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    Method and system for integrated pitch control mechanism actuator hydraulic fluid transfer
    161.
    发明授权
    Method and system for integrated pitch control mechanism actuator hydraulic fluid transfer 有权

    公开(公告)号：US10393137B2

    公开(公告)日：2019-08-27

    申请号：US15043036

    申请日：2016-02-12

    Applicant: General Electric Company

    Inventor： Daniel Alan Niergarth ,  Darek Tomasz Zatorski ,  Christopher James Kroger

    IPC: F04D29/36 ,  F04D29/32 ,  B64C11/38

    Abstract: The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.

    THERMAL MANAGEMENT SYSTEM
    162.
    发明申请
    THERMAL MANAGEMENT SYSTEM 审中-公开

    公开(公告)号：US20190153953A1

    公开(公告)日：2019-05-23

    申请号：US15819443

    申请日：2017-11-21

    Applicant: General Electric Company

    Inventor： Daniel Alan Niergarth ,  Adon Delgado, JR. ,  Brandon Wayne Miller ,  Hendrik Pieter Jacobus de Bock

    IPC: F02C7/224 ,  F02C7/141 ,  F28F23/00

    Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.

    Propulsion engine for an aircraft
    164.
    发明授权
    Propulsion engine for an aircraft 有权

    公开(公告)号：US10252810B2

    公开(公告)日：2019-04-09

    申请号：US15132304

    申请日：2016-04-19

    Applicant: General Electric Company

    Inventor： Daniel Alan Niergarth ,  Randy M. Vondrell ,  Brandon Wayne Miller ,  Patrick Michael Marrinan

    IPC: B64D27/24 ,  B64D27/02 ,  B64D27/12 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36

    Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.01×RFP−0.311, such that the propulsion engine may operate at a desired efficiency.

    TURBOMACHINE WITH A GEARBOX AND INTEGRATED ELECTRIC MACHINE ASSEMBLY
    165.
    发明申请
    TURBOMACHINE WITH A GEARBOX AND INTEGRATED ELECTRIC MACHINE ASSEMBLY 审中-公开

    公开(公告)号：US20190085714A1

    公开(公告)日：2019-03-21

    申请号：US15709535

    申请日：2017-09-20

    Applicant: General Electric Company

    Inventor： Darek Tomasz Zatorski ,  Gert Johannes van der Merwe ,  Brandon Wayne Miller ,  Daniel Alan Niergarth

    IPC: F01D15/10 ,  F01D15/12 ,  F01D1/26 ,  F01D25/16 ,  H02K7/18 ,  H02K7/116 ,  B64D27/10

    Abstract: A turbomachine includes a turbine section including a turbine. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction. The turbomachine also includes a gearbox. The first plurality of turbine rotor blades and the second plurality of turbine rotor blades are each coupled to one of a ring gear, a planet gear, or a sun gear of the gearbox such that the first plurality of turbine rotor blades is rotatable with the second plurality of turbine rotor blades through the gearbox. The turbomachine also includes an electric machine assembly including a rotor coupled to one of the ring gear, the planet gear, or the sun gear of the gearbox such that the rotor rotates relative to a stator during operation.

    Variable pitch fan blade retention system
    166.
    发明授权
    Variable pitch fan blade retention system 有权

    公开(公告)号：US10100653B2

    公开(公告)日：2018-10-16

    申请号：US14878008

    申请日：2015-10-08

    Applicant: General Electric Company

    Inventor： Daniel Alan Niergarth ,  Ian Francis Prentice ,  Christopher James Kroger

    IPC: F01D5/32 ,  F01D7/00 ,  F04D29/32 ,  F04D29/64 ,  F01D5/02 ,  F01D5/12 ,  F01D5/30 ,  F02C3/04 ,  B64C11/32

    Abstract: A variable pitch fan for a gas turbine engine includes a fan blade defining a pitch axis and attached at a radially inner end to a trunnion mechanism. The variable pitch fan also includes a disk having a disk segment with the trunnion mechanism extending at least partially through the disk segment. A key is positioned at least partially in a key slot defined in a base of the trunnion mechanism, and further positioned adjacent to a support member of the disk segment. The key defines a first contact line between the key and the key slot and a second contact line between the key and the support member. The first and second contact lines respectively define a first contact reference line in a second contact reference line. The first and second contact reference lines define an angle with the pitch axis of the fan blade greater than zero degrees and less than ninety degrees.

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