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    Optimized blade tip clearance process for a rub tolerant design
    92.
    发明授权
    Optimized blade tip clearance process for a rub tolerant design 有权
    优化刀片间隙过程，实现耐磨设计

    公开(公告)号：US07658588B1

    公开(公告)日：2010-02-09

    申请号：US11698382

    申请日：2007-01-26

    Applicant: Cheryl A. Schopf ,  Jack W. Wilson, Jr.

    Inventor： Cheryl A. Schopf ,  Jack W. Wilson, Jr.

    IPC: F01D11/08

    CPC classification number: F01D21/003 ,  F01D11/08 ,  F01D11/14 ,  F05D2230/50 ,  F05D2240/11 ,  F05D2260/80

    Abstract: A process for optimizing a blade tip clearance for a rub tolerate design in a gas turbine engine that includes evaluating a selection of candidate materials for galling and heat generation, selecting a subset of the candidate materials and analyze engine transient tip clearance for the subset materials, verifying the optimum material cooling and heat shielding for tip clearance and structures, and analyze and select an engine break-in procedure for the optimum tip clearance between turbine and compressor. If one of the subset materials results in a poor performance, than another material from the candidate materials is selected and reanalyzed until the best materials have been found. When the best materials are found, then a finite element method of analysis is performed from the blade and the static parts that form the tip clearance is performed to evaluate the materials for damage. If required, the blade and tip squealer configuration is altered to reduce stress, or blade tip coating is used. If a micro-crack in the static part will propagate, then the configuration of the hooks, scallops and the part thickness is reconfigured to reduce stress. Then, a #D analysis is performed for out-of-roundness, centerline bending and rotor sag. The design configuration and manufacturing is reiterated in order to optimize out-of-roundness.

    Abstract translation: 一种用于优化用于燃气涡轮发动机中的耐磨设计的叶片顶端间隙的方法，其包括评估用于磨损和产生热量的候选材料的选择，选择所述候选材料的子集并分析所述子集材料的发动机瞬态尖端间隙， 验证顶端间隙和结构的最佳材料冷却和热屏蔽，并分析和选择用于涡轮机和压缩机之间的最佳顶端间隙的发动机启动程序。 如果子集中的一个材料导致性能不佳，则选择和重新分析来自候选材料的另一种材料，直到找到最佳材料。 当找到最好的材料时，从叶片进行有限元分析方法，并执行形成顶端间隙的静态部件，以评估材料的损坏。 如果需要，刀片和尖端尖叫机配置被改变以减少应力，或者使用刀尖涂层。 如果静态部分的微裂纹会传播，则重新配置钩，扇贝和部件厚度的配置以减轻应力。 然后，对于不圆度，中心线弯曲和转子下垂进行#D分析。 重申设计配置和制造，以优化不圆度。

    Determination of the Gap Size of a Radial Gap
    93.
    发明申请
    Determination of the Gap Size of a Radial Gap 失效
    确定径向间隙的间隙尺寸

    公开(公告)号：US20080255799A1

    公开(公告)日：2008-10-16

    申请号：US11632333

    申请日：2005-07-04

    Applicant: Uwe Pfeifer ,  Michael Zidorn

    Inventor： Uwe Pfeifer ,  Michael Zidorn

    IPC: G01B11/14

    CPC classification number: G01S13/58 ,  F01D11/14 ,  F05D2220/32 ,  F05D2260/80 ,  F05D2270/309 ,  G01B15/00 ,  G01B17/00 ,  G01S15/58

    Abstract: The invention relates to a method for determining the size of a radial gap between rotating and torsion-proof parts, particularly the parts of a turbomachine. According to said method, an original signal emitted by a transmitter device located on the surface of the rotating part is received in a modified manner by a receiver device disposed on the torsion-proof part and is redirected to an evaluation unit. Said evaluation device determines and displays the size of the radial gap from the received signal by determining the parameters of the trajectory of the rotating transmitter device.

    Abstract translation: 本发明涉及一种用于确定旋转和扭转部件之间的径向间隙的尺寸的方法，特别是涡轮机的部件。 根据所述方法，由位于所述旋转部件的表面上的发射机装置发射的原始信号由设置在所述抗扭部件上的接收装置以修改的方式被接收，并被重定向到评估单元。 所述评估装置通过确定旋转发射机装置的轨迹的参数来确定和显示来自接收信号的径向间隙的尺寸。

    Sealing device and method for turbomachinery
    94.
    发明授权
    Sealing device and method for turbomachinery 有权
    涡轮机械密封装置及方法

    公开(公告)号：US07435049B2

    公开(公告)日：2008-10-14

    申请号：US10813102

    申请日：2004-03-30

    Applicant: Farshad Ghasripoor ,  Murtuza Lokhandwalla ,  Raymond Edward Chupp ,  Nitin Bhate

    Inventor： Farshad Ghasripoor ,  Murtuza Lokhandwalla ,  Raymond Edward Chupp ,  Nitin Bhate

    IPC: F01D11/06

    CPC classification number: F01D11/14 ,  F01D5/225 ,  Y02T50/673

    Abstract: A compliant seal for use between rotating blades and a static shroud surrounding the rotating blades in a steam or gas turbine is disclosed. The seal includes a tip surface, substantially resistant to wear due to rubbing by the tip of the rotating blades, and an elastic biasing member, comprising a biasing element. The wear-resistant surface is thus biased against the tips of the rotating blades to seal a gas path between the rotating blades and the static shroud.

    Abstract translation: 公开了一种在旋转叶片和围绕蒸汽或燃气轮机中的旋转叶片的静态护罩之间使用的柔性密封件。 密封件包括基本上抵抗由旋转刀片的尖端摩擦而导致的磨损的尖端表面，以及包括偏置元件的弹性偏置构件。 因此耐磨表面被偏压抵靠旋转叶片的尖端以密封旋转叶片和静态护罩之间的气体路径。

    IMPELLER CLEARANCE TOOL
    96.
    发明申请
    IMPELLER CLEARANCE TOOL 失效
    叶轮清洁工具

    公开(公告)号：US20070130766A1

    公开(公告)日：2007-06-14

    申请号：US10806996

    申请日：2004-03-22

    Applicant: Welton White

    Inventor： Welton White

    IPC: B21D53/78

    CPC classification number: F01D11/14 ,  F01D25/00 ,  F04D29/622 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49321 ,  Y10T29/49895

    Abstract: A tool and method are provided for providing a predetermined clearance between an impeller and a shroud of a jet engine assembly, wherein the shroud has a mating surface, and the impeller and shroud are partially disposed within a casing having a mating surface, wherein the shroud mating surface and casing mating surface are configured to mate with an inlet housing having corresponding inner and outer mating surfaces with a distance between the planes thereof. The tool comprises a hub having first and second sides and an opening extending therethrough, the first side having first and second mating surfaces configured to mate with the shroud and casing mating surfaces, respectively. The hub has a distance between the planes in which the first and second mating surfaces lie, and the hub distance is less than the distance between the planes in which the inlet housing inner and outer mating surfaces lie.

    Abstract translation: 提供了一种用于在喷气发动机组件的叶轮和护罩之间提供预定间隙的工具和方法，其中所述护罩具有配合表面，并且所述叶轮和护罩部分地设置在具有配合表面的壳体内，其中所述护罩 配合表面和套管配合表面被配置为与具有相应的内部和外部配合表面的入口壳体配合，并具有其平面之间的距离。 该工具包括具有第一和第二侧面以及延伸穿过其中的开口的轮毂，第一侧面具有分别配置成与护罩和套管配合表面配合的第一和第二配合表面。 轮毂在第一和第二配合表面所在的平面之间具有距离，并且轮毂距离小于入口壳体内部和外部配合表面所在的平面之间的距离。

    Methods and apparatus for maintaining rotor assembly tip clearances
    97.
    发明授权
    Methods and apparatus for maintaining rotor assembly tip clearances 有权
    保持转子总成尖端间隙的方法和装置

    公开(公告)号：US07165937B2

    公开(公告)日：2007-01-23

    申请号：US11005870

    申请日：2004-12-06

    Applicant: Zhifeng Dong ,  Michael J. Epstein ,  Glen William Royal ,  Robert J. Albers

    Inventor： Zhifeng Dong ,  Michael J. Epstein ,  Glen William Royal ,  Robert J. Albers

    IPC: F01D11/08 ,  F03B11/02

    CPC classification number: F01D11/14 ,  F05D2250/18 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y10T29/49323

    Abstract: A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferentially around the rotor assembly such that a clearance is defined between an inner shroud surface of the casing assembly and the rotor blade tips, and coupling a clearance control system to the casing assembly to facilitate maintaining the clearance between the casing assembly and the rotor blade tips, wherein at least a portion of an external surface of the clearance control system is formed with a textured pattern that facilitates increasing the clearance control closure capability during engine operation.

    Abstract translation: 一种方法使得能够组装燃气涡轮发动机。 该方法包括将包括多个周向间隔开的转子叶片的转子组件联接在一起，并且与压缩机流体连通，将壳体组件周向地围绕转子组件联接，使得间隙限定在转子组件的内护罩表面之间 壳体组件和转子叶片尖端，并且将间隙控制系统耦合到壳体组件以便于保持壳体组件和转子叶片尖端之间的间隙，其中间隙控制系统的外表面的至少一部分形成有 有助于增加发动机运行期间的间隙控制关闭能力的纹理图案。

    Capacitive bridge-type probe for measuring blade tip clearance
    98.
    发明授权
    Capacitive bridge-type probe for measuring blade tip clearance 失效
    用于测量叶片顶端间隙的电容式桥式探头

    公开(公告)号：US4818948A

    公开(公告)日：1989-04-04

    申请号：US893276

    申请日：1986-08-05

    Applicant: Kevin A. Dooley

    Inventor： Kevin A. Dooley

    IPC: F01D11/14 ,  G01B7/14 ,  G01D5/241 ,  G01R27/26 ,  H01G7/00

    CPC classification number: F01D11/14 ,  G01B7/14 ,  G01D5/2417

    Abstract: An elongated conductive casing is filled with a dielectric material and has an opening at one end. The dielectric material forms a surface across the opening, and a plate member is disposed on the surface to form the sensitive arm of the capacitive probe. Formed within the casing are four capacitors, including the sensitive arm, which form a capacitive probe.

    Abstract translation: 细长的导电外壳填充有电介质材料，并在一端具有开口。 电介质材料形成穿过开口的表面，并且板构件设置在表面上以形成电容式探针的敏感臂。 在壳体内形成四个电容器，包括形成电容式探头的敏感臂。

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