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公开(公告)号：US20160215628A1
公开(公告)日：2016-07-28
申请号：US14605366
申请日：2015-01-26
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , Daniel A. Snyder , Jaimie Taraskevich , Di Wu
CPC classification number: F01D5/187 , F01D5/147 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2260/22141 , Y02T50/676
Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.
Abstract translation: 在各种实施例中，提供了用作燃气涡轮发动机中的涡轮机叶轮的涡轮叶片的翼型件。 翼型件可以包括根部，尖端和主体。 根可能有第一个区域。 尖端可以具有第二区域。 身体可能有一个由根和尖端限定的和弦。 主体还可以限定冷却室。 冷却室可以具有基本上垂直于弦的第一肋。 冷却室还可以具有部分地在根部和尖端之间延伸的第二肋条。
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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
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.
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公开(公告)号：US09726023B2
公开(公告)日：2017-08-08
申请号：US14605366
申请日：2015-01-26
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , Daniel A. Snyder , Jaimie Taraskevich , Di Wu
CPC classification number: F01D5/187 , F01D5/147 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2260/22141 , Y02T50/676
Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.
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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
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。
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