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公开(公告)号：US10774874B2
公开(公告)日：2020-09-15
申请号：US16055333
申请日：2018-08-06
发明人： Sean Christopher Binion , Steven Douglas Johnson , David Vickery Parker , Stephen Joseph Waymeyer , Nathan Evan McCurdy Gibson
IPC分类号： F16C32/06 , F01D25/16 , F01D25/22 , F02C7/06 , F16C17/12 , F16C33/10 , F16C29/02 , F01D25/18 , F16C37/00
摘要： A bearing assembly including a body defining an outer surface, an inner surface, and an aft surface is generally provided. A first inlet opening is defined through the outer surface in fluid communication with a first internal passage defined by a first internal wall. The first internal passage is in fluid communication with a first outlet opening defined through the inner surface. A second inlet opening is defined through the inner surface in fluid communication with a second internal passage defined by a second internal wall. The second internal passage is in fluid communication with a second outlet opening defined through the aft surface.
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公开(公告)号：US20140140822A1
公开(公告)日：2014-05-22
申请号：US13679093
申请日：2012-11-16
IPC分类号： F01D9/00
CPC分类号： F01D9/00 , F01D5/143 , F01D17/162
摘要： A contoured stator shroud has a stator chord overhang having a surface which varies in elevation forming a plurality of surface contours, wherein the contours reduce clearance between adjacent vanes during off design performance positioning of the vanes.
摘要翻译： 成型定子护罩具有定子弦突出端，其具有在仰角上变化的表面形成多个表面轮廓，其中轮廓在叶片的非设计性能定位期间减小相邻叶片之间的间隙。
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公开(公告)号：US10422345B2
公开(公告)日：2019-09-24
申请号：US15101633
申请日：2014-10-17
摘要： A diffuser for a centrifugal compressor including an annular diffuser housing having a plurality of diffuser flow passages therethrough the housing. Each passage including a throat portion and a diffusing section with upstream and downstream diffusing portions. A diffusing passage centerline includes a linear portion extending downstream through the throat portion and the upstream diffusing portion and a curved portion of the diffusing passage centerline extending downstream from the centerline linear portion through the downstream diffusing portion. The diffuser flow passages may have an equivalent cone angle varying non-linearly or more particularly curvilinearly downstream along curved portion. The downstream diffusing portion may be flared.
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公开(公告)号：US10167725B2
公开(公告)日：2019-01-01
申请号：US14861522
申请日：2015-09-22
发明人： Robert Francis Manning , Victor Hugo Silva Correia , Jared Peter Buhler , Byron Andrew Pritchard, Jr. , William Collins Vining , Corey Bourassa , Gregory Michael Laskowski , David Vickery Parker
摘要： An engine component for a turbine engine includes a particle collector having a substrate configured to retain at least some particles from a particle-laden stream passing through a portion of the engine. A fluid bypass around the substrate of the collector enables the particle-laden stream to bypass the substrate if the substrate is filled with particles.
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公开(公告)号：US10036319B2
公开(公告)日：2018-07-31
申请号：US14867379
申请日：2015-09-28
发明人： Robert Carl Murray , Corey Bourassa , David Vickery Parker , Byron Andrew Pritchard, Jr. , Jonathan Russell Ratzlaff , William Collins Vining , Erich Alois Krammer
CPC分类号： F02C7/052 , B01D45/12 , B01D45/16 , B01D50/002 , B04C3/00 , B04C3/04 , B04C3/06 , B04C2003/006
摘要： A separator assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle separator for separating the fluid stream into a reduced-particle stream and a particle-laden stream, and emitting the particle-laden stream through a scavenge outlet. Another particle remover is fluidly coupled to the scavenge outlet to remove more particles from the air stream.
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公开(公告)号：US20200248571A1
公开(公告)日：2020-08-06
申请号：US16804641
申请日：2020-02-28
发明人： Christopher David King , David Vickery Parker , John Alan Manteiga , Matthew Brian Surprenant , Megan Lynn Williams , Awot Michael Berhe , Jesse Jacob Ollove
IPC分类号： F01D9/02 , F01D9/04 , B22F3/105 , B22F5/00 , B33Y80/00 , B33Y10/00 , B22F5/10 , F04D29/02 , F04D29/44
摘要： A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.
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公开(公告)号：US20190107046A1
公开(公告)日：2019-04-11
申请号：US15725327
申请日：2017-10-05
摘要： An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.
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8.发明申请公开(公告)号：US20180215475A1
公开(公告)日：2018-08-02
申请号：US15421692
申请日：2017-02-01
发明人： Matthew John Hurt , Robert Gregory Carita , Thomas Edward Brinson , Matthew Robert Cerny , Amit Kumar Misra-Martinez , David Vickery Parker , Alejandro Yatzail Perez Valdez
CPC分类号： B64D13/08 , B64D41/00 , B64D2013/0611 , B64D2013/0644 , F02C6/08 , F02C9/18 , F05D2220/50 , F05D2220/76 , Y02T50/56
摘要： Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.
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公开(公告)号：US11186382B2
公开(公告)日：2021-11-30
申请号：US16179148
申请日：2018-11-02
发明人： Peter Allen Andrews, Jr. , Ethan Patrick O'Connor , Daniel Alan Niergarth , Brandon Wayne Miller , Christian Xavier Stevenson , David Vickery Parker
摘要： An engine includes a stripping gas source, a combustion section, and a fuel oxygen conversion unit positioned upstream of the combustion section, the fuel oxygen conversion unit defining a stripping gas flowpath in airflow communication with the stripping gas source. The fuel oxygen conversion unit includes a contactor defining a fuel inlet, a gas inlet in airflow communication with the stripping gas flowpath, and a fuel gas mixture outlet; and a fuel gas separator defining a fuel gas mixture inlet for receiving a fuel gas mixture from the contactor, a liquid fuel outlet, and a stripping gas outlet; wherein the stripping gas flowpath receives substantially all of a stripping gas flow therethrough from the stripping gas source and provides the stripping gas flow to the contactor.
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公开(公告)号：US20210340913A1
公开(公告)日：2021-11-04
申请号：US16864349
申请日：2020-05-01
发明人： Peter Allen Andrews, JR. , Ethan Patrick O'Connor , David Vickery Parker , Brandon Wayne Miller , Richard Alan Wesling , Christian Xavier Stevenson
摘要： A fuel delivery system for a gas turbine engine including a fuel oxygen reduction unit is provided. The fuel oxygen reduction unit defines a liquid fuel flowpath and a stripping gas flowpath and is configured to transfer an oxygen content of a fuel flow through the liquid fuel flowpath to a stripping gas flow through the stripping gas flowpath. The fuel oxygen reduction unit includes an impeller in airflow communication with the stripping gas flowpath for circulating the stripping gas flow through the stripping gas flowpath; and a turbine coupled to the impeller.
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