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    CONVERGENT DIVERGENT EXIT NOZZLE FOR A GAS TURBINE ENGINE
    12.
    发明申请
    CONVERGENT DIVERGENT EXIT NOZZLE FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的变流器出口喷嘴

    公开(公告)号：US20160195038A1

    公开(公告)日：2016-07-07

    申请号：US14817611

    申请日：2015-08-04

    Applicant: United Technologies Corporation

    Inventor： Dmitriy B. Sidelkovskiy ,  Oleg Petrenko ,  Robert E. Malecki ,  Steven H. Zysman

    IPC: F02K1/78 ,  F02C3/04 ,  F02K3/06

    CPC classification number: F02K1/78 ,  B64D29/00 ,  B64D29/02 ,  B64D29/04 ,  F02C3/04 ,  F02K1/00 ,  F02K1/36 ,  F02K1/40 ,  F02K1/52 ,  F02K1/82 ,  F02K3/06 ,  F02K3/077

    Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.

    Abstract translation: 用于燃气涡轮发动机的机舱包括限定中心轴线并具有径向向外表面和径向向内表面的环形主体。 径向向内表面的后部包括轴向延伸的收敛发散出口。 轴向延伸的二次管道穿过会聚发散出口喷嘴中的机舱。 轴向延伸的次级管道包括在收敛发散出口喷嘴的收敛部分处的入口和在会聚发散出口喷嘴的发散部分处的出口。

    Method for separated flow detection
    15.
    发明授权
    Method for separated flow detection 有权

    公开(公告)号：US11027827B2

    公开(公告)日：2021-06-08

    申请号：US16121517

    申请日：2018-09-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Dmitriy B. Sidelkovskiy

    IPC: B64C21/06 ,  B64D29/00 ,  B64D33/02 ,  F01D17/08 ,  F02C7/057

    Abstract: A method to predict an onset of flow separation from a surface of an inner barrel of a nacelle is disclosed. In various embodiments, the method includes determining a static pressure distribution about the inner barrel surface of the nacelle; determining a mean static pressure value and a minimum static pressure value using the static pressure distribution; determining a separation indicator value using the mean static pressure value and the minimum static pressure value; and comparing the separation indicator value against a separation threshold value.

    AFTER-FAN SYSTEM FOR A GAS TURBINE ENGINE
    16.
    发明申请
    AFTER-FAN SYSTEM FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20200325852A1

    公开(公告)日：2020-10-15

    申请号：US16837143

    申请日：2020-04-01

    Applicant: United Technologies Corporation

    Inventor： Dmitriy B. Sidelkovskiy ,  Pitchaiah Vijay Chakka ,  Michael Winter ,  Daniel Bernard Kupratis

    IPC: F02K3/06 ,  F04D29/32

    Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.

    Nacelle
    17.
    发明授权
    Nacelle 有权

    公开(公告)号：US10767596B2

    公开(公告)日：2020-09-08

    申请号：US15660656

    申请日：2017-07-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Dmitriy B. Sidelkovskiy ,  Steven H. Zysman

    IPC: F02K1/72 ,  B64D27/16 ,  F02K3/06 ,  F02K1/80 ,  B64D29/00 ,  B64D29/06 ,  B64D33/02 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04

    Abstract: A nacelle may comprise an inlet cowling defining an inlet of the nacelle, wherein the inlet cowling comprises an inlet cowling maximum point and an inlet cowling aft edge, wherein the inlet cowling aft edge comprises an aft edge length; and a boat tail cowling disposed aft of the inlet cowling, wherein the boat tail cowling comprises a boat tail cowling forward edge having a forward edge length, and wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be smaller than the aft edge length, forming a step, the step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge.

    TRACK FAIRING ASSEMBLY FOR A TURBINE ENGINE NACELLE
    19.
    发明申请
    TRACK FAIRING ASSEMBLY FOR A TURBINE ENGINE NACELLE 审中-公开
    用于涡轮发动机抽油烟机的履带组件

    公开(公告)号：US20160237856A1

    公开(公告)日：2016-08-18

    申请号：US14621456

    申请日：2015-02-13

    Applicant: United Technologies Corporation

    Inventor： Dmitriy B. Sidelkovskiy ,  Steven H. Zysman ,  Robert E. Malecki

    IPC: F01D25/28 ,  F01D25/24

    CPC classification number: F01D25/28 ,  B64D29/00 ,  B64D29/06 ,  F01D25/24 ,  F02C7/20 ,  F02K1/52 ,  F02K1/72 ,  F05D2240/55

    Abstract: The present disclosure relates generally to an aerodynamic track fairing assembly used on an engine nacelle, the track fairing assembly positionable on the aft section of the engine nacelle, the aerodynamic track fairing assembly including an upper section extending toward an aft end of the aft section of the engine nacelle, a bottom section extending toward the aft end of the aft section of the engine nacelle, the bottom section affixed to the upper section to form a track cavity therebetween, and a fairing fitting disposed within the track cavity and affixed to the bottom section.

    Abstract translation: 本公开总体上涉及在发动机舱上使用的空气动力学轨道整流罩组件，轨道整流罩组件可定位在发动机舱的后部，气动履带整流罩组件包括朝向后部的后部的后端延伸的上部 所述发动机舱，朝向所述发动机舱的后部的后端延伸的底部，所述底部固定到所述上部以在其间形成轨道腔;以及整流罩，其布置在所述轨道腔内并固定到所述底部 部分。

    Gas Turbine Engine Assembly Including A Thrust Reverser
    20.
    发明申请
    Gas Turbine Engine Assembly Including A Thrust Reverser 审中-公开
    包括推力逆变器的燃气轮机发动机组件

    公开(公告)号：US20140216005A1

    公开(公告)日：2014-08-07

    申请号：US13630234

    申请日：2012-09-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Dmitriy B. Sidelkovskiy ,  Robert E. Malecki ,  Oleg Petrenko

    IPC: F02K1/72

    CPC classification number: F02K1/72 ,  F02K3/06 ,  F05D2220/323

    Abstract: An exemplary gas turbine engine assembly includes a thrust reverser that is selectively moveable between a stowed position and a thrust reversing position. The thrust reverser includes an outer surface having a first outer surface area when the thrust reverser is in the stowed position and a second, smaller outer surface area when the thrust reverser is in the thrust reversing position.

    Abstract translation: 示例性的燃气涡轮发动机组件包括可在收起位置和推力反向位置之间选择性地移动的推力反向器。 推力反向器包括当推力反向器处于收起位置时具有第一外表面区域的外表面和当推力反向器处于推力反向位置时的第二较小的外表面区域。

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