially uniform pattern prior to exhaust. 27. The method of claim 26, further comprising: generating a first shock wave from a leading edge of the external compression surface of the external compression inlet;generating a second shock wave that, during operation of the external compression inlet a predetermined supersonic speed, extends from the external compression surface to intersect the first shock wave at a point substantially adjacent to the cowl lip; and generating compression of the supersonic flow by a curved section of the external compression surface.

이 특허에 인용된 특허 (87)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

Low shock strength propulsion system

초록

대표
청구항
▼

이 특허에 인용된 특허 (87)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Low shock strength propulsion system

초록

대표청구항 ▼

이 특허에 인용된 특허 (87)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

대표
청구항
▼