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    TANDEM ROTOR BLADES
    1.
    发明申请
    TANDEM ROTOR BLADES 审中-公开

    公开(公告)号：US20200217205A1

    公开(公告)日：2020-07-09

    申请号：US16827135

    申请日：2020-03-23

    Applicant: United Technologies Corporation

    Inventor： Matthew P. Forcier ,  Brian J. Schuler

    IPC: F01D5/14 ,  F04D29/32 ,  F01D9/04 ,  F01D11/00

    Abstract: A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages are defined radially inward relative to the compressor case. The plurality of stages include at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.

    Turbomachine rotors with thermal regulation
    2.
    发明授权
    Turbomachine rotors with thermal regulation 有权

    公开(公告)号：US10161251B2

    公开(公告)日：2018-12-25

    申请号：US14851588

    申请日：2015-09-11

    Applicant: United Technologies Corporation

    Inventor： Matthew E. Bintz ,  Matthew P. Forcier ,  Paul J. Hiester

    IPC: F01D5/08 ,  F01D25/12 ,  F01D5/06 ,  F04D29/58 ,  F04D29/32 ,  F02C7/18

    Abstract: A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.

    Actively-driven bleed source switching
    4.
    发明授权
    Actively-driven bleed source switching 有权

    公开(公告)号：US11459906B2

    公开(公告)日：2022-10-04

    申请号：US15601544

    申请日：2017-05-22

    Applicant: United Technologies Corporation

    Inventor： Jonathan Ortiz ,  William K. Ackermann ,  Matthew P. Forcier

    IPC: F01D21/00 ,  F01D25/12 ,  F02C7/12 ,  F02C9/18 ,  F01D17/10 ,  F01D17/14 ,  F01D5/02 ,  F04D27/00

    Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, and a bleed duct in fluid communication with the bleed ports and configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet. A valve is located at each bleed port of and is configured to move between an opened position and a closed position, and one or more sensors are located along the bleed flowpath to sense one or more conditions of the bleed air cooling system. The valve at a particular bleed port is moved to the opened position based on the sensed one or more conditions.

    HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING OUTER DIAMETER GAS EXTRACTION
    7.
    发明申请
    HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING OUTER DIAMETER GAS EXTRACTION 审中-公开
    高压压缩机使用外径气体提取的转子热调节

    公开(公告)号：US20160123176A1

    公开(公告)日：2016-05-05

    申请号：US14877965

    申请日：2015-10-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William K. Ackermann ,  Matthew P. Forcier ,  Paul J. Hiester

    IPC: F01D17/10 ,  F02C3/06 ,  F01D25/24 ,  F04D29/32 ,  F01D5/02

    Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades. A lower pressure tap and a higher pressure tap tap air from two distinct locations within the compressor and radially outwardly through the outer housing. A valve selectively delivers at least one of the lower pressure tap and the higher pressure tap to the bore of the disc. A control for the valve is programmed to move the valve to a position delivering the higher pressure tap at a point prior to take-off when the compressor is mounted in a gas turbine engine on an aircraft. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

    Abstract translation: 用于燃气涡轮发动机的压缩机包括具有叶片和盘的压缩机转子，其具有径向地位于盘的内侧的孔。 径向外壳围绕叶片的外径。 来自压缩机内的两个不同位置的较低压力抽头和较高压力的抽头抽风，并通过外壳径向向外。 选择性地将低压抽头和较高压力抽头中的至少一个输送到盘的孔。 编程该阀门的控制，以便当压缩机安装在飞机上的燃气涡轮发动机中时，将阀移动到在起飞前的某一点处传送高压龙头的位置。 还公开了一种燃气涡轮发动机和操作燃气涡轮发动机的方法。

    TURBOMACHINE ROTORS WITH THERMAL REGULATION
    8.
    发明申请
    TURBOMACHINE ROTORS WITH THERMAL REGULATION 审中-公开
    涡轮转子与热调节

    公开(公告)号：US20160076378A1

    公开(公告)日：2016-03-17

    申请号：US14851588

    申请日：2015-09-11

    Applicant: United Technologies Corporation

    Inventor： Matthew E. Bintz ,  Matthew P. Forcier ,  Paul J. Hiester

    IPC: F01D5/08 ,  F01D25/12 ,  F01D5/06

    CPC classification number: F01D5/08 ,  F01D5/06 ,  F01D5/081 ,  F01D25/12 ,  F02C7/18 ,  F04D29/321 ,  F04D29/584 ,  F05D2220/30 ,  F05D2240/20 ,  F05D2260/20

    Abstract: A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.

    Abstract translation: 用于涡轮机的转子盘包括盘体，被配置为连接到或包括设置在盘体的径向向外部分上的转子叶片的边缘，限定在盘体的径向向内部分中的孔，并且被构造成径向地 邻近轴，并且限定在盘体中的热调节孔，位于轮辋的径向内侧，用于当设置在涡轮机的阶段中时允许流动轴向地通过盘体;以及限定在盘中的热调节孔 主体，用于当设置在涡轮机的阶段时允许流动通过盘体。

    Passively-driven bleed source switching
    9.
    发明授权
    Passively-driven bleed source switching 有权

    公开(公告)号：US10473037B2

    公开(公告)日：2019-11-12

    申请号：US15601563

    申请日：2017-05-22

    Applicant: United Technologies Corporation

    Inventor： Jonathan Ortiz ,  William K. Ackermann ,  Matthew P. Forcier

    IPC: F01D9/06 ,  F02C9/18 ,  F02C7/18 ,  F02C6/08

    Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.

    PASSIVELY-DRIVEN BLEED SOURCE SWITCHING
    10.
    发明申请
    PASSIVELY-DRIVEN BLEED SOURCE SWITCHING 审中-公开

    公开(公告)号：US20180334966A1

    公开(公告)日：2018-11-22

    申请号：US15601563

    申请日：2017-05-22

    Applicant: United Technologies Corporation

    Inventor： Jonathan Ortiz ,  William K. Ackermann ,  Matthew P. Forcier

    IPC: F02C9/18 ,  F02C7/18 ,  F01D9/06

    CPC classification number: F02C9/18 ,  F01D9/065 ,  F02C6/08 ,  F02C7/18 ,  F05D2260/20 ,  F05D2260/50 ,  F05D2270/3015

    Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.

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