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    Vortex-Injector Casing for an Axial Turbomachine Compressor
    145.
    发明申请
    Vortex-Injector Casing for an Axial Turbomachine Compressor 审中-公开
    用于轴流涡轮机压缩机的涡流喷射器套管

    公开(公告)号：US20170058687A1

    公开(公告)日：2017-03-02

    申请号：US15184692

    申请日：2016-06-16

    Applicant: TECHSPACE AERO S.A.

    Inventor： STÉPHANE HIERNAUX

    IPC: F01D11/04 ,  F01D11/14 ,  F01D11/10

    CPC classification number: F01D11/04 ,  F01D11/10 ,  F01D11/14 ,  F04D27/0215 ,  F04D27/0238 ,  F04D29/526 ,  F04D29/685 ,  F05D2220/32 ,  F05D2240/55

    Abstract: The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.

    Abstract translation: 本申请提出了一种轴向涡轮机压缩机，其包括具有至少一个环形排的转子叶片的转子，围绕该行转子叶片的定子壳体，壳体包括用于产生反涡流的装置。 在压缩机运行期间，叶片的运动在叶片尖端产生泄漏涡流。 发电装置又将与涡流相反的方向旋转的反涡流喷射以抵消泄漏涡流。 这提高了压缩机的浪涌裕度。 本申请还提供了一种通过反涡流喷射来控制涡轮机压缩机的稳定性的方法。

    Gas turbine thermal control and related method
    147.
    发明授权
    Gas turbine thermal control and related method 有权
    燃气轮机热控及相关方法

    公开(公告)号：US09422824B2

    公开(公告)日：2016-08-23

    申请号：US13654689

    申请日：2012-10-18

    Applicant: General Electric Company

    Inventor： Matthew Stephen Casavant ,  Kenneth Damon Black ,  David Martin Johnson ,  Radu Ioan Danescu

    IPC: F01D11/24 ,  F01D11/16 ,  F01D11/02 ,  F01D11/18 ,  F01D11/20 ,  F01D11/14

    CPC classification number: F01D11/24 ,  F01D11/025 ,  F01D11/14 ,  F01D11/16 ,  F01D11/18 ,  F01D11/20 ,  F01D25/14 ,  F01D25/26 ,  F02C7/12

    Abstract: Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.

    Abstract translation: 通过从压缩机供给热控制气体到外壳和内壳之间的空间，为燃气轮机壳体提供热控制，并且通过多个孔将热控制气体从空间传递通过内壳体中的开口 通过附接到内壳的外表面的板限定。 孔以预定的不均匀分布布置，其对应于期望的优先冲击图案以提供不均匀的热传递。 燃气轮机热控制组件包括在燃气轮机运行期间通过从内壳的径向外侧到燃气轮机内部的热控制气体流动路径，从内壳提供优先传热的结构。

    Turbomachine clearance control configuration using a shape memory alloy or a bimetal
    148.
    发明授权
    Turbomachine clearance control configuration using a shape memory alloy or a bimetal 有权
    涡轮机间隙控制配置使用形状记忆合金或双金属

    公开(公告)号：US09169741B2

    公开(公告)日：2015-10-27

    申请号：US13479315

    申请日：2012-05-24

    Applicant: Jaroslaw Leszek Szwedowicz ,  Alexey Mozharov ,  Stefan Irmisch

    Inventor： Jaroslaw Leszek Szwedowicz ,  Alexey Mozharov ,  Stefan Irmisch

    IPC: F01D11/14 ,  F01D11/18 ,  F01D11/24

    CPC classification number: F01D11/18 ,  F01D11/24 ,  F05D2300/505

    Abstract: A turbomachine which operates at enhanced operating temperatures includes a stationary component. A rotating component includes a clearance to avoid a rubbing contact between the stationary component and the rotating component, the clearance including a first value in a stationary state of the turbomachine and a second value in a steady-state operation of the machine, wherein during a transient operating phase between the stationary state and the steady-state operation, the clearance includes a value which traverses a curve having an extreme value on account of a different time variation of a rotational speed and a thermal expansion of different components. A compensating device includes a non-linear compensation mechanism configured to reduce or compensate the extreme value during the transient operating phase.

    Abstract translation: 在增强的工作温度下操作的涡轮机包括固定部件。 旋转部件包括间隙，以避免固定部件和旋转部件之间的摩擦接触，间隙包括在涡轮机的静止状态下的第一值和机器的稳态操作中的第二值，其中在 在静止状态和稳态操作之间的瞬时动作相位，间隙包括由于不同部件的转速和热膨胀的不同时间变化而横过具有极值的曲线的值。 补偿装置包括被配置为在过渡操作阶段期间减少或补偿极值的非线性补偿机构。

    Method and apparatus for obtaining discrete axial clearance data using radial clearance sensors
    149.
    发明授权
    Method and apparatus for obtaining discrete axial clearance data using radial clearance sensors 有权
    使用径向间隙传感器获得离散轴向间隙数据的方法和装置

    公开(公告)号：US09037434B2

    公开(公告)日：2015-05-19

    申请号：US13342473

    申请日：2012-01-03

    Applicant: Fred Thomas Willett, Jr. ,  Emad Andarawis Andarawis

    Inventor： Fred Thomas Willett, Jr. ,  Emad Andarawis Andarawis

    IPC: G01B7/00 ,  G01B7/14 ,  F01D11/14 ,  F01D17/02 ,  F01D21/00 ,  F01D11/08 ,  F01D21/04 ,  G06F19/00 ,  F04D29/66

    CPC classification number: G01B7/14 ,  F01D11/08 ,  F01D11/14 ,  F01D17/02 ,  F01D21/003 ,  F01D21/04 ,  F04D29/66 ,  F05D2220/31 ,  G06F19/00

    Abstract: A method and apparatus for determining axial clearance data between a rotor and a stator are disclosed. At least one radial clearance sensor is positioned on the stator and is configured to gather radial clearance data, i.e., measurements of a radial distance between the rotor and the stator taken at discrete time intervals. A computing device is operably connected with the at least one radial clearance sensor and is configured to use the radial clearance data to determine axial clearance data, i.e., an axial distance between the stator and the rotor. In one embodiment, the computing device uses, among other data points, an indication of a loss of signal from at least one radial clearance sensor to extrapolate the axial clearance data.

    Abstract translation: 公开了一种用于确定转子和定子之间的轴向间隙数据的方法和装置。 至少一个径向间隙传感器定位在定子上并且被配置成收集径向间隙数据，即以离散时间间隔采集的转子和定子之间的径向距离的测量。 计算装置与所述至少一个径向间隙传感器可操作地连接，并且被配置为使用所述径向间隙数据来确定轴向间隙数据，即所述定子和所述转子之间的轴向距离。 在一个实施例中，计算设备除了其他数据点之外还使用来自至少一个径向间隙传感器的信号损失的指示来推断轴向间隙数据。

    Impingement cooling arrangement for a gas turbine engine
    150.
    发明授权
    Impingement cooling arrangement for a gas turbine engine 有权
    用于燃气涡轮发动机的冲击冷却装置

    公开(公告)号：US08414255B2

    公开(公告)日：2013-04-09

    申请号：US12708207

    申请日：2010-02-18

    Applicant: Peter T Ireland ,  Gareth Newcombe ,  Andrew J Mullender

    Inventor： Peter T Ireland ,  Gareth Newcombe ,  Andrew J Mullender

    IPC: F01D25/14 ,  F01D11/14

    CPC classification number: F01D5/186 ,  F01D5/187

    Abstract: There is disclosed an impingement cooling arrangement for a gas turbine engine (6), and an engine provided with such an arrangement. The cooling arrangement comprises at least part of a casing (21) configured to define a flowpath for the passage of hot gases through the engine, and a manifold (22) configured to direct cooling air against an outer surface (23) of the casing for impingement cooling thereof. The arrangement is characterized by said manifold (22) being configured to direct a primary flow of cooling air (65) against a first area (64) of the casing outer surface (23) for impingement cooling of said first area, and to recirculate (66) at least a portion of said primary flow of cooling air after impingement against said first area (64) and to direct at least a portion of the recirculated flow against a second area (67) of the casing outer surface (23) for impingement cooling of said second area (67). In a preferred arrangement, the manifold (22) is spaced from said casing (21) so as to define a space (41) between the manifold and the outer surface (23) of the casing, and the manifold (22) further comprises a baffle (46) extending at least partially across said space, substantially towards said casing (21), so as to at least partially divide said space (41) into a first region (58) adjacent said first area (64), and a second region (59) adjacent said second area (67).

    Abstract translation: 公开了一种用于燃气涡轮发动机（6）的冲击冷却装置和具有这种装置的发动机。 冷却装置包括构造成限定用于使热气体通过发动机的流路的壳体（21）的至少一部分，以及构造成将冷却空气引导到壳体的外表面（23）的歧管（22），用于 冲击冷却。 该装置的特征在于，所述歧管（22）构造成将冷却空气（65）的主流引导到壳体外表面（23）的第一区域（64）上，用于冲击冷却所述第一区域，并使 66）在冲击所述第一区域（64）之后的所述主要冷却空气流的至少一部分并且将所述再循环流的至少一部分引导到所述壳体外表面（23）的用于冲击的第二区域（67） 所述第二区域（67）的冷却。 在优选的布置中，歧管（22）与所述壳体（21）间隔开，以便在歧管和壳体的外表面（23）之间限定一个空间（41），而歧管（22）还包括一个 挡板（46）至少部分地延伸穿过所述空间，基本上朝向所述壳体（21）延伸，以便至少部分地将所述空间（41）分隔成与所述第一区域（64）相邻的第一区域（58），并且第二 邻近所述第二区域（67）的区域（59）。

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