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1. 发明申请

WO2016025056A3 TURBINE ENGINE AND PARTICLE SEPARATORS THEREFORE 审中-公开
标题翻译：涡轮发动机及其颗粒分离器
公开(公告)号：WO2016025056A3
公开(公告)日：2016-08-04
申请号：PCT/US2015033108
申请日：2015-05-29
申请人： GEN ELECTRIC
发明人： STONE TIMOTHY DERYCK , LASKOWSKI GREGORY MICHAEL , PROCTOR ROBERT , STOVER CURTIS , MANNING ROBERT FRANCIS , CORREIA VICTOR HUGO SILVA , BUHLER JARED PETER , MURRAY ROBERT CARL , BOURASSA COREY , PRITCHARD BYRON ANDREW JR , RATZLAFF JONATHAN RUSSELL
IPC分类号： F02C7/05 , B01D45/16
CPC分类号： F02C7/05 , B01D45/16 , B04C3/00 , B04C3/06 , B04C2003/003 , B04C2003/006 , F01D25/12 , F02C7/12 , F05D2260/607 , Y02T50/675
摘要： A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.
摘要翻译：具有连接到涡轮部分的旁路流体导管的涡轮发动机包括位于旁路流体导管内的至少一个颗粒分离器，以在旁路流到达涡轮部分用于冷却之前将颗粒与旁路流体流分离。用于从流体流中去除颗粒的离心分离器包括角速度增加器，颗粒出口，角速度增加器下游的角速度减小器和设置在角速度增大器和角速度减小器之间的弯曲部。

2. 发明申请

WO2016032585A2 TURBINE ENGINE, COMPONENTS, AND METHODS OF COOLING SAME 审中-公开
标题翻译：涡轮发动机，组件和冷却方法
公开(公告)号：WO2016032585A2
公开(公告)日：2016-03-03
申请号：PCT/US2015032855
申请日：2015-05-28
申请人： GEN ELECTRIC
发明人： MANNING ROBERT FRANCIS , STONE TIMOTHY DERYCK , BUHLER JARED PETER , CORRELA VICTOR HUGO SILVA , LASKOWSKI GREGORY MICHAEL , MURRAY ROBERT CARL , PROCTOR ROBERT , RATZLAFF JONATHAN RUSSELL , S JOHN HOWARD , STOVER CURTIS WALTON
IPC分类号： F02C7/052
CPC分类号： F01D25/32 , B01D45/16 , B04C3/00 , B04C3/06 , B04C2003/003 , B04C2003/006 , F01D5/08 , F01D25/12 , F02C3/04 , F02C7/05 , F02C7/052 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35
摘要： A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced- particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.
摘要翻译：用于从流体流中去除颗粒的离心分离器包括配置成增加流体流的角速度的角速度增加器，配置成分离流体流以形成浓缩颗粒流和减少颗粒流的分流器，以及出口导管，其被配置为接收减少的颗粒流。用于涡轮发动机的诱导器组件包括具有流道的诱导器，所述诱导器具有与发动机的涡轮段流体连通的诱导器入口和诱导器出口以及包括颗粒分离器的颗粒分离器，所述颗粒分离器接收来自发动机的压缩机部分和分流器。涡轮发动机包括冷却空气流动回路，该冷却空气流动回路将流体流供应到发动机的涡轮部分以用于冷却，位于冷却空气流动回路内的颗粒分离器以及形成流体连通的冷却空气流动回路的一部分的诱导器与粒子分离器。一种冷却具有诱导轮的涡轮发动机的旋转叶片的方法包括：引导来自涡轮发动机的一部分的冷却流体流朝向旋转叶片，通过使冷却流体流经过惯性分离器而从冷却流体流中分离出粒子，从惯性分离器释放的减少的颗粒流到旋转叶片的速度，并且通过将来自惯性分离器的减少的颗粒流释放到诱导器中的冷却通道中来定向减少的颗粒流。

3. 发明申请

WO2009148655A3 TURBINE AIRFOIL WITH METERED COOLING CAVITY 审中-公开
标题翻译：具有计量冷却空气的涡轮机空气
公开(公告)号：WO2009148655A3
公开(公告)日：2010-08-26
申请号：PCT/US2009035976
申请日：2009-03-04
申请人： GEN ELECTRIC , CORREIA VICTOR HUGO SILVA , DEMERS DANIEL EDWARD , MANNING ROBERT FRANCIS
发明人： CORREIA VICTOR HUGO SILVA , DEMERS DANIEL EDWARD , MANNING ROBERT FRANCIS
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/189 , F05D2260/201
摘要： A turbine airfoil for a gas turbine engine includes: (a) spaced-apart pressure and suction sidewalls extending between a leading edge and a trailing edge; (b) a first cavity disposed between the pressure and suction sidewalls, the first cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates with an exterior surface of the airfoil; (c) a second cavity disposed between the pressure and suction sidewalls, the second cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates solely with the suction sidewall of the airfoil; and (d) a metering structure adapted to substantially restrict air flow into the second cavity.
摘要翻译：用于燃气涡轮发动机的涡轮机翼片包括：（a）在前缘和后缘之间延伸的间隔开的压力和吸力侧壁; （b）设置在压力侧和吸力侧壁之间的第一空腔，第一空腔适于从发动机内的源供给冷却空气，并连接到与翼型件的外表面连通的至少一个薄膜冷却孔; （c）设置在所述压力和吸力侧壁之间的第二腔，所述第二腔适于从所述发动机内的源供给冷却空气，并且连接到至少一个仅与所述翼型的吸力侧壁连通的薄膜冷却孔 ; 和（d）适于基本上限制空气流入第二腔的计量结构。

4. 发明专利

JP2001073704A COOLING TIP OF ROTOR BLADE 失效
公开(公告)号：JP2001073704A
公开(公告)日：2001-03-21
申请号：JP2000197543
申请日：2000-06-30
申请人： GEN ELECTRIC
发明人： CORREIA VICTOR H S , MANNING ROBERT FRANCIS
IPC分类号： F01D5/18 , F01D5/20
摘要： PROBLEM TO BE SOLVED: To provide turbine rotor blade with improved cooling. SOLUTION: The turbine rotor blade includes hollow wing part having squealer tip rib 36 stretching outside from tip cap 40 closing wing part. Impingement baffle 44 is provided separated inside from tip cap making up tip plenum 46 between tip cap. Impingement holes 48 go through the baffle toward the joint, so that the jet stream of cooling conductor collides with cap joint 42.

5. 发明专利

JP2000199404A TURBINE BLADE PORTION AND BLADE PORTION COOLING METHOD 失效
公开(公告)号：JP2000199404A
公开(公告)日：2000-07-18
申请号：JP33911799
申请日：1999-11-30
申请人： GEN ELECTRIC
发明人： MANNING ROBERT FRANCIS , SOLDA ROBERT BARRY , PAREKH LALIT KUMAR , TASLIM MOHAMMAD ESMAIL
IPC分类号： F01D9/02 , F01D5/18
摘要： PROBLEM TO BE SOLVED: To obtain a blade portion equipped with a cooling circuit having an improved cooling efficiency compared with a generally known three-pass cooling circuit despite of its simpler configuration and lower production costs than the blade portion having a five-pass cooling circuit. SOLUTION: A blade portion 100 for a turbine engine includes a three-pass serpentine cooling cavity 102 comprising an interconnected leading edge chamber 114, an extra large intermediate chamber 116, and a trailing edge chamber 118. The cavity comprises a combination of a plurality of ribs 124, 126, a plurality of pins 130, a purge air-swirler 146, a deflection vane 134 and a metering partition 142. The cavity mixes high pressure air, improves an air cooling efficiency in the blade portion, and effects control of a uniform flow rate. The metering partition reduces air pressure in the trailing edge chamber and enables reducing the number of trailing edge slots.

6. 发明专利

JP2001200704A COOLED BLADE PART OF GAS TURBINE ENGINE, AND METHOD OF MANUFACTURING THE SAME 失效
公开(公告)号：JP2001200704A
公开(公告)日：2001-07-27
申请号：JP2000373651
申请日：2000-12-08
申请人： GEN ELECTRIC
发明人： TSAI GENE C F , TUNG SUNG , FLAHERTY TERENCE CARROLL , MANNING ROBERT FRANCIS
IPC分类号： F01D9/02 , F01D5/18
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade part, having an improved trailing edge cooling which does not require heat insulating coating. SOLUTION: A blade part 40 to be used for gas turbine engine is provided with a positive pressure side 42 and a negative pressure side 44 to be connected to each other in a trailing edge wall 60 forming a trailing edge 48. The blade part 40 includes at least one cooling hole 68, which extends through the trailing edge wall 60 and feeds the cooling fluid from the positive pressure side 42 to the negative pressure side 44 of the blade part 40.

7. 发明专利

JP2002364306A GAS TURBINE ENGINE COMPONENT 审中-公开
公开(公告)号：JP2002364306A
公开(公告)日：2002-12-18
申请号：JP2002087289
申请日：2002-03-27
申请人： GEN ELECTRIC
发明人： LIOTTA GARY CHARLES , MANNING ROBERT FRANCIS
IPC分类号： F01D9/02 , F01D9/04 , F01D25/12 , F01D25/24
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine engine component with an integral type outer wall and shroud segment. SOLUTION: The gas turbine engine component 50 comprises a nozzle outer wall 52, plural nozzle vanes 54 extending inward from the outer wall 52, and an inner wall 58 extending in the circumferential direction along the inner end part of the vanes 54. The component 50 also has the shroud integral with the outer wall 52 surrounding plural blades supported by the engine and rotating around the center line 24 of the engine.

8. 发明专利

JP2000161004A LEADING EDGE ISOLATED COOLING FOR AEROFOIL 失效
公开(公告)号：JP2000161004A
公开(公告)日：2000-06-13
申请号：JP32480999
申请日：1999-11-16
申请人： GEN ELECTRIC
发明人： MANNING ROBERT FRANCIS , ACQUAVIVA PAUL JOSEPH , DEMERS DANIEL EDWARD
IPC分类号： F01D5/18 , F01D9/02
摘要： PROBLEM TO BE SOLVED: To improve inside cooling action by disposing an isolation plenum along the first side wall and adjacent the leading edge passage, extending a plurality of film cooing gill holes through the first sidewall and which are separated from the leading edge passage by a partition wall having a plurality of inlet holes, and disposing the plurality of the film cooling gill holes in flow communication with the isolation plenum. SOLUTION: An isolation plenum 38 extends along the first side wall 22 and adjacent the leading edge passage 34, and is separated from the leading edge passage 34 by a partition wall 40 having a plurality of inlet holes 42 for receiving a part of cooling air from the leading edge passage 34. A plurality of film cooling gill holes extending through the first side wall 22 are disposed in flow communication with the isolation plenum 38. The first side wall 22 is not bored along the isolation plenum 38 from a final train of leading edge hole 36 to the gill hole 44, and the inner surface of the first side wall 22 in this region is cooled from the isolation plenum 38 inside by cooling air from the inlet holes 42. Cooling air after using is discharged into combustion gas of relatively low pressure through the gill hole 44, a cooling film is formed, and the first side wall 22 disposed downstream the gill hole 44 is cooled by the film cooling.

9. 发明专利

JP2002235502A TURBINE BLADE FOR GAS TURBINE ENGINE, AND COOLING METHOD OF TURBINE BLADE 审中-公开
公开(公告)号：JP2002235502A
公开(公告)日：2002-08-23
申请号：JP2001337237
申请日：2001-11-02
申请人： GEN ELECTRIC
发明人： DEMERS DANIEL EDWARD , MANNING ROBERT FRANCIS , ACQUAVIVA PAUL JOSEPH
IPC分类号： F01D5/18
摘要： PROBLEM TO BE SOLVED: To provide a turbine rotor blade for cooling the inside used for a gas turbine engine. SOLUTION: The turbine blade 30 has a platform 40 and a profile part 42 extending radially from the platform 40. An internal cooling circuit 54 is formed in the profile part 42, and cools the profile part 42 by circulating a cooling medium through the profile part 42. At least one supply passage 110 is provided, a part of the cooling medium having passed at least partially through the internal cooling circuit 54 is directed to the above part of the platform 40, and the platform 40 is cooled.

10. 发明专利

JP2000345808A PRESSURE COMPENSATION TURBINE NOZZLE 失效
公开(公告)号：JP2000345808A
公开(公告)日：2000-12-12
申请号：JP2000135290
申请日：2000-05-09
申请人： GEN ELECTRIC
发明人： TUNG STEPHEN KIN-KEUNG , SOLDA ROBERT BARRY , MANNING ROBERT FRANCIS
IPC分类号： F01D9/02 , F01D5/18
摘要： PROBLEM TO BE SOLVED: To provide a turbine nozzle having improved cooling with a pressure loss minimized. SOLUTION: This turbine nozzle includes an inner and an outer bands 22 and 24 having air inlets 36 and 38, respectively. A plurality of hollow vanes 26 are integrally combined with the bands so as to provide communication between the inlets and air flow. The respective vanes have a first and a second cooling flow passages 40 and 42 extending between the bands 22 and 24. The flow passage 40 is separated from the flow passage 42 by an inclined barrier 46. The barrier 46 is constructed such that a pressure drop is decreased at delivery of cooling air by converging the two flow passages 40 and 42 in directions away from the corresponding inlets 36 and 38.

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