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    AIR PRESSURISATION SYSTEM
    1.
    发明公开
    AIR PRESSURISATION SYSTEM 审中-公开

    公开(公告)号：EP4435265A1

    公开(公告)日：2024-09-25

    申请号：EP24157560.4

    申请日：2024-02-14

    申请人： Rolls-Royce plc

    发明人： Murray, Christopher ,  Howarth, Nicholas

    IPC分类号： F04D17/10 ,  F02C7/06 ,  F02C7/28 ,  F04D25/02 ,  F04D29/056 ,  F04D29/063 ,  F04D29/12

    CPC分类号： F04D17/10 ,  F04D25/02 ,  F04D29/056 ,  F05D2260/602220130101 ,  F04D29/063 ,  F04D29/124 ,  F02C7/28 ,  F02C7/06

    摘要： There is provided an air pressurisation system (400, 401) for an aircraft (800). The air pressurisation system comprises a blower compressor (420, 500) configured to be mechanically coupled to a spool (440) of a gas turbine engine (10) and configured to receive an inlet flow of air from a bypass duct (22) of the gas turbine engine, wherein the blower compressor comprises: a rotor (502) configured to be mechanically coupled to the spool of the gas turbine engine; an oil-lubricated bearing (512) for supporting rotation of the rotor, wherein the oil-lubricated bearing is disposed within a bearing chamber (510); and a seal assembly (514, 600, 700) for restricting oil from the bearing chamber from reaching an inlet (506a) of the blower compressor, wherein the seal assembly comprises: a seal (614) disposed between the bearing chamber and an air buffer chamber (608); an air buffer inlet (616) configured to receive a flow of pressurised air into the air buffer chamber; and an air buffer outlet (618) configured to allow the flow of pressurised air to be exhausted from the air buffer chamber together with oil from the bearing chamber that has passed through the seal and become entrained within the flow of pressurised air; and a delivery line (310) configured to convey air compressed by the blower compressor to a cabin pressurisation system of the aircraft.

    AIRCRAFT TAIL CONE MOUNTED GENERATORS
    2.
    发明公开
    AIRCRAFT TAIL CONE MOUNTED GENERATORS 审中-公开

    公开(公告)号：EP4414548A1

    公开(公告)日：2024-08-14

    申请号：EP24156633.0

    申请日：2024-02-08

    申请人： Hamilton Sundstrand Corporation

    发明人： LEMMERS, Glenn C. ,  FRANKLIN, Mark J. ,  BEHLING, David S.

    IPC分类号： F02C7/32

    CPC分类号： F02C7/32 ,  F02C7/28 ,  F02C7/36 ,  F02K1/78 ,  F05D2220/7620130101 ,  F01D15/10 ,  F05D2260/3620130101 ,  F05D2260/403120130101 ,  F01D25/30

    摘要： Aircraft engines include an engine housing, a core assembly arranged within the engine housing (550) and comprising an engine shaft (408) arranged axially within the engine housing extending in a forward-aftward direction, and a tail cone assembly (200) attached to an aft end of the engine housing. The tail cone assembly includes a tail cone housing (402) and an aircraft machine arranged within the tail cone housing the aircraft machine comprising a rotor shaft (420). An input shaft (204) is configured between the engine shaft and the rotor shaft and a rotor coupling (436) configured to sealing connect the rotor shaft and the input shaft, the rotor coupling configured to providing sealing engagement between the rotor shaft and the input shaft during at least one of relative axial displacement and relative radial displacement between the rotor shaft and the input shaft.