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    Variable area nozzle assembly for an aircraft propulsion system
    1.
    发明授权
    Variable area nozzle assembly for an aircraft propulsion system 有权

    公开(公告)号：US12065937B1

    公开(公告)日：2024-08-20

    申请号：US18394669

    申请日：2023-12-22

    申请人： RTX Corporation

    发明人： Michael G. McCaffrey ,  Nathan L. Messersmith

    IPC分类号： F01D17/14 ,  B64D27/10 ,  B64D33/04 ,  F01D17/16

    CPC分类号： F01D17/14 ,  B64D27/10 ,  B64D33/04 ,  F01D17/16 ,  F05D2220/323 ,  F05D2250/90

    摘要： A variable area nozzle assembly includes a fixed center plug, a fixed outer nozzle, and an inner nozzle. The fixed center plug includes a plug body and a protrusion. The fixed outer nozzle extends about the fixed center plug. The inner nozzle extends about the fixed center plug. The inner nozzle is disposed between the fixed center plug and the fixed outer nozzle. The inner nozzle forms a primary duct between the inner nozzle and the fixed outer nozzle. The primary duct includes an exit plane. The inner nozzle body forms a secondary duct and a gap. The gap is a nozzle outlet of the secondary duct. The gap includes a gap inlet and a gap outlet. The gap inlet is disposed upstream of the protrusion. The gap outlet is disposed downstream of the protrusion. The inner nozzle body is translatable between a first position and a second position. In the first position, the primary duct has a first area at the exit plane and the inner nozzle body is disposed at the protrusion. In the second position, the primary duct has a second area at the exit plane and the inner nozzle body is spaced from the protrusion.

    EXHAUST SYSTEMS HAVING ADJUSTABLE NOZZLES AND RELATED METHODS
    4.
    发明公开
    EXHAUST SYSTEMS HAVING ADJUSTABLE NOZZLES AND RELATED METHODS 审中-公开

    公开(公告)号：US20240140611A1

    公开(公告)日：2024-05-02

    申请号：US17978011

    申请日：2022-10-31

    申请人： The Boeing Company

    发明人： Jason Boyer

    IPC分类号： B64D33/04 ,  B64C27/04

    CPC分类号： B64D33/04 ,  B64C27/04 ,  B64D2033/045

    摘要： Exhaust systems having adjustable nozzles and related methods are disclosed. An example exhaust system includes a nozzle. A portion of the nozzle is moveable from a first position to a second position to change an angle of convergence of the nozzle. The example exhaust system includes an exit area. The portion of the nozzle is at least partially disposed in the exit area. An opening is defined between the exit area and the portion of the nozzle disposed in the exit area. A size of the opening is to change in response to movement of the portion of the nozzle.

    Tail cone mounted generator input shaft for an aircraft
    9.
    发明授权
    Tail cone mounted generator input shaft for an aircraft 有权

    公开(公告)号：US11807380B2

    公开(公告)日：2023-11-07

    申请号：US17172207

    申请日：2021-02-10

    申请人： Hamilton Sundstrand Corporation

    发明人： Thomas John Wise ,  Glenn C. Lemmers, Jr. ,  Mark J. Franklin

    IPC分类号： B64D33/08 ,  B64D33/02 ,  B64D33/04

    CPC分类号： B64D33/08 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/024 ,  B64D2033/0273

    摘要： A jet engine includes a housing, an intake portion leading into the housing, and an exhaust portion leading from the housing. The exhaust portion includes an exhaust duct and a tail cone arranged radially inwardly of the exhaust duct. An engine portion is arranged in the housing between the intake portion and the exhaust portion. A generator is arranged in the tail cone and is operatively connected to the engine portion. A drive shaft extends from the engine portion to the generator. The drive shaft includes a first end coupled to the engine portion, a second end connected to the generator, and an intermediate portion extending therebetween. The intermediate portion includes a cooling passage that extends from the second end toward a terminal end that terminates short of the first end of the drive shaft.