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    INTERCOOLED COOLING AIR WITH LOW TEMPERATURE BEARING COMPARTMENT AIR
    41.
    发明申请
    INTERCOOLED COOLING AIR WITH LOW TEMPERATURE BEARING COMPARTMENT AIR 审中-公开

    公开(公告)号：US20190383167A1

    公开(公告)日：2019-12-19

    申请号：US16012152

    申请日：2018-06-19

    Applicant: United Technologies Corporation

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

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

    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.

    Hybrid airfoil cooling
    42.
    发明授权
    Hybrid airfoil cooling 有权

    公开(公告)号：US10428660B2

    公开(公告)日：2019-10-01

    申请号：US15420882

    申请日：2017-01-31

    Applicant: United Technologies Corporation

    Inventor： James D Hill ,  Ram Ranjan ,  Glenn Levasseur

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

    Abstract: An airfoil may comprise an airfoil body having a leading edge and a trailing edge. A heat pipe may be disposed within the airfoil. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be disposed within the airfoil body and may be configured to remove heat from the trailing edge. The second cooling apparatus may be disposed within the airfoil body and may be configured to remove heat from the leading edge.

    Rotor blade having anti-wear surface
    43.
    发明授权
    Rotor blade having anti-wear surface 有权

    公开(公告)号：US10294801B2

    公开(公告)日：2019-05-21

    申请号：US15659360

    申请日：2017-07-25

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu ,  Glenn Levasseur ,  Gregory M. Dolansky

    IPC: F01D5/28 ,  F04D29/32 ,  F01D5/14 ,  F01D5/20 ,  F01D5/22 ,  F01D11/08 ,  F02C3/04

    Abstract: A rotor blade includes a main body that extends radially outward from a first end to a second end, and includes a platform at the second end that extends circumferentially between opposing first and second sidewalls. The platform includes a first lateral wall that is situated between leading and trailing edges of the platform. The first lateral wall extends circumferentially between the first and second sidewalls and radially outward from the platform. The first lateral wall includes an extension that extends the first lateral wall circumferentially outward from the first sidewall. Respective portions of the first and second sidewalls adjacent to the first lateral wall reside in respective first and second planes, and the extension includes an outer face situated outside of the first and second planes. A majority of the first lateral wall includes a first material, and the outer face includes a second material having a different resistance to wear than the first material.

    ROTOR BLADE HAVING ANTI-WEAR SURFACE
    45.
    发明申请
    ROTOR BLADE HAVING ANTI-WEAR SURFACE 审中-公开

    公开(公告)号：US20190032498A1

    公开(公告)日：2019-01-31

    申请号：US15659360

    申请日：2017-07-25

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu ,  Glenn Levasseur ,  Gregory M. Dolansky

    IPC: F01D5/28 ,  F04D29/32

    Abstract: A rotor blade includes a main body that extends radially outward from a first end to a second end, and includes a platform at the second end that extends circumferentially between opposing first and second sidewalls. The platform includes a first lateral wall that is situated between leading and trailing edges of the platform. The first lateral wall extends circumferentially between the first and second sidewalls and radially outward from the platform. The first lateral wall includes an extension that extends the first lateral wall circumferentially outward from the first sidewall. Respective portions of the first and second sidewalls adjacent to the first lateral wall reside in respective first and second planes, and the extension includes an outer face situated outside of the first and second planes. A majority of the first lateral wall includes a first material, and the outer face includes a second material having a different resistance to wear than the first material.

    PLATED POLYMER AVIATION COMPONENTS
    47.
    发明申请
    PLATED POLYMER AVIATION COMPONENTS 审中-公开
    镀聚合物航空组件

    公开(公告)号：US20160167791A1

    公开(公告)日：2016-06-16

    申请号：US14903566

    申请日：2014-07-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James T. Roach ,  Grant Cook ,  Shari L. Bugaj ,  Majidullah Dehlavi ,  Kevin W. Schlichting ,  Joseph Parkos ,  Glenn Levasseur

    IPC: B64D15/00 ,  H05B3/06 ,  C23C18/16 ,  C25D5/56 ,  C25D7/00

    Abstract: Aviation components comprising a polymeric substrate having an outer surface wherein a metal is plated onto the outer surface to form a plated layer are disclosed. A method to make aviation components comprising a polymeric substrate having an outer surface and where a metal is plated onto the outer surface is disclosed. An over-plated heating element for shedding ice from an aircraft component having a polymeric substrate with a pocket to receive a heating element, a metal deposited onto the substrate, a heating element positioned within the pocket and a covering layer deposited onto the heating element and the plated layer is disclosed.

    Abstract translation: 公开了包括具有外表面的聚合物基材的航空部件，其中将金属镀在外表面上以形成镀层。 公开了一种使包括具有外表面的聚合物基材和其中金属被镀在外表面上的航空部件的方法。 一种用于从具有带有凹穴的聚合物基底的飞机部件脱落冰以接收加热元件的过镀层加热元件，沉积在基底上的金属，位于该凹槽内的加热元件和沉积在加热元件上的覆盖层， 公开了镀层。

    GEARED TURBOFAN HIGH GEARBOX POWER DENSITY
    50.
    发明申请
    GEARED TURBOFAN HIGH GEARBOX POWER DENSITY 审中-公开
    齿轮变速箱高齿轮功率密度

    公开(公告)号：US20150267618A1

    公开(公告)日：2015-09-24

    申请号：US14431839

    申请日：2013-03-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  William G. Sheridan ,  Glenn Levasseur

    IPC: F02C7/36 ,  B23P15/14 ,  F16H57/04 ,  F16H1/36 ,  F16H1/48

    CPC classification number: F02C7/36 ,  B23P15/14 ,  F02C3/107 ,  F05D2260/40311 ,  F16H1/36 ,  F16H1/48 ,  F16H57/0412 ,  F16H57/0486 ,  Y02T50/671 ,  Y10T29/49316

    Abstract: A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency.

    Abstract translation: 用于燃气涡轮发动机的齿轮架构包括被支撑用于围绕轴线旋转的中心齿轮，与中心齿轮接合的多个中间齿轮和限定中间齿轮的环形齿轮。 在由涡轮部分驱动的输入轴和太阳齿轮之间提供第一柔性联轴器。 齿轮架构提供功率密度，其功率密度包括在限定范围内与齿轮架构的重量相关的功率（HP），该功率有利于整个发动机的重量和效率。

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