公开(公告)号：US20180010467A1

公开(公告)日：2018-01-11

申请号：US15203027

申请日：2016-07-06

Applicant: General Electric Company

Inventor： Xiuzhang James Zhang ,  Kevin Richard Kirtley ,  Lisa DeBellis

IPC: F01D5/22 ,  F01D5/20 ,  F01D11/08

CPC classification number: F01D5/225 ,  F01D5/20 ,  F01D11/08 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/307 ,  F05D2240/55 ,  Y02T50/671 ,  Y02T50/673

Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.

公开(公告)号：US09810072B2

公开(公告)日：2017-11-07

申请号：US14288748

申请日：2014-05-28

Applicant: General Electric Company

Inventor： Zhirui Dong ,  Xiuzhang James Zhang ,  Jason Adam Neville

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D5/186 ,  F01D5/085 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/676

Abstract: A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.

公开(公告)号：US20170298744A1

公开(公告)日：2017-10-19

申请号：US15099116

申请日：2016-04-14

Applicant: General Electric Company

Inventor： Xiuzhang James Zhang ,  James Tyson Balkcum, III ,  Ian Darnall Reeves ,  Joseph Anthony Cotroneo

IPC: F01D5/18 ,  F01D5/20

CPC classification number: F01D5/187 ,  F01D5/18 ,  F01D5/20 ,  F01D5/225 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2240/55 ,  F05D2260/20

Abstract: A turbine blade includes a tip shroud having a seal rail. The seal rail includes a tangential surface extending between tangential ends. The turbine blade includes a root portion configured to couple to a rotor and an airfoil portion extending between the root portion and the tip shroud. The seal rail includes a cooling passage extending along a length of the seal rail. The cooling passage is fluidly coupled to a cooling plenum to receive a cooling fluid via an intermediate cooling passage extending between the cooling passage and a cooling plenum. The seal rail includes cooling outlet passages fluidly coupled to the cooling passage. The cooling outlet passages are disposed within the seal rail and extend between the cooling passage and the tangential surface of the seal rail. The cooling outlet passages are configured to discharge the cooling fluid from the tip shroud via the tangential surface.

公开(公告)号：US09708916B2

公开(公告)日：2017-07-18

申请号：US14335047

申请日：2014-07-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Xiuzhang James Zhang ,  Lisa DeBellis ,  Haiping Wang

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2230/11 ,  F05D2230/12 ,  F05D2230/21 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

Abstract: A casted turbine bucket having at least one machined plenum including a plenum chamber and at least one plenum passage connected to a plenum inlet at a root portion of turbine bucket, and a method to feed cooling flow to the turbine bucket using the machined plenum that receives cooling flow from the root portion of the turbine bucket.

公开(公告)号：US20160298545A1

公开(公告)日：2016-10-13

申请号：US14684908

申请日：2015-04-13

Applicant: General Electric Company

Inventor： Xiuzhang James Zhang ,  Sandip Dutta ,  Gary Michael Itzel

IPC: F02C7/18 ,  F01D5/02 ,  F02C3/06 ,  F01D5/18

CPC classification number: F02C7/185 ,  F01D5/02 ,  F01D5/187 ,  F02C3/06 ,  F05D2220/3212 ,  F05D2230/11 ,  F05D2240/24 ,  F05D2240/306 ,  F05D2240/307 ,  F05D2240/35 ,  F05D2260/20

Abstract: A turbine airfoil includes a leading edge, a trailing edge, a root and a tip. Also included is a pressure side wall extending between the leading edge and the trailing edge and between the root and the tip. Further included is a suction side wall extending between the leading edge and the trailing edge and between the root and the tip. Yet further included is a non-circular cooling channel defined by the turbine airfoil and extending radially from the root to the tip, the non-circular cooling channel routing a cooling air to an outlet hole formed in the tip. Also included is an exhaust hole defined by the turbine airfoil and extending from the non-circular cooling channel to the suction side wall, the exhaust hole radially located between the root and the tip.

Abstract translation: 涡轮机翼片包括前缘，后缘，根部和尖端。 还包括在前缘和后缘之间以及根部和尖端之间延伸的压力侧壁。 还包括在前缘和后缘之间以及根部与尖端之间延伸的吸力侧壁。 还包括由涡轮机翼型件限定并从根部到顶端径向延伸的非圆形冷却通道，非圆形冷却通道将冷却空气引导到形成在尖端中的出口孔。 还包括由涡轮机翼型件限定并从非圆形冷却通道延伸到吸入侧壁的排气孔，排气孔位于根部和尖端之间。

公开(公告)号：US20150075180A1

公开(公告)日：2015-03-19

申请号：US14030645

申请日：2013-09-18

Applicant: General Electric Company

Inventor： Xiuzhang James Zhang ,  James W. Vehr

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D11/006 ,  F01D11/04 ,  F01D25/12 ,  F05D2260/201 ,  F05D2260/202

Abstract: A turbine bucket is disclosed herein. The turbine bucket may include a platform and a shank portion extending radially inward from the platform. The shank portion may include a slash face, a radial seal pin groove formed in the slash face, and at least one cooling hole disposed in the slash face about the radial seal pin groove.

Abstract translation: 本文公开了涡轮机桶。 涡轮机桶可以包括从平台径向向内延伸的平台和柄部分。 柄部分可以包括斜面，形成在斜面上的径向密封销槽和围绕径向密封销槽设置在斜面上的至少一个冷却孔。

公开(公告)号：US20140112753A1

公开(公告)日：2014-04-24

申请号：US13654822

申请日：2012-10-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Xiuzhang James Zhang ,  Gary Michael Itzel ,  Ibrahim Sezer

IPC: F03B11/00

CPC classification number: F01D11/006 ,  F01D11/122

Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.

Abstract translation: 涡轮机系统的密封装置包括具有外部尖端的桶，以及从外部末端径向向外延伸的至少一个铲斗脊，所述至少一个铲斗脊包含可磨损材料。 还包括从桶的外端径向向外设置的固定护罩。 还包括至少一个护罩脊，其从固定护罩朝向桶的外部末端径向向内延伸，所述至少一个护罩脊包括可磨损材料。

公开(公告)号：US10704406B2

公开(公告)日：2020-07-07

申请号：US15620896

申请日：2017-06-13

Applicant: General Electric Company

Inventor： Jalindar Appa Walunj ,  Shashwat Swami Jaiswal ,  Stephen Paul Wassynger ,  Xiuzhang James Zhang

IPC: F01D11/08 ,  F01D5/22 ,  F01D5/18 ,  F01D11/10

Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.

公开(公告)号：US10247009B2

公开(公告)日：2019-04-02

申请号：US15163061

申请日：2016-05-24

Applicant: General Electric Company

Inventor： Melbourne James Myers ,  Xiuzhang James Zhang ,  Stuart Samuel Collins ,  Camilo Andres Sampayo ,  Joseph Block

IPC: F01D5/08 ,  F01D5/18 ,  F01D5/14

Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

公开(公告)号：US10066488B2

公开(公告)日：2018-09-04

申请号：US14955563

申请日：2015-12-01

Applicant: General Electric Company

Inventor： Melbourne James Myers ,  Camilo Andres Sampayo ,  Xiuzhang James Zhang

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/08

Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge of the platform. A related turbomachine is also disclosed.