-
公开(公告)号：US10584605B2
公开(公告)日：2020-03-10
申请号：US15672991
申请日：2017-08-09
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc. , Rolls-Royce plc
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Joseph P. Lamusga , Brian J. Shoemaker , Steven Hillier
Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
-
公开(公告)号：US20200063571A1
公开(公告)日：2020-02-27
申请号：US16113502
申请日：2018-08-27
Applicant: Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc.
Inventor： Ted J. Freeman , Aaron D. Sippel , Robert J. Shinavski
Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes an airfoil and a tip to discourage air leakage over the tip of the turbine blade. The turbine blade is designed considering weight and strength to include a lightening hole.
-
公开(公告)号：US20200024973A1
公开(公告)日：2020-01-23
申请号：US16244874
申请日：2019-01-10
Inventor： Richard C. Uskert , Kang N. Lee , Ted J. Freeman
Abstract: A blade and method for producing the blade for a gas turbine engine are described herein. The blade may include a composite airfoil. The airfoil may comprise a ceramic material, and a distal end. A tip may extend from the distal end of the airfoil. The tip of the airfoil may comprise a substantially porous structure and may comprise infiltrated material extending from an airfoil preform to a tip preform to join the airfoil preform and the tip preform.
-
公开(公告)号：US20190390558A1
公开(公告)日：2019-12-26
申请号：US16013385
申请日：2018-06-20
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas
Abstract: A turbine vane assembly includes an airfoil, a support strut, and an inner seal panel. The airfoil is formed to include an interior region of the airfoil. The support strut is located in the interior region of the airfoil and configured to carry loads that act on the airfoil. The inner seal panel extends at least partway about the axis to resist fluid communication between a region upstream of the inner seal panel and a region downstream of the inner seal panel.
-
公开(公告)号：US10465534B2
公开(公告)日：2019-11-05
申请号：US15172997
申请日：2016-06-03
Inventor： Ted J. Freeman , Thomas D. Nixon , Sean E. Landwehr , Aaron D. Sippel , Donald W. Reinhart
Abstract: A ceramic matrix composite component and a ceramic insert, and a method for producing the same. The ceramic matrix composite component may include an exterior surface comprising silicon fibers in a silicon carbide matrix. The insert may include a continuous porosity bonded to the exterior surface of the ceramic matrix composite component. The silicon carbide matrix of the ceramic matrix composite component may extend into the porosity of the ceramic insert to bond the ceramic insert to the ceramic matrix composite component.
-
Patent Agency Ranking
公开(公告)号：US10309257B2
公开(公告)日：2019-06-04
申请号：US15055004
申请日：2016-02-26
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Richard C. Uskert , Peter J. Loftus , Andrew J. Lazur
IPC: F01D25/24
Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier.
-
公开(公告)号：US10196919B2
公开(公告)日：2019-02-05
申请号：US15004448
申请日：2016-01-22
Inventor： Mark O'Leary , Daniel K. Vetters , Matthew R. Brandt , Ted J. Freeman
Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
-
公开(公告)号：US10184352B2
公开(公告)日：2019-01-22
申请号：US15004436
申请日：2016-01-22
Inventor： Mark O'Leary , Daniel K. Vetters , Matthew R. Brandt , Ted J. Freeman
Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
-
公开(公告)号：US20180371930A1
公开(公告)日：2018-12-27
申请号：US15989666
申请日：2018-05-25
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Aaron D. Sippel , Bruce E. Varney , Ted J. Freeman , Christopher Barrett
Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.
-
公开(公告)号：US10082085B2
公开(公告)日：2018-09-25
申请号：US14543398
申请日：2014-11-17
Inventor： David J. Thomas , Ted J. Freeman
CPC classification number: F02C7/28 , F01D5/282 , F01D11/005 , F02C7/20 , Y02T50/672
Abstract: A gas turbine engine assembly includes a support component, an engine component, and a seal. The annular support component is formed to include a notch. The engine component is mounted in spaced-apart relation to the support component so that a gap is formed between the support component and the engine component. The seal is located in the notch and is adapted to close the gap.
-
-
-
-
-
-
-
-
-
Search Results
293
records
(took 0.024 seconds)
