公开(公告)号：US20180202663A1

公开(公告)日：2018-07-19

申请号：US15407820

申请日：2017-01-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Benjamin Lamar DANIEL ,  Kassy Moy HART ,  David William CIHLAR ,  Steven Charles WOODS ,  Jonathan Glenn REED

IPC: F23R3/34

CPC classification number: F23R3/346 ,  F23R3/283 ,  F23R2900/00018

Abstract: A process includes manufacturing a gas turbine fuel injector body having a stub flange extending radially outward about a circumference of the gas turbine fuel injector body. The stub flange is sized to engage a stepped ledge along a central opening of a mounting flange. The central opening is sized to receive the gas turbine fuel injector body. A gas turbine fuel injector includes a gas turbine fuel injector body and a mounting flange. A method of mounting a gas turbine fuel injector includes placing a stub flange of a gas turbine fuel injector body between a surface of an injector boss and a stepped ledge of a mounting flange. The method also includes securing the gas turbine fuel injector to the injector boss with a plurality of bolts, each bolt extending through a mounting hole in the mounting flange and into a threaded hole in the injector boss.

公开(公告)号：US20180355725A1

公开(公告)日：2018-12-13

申请号：US15621394

申请日：2017-06-13

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Victor John MORGAN ,  Andres Jose GARCIA-CRESPO ,  Elisabeth Kraus BLACK ,  George Andrew GERGELY ,  Jonathan Glenn REED

IPC: F01D5/08

CPC classification number: F01D5/085 ,  B22F3/1055 ,  B22F5/009 ,  B23K1/0018 ,  B23K26/342 ,  B23K31/02 ,  B23K2101/001 ,  B23K2103/26 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/186 ,  F01D5/187 ,  F01D9/023 ,  F01D9/065 ,  F01D25/12 ,  F02K1/822 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2230/51 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/204 ,  F23R3/002 ,  F23R2900/00018 ,  F23R2900/03044

Abstract: A method of creating a cooling arrangement for a turbine component, and a cooling arrangement are provided. The turbine component includes an interior cooling passage formed therein. The method comprises a step of forming a slot through a sidewall of the turbine component. The method further comprises a step of forming an insert having one or more cooling features and a cavity. The method further comprises a step of positioning the insert within the slot. The method further comprises a step of securing the insert within the slot. The method further comprises a step of forming at least one passage in fluid communication with the internal cooling passage, the insert, and an exterior surface of the turbine component.