公开(公告)号：US20240011413A1

公开(公告)日：2024-01-11

申请号：US18328076

申请日：2023-06-02

Applicant: General Electric Company ,  Oliver Crispin Robotics Limited

Inventor： Michael Robert Millheam ,  Andrew Crispin Graham ,  Byron Andrew Pritchard, JR. ,  David Scott Diwinsky ,  Jeremy Clyde Bailey ,  Michael Edward Eriksen ,  Ambarish Jayant Kulkarni

IPC: F01D25/00

CPC classification number: F01D25/002 ,  F02C7/30

Abstract: A method of repairing a component of a gas turbine engine in situ, wherein the component includes a deposit, includes directing a flow of gas, which may be an oxygen-containing gas, to the deposit of the component; and heating the component including the deposit while the component is installed in the gas turbine engine and for a duration sufficient to substantially remove the deposit.

公开(公告)号：US20200224552A1

公开(公告)日：2020-07-16

申请号：US16735191

申请日：2020-01-06

Applicant: General Electric Company ,  Oliver Crispin Robotics Limited

Inventor： Michael Robert Millhaem ,  Andrew Crispin Graham ,  Byron Andrew Pritchard, JR. ,  David Scott Diwinsky ,  Jeremy Clyde Bailey ,  Michael Edward Eriksen ,  Ambarish Jayant Kulkarni

IPC: F01D25/00 ,  F02C7/30

Abstract: A method of repairing a component of a gas turbine engine in situ, wherein the component includes a deposit, includes directing a flow of gas, which may be an oxygen-containing gas, to the deposit of the component; and heating the component including the deposit while the component is installed in the gas turbine engine and for a duration sufficient to substantially remove the deposit.

公开(公告)号：US20170234734A1

公开(公告)日：2017-08-17

申请号：US15043508

申请日：2016-02-13

Applicant: General Electric Company

Inventor： Mohamed Sakami ,  Nirm Velumylum Nirmalan ,  Jeremy Clyde Bailey

IPC: G01J5/06 ,  G02B23/24 ,  G02B7/02 ,  G01J5/00 ,  H04N5/225

Abstract: An apparatus for insertion through an opening in an outer casing of a gas turbine engine and inspection of internal turbine components at elevated temperatures having an optical sight tube configured to optically communicate with an interior of gas turbine engine via a distal end disposed at the interior and a proximal end disposed exterior of the internal turbine components and defined by a first longitudinal wall, at least one lens at the distal end of the optical sight tube adjacent to the longitudinal wall; and at least one longitudinal cooling groove in the longitudinal wall for flowing a cooling medium from a location external to the turbine to cool the optical sight tube at a location at least adjacent the distal end.

公开(公告)号：US20170234225A1

公开(公告)日：2017-08-17

申请号：US15043511

申请日：2016-02-13

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Jeremy Clyde Bailey

IPC: F02C7/141 ,  F23R3/16 ,  F23R3/00

CPC classification number: F02C7/141 ,  F01D5/187 ,  F05D2250/232 ,  F05D2250/241 ,  F05D2250/28 ,  F05D2250/61 ,  F05D2260/2212 ,  F05D2260/607 ,  F15D1/005 ,  F16K1/00 ,  Y02T50/672 ,  Y02T50/676

Abstract: An apparatus and method for an engine component having a hot surface adjacent a hot combustion gas flow and a cooling surface adjacent a cooling fluid flow can include at least one dimple for enhancing the cooling along the cooling surface. The dimple can be shaped having a head and a tail with the head disposed upstream of the tail to provide for reduced dust collection along the engine component.

公开(公告)号：US20170107826A1

公开(公告)日：2017-04-20

申请号：US14884075

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield ,  David Benjamin Helmer ,  Jeremy Clyde Bailey ,  Robert David Briggs

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

公开(公告)号：US09599514B2

公开(公告)日：2017-03-21

申请号：US13748769

申请日：2013-01-24

Applicant: General Electric Company

Inventor： Jordi Estevadeordal ,  Nirm Velumylum Nirmalan ,  Nilesh Tralshawala ,  Jeremy Clyde Bailey

IPC: F02C3/00 ,  G01J5/60 ,  F02C7/00 ,  G01J5/08 ,  G01J5/00 ,  G01J5/02 ,  G01J5/04

CPC classification number: G01J5/602 ,  F02C7/00 ,  G01J5/0088 ,  G01J5/0205 ,  G01J5/043 ,  G01J5/0806 ,  G01J5/0859 ,  G01J5/0862 ,  G01J5/0865 ,  G01J2005/0077

Abstract: A multi-color pyrometry imaging system for a high-temperature asset includes at least one viewing port in optical communication with at least one high-temperature component of the high-temperature asset. The system also includes at least one camera device in optical communication with the at least one viewing port. The at least one camera device includes a camera enclosure and at least one camera aperture defined in the camera enclosure, The at least one camera aperture is in optical communication with the at least one viewing port. The at least one camera device also includes a multi-color filtering mechanism coupled to the enclosure. The multi-color filtering mechanism is configured to sequentially transmit photons within a first predetermined wavelength band and transmit photons within a second predetermined wavelength band that is different than the first predetermined wavelength band.

公开(公告)号：US20150147158A1

公开(公告)日：2015-05-28

申请号：US14089920

申请日：2013-11-26

Applicant: General Electric Company

Inventor： Guanghua Wang ,  Ronald Scott Bunker ,  Jeremy Clyde Bailey ,  James Peter DeLancey ,  David Benjamin Helmer

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/304 ,  F05D2250/13 ,  F05D2250/131 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/324 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil and method of cooling a airfoil including a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, is provided. A plurality of trailing edge bleed slots are in fluid communication with the at least one internal cooling channel, wherein a downstream edge of the pressure side of the airfoil lies upstream of a downstream edge of the suction side to expose the plurality of trailing edge bleed slots proximate to the trailing edge of the airfoil. The at least one internal cooling channel is configured to supply the cooling fluid from a source of cooling fluid towards the plurality of trailing edge bleed slots. A plurality of obstruction features are disposed within the at least one internal cooling channel and at a downstream edge of the remaining pressure side. The one or more obstruction features are configured having a predefined substantially polygon shape, to distribute a flow of the cooling fluid and provide distributed cooling to the plurality of trailing edge bleed slots.

Abstract translation: 提供了一种用于冷却包括前缘，后缘，吸力侧，压力侧和构造成输送冷却流体的至少一个内部冷却通道的翼型的翼型件和方法。 多个后缘排出槽与至少一个内部冷却通道流体连通，其中翼型的压力侧的下游边缘位于吸力侧的下游边缘的上游，以暴露多个后缘排放槽 靠近翼型件的后缘。 至少一个内部冷却通道构造成将冷却流体从冷却流体源向多个后缘排出槽供应。 多个阻塞特征设置在至少一个内部冷却通道内和在剩余压力侧的下游边缘处。 一个或多个障碍物特征被构造成具有预定的基本上多边形的形状，以分配冷却流体的流动并且向多个后缘排放槽提供分布式冷却。