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    Rotorcraft having increased altitude density ceiling
    3.
    发明授权
    Rotorcraft having increased altitude density ceiling 有权

    公开(公告)号：US10513982B2

    公开(公告)日：2019-12-24

    申请号：US15439728

    申请日：2017-02-22

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Zachary Edwin Dailey ,  Frank Bradley Stamps ,  Martin Peryea

    IPC: B64D33/08 ,  F02C7/36 ,  F02C7/141 ,  F02C7/232 ,  F02C9/40 ,  F02C7/16 ,  F02C3/30 ,  F02C7/22 ,  F02C7/143 ,  F02C9/28 ,  B64C27/00 ,  B64D33/02

    Abstract: A rotorcraft has a low density altitude flight mode and a high density altitude flight mode. The rotorcraft includes a turboshaft engine forming a gas path in sequence through an air inlet section, a compressor section, a combustor section, a turbine section and an exhaust section. A drive system is coupled to the engine and is operable responsive to rotation of at least a portion of the turbine section. A rotor is coupled to the drive system and is operable to receive torque and rotational energy therefrom. A fuel injection system supplies fuel to the combustor section. An oxidizer injection system and a coolant injection system are used to selectively inject an oxidizer and a coolant into the gas path when it is desired to operate the rotorcraft in the high density altitude flight mode, thereby increasing the altitude density ceiling of the rotorcraft for maneuvers including takeoffs and landings.

    Deployable Apparatus to Prevent Helicopter Rollover
    7.
    发明申请
    Deployable Apparatus to Prevent Helicopter Rollover 审中-公开

    公开(公告)号：US20180305040A1

    公开(公告)日：2018-10-25

    申请号：US15491483

    申请日：2017-04-19

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Scott David Poster ,  Martin Peryea

    IPC: B64F1/22 ,  B64C25/56 ,  B64C27/06

    CPC classification number: B64F1/221 ,  B64C25/56 ,  B64C27/06

    Abstract: The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft; and a first and/or second air bladder attached to a second end of the first and/or second boom, wherein the first and/or second air bladders are configured to inflate when an aircraft lands in the water, wherein deployment of the first and second boom and air bladder prevents aircraft rollover upon water landing; or a deployable keel affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.

    MULTIPLE POWER ASSURANCE CHECK PROCEDURE FOR AIRCRAFT WITH AN ENGINE INLET BARRIER FILTER INSTALLED
    9.
    发明申请
    MULTIPLE POWER ASSURANCE CHECK PROCEDURE FOR AIRCRAFT WITH AN ENGINE INLET BARRIER FILTER INSTALLED 审中-公开
    安装发动机入口过滤器的飞机多功能保修检查程序

    公开(公告)号：US20160347479A1

    公开(公告)日：2016-12-01

    申请号：US15167886

    申请日：2016-05-27

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Joshua Robert O'Neil ,  Martin Peryea ,  Andrew Jordan Birkenheuer

    IPC: B64F5/00 ,  B64D43/00

    CPC classification number: B64D43/00 ,  B64D2033/0246 ,  B64D2045/0085 ,  B64F5/60

    Abstract: A method of conducting an engine power assurance check includes performing a first engine power assurance check wherein the first engine power assurance check is judged as passing or failing based on power performance values calculated assuming the presence of a substantially clogged or blocked inlet barrier filter and in response to a fail result of the first engine power assurance check, performing a second engine power assurance check wherein the second power assurance check is judged as passing or failing based on power performance values calculated assuming at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.

    Abstract translation: 执行发动机功率保证检查的方法包括执行第一发动机功率保证检查，其中基于基本上堵塞或阻塞的入口阻挡过滤器的存在而计算的功率性能值，将第一发动机功率保证检查判断为通过或失败，并且 响应于所述第一发动机功率保证检查的故障结果，执行第二发动机功率保证检查，其中所述第二功率保证检查基于假定安装无入口阻挡滤波器的至少一个而计算的功率性能值被判断为通过或失败; 安装的入口挡板过滤器的开路旁路。

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