公开(公告)号：US10557412B2

公开(公告)日：2020-02-11

申请号：US15608547

申请日：2017-05-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Baumann ,  Brian Barainca ,  Rolf Thorsen ,  Mark E. Simonds ,  Gary F. Fowler ,  Hector M. Pinero

IPC: F02C7/055 ,  F01D21/04 ,  F01D11/12 ,  F01D5/24 ,  F02C7/045 ,  F02C7/05

Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.

公开(公告)号：US20180347465A1

公开(公告)日：2018-12-06

申请号：US15608547

申请日：2017-05-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Baumann ,  Brian Barainca ,  Rolf Thorsen ,  Mark E. Simonds ,  Gary F. Fowler ,  Hector M. Pinero

IPC: F02C7/055 ,  F02C7/045

CPC classification number: F02C7/055 ,  F01D5/24 ,  F01D11/122 ,  F01D21/045 ,  F02C7/045 ,  F02C7/05

Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion- of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.

公开(公告)号：US09964404B2

公开(公告)日：2018-05-08

申请号：US14765010

申请日：2014-02-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Zhong Ouyang ,  David A. Raulerson ,  Kevin D. Smith ,  Hector M. Pinero ,  Jaimie Taraskevich ,  Jesse R. Boyer

IPC: 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.

公开(公告)号：US20160001354A1

公开(公告)日：2016-01-07

申请号：US14767612

申请日：2014-02-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Hector M. Pinero ,  Richard H. Page

IPC: B22C9/24 ,  B22C9/10 ,  F01D5/18 ,  B22D21/02 ,  B22D25/02 ,  F01D9/04 ,  B22C9/04 ,  B22C9/12

CPC classification number: B22C9/24 ,  B22C9/04 ,  B22C9/10 ,  B22C9/108 ,  B22C9/12 ,  B22C21/14 ,  B22D21/025 ,  B22D25/02 ,  F01D5/18 ,  F01D5/187 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2300/177 ,  F05D2300/20 ,  Y02T50/676

Abstract: A method of manufacturing a gas turbine engine component includes providing a core having a brittle feature, supporting the feature with a first meltable material, arranging the core with the first meltable material in a first mold, and surrounding the core and the first meltable material with a second meltable material to provide a component shape. The method also includes coating the second meltable material with a refractory material to produce a second mold, removing the first and second meltable material, and casting a component in the second mold.

Abstract translation: 一种制造燃气涡轮发动机部件的方法包括提供具有脆性特征的芯部，用第一可熔融材料支撑该特征，将芯体与第一可熔材料一起设置在第一模具中，并且围绕芯部和第一可熔融材料， 第二可熔融材料，以提供部件形状。 该方法还包括用耐火材料涂覆第二可熔材料以产生第二模具，去除第一和第二可熔融材料，以及将组件浇铸在第二模具中。

公开(公告)号：US20150369596A1

公开(公告)日：2015-12-24

申请号：US14765010

申请日：2014-02-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Zhong Ouyang ,  David A. Raulerson ,  Kevin D. Smith ,  Hector M. Pinero ,  Jaimie Taraskevich ,  Jesse R. Boyer

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

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和至少一个扩大的冷却通道之间的部件的完整厚度，在外部冷却通道 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该部件的外部厚度。 从外部冷却通道的内壁到至少一个扩大的冷却通道，通过从完整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来确定厚度。