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    PLATED POLYMERS WITH INTUMESCENT COMPOSITIONS AND TEMPERATURE INDICATORS
    32.
    发明申请
    PLATED POLYMERS WITH INTUMESCENT COMPOSITIONS AND TEMPERATURE INDICATORS 审中-公开
    具有核心成分和温度指示剂的聚合物

    公开(公告)号：US20160145447A1

    公开(公告)日：2016-05-26

    申请号：US14903888

    申请日：2014-07-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael S. Miarecki ,  Grant O. Cook ,  Wendell V. Twelves ,  Glenn Levasseur ,  Charles R. Watson

    IPC: C09D5/26 ,  B32B37/12 ,  B05D5/00 ,  B05D7/02 ,  C23C26/00

    Abstract: A plated polymer component is disclosed. The plated polymer component may comprise a polymer support, a metal plating deposited on a surface of the polymer support, and at least one flame-retardant additive included in the polymer support. In another aspect, the plated polymer component may comprise a polymer substrate, a metal plating deposited on a surface of the polymer substrate, and a temperature-indicating coating applied to at least one of of the polymer substrate.

    Abstract translation: 公开了镀覆的聚合物组分。 镀覆的聚合物组分可以包含聚合物载体，沉积在聚合物载体的表面上的金属电镀以及包含在聚合物载体中的至少一种阻燃添加剂。 在另一方面，电镀聚合物组分可以包括聚合物基底，沉积在聚合物基底的表面上的金属电镀，以及施加到聚合物基底中的至少一个的温度指示涂层。

    COOLING HOLE WITH CRENELLATION FEATURES
    35.
    发明申请
    COOLING HOLE WITH CRENELLATION FEATURES 有权
    冷凝孔与发条特点

    公开(公告)号：US20140193246A1

    公开(公告)日：2014-07-10

    申请号：US14204465

    申请日：2014-03-11

    Applicant: United Technologies Corporation

    Inventor： Glenn Levasseur ,  Edward F. Pietraszkiewicz

    IPC: F01D25/14

    CPC classification number: F01D25/14 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/324 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676 ,  Y10T29/49229 ,  Y10T29/49323

    Abstract: A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region.

    Abstract translation: 燃气涡轮发动机的部件的壁包括第一和第二壁表面，位于第一壁表面处的入口，位于第二表面处的出口，从入口开始并从入口的下游延伸的计量部分，以及 扩散部分从计量部分延伸并终止在出口处。 扩散部分包括形成在出口的上游端的前缘，形成在出口的下游端的后缘，在后缘的上游的身体区域，以及位于身体区域上的多个分类特征。

    Aircraft component repair scheduling system and process
    36.
    发明授权
    Aircraft component repair scheduling system and process 有权

    公开(公告)号：US11447271B2

    公开(公告)日：2022-09-20

    申请号：US16376324

    申请日：2019-04-05

    Applicant: United Technologies Corporation

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

    IPC: B64F5/60 ,  B64F5/40 ,  F01D21/00 ,  G01M15/14 ,  G07C5/08

    Abstract: A maintenance scheduling 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. Each of the gas turbine engine components is a single route component and has been utilized in a substantially identical single route. 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 maintenance schedule module is configured determine a predictive model operable to determine a predicted wear pattern of a second single route component that is substantially identical to the gas turbine engine components.

    Aircraft component qualification system and process including variation modeling
    37.
    发明授权
    Aircraft component qualification system and process including variation modeling 有权

    公开(公告)号：US11170140B2

    公开(公告)日：2021-11-09

    申请号：US16026627

    申请日：2018-07-03

    Applicant: United Technologies Corporation

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

    IPC: G06F30/20 ,  G06F111/10 ,  G06N20/00

    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.

    AIRCRAFT COMPONENT REPAIR SCHEDULING SYSTEM AND PROCESS
    38.
    发明申请
    AIRCRAFT COMPONENT REPAIR SCHEDULING SYSTEM AND PROCESS 审中-公开

    公开(公告)号：US20200317371A1

    公开(公告)日：2020-10-08

    申请号：US16376324

    申请日：2019-04-05

    Applicant: United Technologies Corporation

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

    IPC: B64F5/60 ,  G07C5/08 ,  B64F5/40 ,  G01M15/14 ,  F01D21/00

    Abstract: A maintenance scheduling 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. Each of the gas turbine engine components is a single route component and has been utilized in a substantially identical single route. 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 maintenance schedule module is configured determine a predictive model operable to determine a predicted wear pattern of a second single route component that is substantially identical to the gas turbine engine components.

    Intercooled cooling air with low temperature bearing compartment air
    39.
    发明授权
    Intercooled cooling air with low temperature bearing compartment air 有权

    公开(公告)号：US10718233B2

    公开(公告)日：2020-07-21

    申请号：US16012152

    申请日：2018-06-19

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Glenn Levasseur ,  Brian D. Merry

    IPC: F02C7/18 ,  F01D25/12 ,  F04D29/58 ,  F02K3/06

    Abstract: A gas turbine engine includes a plurality of rotatable components housed within a main compressor section and a turbine section. A cooling system is connected to tap air from said main compressor section. A first tap is connected to a first heat exchanger. The first heat exchanger is connected to a cooling compressor for raising a pressure of the tapped air downstream of the first heat exchanger. A second heat exchanger is downstream of the cooling compressor, and a connection is downstream of the second heat exchanger for delivering air to a bearing compartment. A connection intermediate the cooling compressor and the second heat exchanger delivers cooling air to at least one of the rotatable components.

    Variable displacement flutter damper for a turbofan engine
    40.
    发明授权
    Variable displacement flutter damper for a turbofan engine 有权

    公开(公告)号：US10539156B2

    公开(公告)日：2020-01-21

    申请号：US15452641

    申请日：2017-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Ian T. Marchaj ,  Glenn Levasseur

    IPC: F02C7/045 ,  F04D29/66 ,  F04D29/52 ,  F04D27/00 ,  F02K3/06 ,  B64D33/02 ,  F02K1/82

    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.

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