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    MULTI-MATERIAL TURBINE AIRFOIL
    92.
    发明申请
    MULTI-MATERIAL TURBINE AIRFOIL 审中-公开
    多材料涡轮机空气

    公开(公告)号：US20160245098A1

    公开(公告)日：2016-08-25

    申请号：US15027312

    申请日：2015-07-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gary D. Roberge

    IPC: F01D5/28 ,  F01D25/12 ,  F04D29/32 ,  F01D5/18 ,  F01D9/04 ,  F01D25/00

    CPC classification number: F01D5/282 ,  B23P15/04 ,  F01D5/147 ,  F01D5/18 ,  F01D5/284 ,  F01D9/041 ,  F01D25/005 ,  F01D25/12 ,  F04D29/321 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2260/36 ,  F05D2300/5023 ,  F05D2300/522 ,  Y02T50/672

    Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100F higher than that of the second material. A gas turbine engine is also disclosed.

    Abstract translation: 涡轮机部件包括平台和从平台径向延伸并从前缘延伸到后缘的翼型件。 前缘部分限定翼型件的前缘和包括后缘的后缘部分。 前缘部分和后缘部分之一也包括平台。 前缘部分由不同于形成后缘部分的第二材料的第一材料形成。 第一材料具有比第二材料高至少100°F的工作温度能力。 还公开了一种燃气涡轮发动机。

    FLOW PATH ROUTING WITHIN A GAS TURBINE ENGINE
    93.
    发明申请
    FLOW PATH ROUTING WITHIN A GAS TURBINE ENGINE 审中-公开
    在气体涡轮发动机中的流路径路由

    公开(公告)号：US20150345425A1

    公开(公告)日：2015-12-03

    申请号：US14489777

    申请日：2014-09-18

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F02K3/02 ,  F02C7/18

    CPC classification number: F02K1/386 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105 ,  F05D2240/122 ,  F05D2240/129

    Abstract: An example gas turbine engine with multiple flow paths includes, among other things, a core flow path extending from a compressor section to an exhaust section, a bypass duct providing a bypass flow path radially outside the core flow path, and a flow injection device to selectively communicate a first amount of flow or a second amount of flow from the bypass flow path to the exhaust section, the first amount of flow different than the second amount of flow.

    Abstract translation: 具有多个流动路径的示例性燃气涡轮发动机尤其包括从压缩机部分延伸到排气部分的核心流动路径，在核心流动路径的径向外侧提供旁路流动路径的旁路管道，以及流动注射装置 选择性地将来自旁路流动路径的第一流量或第二量的流量传送到排气部分，第一流量不同于第二流量。

    Integrated Heat Exchangers for Low Fan Pressure Ratio Feared Turbofan
    94.
    发明申请
    Integrated Heat Exchangers for Low Fan Pressure Ratio Feared Turbofan 有权
    低风扇压力比的集成热交换器有效的涡轮风扇

    公开(公告)号：US20150285186A1

    公开(公告)日：2015-10-08

    申请号：US14646990

    申请日：2013-11-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gary D. Roberge

    IPC: F02K3/115 ,  F02C7/18

    CPC classification number: F02K3/115 ,  F01D9/065 ,  F02C7/06 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F02K3/105 ,  F05D2210/12 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2250/182 ,  F05D2250/60 ,  F05D2260/20 ,  F05D2260/213 ,  F05D2260/4031 ,  F05D2260/98 ,  Y02T50/676

    Abstract: An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.

    Abstract translation: 提供了一种用于在旁路配置的燃气涡轮发动机内的润滑的机械系统的油冷却系统和方法。 表面冷却器与润滑的机械系统流体连接，以从润滑的机械系统接收油，用于冷却和再利用。 在一个实施例中，表面冷却器安装在旁路构造的燃气涡轮发动机的旁路气流路径内的现有表面上，以提供有效的冷却，同时避免在旁路路径中引入额外的空气动力学干扰。 在一个实施例中，表面冷却器安装在风扇壳体或风扇出口导叶上。

    Gas turbine engine systems and related methods involving multiple gas turbine cores
    95.
    发明授权
    Gas turbine engine systems and related methods involving multiple gas turbine cores 有权
    燃气轮机发动机系统及涉及多个燃气轮机的相关方法

    公开(公告)号：US08726633B2

    公开(公告)日：2014-05-20

    申请号：US13680857

    申请日：2012-11-19

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F02K3/02

    CPC classification number: F02C9/00 ,  F02C3/113 ,  F02K3/06 ,  F02K3/12 ,  F05D2220/76 ,  F05D2240/40 ,  F05D2260/74

    Abstract: Gas turbine engine systems and related methods involving multiple gas turbine cores are provided. In this regard, a representative gas turbine engine includes: an inlet; a blade assembly mounted to receive intake air via the inlet; and multiple gas turbine cores located downstream of the blade assembly, each of the multiple gas turbine cores being independently operative in a first state, in which rotational energy is provided to rotate the blade assembly, and a second state, in which rotational energy is not provided to rotate the blade assembly.

    Abstract translation: 提供了涉及多个燃气涡轮机磁芯的燃气涡轮发动机系统和相关方法。 在这方面，代表性的燃气涡轮发动机包括：入口; 安装成经由所述入口接收进气的叶片组件; 以及位于叶片组件下游的多个燃气涡轮机芯，多个燃气涡轮机芯中的每一个独立地在第一状态下工作，其中提供旋转能量以旋转叶片组件，以及第二状态，其中转动能不是 被提供以旋转叶片组件。

    Gas turbine engine geared architecture
    99.
    发明授权
    Gas turbine engine geared architecture 有权

    公开(公告)号：US11286863B2

    公开(公告)日：2022-03-29

    申请号：US16178959

    申请日：2018-11-02

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F02C7/36 ,  F02C3/073

    Abstract: A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan. A method of adjusting rotational speeds within a gas turbine engine is also disclosed.

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