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    MODULAR SERPENTINE COOLING SYSTEMS FOR TURBINE ENGINE COMPONENTS
    21.
    发明申请
    MODULAR SERPENTINE COOLING SYSTEMS FOR TURBINE ENGINE COMPONENTS 有权
    用于涡轮发动机组件的模块式SERPENTINE冷却系统

    公开(公告)号：US20100183428A1

    公开(公告)日：2010-07-22

    申请号：US12355895

    申请日：2009-01-19

    Applicant: George Liang

    Inventor： George Liang

    IPC: F02C7/12

    CPC classification number: F01D5/187 ,  F01D25/12 ,  F05D2230/90 ,  F05D2250/12 ,  F05D2250/15 ,  F05D2250/185 ,  F05D2250/70 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/22141 ,  F23R3/002 ,  F23R3/04 ,  F23R2900/03045

    Abstract: A cooling system for use in a turbine engine component exposed to high temperatures during engine operation. The system includes a serpentine flow passage and an exhaust region. The serpentine flow passage includes a coolant supply inlet. The passage can be configured so that neighboring portions of the passage have coolant flowing in the same direction or, alternatively, in opposite directions. A number of flow disrupting structures, such as microfins and trip strips, can be located along the flow passage. The exhaust region can discharge coolant from the system at reduced exit momentum. The exiting flow can provide film cooling to the component. The cooling system can be provided in a small modular form, which can increase cooling design flexibility and can allow cooling designs tailored to the unique cooling requirements of the individual component. As a result, the modules can result in high levels of cooling effectiveness.

    Abstract translation: 用于在发动机运行期间暴露于高温的涡轮发动机部件中的冷却系统。 该系统包括蛇形流动通道和排气区域。 蛇形流动通道包括冷却剂供应入口。 通道可以被构造成使得通道的相邻部分具有沿同一方向流动的冷却剂，或者相反的方向。 可以沿流动通道设置许多流动干扰结构，例如微孔和跳闸条。 排气区域可以以减小的出口动量从系统排出冷却剂。 离开的流动可以向组件提供薄膜冷却。 冷却系统可以以小的模块化形式提供，这可以增加冷却设计的灵活性，并且可以允许根据单独部件的独特冷却要求定制冷却设计。 因此，这些模块可以产生高水平的冷却效果。

    Turbine bladed with tip cooling
    22.
    发明授权
    Turbine bladed with tip cooling 失效
    涡轮机刀片冷却

    公开(公告)号：US07713026B1

    公开(公告)日：2010-05-11

    申请号：US11715048

    申请日：2007-03-06

    Applicant: George Liang

    Inventor： George Liang

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F05D2250/15

    Abstract: A turbine blade with a blade tip cooling passage formed within the blade tip and extending from the leading edge to the trailing edge. The blade tip passage includes a plurality of fins extending from the pressure side to the suction side walls of the passage, and in which each fin includes a cooling air opening, the openings of which alternate from the pressure side to the suction side in the passage to force the cooling air to flow in a sinusoidal manner. The openings also alternate from the bottom of the passage to the top of the passage so that the cooling air flows in a spiral shape manner. Film cooling holes are positioned along the pressure side walls for some of the spaces formed between adjacent fins to provide film cooling for the blade. A leading edge cooling supply channel supplies cooling air to the blade tip passage through a metering and impingement hole in the first space of the passage located on the leading edge. The fins with the alternating pattern of openings produce both impingement cooling and vortex cooling for the blade tip.

    Abstract translation: 一种涡轮叶片，其具有叶片尖端冷却通道，其形成在叶片尖端内并且从前缘延伸到后缘。 叶片尖端通道包括从压力侧延伸到通道的吸力侧壁的多个翅片，其中每个翅片包括冷却空气开口，其中开口在通道中从压力侧到吸力侧交替 以迫使冷却空气以正弦方式流动。 开口也从通道的底部交替到通道的顶部，使得冷却空气以螺旋形状流动。 薄膜冷却孔沿着压力侧壁设置，用于形成在相邻散热片之间的一些空间，以为叶片提供薄膜冷却。 前缘冷却供应通道通过位于前缘的通道的第一空间中的计量和冲击孔向叶片尖端通道提供冷却空气。 具有交替开口图案的翅片产生叶片尖端的冲击冷却和涡流冷却。

    Housing for a centrifugal fan, pump, or turbine
    24.
    发明授权
    Housing for a centrifugal fan, pump, or turbine 有权
    离心风机，泵或涡轮机的外壳

    公开(公告)号：US07416385B2

    公开(公告)日：2008-08-26

    申请号：US11496013

    申请日：2006-07-28

    Applicant: Jayden David Harman

    Inventor： Jayden David Harman

    IPC: F01D1/02

    CPC classification number: F04D29/426 ,  F01D9/026 ,  F04D17/06 ,  F04D29/30 ,  F04D29/4226 ,  F04D29/4233 ,  F05D2250/15 ,  F05D2250/25 ,  Y10S416/02

    Abstract: A housing for a blower, fan or pump or turbine, the housing adapted to be associated with a rotor adapted in use to cooperate with fluid flowing through the housing wherein the housing comprises a shroud for guiding the fluid moving in association with the rotor, the rotor having at least one vane adapted to cooperate with the fluid to drive or to be driven by the fluid, wherein the shroud is configured to promote vortical flow of the fluid through the housing.

    Abstract translation: 一种用于鼓风机，风扇或泵或涡轮机的壳体，该壳体适于与适于在使用中与流过壳体的流体配合的转子相关联，其中壳体包括用于引导与转子一起移动的流体的护罩， 转子具有适于与流体配合以驱动或由流体驱动的至少一个叶片，其中所述护罩构造成促进流体通过所述壳体的涡旋流动。

    TURBINE HOUSING FOR HIGH EXHAUST TEMPERATURE
    26.
    发明申请
    TURBINE HOUSING FOR HIGH EXHAUST TEMPERATURE 有权
    用于高排气温度的涡轮机外壳

    公开(公告)号：US20030053910A1

    公开(公告)日：2003-03-20

    申请号：US09952766

    申请日：2001-09-14

    Inventor： Diaa M. Hosny

    IPC: F04D029/44

    CPC classification number: F02B37/025 ,  F01D9/026 ,  F05D2220/40 ,  F05D2250/15 ,  Y02T10/144

    Abstract: A turbocharger turbine housing of this invention comprises a generally circular-shaped body having an exhaust gas inlet flange at a radial housing end and an exhaust gas outlet at an axial end. The inlet flange is configured having openings to two volutes that are separated by a wall divider, thereby forming an X-shaped pattern. The inlet flange is additionally configured having rounded and uniform thickness walls. The volutes are configured having a nonuniform shape and size, and the wall divider is configured having a diminishing area between the volutes, moving through the housing away from the inlet flange. The volutes are configured having a nonuniform shape and size with respect to one another as well moving through the turbine housing. Configured in this manner, turbocharger turbine housings of this invention serve to minimize thermal stress effects caused from transient thermal loading, thereby minimizing and/or eliminating thermal stress relating damage such as cracking.

    Abstract translation: 本发明的涡轮增压器涡轮机壳体包括大致圆形的主体，其具有在径向壳体端处的排气入口凸缘和在轴向端部处的排气出口。 入口法兰被构造成具有通过壁分隔件分隔开的两个蜗壳的开口，从而形成X形图案。 入口法兰另外构造成具有圆形和均匀的厚度壁。 蜗壳被构造成具有不均匀的形状和尺寸，并且壁分隔件构造成具有在蜗壳之间减小的面积，通过壳体远离入口凸缘移动。 蜗壳构造成相对于彼此具有不均匀的形状和尺寸，并且移动通过涡轮壳体。 以这种方式配置，本发明的涡轮增压器涡轮机壳体用于最小化由瞬时热负荷引起的热应力作用，从而最小化和/或消除相关损伤（例如开裂）的热应力。

    Centrifugal blower
    28.
    发明授权
    Centrifugal blower 有权
    离心式鼓风机

    公开(公告)号：US06273679B1

    公开(公告)日：2001-08-14

    申请号：US09453169

    申请日：1999-12-02

    Applicant: Sang-Kwon Na

    Inventor： Sang-Kwon Na

    IPC: F01D102

    CPC classification number: F01D9/026 ,  F04D29/4226 ,  F05D2200/23 ,  F05D2240/14 ,  F05D2250/15 ,  F05D2250/312 ,  F05D2250/34 ,  F05D2260/96

    Abstract: A centrifugal blower comprising a siroco fan having a plurality of blowing fans, and a scroll casing forming a spiral draft passage at an external side of the siroco fan, where a siroco fan is so mounted that spiral centers (02,03) comprising the draft passage of the scroll casing are detached from a center (01) of the siroco fan at a predetermined distance, such that a spiral curve of the scroll casing is simply changed to a non-linear curve to thereby enable to increase a flow rate even at a low revolution of the siroco fan and to reduce noise.

    Abstract translation: 一种离心式鼓风机，包括具有多个吹风扇的西罗克风扇，以及在所述西洛风扇的外侧形成螺旋通风通道的涡旋壳体，其中所述西罗克风扇被安装成使得螺旋中心（02,03）包括所述牵伸 涡旋壳体的通道以预定距离从硅酮风扇的中心（01）分离，使得涡旋壳体的螺旋曲线简单地变为非线性曲线，从而能够增加即使在 西洛酮风扇的低转速并降低噪音。

    Method and apparatus for cooling an airfoil
    29.
    发明授权
    Method and apparatus for cooling an airfoil 有权
    用于冷却机翼的方法和装置

    公开(公告)号：US06247896B1

    公开(公告)日：2001-06-19

    申请号：US09338376

    申请日：1999-06-23

    Applicant: Thomas A. Auxier ,  James P. Downs ,  William S. Kvasnak ,  Friedrich O. Soechting ,  William H. Calhoun ,  Douglas A. Hayes

    Inventor： Thomas A. Auxier ,  James P. Downs ,  William S. Kvasnak ,  Friedrich O. Soechting ,  William H. Calhoun ,  Douglas A. Hayes

    IPC: F01D518

    CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2230/14 ,  F05D2250/15 ,  F05D2250/70 ,  F05D2260/2214

    Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

    Abstract translation: 提供了一种用于冷却燃气涡轮发动机内的壁的方法和装置，其包括以下步骤：（1）提供具有内表面和外表面的壁; （2）在所述壁内提供具有在所述内表面和所述外表面之间延伸的用于冷却空气的通道的所述壁内的冷却微电路; 和（3）通过增加微电路内的每单位流动的平均热传递系数来增加从通道内的壁到流体流的传热。 根据一个方面，本发明的方法和装置可以被调整以使手上的壁的热分布基本匹配。

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