公开(公告)号：US10669875B2

公开(公告)日：2020-06-02

申请号：US15939070

申请日：2018-03-28

Applicant: Solar Turbines Incorporated

Inventor： Jorge Hernandez ,  David Jeorling ,  Makarand Sovani

IPC: F01D11/00 ,  F04D29/32

Abstract: This disclosure provides a cross key anti rotation spacer for use in a gas turbine engine. A compressor disk assembly can have a cross key ring having a plurality of keys, teeth, or castellations, alternating with a plurality of gaps to form a cross key surface. The keys or teeth of the cross key surface can mesh with corresponding teeth formed on a spacer of a compressor rotor assembly. The spacer teeth, in connection with the teeth or keys of the cross key ring can prevent rotation between the spacer and compressor disk. This is particularly beneficial during transient operations, such as startup and shutdown of the gas turbine engine.

公开(公告)号：US20240246221A1

公开(公告)日：2024-07-25

申请号：US18156524

申请日：2023-01-19

Applicant: Solar Turbines Incorporated

Inventor： Tom Leen ,  David Jeorling ,  Jose Vigo Molina ,  Garrett Gauthier

IPC: B25H7/04

CPC classification number: B25H7/04

Abstract: A scribing device for a component includes a holder and a first scribing assembly coupled to the holder. The first scribing assembly includes a first scribing tool including a first scribing tip configured to define a first annular scribe mark on a circumferential surface of the component, and a first biasing member configured to bias the first scribing tool towards the circumferential surface of the component. The scribing device further includes a second scribing assembly. The second scribing assembly includes a second scribing tool including a second scribing tip configured to define a second annular scribe mark on the circumferential surface of the component, and a second biasing member configured to bias the second scribing tool towards the circumferential surface of the component.

公开(公告)号：US09371735B2

公开(公告)日：2016-06-21

申请号：US13689250

申请日：2012-11-29

Applicant: Solar Turbines Incorporated

Inventor： William Landon Reilly ,  David Jeorling ,  Adrian Nazareno Reyes

IPC: F01D5/18 ,  F01D9/04

CPC classification number: F01D9/041 ,  F01D5/189 ,  F05D2230/232

Abstract: An impingement cover (460) for fusing to a gas turbine engine turbine nozzle (451) with a nozzle rail (455) includes a body and a plurality of tabs for forming a first fuse with the nozzle rail (455). The body has a plate like shape and includes a plurality of impingement holes (464), a first edge, a second edge, and a first airfoil cooling hole (470). The plurality of tabs includes a first tab (461) extending from the first edge, and a second tab (462) extending from the second edge. The second tab (462) is located in a different quadrant of the body than the first tab (461).

Abstract translation: 用于利用喷嘴轨道（455）熔接到燃气涡轮发动机涡轮喷嘴（451）的冲击盖（460）包括主体和用于与喷嘴导轨（455）形成第一保险丝的多个突出部。 主体具有板状形状并且包括多个冲击孔（464），第一边缘，第二边缘和第一翼面冷却孔（470）。 多个突出部包括从第一边缘延伸的第一突出部（461）和从第二边缘延伸的第二突出部（462）。 第二片（462）位于与第一片（461）相比的身体的不同象限中。

公开(公告)号：US20190301295A1

公开(公告)日：2019-10-03

申请号：US15939070

申请日：2018-03-28

Applicant: Solar Turbines Incorporated

Inventor： Jorge Hernandez ,  David Jeorling ,  Makarand Sovani

IPC: F01D11/00 ,  F04D29/32

Abstract: This disclosure provides a cross key anti rotation spacer for use in a gas turbine engine. A compressor disk assembly can have a cross key ring having a plurality of keys, teeth, or castellations, alternating with a plurality of gaps to form a cross key surface. The keys or teeth of the cross key surface can mesh with corresponding teeth formed on a spacer of a compressor rotor assembly. The spacer teeth, in connection with the teeth or keys of the cross key ring can prevent rotation between the spacer and compressor disk. This is particularly beneficial during transient operations, such as startup and shutdown of the gas turbine engine.

公开(公告)号：US20140147259A1

公开(公告)日：2014-05-29

申请号：US13689250

申请日：2012-11-29

Applicant: SOLAR TURBINES INCORPORATED

Inventor： William Landon Reilly ,  David Jeorling ,  Adrian Nazareno Reyes

IPC: F01D25/14

CPC classification number: F01D9/041 ,  F01D5/189 ,  F05D2230/232

Abstract: An impingement cover (460) for fusing to a gas turbine engine turbine nozzle (451) with a nozzle rail (455) includes a body and a plurality of tabs for forming a first fuse with the nozzle rail (455). The body has a plate like shape and includes a plurality of impingement holes (464), a first edge, a second edge, and a first airfoil cooling hole (470). The plurality of tabs includes a first tab (461) extending from the first edge, and a second tab (462) extending from the second edge. The second tab (462) is located in a different quadrant of the body than the first tab (461).

Abstract translation: 用于利用喷嘴轨道（455）熔接到燃气涡轮发动机涡轮喷嘴（451）的冲击盖（460）包括主体和用于与喷嘴导轨（455）形成第一保险丝的多个突出部。 主体具有板状形状并且包括多个冲击孔（464），第一边缘，第二边缘和第一翼面冷却孔（470）。 多个突出部包括从第一边缘延伸的第一突出部（461）和从第二边缘延伸的第二突出部（462）。 第二片（462）位于与第一片（461）相比的身体的不同象限中。