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    External Mixing Chamber for a Gas Turbine Engine with Cooled Turbine Cooling Air
    22.
    发明申请
    External Mixing Chamber for a Gas Turbine Engine with Cooled Turbine Cooling Air 审中-公开

    公开(公告)号：US20180223736A1

    公开(公告)日：2018-08-09

    申请号：US15424927

    申请日：2017-02-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James D. Hill ,  Frederick M. Schwarz

    IPC: F02C7/18 ,  F02C3/107 ,  F01D25/12

    CPC classification number: F02C7/185 ,  F01D25/12 ,  F02C3/107 ,  F02C6/08 ,  F02C7/18 ,  F05D2260/213 ,  Y02T50/676

    Abstract: A gas turbine engine comprises a compressor section and a turbine section, the compressor section having a last compressor stage. High pressure cooling air is tapped from a location downstream of the last compressor stage and passed through a heat exchanger. Lower pressure air passes across the heat exchanger to cool the high pressure cooling air. A housing surrounds the compressor section and the turbine section and there being a space radially outwardly of the housing, and a mixing chamber received in the space radially outwardly of the housing, the mixing chamber receiving the high pressure cooling air downstream of the heat exchanger, and further receiving air at a temperature higher than a temperature of the high pressure cooling air downstream of the heat exchanger. Mixed air from the mixing chamber is returned into the housing and utilized to cool at least the turbine section.

    Gas Turbine Engine With Single Turbine Driving Two Compressors
    23.
    发明申请
    Gas Turbine Engine With Single Turbine Driving Two Compressors 审中-公开
    燃气轮机发动机与单涡轮驱动两台压缩机

    公开(公告)号：US20160160761A1

    公开(公告)日：2016-06-09

    申请号：US14921324

    申请日：2015-10-23

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  James D. Hill ,  William F. Schneider ,  Jonathan F. Zimmitti

    IPC: F02C7/36 ,  F02C9/16 ,  F02C3/04

    CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/113 ,  F02C9/16 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2270/02

    Abstract: A gas turbine engine comprises a lower pressure compressor and a higher pressure compressor. A single turbine drives both the lower pressure compressor and the higher pressure compressor through a gear reduction. The gear reduction includes an actuator and at least two available speeds, such that the lower pressure compressor can selectively be operated at either of at least two speeds relative to the higher pressure compressor. A method of operating a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括低压压缩机和高压压缩机。 单个涡轮机通过齿轮减速器驱动低压压缩机和较高压力的压缩机。 齿轮减速包括致动器和至少两个可用速度，使得低压压缩机可选择性地相对于较高压力的压缩机以至少两个速度运行。 还公开了一种操作燃气涡轮发动机的方法。

    PULSE DETONATION COMBUSTOR
    24.
    发明申请
    PULSE DETONATION COMBUSTOR 审中-公开
    脉冲爆炸燃烧器

    公开(公告)号：US20160102609A1

    公开(公告)日：2016-04-14

    申请号：US14815400

    申请日：2015-07-31

    Applicant: United Technologies Corporation

    Inventor： James D. Hill ,  Martin Haas ,  Robert B. Fowler ,  Jeffery A. Lovett ,  Roger F. Blinn

    IPC: F02C5/02 ,  F02C7/00 ,  F23R7/00 ,  F23C15/00

    Abstract: A pulse detonation combustor may include a valve and a tubular combustor wall, which forms an airflow inlet and a combustion chamber. The valve may be configured to selectively fluidly couple the airflow inlet with the combustion chamber. The valve may include a center body and an annular projection. The center body and the projection may be configured to sealingly engage with one another.

    Abstract translation: 脉冲爆震燃烧器可以包括形成气流入口和燃烧室的阀和管状燃烧器壁。 阀可以被配置为选择性地将气流入口与燃烧室流体地联接。 阀可以包括中心体和环形突起。 中心体和突起可以被配置为彼此密封地接合。

    THERMAL BARRIER COATING INSIDE COOLING CHANNELS
    25.
    发明申请
    THERMAL BARRIER COATING INSIDE COOLING CHANNELS 审中-公开
    热障涂层在冷却通道内

    公开(公告)号：US20160032731A1

    公开(公告)日：2016-02-04

    申请号：US14799994

    申请日：2015-07-15

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  Wesley K. Lord

    IPC: F01D5/18

    CPC classification number: F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F01D5/288 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的转子包括可绕轴线旋转的转子盘和连接到转子盘的径向外侧的气体通道壁。 气体通道壁限定气体通道的径向向内部分。 多个转子轮辐径向地位于转子盘和气体通道壁之间。 多个转子轮辐在周向间隔开以限定转子盘和气体通道壁之间的多个冷却通道。 热屏障涂层设置在多个冷却通道中的至少一个的表面上。 还公开了一种冷却转子组件的方法。

    Gas turbine engine blade with variable density and wide chord tip
    27.
    发明授权
    Gas turbine engine blade with variable density and wide chord tip 有权

    公开(公告)号：US10954799B2

    公开(公告)日：2021-03-23

    申请号：US16397265

    申请日：2019-04-29

    Applicant: United Technologies Corporation

    Inventor： Pitchaiah Vijay Chakka ,  James D. Hill ,  David R. Pack

    IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28

    Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.

    Overcooled air cooling system with annular mixing passage
    30.
    发明授权
    Overcooled air cooling system with annular mixing passage 有权

    公开(公告)号：US10100738B2

    公开(公告)日：2018-10-16

    申请号：US14600862

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： James D. Hill ,  William K. Ackermann

    IPC: F02C7/18 ,  F02C3/04 ,  F01D25/12 ,  F02K3/115 ,  F02C6/06 ,  F23R3/04 ,  F02C6/08 ,  F01D9/02 ,  F02C9/18 ,  F02C7/12 ,  F01D5/08

    Abstract: A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.

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