中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

548 records (took 0.04 seconds)

    Pivot thrust reverser with multi-point actuation
    161.
    发明授权
    Pivot thrust reverser with multi-point actuation 有权
    枢轴推力反向器多点驱动

    公开(公告)号：US09581108B2

    公开(公告)日：2017-02-28

    申请号：US14184376

    申请日：2014-02-19

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02K1/72 ,  F02K1/60 ,  F02K1/62 ,  F02K1/64 ,  B64D29/00 ,  B23P19/04 ,  F02K1/76

    CPC classification number: F02K1/763 ,  B23P19/04 ,  B64D29/00 ,  B64D33/04 ,  F02K1/60 ,  F02K1/605 ,  F02K1/62 ,  F02K1/64 ,  F02K1/72 ,  F05D2260/50 ,  Y10T29/49229

    Abstract: One embodiment includes a pivot thrust reverser with a first pivot door with an upper linkage and a lower linkage and a second pivot door, spaced from the first pivot door, with an upper linkage and a lower linkage. A first actuator is located on a first side of an attachment location to drive the first pivot door. A second actuator is located on a second side of the attachment location to drive the second pivot door. A third actuator is located substantially radially opposite the attachment location to drive both the first pivot door and the second pivot door. The first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator. The second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.

    Abstract translation: 一个实施例包括枢转推力反向器，其具有带有上连杆的第一枢转门和下连杆以及与第一枢转门隔开的第二枢转门，具有上连杆和下连杆。 第一致动器位于附接位置的第一侧以驱动第一枢轴门。 第二致动器位于附接位置的第二侧以驱动第二枢转门。 第三致动器基本上位于与附接位置径向相对的位置，以驱动第一枢转门和第二枢转门。 第一枢转门构造成通过第一致动器和第三致动器由收起位置枢转到展开位置。 第二枢转门构造成通过第二致动器和第三致动器由收起位置枢转到展开位置。

    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER
    164.
    发明申请
    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER 有权
    双通道热交换器的双向冷却空气

    公开(公告)号：US20160312704A1

    公开(公告)日：2016-10-27

    申请号：US14695504

    申请日：2015-04-24

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry ,  Wesley K. Lord

    IPC: F02C7/18

    CPC classification number: F02C7/185 ,  F01D25/12 ,  F02C3/13 ,  F02C7/143 ,  F05D2210/44 ,  F05D2220/3212 ,  F05D2220/3218 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  Y02T50/676

    Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有下游最末端和更上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 热交换器具有至少两个通道，其中一个通道径向向外通过空气，另一个通道使空气径向向内返回到压缩机。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    166.
    发明申请
    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 审中-公开
    燃气涡轮发动机压缩机装置

    公开(公告)号：US20160290241A1

    公开(公告)日：2016-10-06

    申请号：US15184253

    申请日：2016-06-16

    Applicant: United Technologies Corporation

    Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC: F02C7/36 ,  F02C3/04 ,  F02K3/06 ,  F01D5/12 ,  F01D25/24 ,  F01D9/02 ,  F01D25/28 ,  F02C7/28 ,  F02C7/06 ,  F02K3/02

    CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D5/12 ,  F01D9/02 ,  F01D21/003 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/40 ,  F05D2260/4031 ,  F05D2260/40311

    Abstract: A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to about 8 at cruise power. A gear arrangement is configured to drive the fan section. A compressor section includes both a first compressor section and a second compressor section. A turbine section is configured to drive the gear arrangement, and may have a low pressure turbine with four stages and a low pressure turbine pressure ratio greater than about 5:1, and a high pressure turbine with two stages. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than about 40, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor section is greater than about 7.

    Abstract translation: 除了别的以外，燃气涡轮发动机还包括风扇部分，核心发动机，旁通通道和旁路比，其被定义为与进入核心发动机的空气体积相比进入旁路通道的空气量， 旁路比在巡航功率时大于或等于约8。 齿轮装置被配置成驱动风扇部分。 压缩机部分包括第一压缩机部分和第二压缩机部分。 涡轮部分构造成驱动齿轮装置，并且可以具有四级的低压涡轮机和大于约5:1的低压涡轮机压力比，以及具有两级的高压涡轮机。 整个压力比通过跨第一压缩机段的压力比和跨越第二压缩机段的压力比的组合提供，并且在海平面和静态的额定额定起飞功率下测量大于约40。 跨越第二压缩机部分的压力比大于约7。

    INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL
    167.
    发明申请
    INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL 审中-公开
    具有辅助压缩机控制的隔热冷却空气

    公开(公告)号：US20160237907A1

    公开(公告)日：2016-08-18

    申请号：US14745550

    申请日：2015-06-22

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Gary D. Roberge

    IPC: F02C7/18 ,  F02C3/04

    CPC classification number: F02C7/18 ,  F02C7/185 ,  F05D2260/213 ,  Y02T50/676

    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor, which compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor rotates at a speed proportional to a speed of at least one rotor in the turbine section. The cooling compressor is allowed to rotate at a speed that is not proportional to a speed of the at least one rotor under certain conditions. An intercooling system for a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 分接头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，使抽头的空气通过热交换器，然后到达冷却压缩机，冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机 。 冷却压缩机以与涡轮机部分中的至少一个转子的速度成比例的速度旋转。 允许冷却压缩机在某些条件下以与至少一个转子的速度成比例的速度旋转。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

    INTERCOOLED COOLING AIR WITH IMPROVED AIR FLOW
    168.
    发明申请
    INTERCOOLED COOLING AIR WITH IMPROVED AIR FLOW 有权
    具有改进的空气流的隔热冷却空气

    公开(公告)号：US20160237901A1

    公开(公告)日：2016-08-18

    申请号：US14745564

    申请日：2015-06-22

    Applicant: United Technologies Corporation

    Inventor： Mark F. Zelesky ,  Gabriel L. Suciu ,  Brian D. Merry

    IPC: F02C7/141 ,  F02C7/36 ,  F02C7/32

    CPC classification number: F02C6/08 ,  F02C7/143 ,  F02K3/115 ,  F05D2260/211 ,  Y02T50/676

    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor includes a downstream connection that delivers discharge pressure air to an upstream location in the high pressure turbine and a second tap from an intermediate pressure location within the cooling compressor. The second tap is connected to a downstream location within the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 冷却压缩机包括下游连接，其将排出压力空气输送到高压涡轮机中的上游位置，以及从冷却压缩机内的中间压力位置输出第二分接头。 第二分接头连接到高压涡轮机内的下游位置。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

    Gas Turbine Engine With Single Turbine Driving Two Compressors
    170.
    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。

Patent Agency Ranking