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    Asymmetric fan nozzle in high-BPR separate-flow nacelle
    61.
    发明授权
    Asymmetric fan nozzle in high-BPR separate-flow nacelle 有权

    公开(公告)号：US10330047B2

    公开(公告)日：2019-06-25

    申请号：US14768830

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Wesley K. Lord ,  Robert E. Malecki

    IPC: F02K3/02 ,  F02K3/06 ,  F02K1/78 ,  B64D33/02 ,  F01D25/24 ,  F02C3/04 ,  B64D33/04

    Abstract: A fan nozzle for an aircraft gas turbine engine is comprised of a core engine cowl that is disposed within a fan cowl so that an air flow area is defined therebetween. The core engine cowl and fan cowl are disposed around a horizontal central plane. The fan cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a first radius and a lower substantially semi-circular portion having a second radius. The core engine cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a third radius and a lower substantially semi-circular portion having a third radius. The upper substantially semi-circular portion of the core engine cowl includes a left arcuate member and a right arcuate member. The second radius is less than the first radius and the third radius is less than the fourth radius.

    INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER
    66.
    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。

    TRANSVERSE-MOUNTED POWER TURBINE DRIVE SYSTEM
    67.
    发明申请
    TRANSVERSE-MOUNTED POWER TURBINE DRIVE SYSTEM 审中-公开
    横向安装的动力涡轮机驱动系统

    公开(公告)号：US20160290227A1

    公开(公告)日：2016-10-06

    申请号：US15104114

    申请日：2014-12-12

    Applicant: United Technologies Corporation

    Inventor： Wesley K. Lord

    IPC: F02C3/04 ,  F02C7/36

    Abstract: The present disclosure relates generally to an aircraft with counter-rotating pusher props powered by a gas turbine engine having a power turbine disposed substantially perpendicular to the compressor, combustor and turbine gas generator power core axis, as well as to the aircraft longitudinal axis.

    Abstract translation: 本公开总体上涉及具有由具有基本上垂直于压缩机，燃烧器和涡轮机气体发生器功率核心轴以及飞行器纵向轴线设置的动力涡轮机的燃气涡轮发动机驱动的反向旋转推动器道具的飞行器。

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    69.
    发明申请
    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
    低压风扇发动机在入口和风扇尺寸之间存在尺寸关系

    公开(公告)号：US20160108854A1

    公开(公告)日：2016-04-21

    申请号：US14882760

    申请日：2015-10-14

    Applicant: United Technologies Corporation

    Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

    IPC: F02K3/06 ,  F04D19/02 ,  F01D15/12 ,  F01D17/10 ,  F01D5/02 ,  F01D5/12

    CPC classification number: F02K3/06 ,  F01D5/02 ,  F01D5/141 ,  F01D15/12 ,  F01D17/105 ,  F02C7/04 ,  F02C7/045 ,  F04D29/522 ,  F04D29/547 ,  F05D2220/32 ,  F05D2250/00 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, a geared architecture configured to drive the fan, a turbine section configured to drive the geared architecture, a compressor section including a first compressor and a second compressor, and an inlet portion forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机组件包括除了别的以外的包括多个风扇叶片的风扇，具有基于风扇叶片的尺寸的尺寸D的风扇的直径，每个风扇 具有前缘的叶片，配置成驱动风扇的齿轮架构，构造成驱动齿轮架构的涡轮部分，包括第一压缩机和第二压缩机的压缩机部分以及风扇前部的入口部分。 入口部分的长度在至少一些风扇叶片的前缘的位置与入口部分的前边缘之间具有尺寸L。 L / D的尺寸关系为约0.2至约0.45。

    THERMAL BARRIER COATING INSIDE COOLING CHANNELS
    70.
    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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