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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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公开(公告)号：US09915151B2
公开(公告)日：2018-03-13
申请号：US14721164
申请日：2015-05-26
发明人： John Alan Weaver , Okey Kwon
CPC分类号： F01D5/188 , F01D5/282 , F01D9/02 , F05D2240/12 , F05D2260/221 , F05D2300/6033
摘要： An airfoil may be provided that includes a CMC body and a support piece. The CMC body has an inner surface that defines a chamber within the CMC body. The support piece may be positioned within the chamber of the CMC body. The support piece comprises a channel in a surface of the support piece, the surface being in contact with the inner surface of the CMC body. The channel and the inner surface of the CMC body define a passageway for a cooling fluid. The passageway may wind about the circumference of the CMC body and extend along the span of the airfoil. Outlets may be positioned through the CMC body allowing fluid communication between the passageway and the outer surface of the CMC body.
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公开(公告)号：US20180066524A1
公开(公告)日：2018-03-08
申请号：US15255187
申请日：2016-09-02
CPC分类号： F01D5/187 , F01D5/186 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2260/202 , F05D2260/221 , Y02T50/676
摘要： A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.
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公开(公告)号：US20180051572A1
公开(公告)日：2018-02-22
申请号：US15238324
申请日：2016-08-16
CPC分类号： F01D5/187 , F01D5/186 , F01D5/20 , F01D9/041 , F01D25/12 , F02K3/06 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/323 , F05D2240/125 , F05D2240/307 , F05D2250/71 , F05D2260/202 , F05D2260/221 , F05D2260/232 , F05D2260/607 , Y02T50/676
摘要： A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior and spanning from a root to a tip. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define an air flow channel within the airfoil. The air flow channel can have at least one tip turn at the partial-length rib, having at least one hole, for example a film hole, in a portion of the tip.
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公开(公告)号：US09856738B2
公开(公告)日：2018-01-02
申请号：US14376428
申请日：2012-12-12
发明人： Fathi Ahmad , Nihal Kurt , Mario Nitsche , Marco Schuler , Andreas Varnholt
CPC分类号： F01D5/188 , F01D5/187 , F01D9/02 , F05D2250/185 , F05D2260/221
摘要： A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.
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