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    VARIABLE GEAR RATIO GAS TURBINE ENGINE SYSTEM
    2.
    发明申请
    VARIABLE GEAR RATIO GAS TURBINE ENGINE SYSTEM 审中-公开

    公开(公告)号：US20200095930A1

    公开(公告)日：2020-03-26

    申请号：US16137102

    申请日：2018-09-20

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Eric Blumer ,  David K. Jan

    IPC: F02C3/113 ,  F02C7/36

    Abstract: A variable gear ratio gas turbine engine system includes a planetary gear set, a gas turbine engine, an electric machine, and a controller. The gas turbine engine includes at least a low-pressure compressor, a high-pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine. The low-pressure turbine is coupled to the low-pressure compressor via the planetary gear set. The electric machine is coupled to the planetary gear set and its rotational speed is used, at least in part, to vary the gear ratio of the planetary gear set. The controller is in operable communication with the gas turbine engine and the electric machine and is configured to control: the low-pressure turbine to rotate at a substantially constant speed and the rotational speed of the electric machine to thereby vary the gear ratio of the planetary gear set, whereby the speed at which the low-pressure compressor rotates is also varied.

    Gas turbine engines with plug resistant effusion cooling holes
    3.
    发明授权
    Gas turbine engines with plug resistant effusion cooling holes 有权

    公开(公告)号：US10101030B2

    公开(公告)日：2018-10-16

    申请号：US14475106

    申请日：2014-09-02

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Rodolphe Dudebout ,  Eric Blumer

    IPC: F23R3/06 ,  F23R3/00 ,  F01D5/18 ,  F01D9/02 ,  F23R3/04

    Abstract: A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.

    AIRCRAFT SYSTEMS AND METHODS WITH GREEN FUEL TANKS
    7.
    发明申请
    AIRCRAFT SYSTEMS AND METHODS WITH GREEN FUEL TANKS 审中-公开
    具有绿色燃油箱的飞机系统和方法

    公开(公告)号：US20150266589A1

    公开(公告)日：2015-09-24

    申请号：US14223428

    申请日：2014-03-24

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Eric Blumer ,  Mukund Acharya ,  Audie Mak ,  Mario Scaini ,  Bijan F. Hagh

    IPC: B64D37/00 ,  H01M8/06 ,  B64D37/34 ,  B64D41/00 ,  B64D37/02 ,  B64D37/30

    CPC classification number: B64D37/00 ,  B64D37/02 ,  B64D37/30 ,  B64D37/34 ,  B64D41/00 ,  F02C9/40 ,  H01M8/0625 ,  H01M2250/20 ,  Y02T50/44 ,  Y02T50/671 ,  Y02T50/678 ,  Y02T90/32

    Abstract: An aircraft system includes a main fuel tank configured to house primary fuel and a green fuel tank configured to house green fuel. The mixing apparatus is configured to mix the primary fuel and the green fuel to result in a predetermined ratio of mixed fuel. A controller selectively commands a first amount of primary fuel and a second amount of green fuel to result in the predetermined ratio of mixed fuel. The main aircraft engine is configured to operate, in a first main engine mode, with the primary fuel from the main fuel tank and to operate, in a second main engine mode, with the mixed fuel from the mixing apparatus based on commands from the controller. The auxiliary power source is configured to operate with at least a portion of the green fuel from the green fuel tank based on commands from the controller.

    Abstract translation: 飞机系统包括：主燃料箱，其构造成容纳一次燃料;以及绿色燃料箱，其构造成容纳绿色燃料。 混合装置被配置为混合初级燃料和绿色燃料以产生混合燃料的预定比例。 控制器选择性地命令第一量的初级燃料和第二量的绿色燃料导致混合燃料的预定比例。 主飞机发动机被构造成以第一主发动机模式与来自主燃料箱的主燃料一起操作，并且在第二主发动机模式下，基于来自控制器的命令从混合装置操作混合燃料 。 辅助动力源被配置为基于来自控制器的命令与来自绿色燃料箱的绿色燃料的至少一部分一起操作。

    HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM WITH MOTORS USING INDUCTION EFFECT
    8.
    发明申请
    HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM WITH MOTORS USING INDUCTION EFFECT 审中-公开

    公开(公告)号：US20180141671A1

    公开(公告)日：2018-05-24

    申请号：US15358595

    申请日：2016-11-22

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Cristian Anghel ,  Eric Blumer

    IPC: B64D27/24 ,  B64D31/00 ,  B64C29/00

    Abstract: A hybrid electric aircraft propulsion system at least includes a motor with induction effect to drive a propeller or propulsion fan. The motor is directly supplied from the electrical output of a generator. The generator is driven by a variable speed engine and as such the generator has a output frequency proportional to the speed of the engine. A controller is operatively coupled to the motor, the generator and the engine. The controller is operable to control a speed of the engine and the excitation of the generator to provide an output at a target voltage and frequency to drive the motor at a desired torque and speed.

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