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公开(公告)号：US20210108798A1
公开(公告)日：2021-04-15
申请号：US16599751
申请日：2019-10-11
Inventor： Ted J. Freeman , Aaron D. Sippel , Jack D. Petty , Gregory W. Zeaton
IPC: F23R3/00
Abstract: A combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.
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公开(公告)号：US20210108533A1
公开(公告)日：2021-04-15
申请号：US17113235
申请日：2020-12-07
Inventor： Jun Shi , Li Li , Ted J. Freeman
Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.
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公开(公告)号：US10934891B2
公开(公告)日：2021-03-02
申请号：US15803337
申请日：2017-11-03
Inventor： Ted J. Freeman , Aaron D. Sippel , Daniel K. Vetters , David J. Thomas , Alexandra R. Baucco
Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
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公开(公告)号：US10934863B2
公开(公告)日：2021-03-02
申请号：US16189682
申请日：2018-11-13
Inventor： Daniel K. Morrison , Ted J. Freeman
IPC: F01D5/30
Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials.
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公开(公告)号：US10927689B2
公开(公告)日：2021-02-23
申请号：US16119388
申请日：2018-08-31
Inventor： David J. Thomas , Aaron D. Sippel , Ted J. Freeman
Abstract: A vane assembly for a gas turbine engine is provided having an outer casing and an inner casing radially spaced apart from the outer casing. An airfoil extends radially between the outer casing and the inner casing. The airfoil includes a spar having an outer endwall positioned adjacent the outer casing and an inner endwall positioned adjacent the inner casing. A pressure side and a suction side extend between the inner endwall and the outer endwall. A ceramic matrix composite cover has a pressure side extending along the pressure side of the spar and a suction side extending along the suction side of the spar.
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Patent Agency Ranking
公开(公告)号：US10704404B2
公开(公告)日：2020-07-07
申请号：US15076127
申请日：2016-03-21
Inventor： Jun Shi , Ted J. Freeman , David J. Thomas
Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a pressure-activated seal. The pressure-activated seal is arranged in a channel formed between a first component and a second component that opens toward the high pressure zone.
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公开(公告)号：US10697315B2
公开(公告)日：2020-06-30
申请号：US15937194
申请日：2018-03-27
Inventor： Ted J. Freeman , Aaron D. Sippel
Abstract: A blade track used in gas turbine engines to define an outer boundary of the primary gas path through a turbine section of a gas turbine engine is disclosed. The blade track includes segments comprising ceramic matrix composite materials that are assembled such that the blade track segments keystone against one another to provide a self-supporting full hoop assembly. Circumferentially-extending splines may be used to couple adjacent segments to one. Also disclosed are other heat shielding assemblies used in gas turbine engines that share features with the illustratively disclosed blade track.
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公开(公告)号：US10655482B2
公开(公告)日：2020-05-19
申请号：US15015690
申请日：2016-02-04
Inventor： Ted J. Freeman , Jeffrey A. Walston , Jun Shi , Tara G. Schetzel
Abstract: A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars. The outer and inner end walls cooperate to form a flowpath.
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公开(公告)号：US10655479B2
公开(公告)日：2020-05-19
申请号：US16032848
申请日：2018-07-11
Inventor： Aaron D. Sippel , Ted J. Freeman
Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.
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公开(公告)号：US20200080434A1
公开(公告)日：2020-03-12
申请号：US16128753
申请日：2018-09-12
Inventor： David J. Thomas , Ted J. Freeman , Aaron D. Sippel
IPC: F01D9/04
Abstract: A vane assembly for use in a gas turbine engine includes an airfoil, a strut, and a support member. The airfoil is configured to interact with gases flowing through a primary gas path of the engine. The strut is located in an interior region of the airfoil and configured to carry loads that act on the airfoil by the gases. The support member is configured to compensate for relative thermal expansion between the components of the vane assembly caused by heat generated during use of the engine to locate the airfoil radially in the primary gas path.
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