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公开(公告)号：US20200072063A1
公开(公告)日：2020-03-05
申请号：US16119504
申请日：2018-08-31
Inventor： Aaron D. Sippel , Ted J. Freeman , Loic Fabries
IPC: F01D5/30
Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system that includes a plurality of platforms and pins. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the wheel to define a flow path of the gas turbine engine and the pins extend into the platforms and the disk to couple the platforms with the disk.
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公开(公告)号：US10563522B2
公开(公告)日：2020-02-18
申请号：US14797916
申请日：2015-07-13
Inventor： David J. Thomas , Ted J. Freeman , Jeffrey A. Walston
Abstract: Stationary vanes and rotating blades of a gas turbine engine are disclosed that include airfoils formed from ceramic matrix composite materials. The airfoils include at least one layer of ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the matrix material. A core of the airfoils is surrounded by the at least one layer of ceramic-containing fiber/matrix material.
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公开(公告)号：US20200018177A1
公开(公告)日：2020-01-16
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：US20190390557A1
公开(公告)日：2019-12-26
申请号：US16016208
申请日：2018-06-22
Inventor： Jun Shi , 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：US10428674B2
公开(公告)日：2019-10-01
申请号：US15420793
申请日：2017-01-31
Inventor： Aaron D. Sippel , Brian J. Shoemaker , Ted J. Freeman
Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.
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Patent Agency Ranking
公开(公告)号：US10408084B2
公开(公告)日：2019-09-10
申请号：US15056345
申请日：2016-02-29
Inventor： David J. Thomas , Ted J. Freeman , Jeffrey A. Walston , Andrew J. Lazur
Abstract: A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.
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公开(公告)号：US10370994B2
公开(公告)日：2019-08-06
申请号：US15159163
申请日：2016-05-19
Inventor： David J. Thomas , Joseph P. Lamusga , Ted J. Freeman , Aaron D. Sippel
Abstract: An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap.
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公开(公告)号：US20190093512A1
公开(公告)日：2019-03-28
申请号：US16057221
申请日：2018-08-07
Inventor： Aaron D. Sippel , Bruce E. Varney , Ted J. Freeman , Kevin P. Holley
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 segments and joints.
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公开(公告)号：US20190032503A1
公开(公告)日：2019-01-31
申请号：US16043708
申请日：2018-07-24
Inventor： Jun Shi , Li Li , Ted J. Freeman
Abstract: An example high-performance system may include an example high-performance component. The high-performance component may include a substrate defining a channel. The channel defines a leading ramp and a trailing ramp. The example high-performance component includes an abradable track between the leading and the trailing ramps. The abradable track includes a porous abradable composition. The example high-performance system may include a rotating component configured to contact and abrade the abradable track. An example technique for forming the abradable track includes thermal spraying a precursor composition at the channel to form the abradable track.
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公开(公告)号：US20180216481A1
公开(公告)日：2018-08-02
申请号：US15420793
申请日：2017-01-31
Inventor： Aaron D. Sippel , Brian J. Shoemaker , Ted J. Freeman
CPC classification number: F01D11/122 , F01D21/003 , F05D2230/90 , F05D2240/11 , F05D2260/80 , F05D2300/6033
Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.
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