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公开(公告)号：US11725535B2
公开(公告)日：2023-08-15
申请号：US16107012
申请日：2018-08-21
Inventor： Ted J. Freeman , Bruce E. Varney , David J. Thomas , Jeffrey A. Walston
CPC classification number: F01D25/005 , F01D5/282 , F01D5/284 , F01D9/042 , F01D9/065 , F05D2230/642 , F05D2300/6033 , Y02T50/60
Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil.
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公开(公告)号：US11713694B1
公开(公告)日：2023-08-01
申请号：US18072145
申请日：2022-11-30
Applicant: Rolls-Royce Corporation
Inventor： Ted J. Freeman , Aaron D. Sippel
CPC classification number: F01D25/243 , F01D11/08 , F01D25/005 , F01D25/246 , F05D2230/60 , F05D2260/30 , F05D2300/6033
Abstract: A turbine shroud assembly includes a carrier assembly, a blade track segment, and a retainer. The carrier assembly is arranged circumferentially at least partway around an axis and includes a fore carrier segment and an aft carrier segment coupled with the fore carrier. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the fore carrier segment, the blade track segment, and the aft carrier segment to couple the blade track segment with the carrier assembly.
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公开(公告)号：US20230026089A1
公开(公告)日：2023-01-26
申请号：US17960529
申请日：2022-10-05
Applicant: Rolls-Royce Corporation
Inventor： Ted J. Freeman , Aaron D. Sippel , David J. Thomas
IPC: F01D11/08
Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.
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公开(公告)号：US11466858B2
公开(公告)日：2022-10-11
申请号：US16599756
申请日：2019-10-11
Inventor： Ted J. Freeman , Aaron D. Sippel , Jack D. Petty , Gregory W. Zeaton
Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.
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公开(公告)号：US11441441B1
公开(公告)日：2022-09-13
申请号：US17351736
申请日：2021-06-18
Applicant: Rolls-Royce Corporation
Inventor： Ted J. Freeman , Aaron D. Sippel , David J. Thomas
IPC: F01D11/08
Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.
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Patent Agency Ranking
公开(公告)号：US11346237B1
公开(公告)日：2022-05-31
申请号：US17330127
申请日：2021-05-25
Applicant: Rolls-Royce Corporation
Inventor： Ted J. Freeman , Aaron D. Sippel , David J. Thomas
Abstract: A turbine shroud assembly includes a carrier assembly, a blade track assembly, and a first biasing member. The carrier assembly includes a carrier segment having an outer wall, a first mount flange and a second mount flange having a chordal seal. The blade track assembly includes a blade track segment and a first mount pin. The first biasing member is arranged axially between and engaged with the carrier segment and the blade track assembly so as to bias an attachment feature of the black track segment into engagement with the chordal seal of the second mount flange.
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公开(公告)号：US11346232B2
公开(公告)日：2022-05-31
申请号：US15959997
申请日：2018-04-23
Inventor： Aaron D. Sippel , Ted J. Freeman
Abstract: The present disclosure relates to turbine blades adapted for use in gas turbine engines. In particular, this disclosure is directed to turbine blades that include components made from ceramic matrix composite materials and that incorporate abradable materials.
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118.发明授权公开(公告)号：US11326474B2
公开(公告)日：2022-05-10
申请号：US16703378
申请日：2019-12-04
Inventor： Ted J. Freeman , Thomas Nixon , Jay Lane , Aaron D. Sippel , Robert F. Proctor
IPC: F01D25/24
Abstract: A gas turbine engine includes a turbine shroud assembly with a carrier and a plurality of turbine shroud segments. Each turbine shroud segment includes a blade track segment and a mount assembly. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a shroud wall and a mount post that extends radially away from the shroud wall. The mount assembly is configured to couple the blade track segment with the carrier.
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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：US11268389B2
公开(公告)日：2022-03-08
申请号：US15978807
申请日：2018-05-14
Inventor： Ted J. Freeman , Aaron D. Sippel , Bruce E. Varney
IPC: F01D5/30
Abstract: A turbine blade is secured with a turbine disk by a retention assembly. The turbine blade includes a blade stem and the disk includes at least one mount post for mounting of the turbine blade. The retention assembly is secured with the disk by forming a diffusion joint with the disk.
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