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公开(公告)号：US20190085725A1
公开(公告)日：2019-03-21
申请号：US15710261
申请日：2017-09-20
摘要： The present disclosure is directed to a gas turbine engine including a first turbine frame defining one or more first struts extended along a radial direction and a turbine rotor assembly. The turbine rotor assembly defines a rotatable drum surrounding a reduction speed reduction assembly and coupled thereto. The turbine rotor assembly includes a first turbine rotor and a second turbine rotor each disposed on one or more bearing assemblies. The first turbine frame defines a first supply conduit through the first strut providing a flow of fluid to the speed reduction assembly and one or more of the bearing assemblies. The first turbine frame further defines a first scavenge conduit providing an egress of at least a portion of the flow of fluid from one or more of the bearing assemblies.
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公开(公告)号：US20190085702A1
公开(公告)日：2019-03-21
申请号：US15710164
申请日：2017-09-20
发明人： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt , Bhaskar Nanda Mondal
摘要： A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.
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公开(公告)号：US11300368B2
公开(公告)日：2022-04-12
申请号：US16532846
申请日：2019-08-06
发明人： Thomas Kupiszewski , Christopher Charles Glynn , Steven Douglas Johnson , John Andrew Kemme , Mehdi Milani Baladi , Michael Epstein
摘要： A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow 46 to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.
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公开(公告)号：US11255221B2
公开(公告)日：2022-02-22
申请号：US15710261
申请日：2017-09-20
摘要： The present disclosure is directed to a gas turbine engine including a first turbine frame defining one or more first struts extended along a radial direction and a turbine rotor assembly. The turbine rotor assembly defines a rotatable drum surrounding a reduction speed reduction assembly and coupled thereto. The turbine rotor assembly includes a first turbine rotor and a second turbine rotor each disposed on one or more bearing assemblies. The first turbine frame defines a first supply conduit through the first strut providing a flow of fluid to the speed reduction assembly and one or more of the bearing assemblies. The first turbine frame further defines a first scavenge conduit providing an egress of at least a portion of the flow of fluid from one or more of the bearing assemblies.
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公开(公告)号：US11199111B2
公开(公告)日：2021-12-14
申请号：US16901568
申请日：2020-06-15
发明人： Jared Peter Buhler , Christopher Charles Glynn , Corey Bourassa , Monty Lee Shelton , Robert Francis Manning , Victor Hugo Silva Correia
IPC分类号： B01D39/00 , F01D25/32 , B01D46/24 , B01D45/12 , B01D46/42 , F01D25/12 , F01D9/06 , B01D45/08 , B01D45/16 , B01D50/00
摘要： An assembly for removing particles from a fluid stream includes a first particle remover having a main flow outlet emitting a first reduced-particle stream and a scavenge flow outlet emitting a particle-laden stream, as well as a second particle remover fluidly coupled to the scavenge flow outlet and emitting a second reduced-particle stream.
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公开(公告)号：US20190249738A1
公开(公告)日：2019-08-15
申请号：US16262222
申请日：2019-01-30
发明人： Leszek Marek Rzeszutek , Christopher Charles Glynn , Darek Tomasz Zatorski , Jakub Jan Broniszewski
CPC分类号： F16F7/08 , F01D11/003 , F01D11/005 , F01D25/04 , F05D2240/55 , F05D2260/96 , F16F2222/04 , F16F2226/04 , F16F2230/30 , F16L55/041
摘要： The present application relates to a frictional damper, a frictional damper assembly and method for installing the frictional damper. The frictional damper comprises a split ring; and a disk spring positioned against the split ring and tensioned by the split ring in an installed state.
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公开(公告)号：US20190085723A1
公开(公告)日：2019-03-21
申请号：US15710191
申请日：2017-09-20
发明人： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt
摘要： A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.
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公开(公告)号：US20190085701A1
公开(公告)日：2019-03-21
申请号：US15710109
申请日：2017-09-20
发明人： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt
摘要： A turbomachine includes a turbine section including a turbine, the turbine having a plurality of turbine rotor blades spaced along the axial direction, each turbine rotor blade extending generally along the radial direction between a radially inner end and a radially outer end. The plurality of turbine rotor blades include a first turbine rotor blade; and a second turbine rotor blade spaced from the first turbine rotor blade along the axial direction, the radially outer end of the first turbine rotor blade coupled to the radially outer end of the second turbine rotor blade. The plurality of turbine rotor blades additionally includes a third turbine rotor blade spaced from the second turbine rotor blade along the axial direction, the radially inner end of the second turbine rotor blade coupled to the radially inner end of the third turbine rotor blade.
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公开(公告)号：US11248675B2
公开(公告)日：2022-02-15
申请号：US16262222
申请日：2019-01-30
发明人： Leszek Marek Rzeszutek , Christopher Charles Glynn , Darek Tomasz Zatorski , Jakub Jan Broniszewski
摘要： The present application relates to a frictional damper, a frictional damper assembly and method for installing the frictional damper. The frictional damper comprises a split ring; and a disk spring positioned against the split ring and tensioned by the split ring in an installed state.
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公开(公告)号：US11156128B2
公开(公告)日：2021-10-26
申请号：US16108732
申请日：2018-08-22
摘要： A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.
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