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公开(公告)号：US20170211399A1
公开(公告)日：2017-07-27
申请号：US15002782
申请日：2016-01-21
发明人： Mohsin Hasan Khan , Sarasija Sudharsan , Ganesh Seshadri , Ravikanth Avancha , Lyle Douglas Dailey
CPC分类号： F01D9/041 , F01D5/141 , F01D5/143 , F01D25/162 , F01D25/246 , F02C7/20 , F05D2220/32 , F05D2240/90 , F05D2250/71 , Y02T50/673
摘要： A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.
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公开(公告)号：US11274563B2
公开(公告)日：2022-03-15
申请号：US15002782
申请日：2016-01-21
发明人： Mohsin Hasan Khan , Sarasija Sudharsan , Ganesh Seshadri , Ravikanth Avancha , Lyle Douglas Dailey
摘要： A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.
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公开(公告)号：US20230340906A1
公开(公告)日：2023-10-26
申请号：US17713649
申请日：2022-04-05
发明人： Paul Hadley Vitt , Lyle Douglas Dailey , Matteo Renato Usseglio , Andreas Peters , Jonathan Ong
CPC分类号： F02C3/067 , F02C7/141 , F02C7/36 , F05D2220/60 , F05D2260/213 , F05D2260/40311
摘要： A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.
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公开(公告)号：US20180347403A1
公开(公告)日：2018-12-06
申请号：US15609368
申请日：2017-05-31
发明人： Mahendran Manoharan , Ganesh Seshadri , Robert J. Beacock , Lyle Douglas Dailey , Ravikanth Avancha
摘要： An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile.
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