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公开(公告)号：US20240209789A1
公开(公告)日：2024-06-27
申请号：US18337717
申请日：2023-06-20
申请人： ROLLS-ROYCE plc
CPC分类号： F02C7/224 , F02C7/06 , F02C7/32 , F05D2260/221 , F05D2260/98
摘要： A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a main gearbox receiving an input from the core shaft and outputting drive to the fan via the fan shaft; a primary oil loop system to supply oil to lubricate the main gearbox; and a heat exchange system arranged to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes transferring 200 to 600 KJ/m3 of heat from the oil to the fuel, using the heat exchange system, at cruise conditions, which may facilitate control of the oil temperature on entry to the main gearbox.
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公开(公告)号：US11959493B2
公开(公告)日：2024-04-16
申请号：US17447866
申请日：2021-09-16
CPC分类号： F04D29/5806 , F04D25/04 , F04D25/06 , H02K9/223 , F05D2220/40 , F05D2220/76 , F05D2260/221
摘要： A turbomachine includes a housing with an e-machine housing. Also, the turbomachine includes a rotating group supported for rotation within the housing. Moreover, the turbomachine includes an e-machine that is configured as at least one of an electric motor and an electric generator, that is operatively coupled to the rotating group, and that includes a stator that is housed within the e-machine housing. Furthermore, the turbomachine includes a thermal bridge member that extends between the stator and the e-machine housing to define a thermal path for heat to transfer from the stator to the e-machine housing. The e-machine housing includes a thermal bridge retainer member that defines an outer boundary of the thermal bridge member.
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公开(公告)号：US11933222B2
公开(公告)日：2024-03-19
申请号：US16267972
申请日：2019-02-05
发明人： Francesco Caratelli
CPC分类号： F02C7/20 , F01D25/145 , F01D25/26 , F02C7/18 , F02C7/24 , F02K3/065 , F05D2210/40 , F05D2260/221 , F05D2260/231 , F05D2270/3032 , F05D2300/614
摘要： An aeroderivative gas turbine provided with a casing, a compressor including a rotor mounted on a generator shaft supported for rotation in the casing, a high pressure turbine arranged in the casing and with a rotor mounted on the generator shaft for co-rotation with the compressor rotor, a combustor, a power turbine arranged in the casing and including a rotor mounted on a turbine shaft to drive a load, wherein a thermal insulation coating is present to reduce heat dispersion through the casing.
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公开(公告)号：US11713683B2
公开(公告)日：2023-08-01
申请号：US17778228
申请日：2021-03-23
发明人： Satoshi Mizukami , Masamitsu Kuwabara , Satoshi Hada , Saki Matsuo , Yoshitaka Uemura , Ryozo Tamura , Yasumasa Kunisada
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2220/32 , F05D2230/10 , F05D2240/30 , F05D2260/202 , F05D2260/221
摘要： A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.
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公开(公告)号：US20190219066A1
公开(公告)日：2019-07-18
申请号：US16331609
申请日：2016-10-07
CPC分类号： F04D29/5806 , A47K10/48 , A47L5/22 , A47L9/00 , F04D17/10 , F04D29/58 , F04D29/584 , F05D2260/221
摘要： An electric blower includes: an electric motor portion including a rotation shaft; a centrifugal impeller; and a heat dissipating portion connecting the centrifugal impeller and the rotation shaft. A boss portion of the centrifugal impeller is provided with a first hole extending in an extending direction of the rotation shaft. The heat dissipating portion includes a first portion connected to an inner circumferential surface of the first hole, and a second portion connected to the first portion in the extending direction and located outside the first hole. A length of the heat dissipating portion in the extending direction is longer than a length of the first hole in the extending direction.
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公开(公告)号：US20190169993A1
公开(公告)日：2019-06-06
申请号：US15832407
申请日：2017-12-05
CPC分类号： F01D5/187 , F02C3/04 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/221
摘要： An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole cluster includes first and second resupply holes that each fluidly interconnect the core and skin passages. The first and second resupply holes intersect one another and terminate in an exit at the skin passage.
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公开(公告)号：US20180306065A1
公开(公告)日：2018-10-25
申请号：US15954746
申请日：2018-04-17
申请人： ROLLS-ROYCE plc
CPC分类号： F01D25/36 , F01D15/10 , F02C7/18 , F05D2220/323 , F05D2220/76 , F05D2260/221 , F05D2260/42
摘要： There is disclosed an auxiliary rotation device 28 for a gas turbine engine 10. The auxiliary rotation device 28 comprises: an electric machine 30 configured to be coupled to a rotor of the gas turbine engine 10; and a dedicated electrical storage device 32 coupled to the electric machine 30. During a period of powered operation of the gas turbine engine 10 the electric machine 30 is configured to act as a generator so as to charge the dedicated electrical storage device 32. Following the period of powered operation of the gas turbine engine 10 the electric machine 30 is configured to act as a motor by discharging the dedicated electrical storage device 32 so as to cause the rotor to rotate for a period of time to provide even cooling of the rotor around its circumference. There is also disclosed a method of cooling a rotor of a gas turbine engine 10 using an auxiliary rotation device 28.
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公开(公告)号：US10006295B2
公开(公告)日：2018-06-26
申请号：US14893795
申请日：2014-05-23
CPC分类号： F01D5/188 , F01D5/02 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2260/202 , F05D2260/221 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.
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公开(公告)号：US09957066B2
公开(公告)日：2018-05-01
申请号：US14621465
申请日：2015-02-13
发明人： Bernard Patrick Bewlay , Ambarish Jayant Kulkarni , Nicole Jessica Tibbetts , Brian Michael Ellis , Manuel K. Bueno , Ever Reyes , Noel Bates , Brian Kalb
CPC分类号： B64F5/30 , B08B9/032 , F01D25/002 , F01D25/12 , F05D2220/323 , F05D2260/221
摘要： Methods and systems for in situ cleaning of internal cooling circuits of a turbine engine with detergent that provide cleaning a turbine engine that includes circumferentially arranged internal impingement cooling circuits that each include a baffle plate configured to air cool a respective surface or component of the turbine engine. Detergent is introduced through the outer wall and proximate to a back side of a baffle plate such that the detergent passes through at least one aperture in the baffle plate and acts at least upon the surface or component that the baffle plate is configured to cool. The detergent may also act on the front side of the baffle plate that is proximate to the surface or component.
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公开(公告)号：US09926807B2
公开(公告)日：2018-03-27
申请号：US14638232
申请日：2015-03-04
IPC分类号： H02K9/22 , F01D25/14 , F01D15/10 , F02D9/10 , F01D5/02 , F01D9/02 , F01D9/04 , H02K7/18 , H02K9/04 , F02M35/10 , F01D17/02 , F01D25/16 , F02D29/06 , F02D9/02
CPC分类号： F01D25/145 , F01D5/021 , F01D9/026 , F01D9/041 , F01D15/10 , F01D17/02 , F01D25/14 , F01D25/16 , F01D25/162 , F02D9/1055 , F02D29/06 , F02D2009/0283 , F02M35/10229 , F05D2220/30 , F05D2220/62 , F05D2220/76 , F05D2230/60 , F05D2240/12 , F05D2240/24 , F05D2250/82 , F05D2260/221 , F05D2260/22141 , F05D2260/606 , F05D2300/5024 , H02K7/1823 , H02K9/04
摘要： Turbine assemblies, loss recovery systems, and related fabrication methods are provided for managing temperatures associated with an electrical generator. One exemplary turbine assembly suitable for use in a loss recovery system includes a wheel configured to rotate in response to a portion of a fluid flow bypassing a flow control valve, a generator including a stator assembly disposed about a rotor coupled to the wheel to rotate in response to rotation of the wheel, a conductive structure in contact with the stator assembly, and an insulating structure radially encompassing the conductive structure and the generator. The conductive structure accesses at least a portion of the fluid flow bypassing the flow control valve and impacting the wheel, thereby providing thermal coupling between the stator assembly and the bypass fluid flow to transfer heat from the stator assembly to the bypass fluid flow via the conductive structure.
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