Thrust recovery outflow valves for use with aircraft
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-033/04
B64D-013/04
B64D-013/02
출원번호
US-0082582
(2016-03-28)
등록번호
US-10071815
(2018-09-11)
발명자
/ 주소
Tretow, Paul R.
Willie, Robert H.
Ferraiolo, Nicholas R.
출원인 / 주소
The Boeing Company
대리인 / 주소
Hanley, Flight & Zimmerman, LLC
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
Thrust recovery outflow valves for aircraft are disclosed. An example thrust recovery outflow valve includes a flow control member having a first aerodynamic surface and a second aerodynamic surface to define at least a portion of a fluid flow passageway between an inlet and an outlet of the thrust
Thrust recovery outflow valves for aircraft are disclosed. An example thrust recovery outflow valve includes a flow control member having a first aerodynamic surface and a second aerodynamic surface to define at least a portion of a fluid flow passageway between an inlet and an outlet of the thrust recovery outflow valve. A first portion of the first aerodynamic surface and a first portion of the second aerodynamic surface provides a converging profile between the inlet and a throat of the fluid flow passageway. A second portion of the first aerodynamic surface and a second portion of the second aerodynamic surface provides a diverging profile between the throat and the outlet of the fluid flow passageway. The fluid flow passageway is positioned at a small angle relative to an outer surface of an aircraft to enable fluid exiting the fluid flow passageway to provide a thrust recovery vector oriented substantially parallel to the outer surface of the aircraft and opposite a direction of drag.
대표청구항▼
1. A thrust recovery outflow valve comprising: a flow control member having a first aerodynamic surface and a second aerodynamic surface to define at least a portion of a fluid flow passageway between an inlet and an outlet of the thrust recovery outflow valve, a first portion of the first aerodynam
1. A thrust recovery outflow valve comprising: a flow control member having a first aerodynamic surface and a second aerodynamic surface to define at least a portion of a fluid flow passageway between an inlet and an outlet of the thrust recovery outflow valve, a first portion of the first aerodynamic surface and a first portion of the second aerodynamic surface to provide a converging profile between the inlet and a throat of the fluid flow passageway, and a second portion of the first aerodynamic surface and a second portion of the second aerodynamic surface to provide a diverging profile between the throat and the outlet of the fluid flow passageway, the flow control member to couple to an outer surface of a fuselage of an aircraft, the fluid flow passageway being positioned at a small angle relative to the outer surface of an aircraft when the valve is in an open position to enable fluid exiting the fluid flow passageway to provide a thrust recovery vector oriented substantially parallel to the outer surface of the aircraft and opposite a direction of drag; anda controller communicatively coupled to the thrust recovery outflow valve, the controller to determine a ratio between a cabin pressure of the aircraft and an atmospheric pressure at a given altitude of the aircraft, the controller to determine a throat area of the fluid flow passageway to accommodate a mass flow rate of cabin air between a cabin of the aircraft and an atmosphere needed to maintain the cabin pressure at a predetermined value and provide an outlet area to enable an exit pressure of cabin air exiting the outlet to be substantially equal to the atmospheric pressure at the given altitude. 2. The valve of claim 1, wherein the thrust recovery vector has an angle of between approximately zero degrees and ten degrees relative to the outer surface of the aircraft. 3. The valve of claim 1, wherein the flow control member includes shields extending from respective sides of the flow control member, the shields to define a portion of the fluid flow passageway. 4. The valve of claim 3, wherein the flow control member includes a first gate movable relative to a second gate, the first gate defining the first aerodynamic surface and the second gate defining the second aerodynamic surface. 5. The valve of claim 4, wherein the shields extend from the first gate. 6. The valve of claim 1, wherein a thrust recovery vector has an angle of between approximately 0 degrees and 10 degrees relative to a body axis of the aircraft when the thrust recovery vector is substantially parallel relative to the body axis. 7. A thrust recovery outflow valve for use with an aircraft: a first gate having a first aerodynamic surface; anda second gate having a second aerodynamic surface, the first gate to move relative to the second gate between an open position to allow fluid flow to atmosphere and a closed position to prevent fluid flow to atmosphere, the first aerodynamic surface of the first gate being spaced from the second aerodynamic surface of the second gate to define a fluid flow passageway having a convergent-divergent shape or profile when the thrust recovery outflow valve is in the open position, the first aerodynamic surface having a first portion and a second position, the second portion positioned between the first portion and an outlet of the thrust recovery outflow valve, the first portion including a curved profile and an upwardly extending surface extending from an end of the curved profile, the second portion having a tapered profile extending between a first end adjacent the first portion and a second end adjacent the outlet; anda controller to determine a ratio between a cabin pressure of the aircraft and an atmospheric pressure at a given altitude of the aircraft, the controller to move the first gate and the second gate to provide an outlet area to enable an exit pressure of cabin air exiting the outlet area to be substantially equal to the atmospheric pressure at the given altitude. 8. The valve of claim 7, wherein the first gate includes side plates extending from the first aerodynamic surface, the side plates to direct the fluid in the fluid flow passageway toward an outlet of the thrust recovery outflow valve. 9. The valve of claim 7, wherein the first aerodynamic surface and the second aerodynamic surface are substantially free of projections into a thrust recovery flow stream from the respective first and second aerodynamic surfaces. 10. The valve of claim 7, wherein the fluid flow passageway includes an inlet, a throat and an outlet, at least one of the throat or the outlet defining the outlet area. 11. The valve of claim 10, wherein at least one of the throat or the outlet is to be oriented closer to parallel relative to the body axis of the aircraft than orthogonal relative to the body axis when the valve is in the open position. 12. The valve of claim 10, wherein a first portion of the fluid flow passageway between the inlet and the throat has a converging profile. 13. The valve of claim 12, wherein a second portion of the fluid flow passageway between the throat and the outlet has a diverging profile. 14. The valve of claim 10, wherein a cross-sectional area at the throat is adjustable by moving the first gate relative to the second gate. 15. A thrust recovery outflow valve for use with an aircraft, the thrust recovery outflow valve comprising: an actuator coupled to a frame;a first gate rotationally coupled to the frame;a second gate rotationally coupled to the frame, a surface of the first gate to be spaced from a surface of the second gate to define a fluid flow passageway between an inlet and an outlet of the thrust recovery outflow valve, the first gate to move relative to the second gate between a closed position to prevent fluid flow through the fluid flow passageway and an open position to allow fluid flow through the fluid flow passageway; anda controller communicatively coupled to the actuator, the controller to determine a position of the first gate relative to the second gate that provides a throat area of the fluid flow passageway to accommodate a predetermined mass flow rate of cabin air, wherein the position of the first gate and the second gate is to provide an outlet area to throat area ratio through at least a portion of the fluid flow passageway that enables cabin air exiting the outlet of the fluid flow passageway to be substantially similar to atmospheric pressure associated with an altitude of the aircraft. 16. The valve of claim 15, wherein the first surface of the first gate and the second surface of the second gate are substantially parallel when the first gate moves relative to the second gate. 17. The valve of claim 15, wherein the first surface of the first gate and the second surface of the second gate define the fluid flow passageway having a convergent-divergent profile. 18. The valve of claim 15, wherein a first portion of the fluid flow passageway between the inlet and the throat provides a converging profile and a second portion of the fluid flow passageway between the throat and the outlet provides a diverging profile. 19. The valve of claim 15, wherein a thrust vector of the fluid exiting the outlet of the thrust recovery outflow valve is closer to parallel relative to an outer mold line of the aircraft than orthogonal relative to the outer mold line. 20. The valve of claim 15, wherein the outlet of the fluid flow passageway is positioned at a small angle relative to an outer surface of the aircraft when the fluid flow passageway is in an open position to enable fluid exiting the fluid flow passageway to provide a thrust recovery thrust vector substantially aligned with at least one of an outer mold line of the aircraft or a direction of flight and opposite a direction of drag.
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이 특허에 인용된 특허 (3)
Royalty, Chuck; Jones, Kevin Allan Kingsley; Leclercq, Ralph Warren; Tanner, Justin A., Cabin pressure outflow valve with simplified whistle eliminator.
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