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    TURBINE ENGINE, COMPONENTS, AND METHODS OF COOLING SAME
    1.
    发明申请
    TURBINE ENGINE, COMPONENTS, AND METHODS OF COOLING SAME 审中-公开
    涡轮发动机，组件和冷却方法

    公开(公告)号：WO2016032585A3

    公开(公告)日：2016-03-03

    申请号：PCT/US2015/032855

    申请日：2015-05-28

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： MANNING, Robert, Francis ,  STONE, Timothy, Deryck ,  BUHLER, Jared, Peter ,  CORRELA, Victor Hugo, Silva ,  LASKOWSKI, Gregory, Michael ,  MURRAY, Robert, Carl ,  PROCTOR, Robert ,  RATZLAFF, Jonathan, Russell ,  STARKWEATHER, John, Howard ,  STOVER, Curtis, Walton

    IPC: F02C7/05 ,  F02C7/052 ,  B01D45/16 ,  B04C3/00 ,  B04C3/06

    Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced- particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.

    Abstract translation: 用于从流体流中除去颗粒的离心分离器包括构造成增加流体流的角速度的角速度增加器，构造成分离流体流以形成浓缩颗粒流的分流器 和减少的颗粒流，以及构造成接收减少的颗粒流的出口导管。 用于涡轮发动机的诱导器组件包括具有流道的诱导器，所述诱导器具有与发动机的涡轮段流体连通的诱导器入口和诱导器出口以及包括颗粒分离器的颗粒分离器，所述颗粒分离器接收来自 发动机的压缩机部分和分流器。 涡轮发动机包括冷却空气流动回路，该冷却空气流动回路将流体流供应到发动机的涡轮部分以用于冷却，位于冷却空气流动回路内的颗粒分离器以及形成流体连通的冷却空气流动回路的一部分的诱导器 与粒子分离器。 一种冷却具有诱导轮的涡轮发动机的旋转叶片的方法包括：引导来自涡轮发动机的一部分的冷却流体流朝向旋转叶片，通过使冷却流体流经过惯性分离器而从冷却流体流中分离出粒子， 从惯性分离器释放的减少的颗粒流到旋转叶片的速度，并且通过将来自惯性分离器的减少的颗粒流释放到诱导器中的冷却通道中来定向减少的颗粒流。

    MODULATED TURBINE COOLING SYSTEM
    2.
    发明申请
    MODULATED TURBINE COOLING SYSTEM 审中-公开

    公开(公告)号：WO2014197089A3

    公开(公告)日：2014-12-11

    申请号：PCT/US2014/028673

    申请日：2014-03-14

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： RAHAIM, John, Joseph ,  FUSINATO, Daniel, John ,  HUNTER, Scott, David ,  KIRK, Joel, Francis ,  MELZAK, Michael, Robert ,  STOVER, Curtis, Walton

    IPC: F01D5/08 ,  F02C7/12

    Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath (P) to a turbine rotor (128). The apparatus includes: a first supply plenum (92) communicating with the primary gas flowpath (P) and first inducers (148 A), the first inducers (148 A) configured to accelerate a first fluid flow from the first supply plenum (92) and discharge it toward the rotor with a tangential velocity; a second supply plenum (96) communicating with the primary gas flowpath (P) and second inducers (148B), the second inducers (148B) configured to accelerate a second fluid flow from the second supply plenum (96) towards the rotor with a tangential velocity; and a cooling modulation valve (98) operable to selectively permit or block the second fluid flow from the primary gas flowpath (P) to the second supply plenum (96). The valve includes a flow control structure (108, 110) disposed in the primary gas flowpath (P) and an actuation structure extending to a location radially outside of a casing (76) defining the primary gas flowpath (P).

    ENGINE COMPONENTS WITH COOLING FEATURES
    4.
    发明申请
    ENGINE COMPONENTS WITH COOLING FEATURES 审中-公开
    发动机组件与冷却功能

    公开(公告)号：WO2016025054A2

    公开(公告)日：2016-02-18

    申请号：PCT/US2015/032597

    申请日：2015-05-27

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： STOVER, Curtis, Walton ,  RAUSCH, Jonathan, Michael ,  ATSUCHI, Satoshi ,  BRAINCH, Gulcharan, Singh ,  BRIGGS, Robert, David ,  BUNKER, Ronald, Scott ,  KULKARNI, Ambarish, Jayant ,  MEADE, Michael, Alan ,  PRITCHARD, Byron, Andrew ,  PROCTOR, Robert

    CPC classification number: F02C7/18 ,  F01D5/189 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2240/81 ,  F05D2250/38 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2260/607 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/673 ,  Y02T50/676

    Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides an array of cooling holes or apertures which are facing the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and are directed at an oblique angle or a non-orthogonal angle to the surface of the insert and further may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling. The engine component comprises an engine component cooling surface having a cooling fluid flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The array of openings create counterflows in substantially opposite directions along the engine component cooling surface.

    Abstract translation: 提供燃气涡轮发动机部件，其利用插入件沿发动机部件的冷却表面提供冷却空气。 插入件提供了一组面向发动机部件的冷却侧表面的冷却孔或孔，并将冷却空气直接冷却到该冷却侧表面上。 孔可以形成为阵列并且以与插入件的表面成倾斜的角度或非正交的角度定向，并且还可以与被冷却的发动机部件的表面成一角度。 发动机部件组件设有逆流冲击冷却。 发动机部件包括在其一侧具有冷却流体流动路径的发动机部件冷却表面和与第一部件相邻的第二部件。 第二部件，例如插入件，可以具有形成阵列的多个开口，其中开口以与第二部件的表面成非正交角延伸穿过第二部件。 开口阵列沿着发动机部件冷却表面沿基本上相反的方向产生逆流。

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