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公开(公告)号：US20220289394A1
公开(公告)日：2022-09-15
申请号：US17571752
申请日：2022-01-10
IPC分类号： B64D27/24 , F01D15/10 , F01D25/18 , F02K5/00 , F04D25/06 , F02C7/32 , B64D27/12 , F02C7/24 , F02K3/06 , F04D19/02 , H02K1/27 , H02K7/18
摘要： A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US10344674B2
公开(公告)日：2019-07-09
申请号：US14990871
申请日：2016-01-08
摘要： A transduct segment, that can include a main tube extending from a first end to a second end and defining a hollow passageway therethrough, a lower platform attached to an outer surface of the main tube on first side of an aperture defined within the main tube, and an upper platform attached to the outer surface of the main tube on second side of the aperture that is opposite of the first side, is provided. The upper platform is integral with the lower platform to define a supply channel therebetween, and the supply channel is in fluid communication with the hollow passageway of the main tube through the aperture defined by the main tube. The lower platform and the upper platform define an interface defining a plurality of channels in fluid communication with the hollow passageway defined by the main tube.
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公开(公告)号：US10126062B2
公开(公告)日：2018-11-13
申请号：US14990884
申请日：2016-01-08
IPC分类号： F28F3/00 , F28D1/02 , F02C7/18 , F28D1/047 , F01D25/12 , F02C7/141 , F28F9/02 , F28D9/00 , F28D21/00
摘要： An annular heat exchanger for a gas turbine engine is provided. The annular heat exchanger can include a first annular ring comprising a first main tube defined by a plurality of transduct segments; a second annular ring comprising a second main tube defined by a plurality of transduct segments and a curvilinear plate defining at least one channel therein that is in fluid communication with a transduct segment of the first main tube and a transduct segment of the second main tube.
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公开(公告)号：US10093428B2
公开(公告)日：2018-10-09
申请号：US15242844
申请日：2016-08-22
摘要： A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.
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公开(公告)号：US20170367218A1
公开(公告)日：2017-12-21
申请号：US15397234
申请日：2017-01-03
CPC分类号： F28D15/04 , F28D7/0025 , F28D7/0066 , F28D9/0093 , F28D15/0233 , F28D15/0266 , F28D15/0275 , F28D20/021 , F28F1/045 , F28F7/02 , F28F2270/00 , H01L23/427 , H05K7/20309 , H05K7/20318 , H05K7/20336 , Y02E60/145
摘要： A heat exchanger includes a core defining a first passageway and a second passageway. The core includes a plurality of unit cells coupled together. Each unit cell of the plurality of unit cells includes a first wall and a second wall. The second wall is spaced from the first wall. The first wall at least partially defines a first passageway portion and a second passageway portion. The second wall at least partially defines the second passageway portion. The second wall extends about the first wall such that the first passageway portion is nested within the second passageway portion.
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公开(公告)号：US20190217963A1
公开(公告)日：2019-07-18
申请号：US16366453
申请日：2019-03-27
IPC分类号： B64D27/24 , F02C7/32 , F02K3/06 , F04D19/02 , B64D27/12 , H02K1/27 , F04D25/06 , F02K5/00 , F01D25/18 , F01D15/10 , F02C7/24 , H02K7/18
CPC分类号： B64D27/24 , B64D27/12 , B64D2027/026 , F01D15/10 , F01D25/183 , F02C7/24 , F02C7/32 , F02K3/06 , F02K5/00 , F04D19/02 , F04D25/06 , F05D2220/323 , F05D2220/768 , F05D2260/98 , H02K1/27 , H02K7/1823
摘要： A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US10184400B2
公开(公告)日：2019-01-22
申请号：US14990898
申请日：2016-01-08
IPC分类号： F02C7/18 , F02C6/08 , F01D25/12 , F02C7/141 , F28D1/03 , F01D25/14 , F02C7/12 , F28F9/02 , F28D7/00 , F28D9/00 , F28D7/16 , F28D21/00 , F28F9/04
摘要： Methods of cooling a hot fluid in an annular duct of a gas turbine engine are provided. The method can include directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, and passing a cooling fluid through the annular duct such that the cooling fluid passes between the radially layered cooling channels. Additionally or alternatively, the method can include passing the hot fluid into a first inner radial tube, through a plurality of cooling channels defined within a plurality of curvilinear plates that are radially layered within the annular duct, and into a second inner radial tube; and passing a cooling fluid through the annular duct.
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公开(公告)号：US10071811B2
公开(公告)日：2018-09-11
申请号：US15242811
申请日：2016-08-22
CPC分类号： B64D27/12 , B64C21/06 , B64D27/18 , B64D27/24 , B64D29/04 , B64D33/00 , B64D2027/026 , B64D2033/0226 , B64D2221/00 , F01D9/065 , F01D15/10 , F01D25/162 , F02C3/04 , F02C7/16 , F02C7/32 , F02K5/00 , F04D25/06 , F05D2220/32 , F05D2220/76 , F05D2260/20 , F05D2260/98 , Y02T50/676
摘要： A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.
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公开(公告)号：US20180051702A1
公开(公告)日：2018-02-22
申请号：US15242811
申请日：2016-08-22
CPC分类号： B64D27/12 , B64D27/18 , B64D27/24 , F01D9/065 , F01D15/10 , F01D25/162 , F02C3/04 , F02C7/16 , F02C7/32 , F02K5/00 , F04D25/06 , F05D2220/32 , F05D2220/76 , F05D2260/20 , F05D2260/98
摘要： A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.
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公开(公告)号：US20170198638A1
公开(公告)日：2017-07-13
申请号：US14990898
申请日：2016-01-08
IPC分类号： F02C7/18
CPC分类号： F02C7/185 , F01D25/12 , F01D25/14 , F02C6/08 , F02C7/12 , F02C7/141 , F05D2260/221 , F28D1/035 , F28D7/005 , F28D7/16 , F28D9/0006 , F28D2021/0026 , F28F9/02 , F28F9/026 , F28F9/04 , Y02T50/675
摘要： Methods of cooling a hot fluid in an annular duct of a gas turbine engine are provided. The method can include directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, and passing a cooling fluid through the annular duct such that the cooling fluid passes between the radially layered cooling channels. Additionally or alternatively, the method can include passing the hot fluid into a first inner radial tube, through a plurality of cooling channels defined within a plurality of curvilinear plates that are radially layered within the annular duct, and into a second inner radial tube; and passing a cooling fluid through the annular duct.
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