Method and means for opposing the rotation of a windmilling turbojet rotor during flight
阅读：77发布：2022-02-05
专利汇可以提供Method and means for opposing the rotation of a windmilling turbojet rotor during flight专利检索，专利查询，专利分析的服务。并且A method and means for opposing the windmilling of the rotor of a turbojet engine on board an aircraft as produced by the incoming stream of air impinging on a disabled turbojet. The windmilling is stopped, in the case of a turbojet engine having a thrust reverser device and a jet-diverting passageway, by moving said thrust reverser device to its thrust reversing position, whereby the flow of air is diverted into said jet-diverting passageway, and throttling said jet-diverting passageway. The jet-diverting passageway may be throttled for this purpose by a mechanical or pneumatic resistance to free flow through such passageway.，下面是Method and means for opposing the rotation of a windmilling turbojet rotor during flight专利的具体信息内容。
1. A method for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caUsed by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes an exhaust assembly adapted to discharge a gas flow in the rearward direction, and a thrust reversal device movable between an operative position projecting into said gas flow to divert said flow in a direction at an angle to said rearward direction, and an inoperative retracted position, said method comprising the steps of (1) moving said thrust reversal device into its operative position, whereby the flow of air which passes through said disabled turbojet engine is diverted by said thrust reversal device, and (2) throttling said diverted flow to increase the discharge pressure of said gas flow and thus increase the resistance in said engine downstream of said rotor sufficient to substantially prevent further gas flow through said disabled engine.
2. A method for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes a jet pipe bifurcated to form two branches, one of said branches terminating in a propulsion nozzle and the other forming a jet-diverting passageway extending at an angle to said propulsion nozzle, said method comprising the steps of (1) closing said first branch at a point downstream of the bifurcation to direct the air flow to said second branch, and (2) throttling said second branch to increase the air pressure in said two branches and thus increase the resistance in said engine downstream of said rotor sufficient to substantially prevent further air flow through said disabled engine.
3. A method for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes a jet pipe bifurcated to form two branches, one of said branches terminating in a propulsion nozzle and the other forming a jet-diverting passageway extending at an angle to said propulsion nozzle, and a thrust reversal device movable between an inoperative position in which said first branch is open and said second branch is closed and an operative position in which said second branch is open and said first branch is closed at a point downstream of the bifurcation, said method comprising the steps of (1) moving said thrust reversal device to its operative position and (2) throttling said second branch to increase the air pressure in said two branches and thus increase the resistance in said engine downstream of said rotor sufficient to substantially prevent further air flow through said disabled engine.
4. A method according to claim 3 wherein said throttle step comprises the step of generating a curtain of pressurized fluid across said second branch.
5. A method according to claim 3 wherein said turbojet engine includes a grid of jet-deflecting vanes extending across said second branch and said throttling step comprises the step of adjusting the angular setting of said jet-deflecting vanes relative to the general direction of flow of the diverted flow of air flowing in said second branch.
6. A method for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein the turbojet engine includes a jet pipe bifurcated to form two branches, one of said branches terminating in a propulsion nozzle and the other branch forming a jet-diverting passageway extending at an angle to said propulsion nozzle, a thrust reversal device including a closure device for each of said branches, means for moving said closure devices and a device coupling together said closure devices so that one of said branches is normally open when the other is closed, said method comprising the steps of (1) rendering said Coupling device inoperative and (2) moving said two closure devices to close both of said branches to increase the air pressure in said two branches and thus increase the resistance to further air flow through said disabled engine.
7. A method for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes a jet pipe bifurcated to form two branches, one of said branches terminating in a propulsion nozzle and the other forming a jet-diverting passageway extending at an angle to said propulsion nozzle, said method comprising the steps of (1) closing said first branch at a point downstream of the bifurcation to direct the air flow to said second branch and (2) introducing a mechanical auxiliary closure device into said second branch to increase the air pressure in said two branches and thus increase the resistance to further air flow through said disabled engine.
8. A method according to claim 7 wherein said turbojet engine includes a thrust reversal device movable between an inoperative position in which said first branch is open and said second branch is closed and an operative position in which said second branch is open and said first branch is closed at a point downstream of the bifurcation, and said first branch is closed by moving said thrust reversal device to its operative position.
9. A method for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes an exhaust assembly adapted to discharge a gas flow in the rearward direction, and a thrust reversal device movable between an operative position projecting into said gas flow to divert said flow in a direction at an angle to said rearward direction, and an inoperative retracted position, said method comprising the steps of (1) moving said thrust reversal device into its operative position, whereby the flow of air which passes through said disabled turbojet engine is diverted by said thrust reversal device, and (2) introducing a mechanical auxiliary closure device across said diverted flow to increase the discharge pressure of the gas flow and thus increase the resistance to further gas flow through said disabled engine.
10. An arrangement for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes an exhaust assembly adapted to discharge a gas flow in a rearward direction, and a thrust reversal device movable between an operative position projecting into said gas flow to divert said flow in a direction at an angle to said rearward direction, and an inoperative retracted position, said arrangement comprising means adapted to throttle the gas flow diverted by the thrust reversal device when in its operative position to increase the discharge pressure of said gas flow and thus increase the resistance in said engine downstream of said rotor sufficient to substantially prevent further gas flow through said disabled engine.
11. An arrangement for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes a jet pipe bifurcated to form two branches, one of said branches terminating in a propulsion nozzle and the other branch forming a jetdiverting passageway extending at an angle to said propulsion nozzle, said arrangement comprising means for closing said first branch a point downstream of the bifurcation, and means adapted to throttle said second branch, when said first branch is closed, to increase the air pressure in said two branches and thus increase the resistance in said engine downstream of said rotor sufficient to substantially prevent further air flow through said disabled engine.
12. An arrangement for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein said turbojet engine includes a jet pipe bifurcated to form two branches, one of said branches terminating in a propulsion nozzle and the other branch forming a jet-diverting passageway extending at an angle to said propulsion nozzle, and a thrust reversal device, movable between an inoperative position in which said first branch is open and said second branch is closed, and an operative position in which said second branch is open and said first branch is closed at a point downstream of the bifurcation, said arrangement comprising means adapted to throttle said second branch when said thrust reversal device is in its operative position to increase the air pressure in said two branches and thus increase the resistance in said engine downstream of said rotor sufficient to substantially prevent further air flow through said disabled engine.
13. An arrangement according to claim 12 wherein said throttling means includes a mechanical auxiliary closure device.
14. An arrangement according to claim 13 wherein said mechanical auxiliary closure device includes a flap adapted to extend across the said second branch.
15. An arrangement according to claim 12 wherein said throttling means include means to generate a curtain of pressurized fluid across said second branch.
16. An arrangement according to claim 12 wherein the turbojet engine includes a grid of jet-deflecting vanes extending across said second branch, and said throttling means include means for adjusting the angular setting of said jet-deflecting vanes relative to the general direction of flow of the diverted flow of air flowing in said second branch towards said grid of vanes between an inoperative position at which said second branch is not throttled and an operative position at which said second branch is throttled.
17. An arrangement according to claim 16 wherein said grid of vanes is mounted for pivotal movement about an axis, and means for adjusting the angular setting of the vanes comprise means for pivoting said grid about said axis between a retracted position at which said second branch is not throttled and an extended position at which said second branch is throttled.
18. An arrangement according to claim 17 wherein said grid is adapted to pivot freely about its axis so as to be urged into its extended position under the action of the pressure of the flow of air flowing in said second branch, said arrangement further comprising means for returning said grid to its retracted position.
19. An arrangement according to claim 18 wherein the means returning the said grid to its retracted position includes cable means and means for winding and unwinding the latter.
20. An arrangement according to claim 17 wherein the means for pivoting the said grid includes a linkage together with jack means for actuating said linkage in two directions.
21. An arrangement according to claim 17 further comprising means for locking said grid in its inoperative position and means for controlling said locking means.
22. An arrangement according to claim 21 wherein said control means are adapted to cooperate sequentially with the means for pivoting the grid.
23. An arrangement according to claim 17 further comprising means for damping the pivotal movement of said grid.
24. An arrangement according to claim 17 further comprising means for closing, when the grid is in its extended position, the gap extending between the adjacent edges of said second branch and said grid so as to constrain the diverted flow of air flowing in said second branch to be directed towards said grid in its extended position.
25. An arrangement according to clAim 24 wherein said gap-closing means include a mechanical barrier.
26. An arrangement according to claim 24 wherein said gap-closing means include means for generating a curtain of pressurized fluid across said gap.
27. An arrangement for opposing during flight the windmilling of the rotor of a disabled turbojet engine of an aircraft caused by a flow of air under dynamic pressure through said disabled turbojet engine, wherein the turbojet engine includes a jet pipe bifurcated to form two branches, one of said branches terminating in a propulsion nozzle and the other branch forming a jet-diverting passageway extending at an angle to said propulsion nozzle, a thrust reversal device including a closure device associated with each of said two branches, means for moving said closure devices, and a device coupling together said closure devices so that one of said branches is open when the other is closed, said arrangement comprising means for rendering said coupling means inoperative to allow said closure devices to be moved to close both of said branches to increase the air pressure in said two branches and thus increase the resistance to further air flow through said disabled engine.
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