公开(公告)号：WO2013154657A3

公开(公告)日：2013-12-05

申请号：PCT/US2013023132

申请日：2013-01-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER DANIEL A ,  LANA KYLE CHARLES ,  SANDOVAL JONATHAN PERRY ,  VIRKLER SCOTT DANIEL ,  TARASKEVICH JAIMIE ,  OTERO EDWIN

IPC: F01D5/26

CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

Abstract translation: 根据本公开的示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮机叶片的空腔中的阻尼器密封件包括中心主体部分，其具有第一端部区域，相对的第二端部 区域和宽度。 阻尼器密封件还包括从中心主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突片，其限定第一扩大部分，第一扩大部分具有大于 中心主体部分和从中心主体部分的相对的第二端部区域延伸的第二部分。

公开(公告)号：EP2836682A4

公开(公告)日：2016-06-01

申请号：EP13775907

申请日：2013-01-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER DANIEL A ,  LANA KYLE CHARLES ,  SANDOVAL JONATHAN PERRY ,  VIRKLER SCOTT DANIEL ,  TARASKEVICH JAIMIE ,  OTERO EDWIN

IPC: F01D5/26 ,  F01D5/22 ,  F01D5/30 ,  F01D11/00

CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

Abstract translation: 根据本公开的示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮叶片的空腔中的阻尼器密封件包括中心主体部分，其具有第一端部区域，相对的第二端部 区域和宽度。 阻尼器密封件还包括从中心主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突出部，其限定第一扩大部分，第一扩大部分具有大于 中心主体部分和从中心主体部分的相对的第二端部区域延伸的第二部分。

公开(公告)号：EP2962061A4

公开(公告)日：2016-11-30

申请号：EP14757641

申请日：2014-02-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： OUYANG ZHONG ,  RAULERSON DAVID A ,  SMITH KEVIN D ,  PINERO HECTOR M ,  TARASKEVICH JAIMIE ,  BOYER JESSE R

IPC: G01B11/06 ,  G01B21/08 ,  G01J5/00 ,  G01N25/00

CPC classification number: G01B21/085 ,  G01J5/0088 ,  G01J5/0896 ,  G01J2005/0081 ,  G01N25/00

Abstract: A method of determining the thickness of an internal wall in a gas turbine engine component includes the steps of utilizing flash thermography to measure a complete thickness of a component between an outer wall and at least one enlarged cooling channel at a location where an outer cooling channel is positioned between the outer wall and the at least one enlarged cooling channel and where at least one member spans the cooling channel, such that the thickness is through the member which spans the outer cooling channel. An outer thickness of the component is measured from the outer wall to an outer wall of the outer cooling channel. A thickness is determined from an inner wall of the outer cooling channel to the at least one enlarged cooling channel by subtracting the measured outer thickness from the complete thickness, and also subtracting a known thickness of the outer cooling channel.

Abstract translation: 一种确定燃气涡轮发动机部件中的内壁厚度的方法包括以下步骤：利用闪蒸热成像测量在外壁与至少一个扩大的冷却通道之间的部件的完整厚度，其中外冷却通道 定位在外壁和至少一个扩大的冷却通道之间，并且其中至少一个构件跨越冷却通道，使得厚度穿过跨过外部冷却通道的构件。 从外壁到外部冷却通道的外壁测量部件的外部厚度。 通过从完全厚度减去所测量的外部厚度，并且还减去外部冷却通道的已知厚度，从外部冷却通道的内壁到至少一个扩大的冷却通道确定厚度。