公开(公告)号：US10519790B2

公开(公告)日：2019-12-31

申请号：US15623696

申请日：2017-06-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Matthew Troy Hafner ,  John McConnell Delvaux ,  Glenn Curtis Taxacher

IPC: F01D11/08 ,  F01D9/04 ,  F01D25/24 ,  F01D11/02 ,  F01D11/22 ,  F01D11/00

Abstract: A turbine component includes an outer shroud arranged within a turbine and further including opposed extending portions. The component further provides an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and including opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The component further provides a load path forming region at least partially extending between facing surfaces of each arcuate portion and corresponding extending portion. During operation of the turbine, load path forming regions extend into direct contact between at least a portion of the facing surfaces of each arcuate portion and corresponding extending portion, resulting in formation of a loading arrangement having generally evenly distributed radial load forces at the load path forming regions.

公开(公告)号：US10280801B2

公开(公告)日：2019-05-07

申请号：US15623715

申请日：2017-06-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Matthew Troy Hafner ,  Frederic Woodrow Roberts, Jr. ,  Glenn Curtis Taxacher

IPC: F01D25/00 ,  F01D25/26 ,  F01D9/04 ,  F01D11/08

Abstract: A turbine component including an outer shroud arranged within a turbine and including opposed extending portions. An inner shroud shields the outer shroud from a gas flowing along a gas path within the turbine during its operation and including opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud. A first pin and second pin have a respective first end and second end. The first arcuate portion having a first engagement region for engaging the first end, and second arcuate portion having a second engagement region for engaging the second end. In response to engagement of the first engagement region and the first end of the first pin, and engagement of the second engagement region and the second end of the second pin, the inner shroud is prevented from twisting relative to the outer shroud.

公开(公告)号：US10087519B1

公开(公告)日：2018-10-02

申请号：US15629532

申请日：2017-06-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Jason Robert Parolini ,  John McConnell Delvaux ,  Srikanth Chandrudu Kottilingam ,  James Joseph Murray ,  Canan Uslu Hardwicke ,  Matthew Troy Hafner

IPC: B01J19/08 ,  B01J19/10 ,  B06B1/00 ,  C23C16/04 ,  C23C16/24

Abstract: A method of making a preform and preform formed by the method. The method includes providing a first pre-preg ply including at least a first fiber and a first resin. The method also includes providing a second pre-preg ply including at least a second fiber and a second resin over at least a portion of the first pre-preg ply. Heat or electromagnetic radiation is used to at least partially cure the first and second resins to form a cured preform. Heat is applied to pyrolyze at least a portion of the resin of the cured preform to form a pyrolyzed preform. A mechanical stimulus including at least one of controlled drying, local explosions, or ultrasonic energy is applied to the pyrolyzed preform. The mechanically treated pyrolyzed preform is subsequently densified by melt infiltration to form a densified preform.

公开(公告)号：US20180272568A1

公开(公告)日：2018-09-27

申请号：US15465726

申请日：2017-03-22

Applicant: General Electric Company

Inventor： Jason Robert Parolini ,  Matthew Troy Hafner ,  James Joseph Murray ,  Srikanth Chandrudu Kottilingam ,  Canan Uslu Hardwicke ,  John McConnell Delvaux

IPC: B29C35/02 ,  B29C33/38 ,  C04B35/80 ,  C04B35/626 ,  C04B35/628 ,  C04B35/657

CPC classification number: B29C35/02 ,  B29C33/38 ,  B29L2031/7504 ,  B32B18/00 ,  C04B35/62645 ,  C04B35/62844 ,  C04B35/62876 ,  C04B35/657 ,  C04B35/803 ,  C04B35/806 ,  C04B2235/3217 ,  C04B2235/3826 ,  C04B2235/3873 ,  C04B2235/5224 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/6026 ,  C04B2235/6028 ,  C04B2235/616 ,  C04B2235/945 ,  C04B2237/38 ,  C04B2237/62 ,  C04B2237/64 ,  F01D5/282 ,  F01D5/284 ,  F05D2260/204 ,  F05D2300/6033

Abstract: The present disclosure is directed to a method for forming a passage in a composite component. The method includes forming a cavity in a fiber preform. The cavity forms a portion of the passage. The method also includes inserting a core into the cavity and placing one or more fiber plies onto the fiber preform to form a fiber preform assembly. The method further includes thermally processing the fiber preform assembly and densifying the fiber preform assembly to form the composite component. The method also includes removing the core from the composite component.

公开(公告)号：US20180112549A1

公开(公告)日：2018-04-26

申请号：US15298572

申请日：2016-10-20

Applicant: General Electric Company

Inventor： Bodhayan Dev ,  Neelesh Digamber Sarawate ,  Matthew Troy Hafner

IPC: F01D11/00 ,  F01D9/04

Abstract: Various embodiments include gas turbine seals and methods of forming such seals for advanced gas path (AGP) heat transfer designed gas turbine engines. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component formed of a ceramic matrix composite and including a seal slot located in an end face, each seal slot having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and an overhanging seal assembly disposed in the seal slot. The overhanging seal assembly including an intersegment seal including a plurality of seal segments defining two vertical seal segments and a plurality of horizontal seal segments and a first overhanging positioner shim seal and a second overhanging positioner shim seal, each including an extended portion. The overhanging seal assembly disposed in the seal slot so as to provide position constrainment of the two vertical seal segments.

公开(公告)号：US20170299187A1

公开(公告)日：2017-10-19

申请号：US15464419

申请日：2017-03-21

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Stanley Kevin Widener ,  Michael John Hughes ,  Matthew Troy Hafner ,  Joseph Vincent Citeno

IPC: F23R3/28 ,  F02C7/18 ,  F01D9/04 ,  F02C7/24

CPC classification number: F23R3/286 ,  F01D9/041 ,  F02C7/18 ,  F02C7/24 ,  F05D2220/30 ,  F05D2240/35 ,  F23R3/283 ,  F23R3/346 ,  F23R2900/03341

Abstract: The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.

公开(公告)号：US09581037B2

公开(公告)日：2017-02-28

申请号：US14697765

申请日：2015-04-28

Applicant: General Electric Company

Inventor： Matthew Troy Hafner ,  Victor John Morgan ,  Jacob John Kittleson ,  Neelesh N. Sarawate

IPC: F16J15/02 ,  F01D11/00 ,  F01D25/12 ,  F02C7/18 ,  F16J15/06

CPC classification number: F01D11/005 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/20 ,  F16J15/064

Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.

Abstract translation: 本申请提供了在面向高压冷却空气流的部件发动机和燃气涡轮机中的热气体路径之间使用的密封件。 密封件可以包括第一垫片，具有空气出口孔的第二垫片，位于第一垫片和第二垫片之间的一个或多个中间层，以及延伸穿过用于高压冷却空气流的中间层的一个或多个冷却路径 从而通过空气出口孔流入热气路径。

公开(公告)号：US20140321982A1

公开(公告)日：2014-10-30

申请号：US13872657

申请日：2013-04-29

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Matthew Troy Hafner

IPC: F01D25/00

CPC classification number: F01D17/08 ,  F01D11/20 ,  Y10T29/49316

Abstract: A turbine blade monitoring arrangement includes a bucket tip located at a radial outer location of a bucket. Also included is at least one component disposed radially outwardly of the bucket tip. Further included is a hollow portion of the at least one component, wherein the hollow portion extends radially from a first end to a second end through the at least one component. Yet further included is a first sealing component operatively coupled to the at least one component proximate the first end of the hollow portion, wherein the first sealing component comprises a translucent material. Also included is a proximity sensor disposed radially outwardly of the at least one component and aligned with the hollow portion, the proximity sensor configured to generate a first signal through the hollow portion to the bucket tip.

Abstract translation: 涡轮叶片监控装置包括位于铲斗的径向外部位置的铲斗前端。 还包括设置在铲斗前端的径向外侧的至少一个部件。 还包括至少一个部件的中空部分，其中中空部分从第一端径向延伸穿过至少一个部件到第二端。 还包括第一密封部件，其可操作地耦合到靠近中空部分的第一端部的至少一个部件，其中第一密封部件包括半透明材料。 还包括接近传感器，其设置在至少一个部件的径向外侧并与中空部分对准，该接近传感器被配置成通过中空部分产生到铲斗前端的第一信号。