IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0863495
(2009-01-30)
|
등록번호 |
US-8342443
(2013-01-01)
|
우선권정보 |
DE-10 2008 007 278 (2008-02-01) |
국제출원번호 |
PCT/EP2009/000620
(2009-01-30)
|
§371/§102 date |
20100802
(20100802)
|
국제공개번호 |
WO2009/095257
(2009-08-06)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Dernier, Esq., Matthew B.
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
2 |
초록
▼
A wing-engine combination includes: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space, which includes: an engine bleed-air duct, which extends along the wingspan direction and along the leading edge of the main wing, including an engine bleed-ai
A wing-engine combination includes: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space, which includes: an engine bleed-air duct, which extends along the wingspan direction and along the leading edge of the main wing, including an engine bleed-air inlet device that is coupled to an engine hot-air space, and including an engine bleed-air outlet device having a discharge orifice on the main wing or a connecting part for coupling the engine bleed-air duct to a consumer of the engine bleed-air, an ambient-air duct, which extends along the engine bleed-air duct, including an ambient-air inlet device which is arranged on an aircraft component of the aircraft, which aircraft component faces the intended flow-around direction of the aircraft and includes an aperture for letting ambient air into the ambient-air duct, and including an ambient-air outlet device with a passage between the ambient-air duct and a premixing chamber of the engine so that the arrangement including the engine bleed-air duct and the ambient-air duct forms a heat exchanger device for cooling the air flowing in the engine bleed-air duct and so that the ambient air conveyed in the ambient-air duct is supplied for combustion in the engine; and an aircraft and a wing section of an aircraft including an engine bleed-air duct arrangement.
대표청구항
▼
1. A wing-engine combination comprising: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space,an engine bleed-air duct, which extends along a wingspan direction and along a leading edge of the main wing, the engine bleed-air duct comprising: an eng
1. A wing-engine combination comprising: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space,an engine bleed-air duct, which extends along a wingspan direction and along a leading edge of the main wing, the engine bleed-air duct comprising: an engine bleed-air inlet device that is coupled to an engine hot-air space, and an engine bleed-air outlet device including a discharge orifice on the main wing or a connecting part for coupling the engine bleed-air duct to a consumer of the engine bleed-air, andan ambient-air duct, which extends along the engine bleed-air duct, the ambient-air duct comprising an ambient-air inlet device which is arranged on an aircraft component of the aircraft and comprises an aperture for letting ambient air into the ambient-air duct, and comprising an ambient-air outlet device with a passage between the ambient-air duct and a premixing chamber of the engine so that the arrangement comprising the engine bleed-air duct and the ambient-air duct forms a heat exchanger device for cooling air flowing in the engine bleed-air duct and so that the ambient air conveyed in the ambient-air duct is supplied for combustion in the engine. 2. The wing-engine combination according to claim 1, wherein the engine bleed-air duct and the ambient-air duct are designed in such a manner that with an intended flow around the wing the engine bleed-air in the engine bleed-air duct flows from the engine to the engine bleed-air outlet device, and the ambient air in the ambient-air duct flows in a direction opposite to a direction of flow of the engine bleed-air. 3. The wing-engine combination according to claim 1, wherein the component of the aircraft on which the aperture of the ambient-air inlet device is provided is arranged on a surface of the wing connection region that extends from the fuselage exterior in the direction of the engine mount spaced apart by 10% of a space between a fuselage exterior and an engine mount, or is arranged on a surface of a belly fairing. 4. The wing-engine combination according to claim 1, wherein the ambient-air duct circumferentially encompasses the engine bleed-air duct in a helical manner at least in some sections. 5. The wing-engine combination according to claim 1, wherein a device for influencing the flow in the ambient-air duct is integrated in the ambient-air duct. 6. The wing-engine combination according to claim 5, wherein the device for influencing the flow comprises a flow assist drive for influencing the flow that is integrated in the ambient-air duct that leads from the ambient-air inlet device to the ambient-air outlet device. 7. The wing-engine combination according to claim 5, wherein the device for influencing the flow comprises a moveable aperture-changing device with a cover for opening and closing the aperture of the ambient-air inlet device. 8. The wing-engine combination according to claim 1, wherein the wing comprises at least one leading edge slat, coupled to the main wing, which leading edge slat is movable relative to the main wing, and which leading edge slat comprises a leading-edge slat de-icing duct that is integrated in the main wing and extends along its wingspan direction, as well as comprising at least one coupling line which fluidically connects the leading-edge slat de-icing duct of at least one leading edge slat to the engine bleed-air duct of the main wing. 9. The wing-engine combination according to claim 8, wherein the leading-edge slat de-icing duct comprises several outlet apertures that discharge at the trailing edge of the leading edge slat. 10. An aircraft with a wing-engine combination comprising: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space,an engine bleed-air duct, which extends along a wingspan direction and along a leading edge of the main wing, the engine bleed-air duct comprising: an engine bleed-air inlet device that is coupled to an engine hot-air space, and an engine bleed-air outlet device comprising a discharge orifice on the main wing or a connecting part for coupling the engine bleed-air duct to a consumer of the engine bleed-air, andan ambient-air duct, which extends along the engine bleed-air duct, the ambient-air duct comprising an ambient-air inlet device which is arranged on an aircraft component of the aircraft and comprises an aperture for letting ambient air into the ambient-air duct, and comprising an ambient-air outlet device with a passage between the ambient-air duct and a premixing chamber of the engine so that the arrangement comprising the engine bleed-air duct and the ambient-air duct forms a heat exchanger device for cooling the air flowing in the engine bleed-air duct and so that the ambient air conveyed in the ambient-air duct is supplied for combustion in the engine, wherein:a device for influencing the flow in the ambient-air duct is integrated in the ambient-air duct,the aircraft comprises at least one sensor device for acquiring flight state data,the aircraft comprises a control device that is functionally coupled to the sensor device and to the device for influencing the flow, and comprises a function which based on the flight-state data, generates control commands for the device for influencing the flow in the ambient-air duct and sends said commands to said device, andthe device for influencing the flow comprises a receiving module for receiving control signals from the control device, and comprises a function which sets the output of the device for influencing the flow. 11. The wing-engine combination according to claim 10, wherein the engine bleed-air duct is coupled to an air conditioning system of the aircraft. 12. The aircraft according to claim 10, wherein at least one of: a sensor device, which is functionally connected to the control device, for acquiring the outside temperature; a sensor device for acquiring the aircraft speed; and a sensor device for acquiring the flight altitude or the absolute pressure are provided. 13. The aircraft according to claim 10, wherein the device for influencing the flow comprises a flow assist drive that in order to intensify the flow in the ambient-air duct extending from the ambient-air inlet device to the ambient-air outlet device is integrated in the ambient-air duct and comprises an interface for receiving control commands from the control device to influence the velocity of the flow in the ambient-air duct in that based on control commands by means of the conveying output of the flow assist drive the speed of the flow is controlled. 14. The aircraft according to claim 10, wherein the device for influencing the flow comprises an aperture-changing device with an aperture-changing mechanism, with a cover for opening and closing the aperture, and an actuator for operating the aperture-changing mechanism, which actuator comprises an interface for receiving control commands from the control device in order to set the opening state of the cover on the basis of control commands for influencing the flow in the ambient-air duct. 15. The aircraft according to claim 10, wherein the flight state data, on the basis of which the control function of the control device generates the control commands for the respective device for influencing the flow, is based on a state variable or a combination of at least one of the following state variables: the outside temperature, the aircraft speed, the flight altitude and the absolute pressure. 16. The aircraft according to claim 15, wherein the state variable or combination of state variables also includes atmospheric humidity. 17. The aircraft according to claim 10, wherein in the main wing at least one of: a temperature measuring device for measuring the temperature of the engine bleed-air is installed in at least one position in the engine bleed-air duct, and a temperature measuring device for acquiring the temperature at a surface region of the leading edge of the main wing is installed between the fuselage and the engine, which temperature measuring device is functionally connected to the control function for the purpose of transmitting the acquired temperature values, and in that the control function comprises a regulating function that generates control commands for transmission to the device for influencing the flow in the ambient-air duct, by means of which control commands a target temperature of the temperature of the engine bleed-air or of the leading edge of the main wing is regulated. 18. The aircraft according to claim 17, wherein the regulating function is activated when the aperture-changing device is at its maximum open position.
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