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    TURBOFAN THRUST REVERSER SYSTEM
    71.
    发明申请
    TURBOFAN THRUST REVERSER SYSTEM 审中-公开
    TURBOFAN THRUST REVERSER系统

    公开(公告)号：US20150337762A1

    公开(公告)日：2015-11-26

    申请号：US14284893

    申请日：2014-05-22

    Applicant: United Technologies Corporation

    Inventor： Allan R. Penda ,  Gabriel L. Suciu ,  William G. Sheridan ,  Wesley K. Lord

    IPC: F02K1/70 ,  F16H3/70 ,  F02C7/36

    CPC classification number: F02K1/70 ,  F02C3/10 ,  F02C3/113 ,  F02C3/145 ,  F02C6/04 ,  F02C7/36 ,  F02K1/32 ,  F02K3/075 ,  F05D2260/40311 ,  F16H3/60 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a core engine, a fan, a bypass duct and a clutch. The fan is driven by the core engine. The bypass duct is configured to receive airflow from the fan. The clutch links the core engine and the fan. The core comprises a reverse-flow, two-spool gas generator in one embodiment. In another embodiment, the fan is driven by a free turbine aerodynamically powered by the core engine. In one embodiment, the clutch includes reverse gearing to reverse rotational output of the fan. In one embodiment, the clutch and reverse gearing are implemented in an epicyclic gear system.

    Abstract translation: 燃气涡轮发动机包括核心发动机，风扇，旁通管道和离合器。 风扇由核心发动机驱动。 旁路管道被配置为从风扇接收气流。 离合器连接核心发动机和风扇。 核心包括在一个实施例中的逆流双阀气体发生器。 在另一个实施例中，风扇由空气动力学地由核心发动机驱动的自由涡轮机驱动。 在一个实施例中，离合器包括倒档以反转风扇的旋转输出。 在一个实施例中，离合器和倒档传动装置实现在行星齿轮系统中。

    Two Spool Gas Generator with Improved Air Porting
    72.
    发明申请
    Two Spool Gas Generator with Improved Air Porting 审中-公开
    具有改进空气流通的两个轴流气发生器

    公开(公告)号：US20150337738A1

    公开(公告)日：2015-11-26

    申请号：US14758277

    申请日：2013-05-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord

    IPC: F02C9/18 ,  F02K3/02 ,  F02C7/12

    CPC classification number: F02C7/12 ,  F02C3/13 ,  F02C3/145 ,  F02C6/04 ,  F02C6/08 ,  F02C9/18 ,  F02K3/00 ,  F02K3/02 ,  F05D2220/3217 ,  F05D2220/3218

    Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.

    Abstract translation: 在特征实施例中，燃气涡轮发动机具有由第一涡轮转子驱动的第一压缩机转子和由第二涡轮转子驱动的第二压缩机转子。 第二压缩机转子在第一压缩机转子的上游，第一涡轮转子位于第二涡轮转子的上游。 空气混合系统从第一压缩机转子的上游位置抽出空气，用于输送到环境控制系统。 空气混合系统从第一空气源和第二空气源接收空气。 第一空气源包括在第一压缩机转子的上游的第一压力下的空气。 第二空气源包括较低的第二压力的空气。 至少一个阀控制来自第一和第二源的空气的混合物以实现环境控制系统的预定压力。

    PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL
    73.
    发明申请
    PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL 审中-公开
    用于空气入口空气流量控制的被动边界层系统

    公开(公告)号：US20140321970A1

    公开(公告)日：2014-10-30

    申请号：US14325583

    申请日：2014-07-08

    Applicant: United Technologies Corporation

    Inventor： Steven H. Zysman ,  Wesley K. Lord ,  Robert M. Miller ,  Oliver V. Atassi

    IPC: F02C9/18

    CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0226 ,  F02C7/045 ,  F05D2250/324 ,  F05D2250/71 ,  F05D2270/17 ,  Y10T137/0536

    Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.

    Abstract translation: 用于燃气涡轮发动机系统的机舱包括具有压力侧和吸力侧的壳体。 通道在压力侧和吸力侧之间延伸，以允许从压力侧到吸力侧的气流。 通道包括在压力侧具有入口的第一弯曲部分。 线性部分与第一弯曲部分连接。 第二弯曲部分与线性部分连接并且在吸力侧具有出口。 出口的横截面积小于线性部分的横截面面积。

    Low pressure ratio fan engine having a dimensional relationship between inlet and fan size
    74.
    发明授权
    Low pressure ratio fan engine having a dimensional relationship between inlet and fan size 有权

    公开(公告)号：US11286811B2

    公开(公告)日：2022-03-29

    申请号：US16391476

    申请日：2019-04-23

    Applicant: United Technologies Corporation

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

    IPC: F01D25/24 ,  F02K3/06 ,  F01D5/14 ,  F02C7/04 ,  F01D5/02 ,  F01D15/12 ,  F01D17/10

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the 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, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.

    Gas turbine engine with low fan noise
    77.
    发明授权
    Gas turbine engine with low fan noise 有权

    公开(公告)号：US10526914B2

    公开(公告)日：2020-01-07

    申请号：US14761689

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Bruce L. Morin ,  Wesley K. Lord

    IPC: F01D25/04 ,  F01D5/02 ,  F01D5/14 ,  F01D9/02 ,  F02K1/15 ,  F02K1/16 ,  F01D17/14

    Abstract: In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle βADP, and may be further configured to have an off-design point fan tip leading edge relative flow angle β at an off-design fan operating point. The variable area fan nozzle may be configured to manipulate the amount of air flowing through the fan so that the absolute value of a difference between the design point fan tip leading edge relative flow angle βADP and the off-design point fan tip leading edge relative flow angle β is in a specified range.

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