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    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER
    81.
    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
    82.
    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
    83.
    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
    84.
    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。

    COUNTER-ROTATING LOW PRESSURE TURBINE WITHOUT TURBINE EXHAUST CASE
    86.
    发明申请
    COUNTER-ROTATING LOW PRESSURE TURBINE WITHOUT TURBINE EXHAUST CASE 审中-公开
    没有涡轮机排气的逆转低压涡轮

    公开(公告)号：US20160040594A1

    公开(公告)日：2016-02-11

    申请号：US14887433

    申请日：2015-10-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Brian D. Merry

    IPC: F02C3/107 ,  F02C7/36

    CPC classification number: F02C3/107 ,  F01D1/26 ,  F01D25/30 ,  F02C7/36 ,  F02K1/78 ,  F02K3/072 ,  F05D2250/36 ,  F05D2250/44 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a compressor section, a combustor section downstream of the compressor section, and a turbine section downstream of the combustor section. A mid-turbine frame includes an outer case portion and is configured to support the turbine section. At least one shaft defines an axis of rotation, and the turbine section comprises an inner rotor directly driving the shaft. The inner rotor includes an inner set of blades. An outer rotor is positioned immediately adjacent to the outer case portion and has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system is positioned downstream of the combustor section, is mounted to the mid-turbine frame, and is coupled to the outer rotor to drive the at least one shaft.

    Abstract translation: 燃气涡轮发动机包括压缩机部分，压缩机部分下游的燃烧器部分和燃烧器部分下游的涡轮部分。 中间涡轮机框架包括外壳部分并且构造成支撑涡轮部分。 至少一个轴限定了旋转轴线，并且涡轮部分包括直接驱动轴的内转子。 内转子包括内组叶片。 外转子定位成紧邻外壳部分并且具有与内组叶片分开的外组叶片。 外转子构造成围绕与内转子的旋转轴线相反的方向旋转。 齿轮系统设置在燃烧器部分的下游，安装到中间涡轮机框架，并且联接到外转子以驱动至少一个轴。

    THERMAL BARRIER COATING INSIDE COOLING CHANNELS
    87.
    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。

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