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A thrust reverser door provides in one aspect a separation of structural and aerodynamic functions through the provision of individual structures. In some embodiments, an aerodynamic element is adjustable in position, while in other embodiments, the relative positions are fixed. An exemplary aerodyn

A thrust reverser door provides in one aspect a separation of structural and aerodynamic functions through the provision of individual structures. In some embodiments, an aerodynamic element is adjustable in position, while in other embodiments, the relative positions are fixed. An exemplary aerodynamic element extends radially into the reverser flow to redirect the flow away from the door surface.

대표청구항 ▼

1. A thrust reverser having at least one thrust reverser door pivotable between stowed closed and deployed open positions, the at least one door comprising a transverse leading edge having a first, second and third frames axially spaced apart from one another to define a radially open channel thereb

1. A thrust reverser having at least one thrust reverser door pivotable between stowed closed and deployed open positions, the at least one door comprising a transverse leading edge having a first, second and third frames axially spaced apart from one another to define a radially open channel therebetween and disposed circumferentially adjacent said leading edge, the first, second and third frames projecting inwardly from an interior side of the at least one door, the third frame mounted to the first and second frames, the third frame extending inwardly beyond inward terminal edges of the first and second frames in said door stowed position. 2. The thrust reverser as defined in claim 1, wherein the third frame is mounted to the first and second frames by a mounting apparatus, the mounting apparatus providing a plurality of axial mounting positions for the third frame relative to the first and second frames. 3. The thrust reverser as defined in claim 2, wherein the axial mounting positions for the third frame are infinitely variable relative to the first and second frames. 4. The thrust reverser as defined in claim 1, wherein the third frame has a varying height along its circumferential length. 5. The thrust reverser as defined in claim 1, wherein the at least one door comprises a single skin extending between the first and second frames. 6. The thrust reverser as defined in claim 5, wherein the second frame is disposed closer to the leading edge than the first frame, and wherein the axial distance between the second frame and the leading edge is less than a distance between the first and second frames. 7. The thrust reverser as defined in claim 1, wherein the third frame is disposed between the first and second frames. 8. A thrust reverser for a turbofan gas turbine engine, the thrust reverser having at least one door movable between a stowed position and a deployed position for deflecting engine thrust, the at least one door having a leading edge with a deflector wall being adjustable in relative position on said at least one door, with said relative position being constant from said stowed position to said deployed position, the wall being generally parallel to the leading edge and extending generally radially inwardly of the at least one door to, in use, redirect engine thrust. 9. The thrust reverser as defined in claim 8, wherein the wall has an infinite number of positions relative to the leading edge. 10. The thrust reverser as defined in claim 8, wherein the wall has a varying height along a length thereof. 11. The thrust reverser as defined in claim 8, wherein the adjustable position is radially inwardly adjustable. 12. The thrust reverser as defined in claim 8, wherein the adjustable position is axially adjustable relative to the leading edge. 13. A thrust reverser comprising at least one door for deflecting engine thrust in a deployed open position thereof, the at least one door having a leading edge and a single skin in a vicinity of the leading edge, the at least one door having at least a first bulkhead extending radially inwardly from the skin, the first bulkhead defining a first member extending generally parallel to the leading edge of the at least one door and being sized and configured relative to the skin to structurally stiffen the skin, the at least one door also having a second member extending radially relative to the skin and disposed adjacent the first member, the at least one door further having a third member extending generally parallel to the leading edge of the at least one door and being sized and configured relative to the skin to structurally stiffen the skin, with the first and third members defining a radially open channel therebetween, the second member having a radial height relative to the skin which is greater than a radial height of the first member in a stowed closed position of said at least one door. 14. The thrust reverser as defined in claim 13, wherein the radial height of the second member varies along a circumferential length. 15. The thrust reverser as defined in claim 13, wherein the second member is mounted to the first member. 16. The thrust reverser as defined in claim 13 wherein the second member is mounted to the first and third members. 17. A method of adjusting an effective length of a thrust reverser door, the method comprising: mounting a substantially radially projecting member inside the thrust reverser door generally parallel and adjacent to a leading edge of the door;deploying the door from stowed closed to deployed open positions with the member having a constant relative position on the door;deflecting gases with the member during a thrust reversal mode when the door is in said deployed position; andchanging said relative position of the member relative to the door to thereby change an aerodynamic effective length of the door. 18. The method as defined in claim 17 wherein the step of changing comprises adjusting an attachment of the member to alter an axial position of the member relative to the door. 19. The method as defined in claim 17 wherein the step of changing comprises adjusting an attachment of the member to alter a radial position of the member relative to the door. 20. The method as defined in claim 17 wherein the step of deflecting comprises deflecting gases asymmetrically relative to the door. 21. A thrust reverser comprising: a pair of thrust reverser doors pivotally mounted to a jet pipe for moving between stowed closed and deployed open positions;each of said doors having axially opposite leading and trailing edges and a pair of radial frames extending radially inwardly and circumferentially along said leading edge in said stowed position, and spaced axially apart to define a U-shaped channel open radially inwardly therebetween; anda kicker frame extending radially inwardly from and circumferentially along said radial frames at said open channel in said stowed position to increase effective aerodynamic length of said doors in said deployed position. 22. A thrust reverser according to claim 21 wherein said kicker frame is mounted axially between said radial frames for selective axial adjustment therebetween. 23. A thrust reverser according to claim 22 wherein said kicker frame is mounted on threaded rods extending axially between said radial frames. 24. A thrust reverser according to claim 22 wherein said kicker frame is mounted between said radial frames with spacers therebetween. 25. A thrust reverser according to claim 21 wherein said kicker frame is integrated in one of said radial frames. 26. A thrust reverser according to claim 21 wherein said kicker frame varies in radial height circumferentially along said door leading edge. 27. A method of using said thrust reverser according to claim 21 comprising: adjusting axial position of said kicker frame between said radial frames for said stowed position; anddeploying open said doors to correspondingly change said effective aerodynamic length of said doors during thrust reverse operation.