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公开(公告)号：US20200063577A1
公开(公告)日：2020-02-27
申请号：US16109237
申请日：2018-08-22
Inventor： Michael J. Whittle , Alexander Wong , Anthony Razzell , Ted J. Freeman
Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.
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公开(公告)号：US11286792B2
公开(公告)日：2022-03-29
申请号：US16526274
申请日：2019-07-30
Applicant: Rolls-Royce plc
Inventor： Anthony Razzell , Michael J. Whittle , Ian M. Edmonds
Abstract: An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a hollow tube that extends through the body to define a cooling passage that extends from the cooling cavity through the airfoil to provide fluid communication between the cooling cavity and a gas path environment surrounding the airfoil.
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公开(公告)号：US10934859B2
公开(公告)日：2021-03-02
申请号：US16111749
申请日：2018-08-24
Inventor： Ted J. Freeman , Anthony Razzell , Michael J. Whittle
Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disk.
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公开(公告)号：US10808553B2
公开(公告)日：2020-10-20
申请号：US16189690
申请日：2018-11-13
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Anthony Razzell
Abstract: 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：US10934862B2
公开(公告)日：2021-03-02
申请号：US16109237
申请日：2018-08-22
Inventor： Michael J. Whittle , Alexander Wong , Anthony Razzell , Ted J. Freeman
IPC: F01D5/30
Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.
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Patent Agency Ranking
公开(公告)号：US20210032995A1
公开(公告)日：2021-02-04
申请号：US16526274
申请日：2019-07-30
Applicant: Rolls-Royce plc
Inventor： Anthony Razzell , Michael J. Whittle , Ian M. Edmonds
Abstract: An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a plurality of cooling passages that extend from the cooling cavity through the airfoil.
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公开(公告)号：US10767495B2
公开(公告)日：2020-09-08
申请号：US16265575
申请日：2019-02-01
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Paul Morrell , Anthony Razzell , Matthew Adams
Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a turbine vane arranged around the support strut. The support strut is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support strut.
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公开(公告)号：US20190323371A1
公开(公告)日：2019-10-24
申请号：US15959906
申请日：2018-04-23
Applicant: Rolls-Royce High Temperature Composites Inc. , Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce plc
Inventor： Stephen Harris , Aaron D. Sippel , Ted J. Freeman , Anthony Razzell
Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. The blades each fit within slots formed in the rotor disk to couple the blades to the rotor disk. Platform segments are arranged about each of the blades.
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公开(公告)号：US11319822B2
公开(公告)日：2022-05-03
申请号：US16868110
申请日：2020-05-06
Inventor： Ted J. Freeman , Jay E. Lane , Michael J. Whittle , Anthony Razzell
IPC: F01D9/04
Abstract: A vane assembly for use with a gas turbine engine includes an outer wall, an inner wall, and a plurality of airfoils. The outer wall and the inner wall extend at least partway about an axis. At least one of the airfoils is coupled with the outer end wall and the inner end wall to transmit force loads through the vane assembly.
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公开(公告)号：US11230937B2
公开(公告)日：2022-01-25
申请号：US16876852
申请日：2020-05-18
Inventor： Ted J. Freeman , Aaron D. Sippel , Alexandra Baucco , Anthony Razzell , Michael J. Whittle , Jeffrey Crutchfield
Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.
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