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公开(公告)号：US20170146024A1
公开(公告)日：2017-05-25
申请号：US14947494
申请日：2015-11-20
Applicant: United Technologies Corporation
Inventor： Nicholas R. Leslie , Mark J. Rogers , Philip Robert Rioux
CPC classification number: F04D29/526 , F01D11/08 , F01D11/12 , F01D11/122 , F01D11/18 , F01D11/24 , F04D29/164 , F04D29/321 , F05D2220/32
Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.
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22.发明申请公开(公告)号：US20160123187A1
公开(公告)日：2016-05-05
申请号：US14893801
申请日：2014-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas R. Leslie , Neil L. Tatman
CPC classification number: F01D25/145 , F01D11/08 , F01D25/08 , F01D25/26 , F05D2220/32 , F05D2240/15 , F05D2260/231 , Y02T50/675
Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment.
Abstract translation: 用于燃气涡轮发动机的隔热罩组件包括围绕轴线限定的第一隔热板段和围绕该轴限定的第二隔热板段。 在第一隔热片段和第二隔热片段之间限定双周向搭接接头。
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