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    AIRCRAFT AND ASSOCIATED METHOD OF CONDITIONING CABIN AIR
    1.
    发明申请
    AIRCRAFT AND ASSOCIATED METHOD OF CONDITIONING CABIN AIR 有权

    公开(公告)号：US20240417080A1

    公开(公告)日：2024-12-19

    申请号：US18334507

    申请日：2023-06-14

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric Sylvain DUROCHER ,  Michel LABRECQUE

    IPC: B64D13/08 ,  B64D27/24 ,  B64D33/08

    Abstract: The aircraft can have a cabin adapted to receive one or more persons; a rotary airfoil device; an electric engine drivingly coupled to the rotary airfoil device; a battery powering the electric engine; a heat pump having a refrigerant circuit fluidly connecting, in sequence, a compressor, a condenser, an expansion valve, and an evaporator; and a pressurized air subsystem having a network of pressurized air lines operable to deliver pressurized air from one or more pressurized air sources to the cabin, the network of pressurized air lines having a hot line fluidly connecting one of the one or more pressurized air sources to a mixing volume, a cold line parallel to the hot line, the cold line fluidly connecting one of the one or more pressurized air sources to the mixing volume, and a delivery line fluidly connecting the mixing volume to the cabin, the hot line connected in heat exchange relationship with a source of heat, the cold line in heat exchange relationship with the evaporator.

    LOW NOISE AEROENGINE INLET SYSTEM
    2.
    发明申请
    LOW NOISE AEROENGINE INLET SYSTEM 有权
    低噪声AEROENGINE INLET系统

    公开(公告)号：US20160053685A1

    公开(公告)日：2016-02-25

    申请号：US14463077

    申请日：2014-08-19

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Michel LABRECQUE ,  Vincent COUTURE-GAGNON ,  Richard ULLYOTT

    IPC: F02C7/045 ,  F02C7/042 ,  F01D17/14

    CPC classification number: F02C7/045 ,  F01D17/143 ,  F01D17/146 ,  F02C7/042 ,  F05D2260/963 ,  Y02T50/672

    Abstract: An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through he inlet duct.

    Abstract translation: 航空发动机具有入口系统，该入口系统包括邻近入口管道的周壁设置的至少一个可变形壁和附接到后侧的多个声学单元，其通过至少一个可变形壁中的相应孔流体连通，入口管 气流。 当处于未部署的位置时，至少一个可变形壁选择性地形成入口管道的周壁的一部分，并且选择性地形成突出到入口管道中的弯曲轮廓，以减少通过入口管道的视线噪声传播。

    LOW NOISE AEROENGINE INLET SYSTEM
    3.
    发明申请
    LOW NOISE AEROENGINE INLET SYSTEM 有权
    低噪声AEROENGINE INLET系统

    公开(公告)号：US20160053684A1

    公开(公告)日：2016-02-25

    申请号：US14463031

    申请日：2014-08-19

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Michel LABRECQUE ,  Vincent COUTURE-GAGNON ,  Richard ULLYOTT

    IPC: F02C7/045 ,  F02K3/06

    CPC classification number: F02C7/045 ,  F02C7/042 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/96

    Abstract: An aeroengine is provided with a splitter apparatus disposed in a section of ain inlet duct. The splitter apparatus can be actuated from a stowed position to a deployed position to allow splitter(s) to selectively move from out of the inlet flow to a position extending into the inlet duct to divide the inlet flow into multiple passages.

    Abstract translation: 航空发动机设置有分配器装置，其设置在进气管道的一部分中。 分流器装置可以从收起位置致动到展开位置，以允许分流器选择性地从入口流动中移出到延伸到入口管道中的位置，以将入口流分成多个通道。

    METHODS AND SYSTEMS FOR CONTROLLING OPERATION OF AIRCRAFT ENGINES
    5.
    发明申请
    METHODS AND SYSTEMS FOR CONTROLLING OPERATION OF AIRCRAFT ENGINES 审中-公开

    公开(公告)号：US20200269989A1

    公开(公告)日：2020-08-27

    申请号：US16872447

    申请日：2020-05-12

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Carmine LISIO ,  Michel LABRECQUE

    IPC: B64D31/00 ,  F02C3/04 ,  B64D35/00 ,  B64D27/10 ,  F02C9/00 ,  B64D31/06 ,  F02C9/58

    Abstract: The present disclosure provides a method and a system for controlling operation of an engine of an aircraft. The method comprises, at a controller of the engine, obtaining an actual engine output power for the engine, the actual engine output power based on a propeller rotation speed and a propeller blade pitch angle; converting the actual engine output power to a predicted thrust value; determining an actual engine power limit associated with a thrust limit of a propeller coupled to the engine from the predicted thrust value; and setting a maximum engine power limit of the engine using the actual engine power limit associated with the thrust limit of the propeller.

    AIRCRAFT AND ASSOCIATED METHOD OF CONDITIONING CABIN AIR
    7.
    发明申请
    AIRCRAFT AND ASSOCIATED METHOD OF CONDITIONING CABIN AIR 有权

    公开(公告)号：US20240417079A1

    公开(公告)日：2024-12-19

    申请号：US18334502

    申请日：2023-06-14

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric Sylvain DUROCHER ,  Michel LABRECQUE

    IPC: B64D13/08 ,  B64D27/24 ,  H01M10/613

    Abstract: The aircraft can have a cabin adapted to receive one or more persons; a rotary airfoil device; an electric engine drivingly coupled to the rotary airfoil device; a battery powering the electric engine; a coolant subsystem having a coolant circuit and a coolant pump operable to circulate a coolant in the coolant circuit, the coolant circuit connected in heat exchange relationship with at least one of the electric engine and the battery; a heat pump having a refrigerant circuit fluidly connecting, in sequence, a compressor, a condenser, an expansion valve, a first evaporator, and an environmental control line branching off from the refrigerant circuit between the condenser and the first evaporator, the environmental control line having a second evaporator and reconnected to the refrigerant circuit between the first evaporator and the compressor, the first evaporator connected in heat exchange relationship with the coolant circuit; and a pressurized air subsystem having a pressurized air line operable to deliver pressurized air from a pressurized air source to the cabin, the pressurized air line connected in heat exchange relationship with the second evaporator.

    LOW NOISE AEROENGINE INLET SYSTEM
    9.
    发明申请
    LOW NOISE AEROENGINE INLET SYSTEM 审中-公开

    公开(公告)号：US20180187599A1

    公开(公告)日：2018-07-05

    申请号：US15908983

    申请日：2018-03-01

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Michel LABRECQUE ,  Vincent COUTURE-GAGNON ,  Richard ULLYOTT

    IPC: F02C7/045 ,  F01D17/14 ,  F02C7/042

    CPC classification number: F02C7/045 ,  F01D17/143 ,  F01D17/146 ,  F02C7/042 ,  F05D2260/963 ,  Y02T50/672

    Abstract: An aeroengine includes an inlet duct having a section including opposed and substantially flat first and second peripheral walls, a first deformable wall providing a portion of the first peripheral wall and a second deformable wall providing a portion of the second peripheral wall. The deformable walls are deformable between undeployed and deployed positions, and each include panels pivotally connected one to another to allow pivotal movement of the panels relative to respective adjacent panels about respective parallel axes oriented transverse to a direction of the air flow. The deformable walls in the undeployed position each being substantially flat to substantially avoid interfering with the air flow, and in the deployed position each projecting into the inlet duct from the respective peripheral wall to reduce an effective cross-sectional area of the inlet duct to reduce line-of-sight noise propagation.

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