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    Tandem rotor blades
    25.
    发明授权
    Tandem rotor blades 有权

    公开(公告)号：US10598024B2

    公开(公告)日：2020-03-24

    申请号：US14882722

    申请日：2015-10-14

    Applicant: United Technologies Corporation

    Inventor： Matthew P. Forcier ,  Brian J. Schuler

    IPC: F01D5/14 ,  F04D29/32 ,  F01D9/04 ,  F01D11/00 ,  F04D29/54 ,  F04D19/02

    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.

    BLEED FLOW SAFETY SYSTEM
    26.
    发明申请
    BLEED FLOW SAFETY SYSTEM 审中-公开

    公开(公告)号：US20180334965A1

    公开(公告)日：2018-11-22

    申请号：US15601524

    申请日：2017-05-22

    Applicant: United Technologies Corporation

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

    IPC: F02C9/18 ,  F01D17/02 ,  F01D9/06 ,  F02C7/18

    CPC classification number: F02C9/18 ,  F01D9/065 ,  F01D17/02 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/30

    Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed ports located at one or more axial locations of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. One or more safety sensors are configured to sense operational characteristics of the gas turbine engine, and a controller is operably connected to the one or more safety sensors and configured to evaluate the sensed operational characteristics for anomalies in operation of the bleed air cooling system.

    HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING DISCHARGE PRESSURE AIR
    28.
    发明申请
    HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING DISCHARGE PRESSURE AIR 审中-公开
    高压压缩机使用放气压力空气的转子热调节

    公开(公告)号：US20160123234A1

    公开(公告)日：2016-05-05

    申请号：US14878018

    申请日：2015-10-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Matthew P. Forcier ,  Paul J. Hiester ,  Andrew J. Murphy

    IPC: F02C9/18 ,  F02C3/04 ,  F04D29/32

    CPC classification number: F02C9/18 ,  F01D5/087 ,  F01D19/02 ,  F02C3/04 ,  F02C6/08 ,  F02C7/185 ,  F04D29/324 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2270/114 ,  Y02T50/676

    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 high pressure air tap includes a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of the lower temperature tapped path and the higher temperature tapped path into the bore of the disc. The valve is operable to selectively block flow of either of the lower pressure and higher pressure tapped paths to the bore of the disc, with the disc including holes to allow air from compressor chambers to communicate with the bore of the disc. 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。 高压空气抽头包括较低的温度挖掘路径和较高的温度挖掘路径，以及用于选择性地将较低温度的攻丝路径和较高温度的攻丝路径之一输送到盘的孔中的阀。 所述阀可操作以选择性地阻挡所述盘的所述孔的所述较低压力和较高压力的任意一个路径的流动，其中所述盘包括孔，以允许来自压缩机室的空气与所述盘的孔连通。 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。

    TANDEM ROTOR BLADES
    29.
    发明申请
    TANDEM ROTOR BLADES 审中-公开
    TANDEM转子叶片

    公开(公告)号：US20160108735A1

    公开(公告)日：2016-04-21

    申请号：US14882722

    申请日：2015-10-14

    Applicant: United Technologies Corporation

    Inventor： Matthew P. Forcier ,  Brian J. Schuler

    IPC: F01D5/14 ,  F01D9/04 ,  F01D11/00 ,  F04D19/02

    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 defined radially inward relative to the compressor case. The plurality of stages includes 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.

    Abstract translation: 燃气涡轮发动机包括压缩机部分和具有低压压缩机（LPC）和高压压缩机（HPC）的压缩机壳体。 HPC是LPC的尾。 压缩机壳体定义一个中心线轴。 压缩机部分还包括限定在压缩机壳体和中心线轴线之间的转子盘。 相对于压缩机壳体径向向内限定的多个级。 多个级包括至少一个串联刀片级。 串联叶片台包括多个叶片对。 每个叶片对与其它叶片对周向间隔开，并且可操作地连接到转子盘。 每个刀片对包括前刀片和后刀片。 后叶片构造成进一步调节相对于前叶片的空气流动，而在它们之间没有中间的定子叶片级覆盖腔。

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