All-supersonic ducted fan for propelling aircraft at high subsonic speeds
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F04D-029/38
F04D-021/00
F01D-005/14
F04D-029/32
F04D-019/00
출원번호
US-0999193
(2014-01-27)
등록번호
US-9212663
(2015-12-15)
발명자
/ 주소
O'Neill, Terrence
출원인 / 주소
O'Neill, Terrence
대리인 / 주소
O'Neill, Francis P.
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A supersonic fan has at least two fan blades extending radially from a rim surface of a hub and is circumscribed by a duct. An inboard leading edge having an inboard sweep angle rotates at approximately Mach 1 or greater. A low-pressure zone generates propulsion. An inboard flow regime may migrate o
A supersonic fan has at least two fan blades extending radially from a rim surface of a hub and is circumscribed by a duct. An inboard leading edge having an inboard sweep angle rotates at approximately Mach 1 or greater. A low-pressure zone generates propulsion. An inboard flow regime may migrate outboard from the rim surface and contaminate the low-pressure zone, reducing propulsion. An outboard leading edge having an outboard sweep angle extends radially from the inboard leading edge to form an apex. The inboard and outboard sweep angles are each at least approximately 30 degrees and in the opposite direction. An inboard vortex forming near to and as a result of the apex trails circumferentially across the fan blades and is positioned to substantially confine the inboard flow regime to be inboard of the apex, thereby preserving the low-pressure zone and increasing propulsion for the supersonic fan.
대표청구항▼
1. A supersonic fan, comprising: a hub having a rim surface;a rim radius defining the radius of the rim surface;at least two fan blades extending radially from the rim surface to a tip radius of the fan blades, the fan blades being configured to generate a low-pressure zone along each fan blade for
1. A supersonic fan, comprising: a hub having a rim surface;a rim radius defining the radius of the rim surface;at least two fan blades extending radially from the rim surface to a tip radius of the fan blades, the fan blades being configured to generate a low-pressure zone along each fan blade for producing propulsion;an inboard leading edge of the fan blade extending from the hub, the inboard leading edge having an inboard length and swept forward in a direction of hub rotation by an inboard sweep angle that is substantially constant;an outboard leading edge extending approximately radially from the inboard leading edge and forming an apex therebetween, the outboard leading edge swept backward from the direction of hub rotation by an outboard sweep angle that is substantially constant from the apex to a blade tip, wherein the inboard and the outboard sweep angles are each between approximately 30 degrees and approximately 70 degrees, and where the apex is offset from the rim surface by greater than approximately 0.25 inch and by less than approximately 40% of a blade span spanning the rim surface to the blade tip;a duct circumscribing the fan blades;a ratio of the rim radius to the tip radius is at least approximately 0.65 for creating a substantially uniform and supersonic airspeed along the outboard leading edge and for enabling a lightweight blade without flutter; andthe apex configured to form a vortex proximate the apex and trailing circumferentially across the fan blades from approximately the direction of hub rotation and substantially confining an inboard flow regime forming proximate to the rim surface to remain inboard of the apex, thereby preserving the low-pressure zone and increasing propulsion for the supersonic fan. 2. The supersonic fan of claim 1, wherein: the outboard leading edge is positioned to be behind a forward shock wave. 3. The supersonic fan of claim 1, wherein: the apex is offset from the rim surface by approximately 0.5 inch and the tip radius is approximately 14 inches. 4. The supersonic fan of claim 1, wherein: each fan blade consists of at least one of the following: metal, carbon composite, molded composite, laminate composite, ceramic, plastic. 5. The supersonic fan of claim 1, further comprising: a duct clearance between the duct and a tip of each fan blade, where the duct clearance is less than approximately 0.010 inch in order to minimize drag. 6. The supersonic fan of claim 1, further comprising: at least one continuous filament surrounded by a cured binder and wound spirally to form the hub having a plane of rotation and a rim width;wherein each fan blade has at least one mounting finger substantially parallel to the plane of rotation and buried adhesively beneath the rim surface, the mounting finger being buried prior to curing the cured binder; andwherein the mounting finger has a finger thickness of less than approximately 15 percent of the rim width, thereby forming the supersonic fan in one piece circumscribed by the duct. 7. The supersonic fan of claim 6, wherein: the continuous filament consists of at least one of the following: glass fiber, carbon fiber, polymer, metal, a plurality of non-woven fibers, unidirectional fabric, para-aramid fiber, ceramic fiber. 8. The supersonic fan of claim 6, wherein: the cured binder consists of at least one of the following: epoxy resin, polyester, polymer. 9. The supersonic fan of claim 6, wherein: a chord of each fan blade is twisted out of the plane of rotation by a blade twist angle approximately about a radial of the hub and within a finger twist zone substantially below the rim surface, the blade twist angle setting an angle of attack. 10. The supersonic fan of claim 1, further comprising: one or more air inlet slats positioned circumferentially along a forward edge of the duct, where a front lip of each slat is radially shaped. 11. The supersonic fan of claim 1, further comprising: a convergence-divergence nozzle aft of the fan blades, the convergence-divergence nozzle optimizing an angle of attack for the fan blades. 12. The supersonic fan of claim 1, further comprising: an array of stator blades aft of the fan blades, the array of stator blades straightening and redirecting an axial flow. 13. A supersonic fan, comprising: a hub having a hub volume defined by an inner circumferential surface perpendicularly adjoining two parallel side surfaces and extending approximately radially to a rim surface having a rim radius and a rim width, the rim radius defining a plane of rotation;at least one continuous filament surrounded by a cured binder having a binder volume, the continuous filament having a filament inner end and a filament outer end, the filament inner end terminating proximate to the inner circumferential surface, the continuous filament spirally wound substantially within the plane of rotation to array laterally between the two side surfaces and to layer radially out to the rim surface where the filament outer end proximately terminates, thereby forming the hub, wherein a ratio of the binder volume to the hub volume is between approximately 20 percent and approximately 65 percent;at least two fan blades each having a working portion including an inboard leading edge and an outboard leading edge, and including at least one mounting finger having a finger thickness, the mounting finger being substantially parallel to the plane of rotation and buried beneath the rim surface, the working portion extending above the rim surface to a tip radius, and where a ratio of the finger thickness to the rim width is less than approximately 25 percent of a ratio of the binder volume to the hub volume; andthe outboard leading edge of each of the at least two fan blades being swept backward from a direction of hub rotation by an outboard sweep angle that is substantially constant out to a blade tip starting at a radial location of less than approximately 40% of a blade span spanning the rim surface to the blade tip, wherein an inboard sweep angle of the inboard leading edge and the outboard sweep angle of the outboard leading edge are each between approximately 30 degrees and approximately 70 degrees; andwherein the cured binder binds the fan blades to the hub for forming the supersonic fan in one piece, where a ratio of the rim radius to the tip radius is at least approximately 0.65 for creating a substantially uniform and supersonic airspeed along the outboard leading edge and for enabling a lightweight blade without flutter, and where the continuous filament provides substantially for a tensile strength resisting centrifugal forces within the hub. 14. The supersonic fan of claim 13, wherein: the continuous filament consists of at least one of the following: glass fiber, carbon fiber, polymer, metal, a plurality of non-woven fibers, unidirectional fabric, para-aramid fiber, ceramic fiber. 15. The supersonic fan of claim 13, wherein: the cured binder consists of at least one of the following: epoxy resin, polyester, polymer. 16. The supersonic fan of claim 13, wherein: each fan blade consists of at least one of the following: metal, carbon composite, molded composite, laminate composite, ceramic, plastic. 17. The supersonic fan of claim 13, wherein: each fan blade contains approximately 6 mounting fingers arranged to be non-overlapping within the rim width. 18. The supersonic fan of claim 13, wherein: the finger thickness ranges from approximately 0.020 inch to approximately 0.060 inch for resisting bending loads. 19. The supersonic fan of claim 13, wherein: a chord of each fan blade is twisted out of the plane of rotation by a blade twist angle approximately about a radial of the hub and within a finger twist zone substantially below the rim surface, the blade twist angle setting an angle of attack. 20. The supersonic fan of claim 13, further comprising: a duct circumscribing the fan blades. 21. A method providing for a supersonic fan, comprising: pultruding at least one continuous filament through a bath of an uncured binder, the continuous filament being thereby coated and forming a coated filament;winding the coated filament spirally into a hub, the hub being shaped substantially as a disk having a plane of rotation, a rim surface, a rim radius and a rim width;embedding at least 2 fan blades into the rim surface, the fan blade having a working portion and at least one mounting finger having a finger thickness, the mounting finger being substantially parallel to and adhering between adjacent windings of the coated filament and thereby displacing a part of the uncured binder, wherein the finger thickness is less than approximately 15 percent of the rim width, the working portion being located opposite the mounting finger and extending above the rim radius to a tip radius, the working portion being configured to generate a low-pressure zone along each fan blade for producing propulsion;curing the hub;circumscribing the fan blades with a duct;dividing the working portion into an inboard length and an outboard length joining at an apex therebetween, the inboard length corresponding to an inboard leading edge extending from the rim surface and the outboard length corresponding to an outboard leading edge extending to a blade tip, the apex being offset from the rim surface by not less than approximately 0.25 inch and by not more than approximately 40% of a blade span spanning the rim surface to the blade tip;sweeping the outboard leading edge backward from a direction of hub rotation by an outboard sweep angle that is substantially constant from the apex to the blade tip and sweeping the inboard leading edge forward in a direction of hub rotation by an inboard sweep angle that is substantially constant, where the inboard and the outboard sweep angles are each between approximately 30 and approximately 70 degrees;limiting a ratio of the rim radius to the tip radius to be greater than approximately 0.65 for creating a substantially uniform and supersonic airspeed across the outboard leading edge, for enabling a lightweight blade without flutter, and for producing the supersonic fan in one piece; andwhere the apex is configured to form a vortex proximate the apex and trailing circumferentially across the fan blades from approximately the direction of hub rotation and substantially confining an inboard flow regime forming proximate to the rim surface to remain inboard of the apex, thereby preserving the low-pressure zone and increasing propulsion for the supersonic fan. 22. The method of claim 21, wherein: the continuous filament consisting of at least one of the following: glass fiber, carbon fiber, polymer, metal, a plurality of non-woven fibers, unidirectional fabric, para-aramid fiber, ceramic fiber. 23. The method of claim 21, wherein: the uncured binder consisting of at least one of the following: epoxy resin, polyester, polymer. 24. The method of claim 21, wherein: each fan blade consisting of at least one of the following: metal, carbon composite, molded composite, laminate composite, ceramic, plastic. 25. The method of claim 21, wherein: the finger thickness ranges from approximately 0.020 inch to approximately 0.060 inch for resisting bending loads. 26. The method of claim 21, further comprising: twisting a chord of each fan blade out of the plane of rotation by a blade twist angle approximately about a radial of the hub and within a finger twist zone that is substantially below the rim surface, the blade twist angle setting an angle of attack.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (11)
Cruzen Gerald S. (Gregory MI), Composite turbine wheel, method of manufacture and fixture therefor.
Bliss Donald B. (Belmont MA), Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor bla.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.