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    INTERCOOLED COOLING AIR TAPPED FROM PLURAL LOCATIONS
    505.
    发明申请
    INTERCOOLED COOLING AIR TAPPED FROM PLURAL LOCATIONS 审中-公开
    从多个地点接收的自动冷却空气

    公开(公告)号：US20160312797A1

    公开(公告)日：2016-10-27

    申请号：US14695534

    申请日：2015-04-24

    Applicant: United Technologies Corporation

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

    IPC: F04D29/58 ,  F01D25/12 ,  F02C7/143

    CPC classification number: F04D29/5826 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02C9/18 ,  F04D29/5833 ,  F05D2220/3212 ,  F05D2220/3217 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/3062 ,  Y02T50/675

    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main 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. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into 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最末端的高压压缩机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。 第一分接头从主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。 第二分接头从距离第一抽头的位置更靠近下游最端的位置敲击空气。 第一和第二抽头混合在一起并被输送到高压涡轮。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

    Full ring sliding nacelle with thrust reverser
    506.
    发明授权
    Full ring sliding nacelle with thrust reverser 有权
    全环滑动机舱与推力反向器

    公开(公告)号：US09435293B2

    公开(公告)日：2016-09-06

    申请号：US14187027

    申请日：2014-02-21

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  T. David Bomzer

    IPC: F02K1/60 ,  F02K1/62 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72

    CPC classification number: F02K1/605 ,  F01D25/24 ,  F02C3/04 ,  F02K1/60 ,  F02K1/62 ,  F02K1/625 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F05D2220/32 ,  F05D2230/72 ,  F05D2240/14 ,  F05D2270/051

    Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.

    Abstract translation: 燃气涡轮发动机包括静止的第一环形部分，并适于部分地围绕发动机芯。 第一环形部分包括前挂架连接部分。 燃气涡轮发动机还包括连接到前挂架并沿着后方向从第一环形部分延伸的轨道。 燃气涡轮发动机还包括第二环形部分，其布置在第一部分的后部并且联接到轨道。 第二环形部分可沿着发动机芯心中心线在关闭位置和至少一个打开位置之间移动。 第二环形部分构造成在关闭位置接合第一环形部分，从而提供对发动机芯的通路。 燃气涡轮发动机还包括布置在第二环形部分中的推力反向器。

    Geared Turbofan With High Gear Ratio And High Temperature Capability
    507.
    发明申请
    Geared Turbofan With High Gear Ratio And High Temperature Capability 审中-公开
    具有高齿轮比和高温能力的齿轮涡轮风扇

    公开(公告)号：US20160237914A1

    公开(公告)日：2016-08-18

    申请号：US14624668

    申请日：2015-02-18

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C9/18 ,  F01D5/28 ,  F02C7/36 ,  F02C7/18 ,  F02C7/32 ,  F02K3/06 ,  F02C3/10

    CPC classification number: F02C9/18 ,  F01D5/28 ,  F01D5/286 ,  F02C3/10 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2300/175 ,  F05D2300/607 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a fan rotor having blades with an outer diameter. The outer diameter is greater than or equal to 77 inches (196 centimeters) and less than or equal to 135 inches (343 centimeter). The fan rotor has less than or equal to 26 fan blades, and is driven by a fan drive turbine through a gear reduction. The gear reduction has a gear ratio of greater than 2.6:1. The fan rotor delivers air into a bypass duct as bypass air, and into a duct leading to a compressor rotor as core air. A ratio of bypass air to the core air is greater than or equal to 12:1. An upstream turbine rotor is upstream of the fan drive turbine and drives a compressor rotor. The upstream turbine rotor has at least two stages, and the fan drive turbine rotor has at least three stages. The turbine blades in at least one stage of the fan drive turbine rotor are provided with a performance enhancing feature, which is at least one of the blades being manufactured by a directionally solidified blade material. The blades are provided as single crystal blades, and have a radially outer platform provided with scalloping to reduce the weight of the blades. The blades are provided with cooling air.

    Abstract translation: 燃气涡轮发动机包括具有外径的叶片的风扇转子。 外径大于或等于77英寸（196厘米）且小于或等于135英寸（343厘米）。 风扇转子具有小于或等于26个风扇叶片，并通过齿轮减速由风扇驱动涡轮驱动。 齿轮减速比的传动比大于2.6：1。 风扇转子将空气作为旁路空气输送到旁通管道中，并进入作为核心空气通向压缩机转子的管道。 旁路空气与核心空气的比例大于或等于12：1。 上游涡轮转子在风扇驱动涡轮机的上游并驱动压缩机转子。 上游涡轮转子具有至少两个阶段，并且风扇驱动涡轮转子具有至少三个阶段。 在风扇驱动涡轮转子的至少一个级中的涡轮叶片设置有性能增强特征，其中至少一个叶片由定向凝固的叶片材料制造。 刀片设置为单晶刀片，并且具有设置有扇形的径向外侧平台，以减小叶片的重量。 叶片设有冷却空气。

    INTERCOOLED COOLING AIR WITH HEAT EXCHANGER PACKAGING
    508.
    发明申请
    INTERCOOLED COOLING AIR WITH HEAT EXCHANGER PACKAGING 有权
    具有热交换器包装的隔热冷却空气

    公开(公告)号：US20160237906A1

    公开(公告)日：2016-08-18

    申请号：US14745539

    申请日：2015-06-22

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry ,  Nathan Snape

    IPC: F02C7/18 ,  F02C3/04

    CPC classification number: F02C7/18 ,  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, 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. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.

    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。 芯壳体具有外周表面和限定内周表面的风扇壳体。 至少一个分叉管在外周表面和内周表面之间延伸。 热交换器被容纳在至少一个分叉管内。

    INTERCOOLED COOLING AIR
    509.
    发明申请
    INTERCOOLED COOLING AIR 审中-公开

    公开(公告)号：US20160237905A1

    公开(公告)日：2016-08-18

    申请号：US14695578

    申请日：2015-04-24

    Applicant: United Technologies Corporation

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

    IPC: F02C7/18 ,  F02C3/04

    CPC classification number: F41A9/63 ,  F02C3/04 ,  F02C7/18 ,  F02C7/185 ,  F02C7/32 ,  F02K3/06 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/4031 ,  F41A9/65 ,  Y02T50/676

    Abstract: Aa 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. An intercooling system for a gas turbine engine is also disclosed.

    Abstract translation: Aa燃气涡轮发动机包括具有具有下游排出口的高压压缩机和更多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。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

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