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    Method of measuring turbine blade tip erosion
    1.
    发明授权
    Method of measuring turbine blade tip erosion 有权

    公开(公告)号：US10526912B2

    公开(公告)日：2020-01-07

    申请号：US15134429

    申请日：2016-04-21

    Applicant: United Technologies Corporation

    Inventor： Stanley J. Funk ,  Edward F. Pietraszkiewicz

    IPC: F01D5/20 ,  F01D21/00 ,  F01D5/14 ,  F01D25/24

    Abstract: A method of designing a turbine blade includes the steps of forming at least two notches on a tip of a turbine blade, each of the at least two notches having a known dimension. The turbine blade has a pressure side and a suction side. The method further includes the step of operating a gas turbine engine including the turbine blade to expand a length of the turbine blade such that the tip of the turbine engages a casing. The method further includes the steps of viewing the tip of the turbine blade after the step of operating of the gas turbine engine, determining an appearance of the notches on the tip and determining a manufacturing length of the turbine blade based on the step of determining the appearance the notches.

    METHOD OF REDUCING MANUFACTURING VARIATION RELATED TO BLOCKED COOLING HOLES
    6.
    发明申请
    METHOD OF REDUCING MANUFACTURING VARIATION RELATED TO BLOCKED COOLING HOLES 审中-公开
    减少与堵塞式冷却孔相关的制造变化的方法

    公开(公告)号：US20150300201A1

    公开(公告)日：2015-10-22

    申请号：US14522656

    申请日：2014-10-24

    Applicant: United Technologies Corporation

    Inventor： James M. Koonankeil ,  Edward F. Pietraszkiewicz ,  Francis M. Tamiso ,  Kirk D. Hlavaty

    IPC: F01D25/12

    CPC classification number: F01D5/141 ,  F01D5/186 ,  F01D5/187 ,  F01D11/00 ,  F01D11/003 ,  F05D2240/127 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A cooling circuit for a gas turbine engine includes a gas turbine engine component having at least one internal cooling cavity defined by an internal wall surface and a plurality of turbulent flow features extending outwardly from the internal wall surface. Each turbulent flow feature is spaced apart from an adjacent turbulent flow feature in a first direction. At least one trench extends through the turbulent flow features in the first direction, and a plurality of cooling holes are formed within the at least one trench. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine component are also disclosed.

    Abstract translation: 用于燃气涡轮发动机的冷却回路包括具有由内壁表面限定的至少一个内部冷却腔和从内壁表面向外延伸的多个湍流特征的燃气涡轮发动机部件。 每个湍流特征与第一方向上的相邻湍流特征间隔开。 至少一个沟槽在第一方向上延伸穿过湍流特征，并且在至少一个沟槽内形成多个冷却孔。 还公开了一种燃气涡轮发动机和形成用于燃气涡轮发动机部件的冷却回路的方法。

    BLADE PLATFORM GUSSET WITH INTERNAL COOLING
    9.
    发明申请
    BLADE PLATFORM GUSSET WITH INTERNAL COOLING 审中-公开

    公开(公告)号：US20170107830A1

    公开(公告)日：2017-04-20

    申请号：US14886201

    申请日：2015-10-19

    Applicant: United Technologies Corporation

    Inventor： Joseph F. Englehart ,  Edward F. Pietraszkiewicz ,  Wieslaw A. Chlus ,  David M. Konopka ,  Luke A. Hmiel ,  Kenneth Boucher

    IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18 ,  F01D5/14

    Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.

    Gas turbine engine serpentine cooling passage with chevrons
    10.
    发明授权
    Gas turbine engine serpentine cooling passage with chevrons 有权
    燃气涡轮发动机蛇形冷却通道与人字形

    公开(公告)号：US09476308B2

    公开(公告)日：2016-10-25

    申请号：US13728069

    申请日：2012-12-27

    Applicant: United Technologies Corporation

    Inventor： Travis Goeller ,  Erik R. Granstrand ,  Irwin D. Singer ,  Dominic J. Mongillo, Jr. ,  Edward F. Pietraszkiewicz

    IPC: F01D5/18

    CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.

    Abstract translation: 燃气涡轮发动机部件包括具有冷却通道的结构，该冷却通道提供通过内壁彼此分离并通过弯曲部流体连接的上游和下游部分。 第一和第二跳闸条分别布置在上游和下游部分中。 第一行程条以彼此之间的第一间距布置。 第二跳闸条以相互间隔开的第二间隔布置。 湍流促进器布置在弯曲中并且以与第一间隔不同的第一跳闸带的第三间隔布置。 湍流促进器被布置在与第二间隔不同的第二跳闸带的第四间隔处。

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