Isentropic compression inlet for supersonic aircraft
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/04
B64D-033/02
B64C-030/00
F02K-007/10
출원번호
US-0629181
(2012-09-27)
등록번호
US-9482155
(2016-11-01)
발명자
/ 주소
Conners, Timothy R.
Henne, Preston A.
Howe, Donald C.
출원인 / 주소
Gulfstream Aerospace Corporation
대리인 / 주소
Ingrassia, Fisher & Lorenz PC
인용정보
피인용 횟수 :
0인용 특허 :
87
초록▼
A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce
A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.
대표청구항▼
1. An external compression inlet for use in a jet engine of the type including a compression surface having a foremost point and a cowl lip characterized by a cowl lip angle, the inlet comprising, in cross section: an initial segment disposed at a leading edge of said compression surface and incline
1. An external compression inlet for use in a jet engine of the type including a compression surface having a foremost point and a cowl lip characterized by a cowl lip angle, the inlet comprising, in cross section: an initial segment disposed at a leading edge of said compression surface and inclined at a constant, initial turn angle α with respect to a free stream, said initial segment being configured to produce, at a predetermined design cruising speed, a bow shock which intersects an intersection point proximate said cowl lip; anda continuously curved segment aft of and structurally contiguous with said initial segment, said continuously curved segment being configured to cooperate with said initial segment to produce, at said predetermined design cruising speed, a terminal shock which extends from said intersection point to said compression surface; wherein said continuously curved segment is configured to produce, at said predetermined design cruising speed, infinitesimally weak shocklets generally directed toward a portion of said terminal shock which extends away from said cowl lip; andwherein, a local angle of inclination of each of a plurality of successive points along said continuously curved segment is relaxed relative to a traditional, unrelaxed isentropic surface, such that at said predetermined design cruising speed a plurality of said infinitesimally weak shocklets extend from a relaxed portion of said continuously curved segment and intersect said terminal shock aft of and spaced apart from said intersection point, and the plurality of said infinitesimally weak shocklets do not focus at said intersection point at said predetermined design cruising speed. 2. The external compression inlet of claim 1, wherein; said continuously curved segment is configured to produce, at said predetermined design cruising speed, a reduced local flow angle relative to a local flow angle produced by a non-relaxed, fully isentropic curved segment, in the vicinity of said cowl lip; andsaid cowl lip angle is substantially aligned with said reduced local flow angle. 3. The external compression inlet of claim 2, wherein said foremost point comprises a leading edge. 4. The external compression inlet of claim 2, wherein said foremost point comprises a leading point. 5. A method of relaxing the geometry of an isentropic region of a compression surface to facilitate a reduced cowl lip angle in an external compression inlet, comprising the steps of: providing an initial, straight segment at one of a leading edge and an apex of said compression surface at a constant, initial turn angle α with respect to a free stream;positioning a cowl lip at a predetermined distance aft of the one of said leading edge and said apex such that, at a specific and predetermined design cruising speed, said initial, straight segment produces a bow shock which intersects a predetermined intersection point proximate said cowl lip;defining, for said specific and predetermined design cruising speed, a terminal shock which extends from said predetermined intersection point to said compression surface;providing a continuously curved concave segment aft of and structurally contiguous with said initial, straight segment;configuring said continuously curved concave segment to produce, at said specific and predetermined design cruising speed, a plurality of successive infinitesimally weak shocklets generally directed towards a portion of said terminal shock which extends away from said cowl lip; andrelaxing, for a plurality of successive points in the aft direction along said continuously curved concave segment, the local angle of inclination of said continuously curved concave segment relative to a traditional isentropic surface, such that at said specific and predetermined design cruising speed a plurality of shocklets extend from said relaxed portion of said continuously curved concave segment and intersect said terminal shock aft of and away from said predetermined intersection point, and said plurality of successive infinitesimally weak shocklets do not focus at said predetermined intersection point at said specific and predetermined design cruising speed. 6. The method of claim 5, further comprising the steps of: reducing, as a result of said relaxing step, a local flow angle relative to a local flow angle of a non-relaxed, fully isentropic curved segment, in the vicinity of said cowl lip; andreducing an angle of inclination of said cowl lip with respect to the free stream to bring said reduced cowl lip angle substantially into alignment with said reduced local flow angle. 7. The method of claim 5, wherein relaxing comprises reducing, for said plurality of successive points in along the aft direction of said continuously curved concave segment, the associated local angle of inclination of said continuously curved concave segment relative to a fully isentropic curved surface.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (87)
Destuynder Roger (Noisy le Sec FRX) Bouttes Jacques (Paris FRX) Poisson-Quinton Philippe (Paris FRX), Active method and installation for the reduction of buffeting of the wings of an aircraft.
Taylor Thomas C. (P.O. Box 1547 Wrightwood CA 92397) Cerna Peter (2815 California ; #4 Dickinson TX 77539), Aerospike for attachment to space vehicle system.
Masashi Shigemi JP; Teruomi Nakaya JP; Shigemi Shindo JP; Minoru Takizawa JP; Takeshi Ohnuki JP, Arithmetic processing method and system in a wide velocity range flight velocity vector measurement system using a square truncated pyramid-shape five-hole pitot probe.
Stephen A. Huyer ; John R. Grant ; James S. Uhlman ; Jeffrey S. Marshall, Method for computing three dimensional unsteady flows by solution of the vorticity equation on a Lagrangian mesh.
Benne Michael Edward ; Donovan John Francis ; Kelble Christopher Allen ; Kihlken Thomas Allen ; Morris Martin Jesse ; Pal Alexander, Method for determining pressure.
Lind Richard C. ; Brenner Martin J., On-line .mu. method for robust flutter prediction in expanding a safe flight envelope for an aircraft model under flight test.
Buisson Dominique (Villemur FRX) Irvoas Joseph (Cugnaux FRX), Process and system for determining the longitudinal position of the center of gravity of an aircraft provided with an ad.
Blackburn Ronald F. ; Warmkessel Barry M. ; Kawamoto Sonja M., System for increasing the aerodynamic and hydrodynamic efficiency of a vehicle in motion.
Braden John A. (2791 Okawana Dr. Marietta GA 30067) Dixon Charles J. (3261 Hickory Crest Dr. Marietta GA 30064), Terraced channels for reducing afterbody drag.
Vdoviak John W. (Marblehead MA) Moyer Roy E. (Cincinnati OH) Evans Dennis C. (Topsfield MA), Turbine engine assembly with aft mounted outlet guide vanes.
Hirschel Ernst H. (Zorneding DEX) Fleckenstein Hubert (Grasbrunn DEX) Thiede Peter (Ganderkesee DEX), Wall with a drag reducing surface and method for making such a wall.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.