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    Multi-material turbine airfoil
    21.
    发明授权
    Multi-material turbine airfoil 有权

    公开(公告)号：US10221701B2

    公开(公告)日：2019-03-05

    申请号：US15027312

    申请日：2014-10-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gary D. Roberge

    IPC: F01D5/14 ,  F01D5/28 ,  F01D5/18 ,  F01D9/04 ,  F01D25/00 ,  F01D25/12 ,  F04D29/32 ,  B23P15/04

    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.

    BRIDGE BRACKET FOR VARIABLE-PITCH VANE SYSTEM
    22.
    发明申请
    BRIDGE BRACKET FOR VARIABLE-PITCH VANE SYSTEM 审中-公开

    公开(公告)号：US20190048892A1

    公开(公告)日：2019-02-14

    申请号：US15674646

    申请日：2017-08-11

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F04D29/56 ,  F04D29/52 ,  F04D29/54

    Abstract: A variable-pitch vane system for a gas turbine engine includes a plurality of vanes and a synchronization ring assembly operably connected to the plurality of vanes. The synchronization ring assembly includes a first synchronization ring, a second synchronization ring and a bridge bracket connecting the first synchronization ring to the second synchronization ring. The bridge bracket includes a first face sheet, a second face sheet, a honeycomb core located between the first face sheet and the second face sheet, a first attachment feature located at a first end of the bridge bracket at which the first synchronization ring is secured, and a second attachment feature located at a second end of the bridge bracket at which the second synchronization ring is secured.

    EXHAUST NOZZLE CONTROL FOR A GAS TURBINE ENGINE
    24.
    发明申请
    EXHAUST NOZZLE CONTROL FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180291837A1

    公开(公告)日：2018-10-11

    申请号：US15966041

    申请日：2018-04-30

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F02K1/08 ,  F02K1/76 ,  F02K1/58 ,  F02K1/42 ,  F02K1/00 ,  F02K1/15 ,  F02K3/02

    Abstract: An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

    MULTI-WALL DEPOSITED THIN SHEET STRUCTURE
    25.
    发明申请
    MULTI-WALL DEPOSITED THIN SHEET STRUCTURE 审中-公开

    公开(公告)号：US20180179641A1

    公开(公告)日：2018-06-28

    申请号：US15388649

    申请日：2016-12-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William J. Brindley ,  Gary D. Roberge

    IPC: C23C24/04 ,  B05D1/02

    CPC classification number: C23C24/04 ,  B05D1/02 ,  B05D1/36 ,  C23C24/08 ,  F01D5/14 ,  F01D5/18 ,  F01D5/288 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2260/202 ,  F05D2260/204

    Abstract: A method for forming a metallic structure having multiple layers includes providing a main tool having a main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing the first layer of material on the main formation surface using a cold-spray deposition technique. The method also includes positioning a secondary tool having a secondary formation surface in a portion of a first volume defined by a first surface of the first layer of material. The method also includes depositing a second layer of material on the secondary formation surface using the cold-spray deposition technique. The method also includes removing the secondary tool such that the first volume is positioned between the first layer of material and the second layer of material.

    Gas Turbine Engine Core Utilized in Both Commercial and Military Engines
    29.
    发明申请
    Gas Turbine Engine Core Utilized in Both Commercial and Military Engines 审中-公开
    燃气轮机发动机核心用于商用和军用发动机

    公开(公告)号：US20150345383A1

    公开(公告)日：2015-12-03

    申请号：US14760810

    申请日：2014-02-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gary D. Roberge ,  Richard A. Carlton ,  Eric A. Hudson

    IPC: F02C3/073 ,  F02C7/24 ,  F02K3/02 ,  F02C3/14

    CPC classification number: F02C3/073 ,  F02C3/107 ,  F02C3/14 ,  F02C7/24 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2230/52 ,  F05D2230/60 ,  Y10T29/49236

    Abstract: A method of manufacturing a military engine includes the steps of designing a commercial engine core, including a combustor, a high pressure compressor driven by a high pressure turbine, and a low pressure turbine designed to drive a low pressure compressor, and a fan through a gear reduction. A high speed fan is attached to the low pressure turbine, such that the combustor, high pressure compressor, low and high pressure turbines from an engine designed for commercial purposes is utilized for military purposes. A gas turbine engine is also disclosed.

    Abstract translation: 一种制造军用发动机的方法包括以下步骤：设计包括燃烧器，由高压汽轮机驱动的高压压缩机和设计成驱动低压压缩机的低压涡轮机的商业发动机芯，以及风扇通过 齿轮减速。 将高速风扇连接到低压涡轮机，使得用于商业目的的发动机的燃烧器，高压压缩机，低压和高压涡轮机用于军事目的。 还公开了一种燃气涡轮发动机。

    Duct mounted heat exchanger
    30.
    发明授权
    Duct mounted heat exchanger 有权

    公开(公告)号：US11650018B2

    公开(公告)日：2023-05-16

    申请号：US16784630

    申请日：2020-02-07

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F28F9/02 ,  F28F27/02 ,  F28F9/22 ,  F28F1/10

    CPC classification number: F28F9/027 ,  F28F1/10 ,  F28F9/22 ,  F28F27/02

    Abstract: A heat exchanger duct includes a wall having ends spaced along a central axis. An inlet manifold is positioned within a downstream portion of the duct at a radially outward location. An outlet manifold is positioned within an upstream portion of the duct at a radially outward location. At least one of the inlet and outlet manifolds extend at least 10 degrees around the circumference of the duct. A central manifold is disposed between the inlet and outlet manifolds, and radially inwardly of the inlet and outlet manifolds. Heat exchanger entrance elements extend radially inward from the inlet manifold to the central manifold, and heat exchanger exit elements extend radially outward from the central manifold to the outlet manifold. A gas turbine engine is also disclosed.

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