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    VARIABLE DISPLACEMENT FLUTTER DAMPER FOR A TURBOFAN ENGINE
    21.
    发明申请
    VARIABLE DISPLACEMENT FLUTTER DAMPER FOR A TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20180258956A1

    公开(公告)日：2018-09-13

    申请号：US15452641

    申请日：2017-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Ian T. Marchaj ,  Glenn Levasseur

    IPC: F04D29/66 ,  F04D29/52 ,  F04D27/00 ,  F02K3/06

    Abstract: Disclosed is a flutter damper, including a chamber having an internal space, a movable diaphragm disposed at least partially within the chamber, the diaphragm separating the chamber into a first chamber and a second chamber, the second chamber forming an acoustic volume, wherein a size of the acoustic volume configures the chamber for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and a biasing member that moves the diaphragm responsive to a signal from an aircraft or engine electronic control (EEC) unit, wherein movement of the diaphragm increases or reduces the size of the acoustic volume of the second chamber.

    Aircraft component repair system and process
    25.
    发明授权
    Aircraft component repair system and process 有权

    公开(公告)号：US12162627B2

    公开(公告)日：2024-12-10

    申请号：US16376294

    申请日：2019-04-05

    Applicant: United Technologies Corporation

    Inventor： Nagendra Somanath ,  Kurt R. Heinemann ,  Evan Selin ,  Glenn Levasseur

    IPC: B64F5/60 ,  G01M15/14

    Abstract: A repair system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters wherein each of the gas turbine engine components is an as-run component and has been exposed to a substantially identical general wear pattern. The computer system includes at least one simulated engine model. The simulated engine model is configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components. A correlation system is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A repair module is configured to generate a repair formula based on the predictive model. The repair formula is configured to receive a set of measured parameters of an as-run gas turbine engine component and determine a suggested repair capable of repairing the as-run gas turbine engine component.

    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS INCLUDING VARIATION MODELING
    26.
    发明申请
    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS INCLUDING VARIATION MODELING 审中-公开

    公开(公告)号：US20200012751A1

    公开(公告)日：2020-01-09

    申请号：US16026627

    申请日：2018-07-03

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  Kurt R. Heinemann ,  Glenn Levasseur

    IPC: G06F17/50

    Abstract: A method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set, and determining a variance model of the first set. The variance model includes a representative parameter profile, which includes a plurality of component parameter profiles. The sum of each of the component parameter profiles is the representative parameter profile. The method also includes determining at least one predicted response models based at least in part on the variance model, identifying as-manufactured parameters of a second engine component, applying the as-manufactured parameters of the second engine component to the at least one predicted response models, thereby generating a predicted response output, and qualifying the second engine component for usage in at least one gas turbine engine corresponding to the at least one predicted response model.

    Gas turbine engine component with converging/diverging cooling passage
    27.
    发明授权
    Gas turbine engine component with converging/diverging cooling passage 有权

    公开(公告)号：US10519778B2

    公开(公告)日：2019-12-31

    申请号：US15007775

    申请日：2016-01-27

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu ,  Glenn Levasseur

    IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

    Abstract: A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet. The inlet portion converges in a first direction from the inlet to the transition and diverges in a second direction from the inlet to the transition. The outlet portion diverges at least in one of the first and second directions from the transition to the outlet.

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