公开(公告)号：US20150041590A1

公开(公告)日：2015-02-12

申请号：US13963276

申请日：2013-08-09

Applicant: General Electric Company

Inventor： Kevin Richard Kirtley ,  David Edward Schick ,  Aaron Ezekiel Smith

IPC: B64C3/00

CPC classification number: B64C3/00 ,  F01D5/187 ,  F01D5/28 ,  F05D2230/30 ,  F05D2240/122 ,  F05D2240/304

Abstract: An airfoil includes a main portion formed of a base material and having an inner core comprising a hollow region. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising a low-melt superalloy operatively coupled to the base material proximate the trailing edge region. Yet further included is at least one cooling passage fluidly coupling the inner core of the main portion to an inner region of the trailing edge region. Also included is a trailing edge region exhaust path disposed in the inner region and configured to route a cooling airflow in a span-wise direction of the airfoil.

Abstract translation: 机翼包括由基材形成并具有包括中空区域的内芯的主体部分。 还包括主要部分的后缘区域。 还包括后缘补充结构，其包括可操作地连接到靠近后缘区域的基底材料的低熔融超合金。 还包括至少一个冷却通道，其将主要部分的内芯流体地连接到后缘区域的内部区域。 还包括设置在内部区域中的后缘区域排气路径，其构造成在翼型的跨度方向上布置冷却气流。

公开(公告)号：US10648346B2

公开(公告)日：2020-05-12

申请号：US15203027

申请日：2016-07-06

Applicant: General Electric Company

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

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

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：US09816388B1

公开(公告)日：2017-11-14

申请号：US15272864

申请日：2016-09-22

Applicant: General Electric Company

Inventor： Kevin Richard Kirtley ,  Ibrahim Sezer ,  Benjamin P. Lacy

IPC: F01D11/08 ,  F01D11/02 ,  F16J15/447 ,  B33Y80/00

CPC classification number: F01D11/02 ,  B22F3/1055 ,  B22F5/009 ,  B33Y80/00 ,  F01D11/127 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/31 ,  F05D2250/121 ,  F05D2250/132 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/283 ,  F05D2260/20 ,  F05D2300/514 ,  F16J15/447

Abstract: A seal in a gas turbine engine includes a shim base and a honeycomb structure having a number of cavities are formed as a single unitary structure using additive manufacturing.