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公开(公告)号：US11415014B2
公开(公告)日：2022-08-16
申请号：US17170339
申请日：2021-02-08
摘要： The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.
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公开(公告)号：US11286798B2
公开(公告)日：2022-03-29
申请号：US16545791
申请日：2019-08-20
发明人： Michael J. Whittle , Daniel K. Vetters , Ted J. Freeman , Eric Koenig , Jeff Crutchfield , Jeffrey A. Walston , David J. Thomas
摘要： An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.
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公开(公告)号：US10858949B2
公开(公告)日：2020-12-08
申请号：US16129294
申请日：2018-09-12
发明人： Jeffrey A. Walston , Andrew Hurst
摘要： A turbine shroud assembly includes a blade track, a multi-piece carrier and a mount assembly. The carrier includes a fore body and an aft body. Attachment pin of the mount assembly extends between fore body and aft body and through an eyelet in an attachment post of the blade track.
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公开(公告)号：US10767497B2
公开(公告)日：2020-09-08
申请号：US16124970
申请日：2018-09-07
摘要： Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components.
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公开(公告)号：US11274567B2
公开(公告)日：2022-03-15
申请号：US16385725
申请日：2019-04-16
发明人： Daniel K. Vetters , Aaron D. Sippel , David J. Thomas , Andrew J. Eifert , Paul A. Davis , Simon L. Jones , Peter Broadhead , Bruce E. Varney , Jeffrey A. Walston , Steven Hillier
IPC分类号： F01D11/18 , F01D11/12 , C04B35/83 , C04B35/01 , C04B35/565 , C04B35/80 , F01D25/12 , F01D25/00 , F04D29/16 , F04D29/52
摘要： A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
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公开(公告)号：US11149560B2
公开(公告)日：2021-10-19
申请号：US16545784
申请日：2019-08-20
发明人： Michael J. Whittle , Daniel K. Vetters , Ted J. Freeman , Eric Koenig , Jeff Crutchfield , Jeffrey A. Walston , David J. Thomas
摘要： An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform.
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公开(公告)号：US20200088050A1
公开(公告)日：2020-03-19
申请号：US16133226
申请日：2018-09-17
摘要： The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.
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公开(公告)号：US10563535B2
公开(公告)日：2020-02-18
申请号：US15090134
申请日：2016-04-04
发明人： Daniel K. Vetters , Aaron D. Sippel , David J. Thomas , Andrew J. Eifert , Paul A. Davis , Simon L. Jones , Peter Broadhead , Bruce E. Varney , Jeffrey A. Walston , Steven Hillier
摘要： A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
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公开(公告)号：US20210062663A1
公开(公告)日：2021-03-04
申请号：US16545791
申请日：2019-08-20
发明人： Michael J. Whittle , Daniel K. Vetters , Ted J. Freeman , Eric Koenig , Jeff Crutchfield , Jeffrey A. Walston , David J. Thomas
摘要： An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.
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公开(公告)号：US10934870B2
公开(公告)日：2021-03-02
申请号：US16133226
申请日：2018-09-17
摘要： The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.
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