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公开(公告)号：EP3108129A4
公开(公告)日：2017-11-22
申请号：EP14882642
申请日：2014-09-18
发明人： SUCIU GABRIEL L , CHANDLER JESSE M
CPC分类号： F02C9/18 , F01D25/162 , F01D25/24 , F02C6/08 , F02C7/052 , F02C7/25 , F04D29/522 , F04D29/542 , F04D29/5853 , F04D29/701 , F05D2220/32 , F05D2240/15
摘要： A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port.
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公开(公告)号：EP3068997A4
公开(公告)日：2017-07-05
申请号：EP14881671
申请日：2014-11-11
发明人： HILL JAMES D , SUCIU GABRIEL L , MERRY BRIAN D , ALVANOS IOANNIS
CPC分类号： F01D11/005 , F01D5/06 , F01D5/081 , F01D9/041 , F01D11/001 , F05D2220/32 , F05D2240/57 , F05D2240/80 , F05D2260/30 , Y02T50/676
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公开(公告)号：EP3004595A4
公开(公告)日：2017-02-22
申请号：EP14807172
申请日：2014-05-06
IPC分类号： F02C7/06 , F01D25/16 , F02C3/06 , F02C3/107 , F02C7/36 , F02K3/06 , F16C19/26 , F16C19/54 , F16C35/06
CPC分类号： F02C3/107 , F01D25/162 , F02C3/06 , F02C7/06 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/52 , F05D2240/55 , F05D2240/60 , F05D2250/312 , F05D2260/40311 , F16C19/26 , F16C19/545 , F16C19/55 , F16C35/06 , F16C2360/23
摘要： A turbofan engine (20) comprises a fan (28). A fan drive gear system (60) is configured to drive the fan. A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. An intermediate spool comprises an intermediate pressure turbine (48), a compressor (42), and an intermediate spool shaft (54) coupling the intermediate pressure turbine to the intermediate spool compressor. A combustor (45) is between a core spool compressor (44) and a high pressure turbine (46). A first (160) main bearing engages a static support (164; 164′) and a forward hub (236) of the intermediate spool. A second (162) main bearing engages the low shaft and the forward hub.
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4.发明公开METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER FLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS 审中-公开方法和设备用于处理VORDIFFUSORSTROMS进行冷却高压涡轮组件
公开(公告)号：EP2961943A4
公开(公告)日：2017-01-11
申请号：EP14756377
申请日：2014-02-28
CPC分类号： F02C7/18 , F01D5/02 , F01D9/041 , F01D9/065 , F01D17/105 , F01D25/12 , F01D25/24 , F02C3/04 , F02C6/08 , F02C7/04 , F02C7/06 , F02C7/14 , F04D29/541 , F05D2220/32 , F05D2240/12 , F05D2240/35 , F05D2260/20 , F05D2260/213 , Y02T50/676
摘要： A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.
摘要翻译： 提供了一种用于燃气涡轮发动机扩散器也包括外护罩到护罩内，所述外护罩之间撑杆的倍数，并且所述的内罩在环形设计流动路径来定义，并且在通信中跨预扩散器入口与 所述环形设计流路。
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5.发明公开METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER AIRFLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS 审中-公开方法和设备用于处理VORDIFFUSOR空气流进行冷却高压涡轮组件
公开(公告)号：EP2961942A4
公开(公告)日：2017-01-11
申请号：EP14756284
申请日：2014-02-28
CPC分类号： F02C7/18 , F01D5/02 , F01D9/041 , F01D9/065 , F01D17/105 , F01D25/12 , F01D25/24 , F02C3/04 , F02C6/08 , F02C7/04 , F02C7/06 , F02C7/14 , F04D29/541 , F05D2220/32 , F05D2240/12 , F05D2240/35 , F05D2260/20 , F05D2260/213 , Y02T50/676
摘要： A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.
摘要翻译： 提供了一种用于燃气涡轮发动机扩散器也包括外护罩到护罩内，所述外护罩之间撑杆的倍数，并且所述的内罩在环形设计流动路径来定义，并且在通信的中间切割扩散预入口与 所述环形设计流路。
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6.发明公开
公开(公告)号：EP2904233A4
公开(公告)日：2016-06-29
申请号：EP13843271
申请日：2013-02-10
发明人： SUCIU GABRIEL L
CPC分类号： F02K3/04 , F01D17/105 , F02C3/107 , F02C7/20 , F02K3/06 , F04D29/325 , F05D2220/32 , F05D2230/50 , F05D2260/4031
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公开(公告)号：EP2943668A4
公开(公告)日：2016-01-20
申请号：EP13870696
申请日：2013-06-07
发明人： SUCIU GABRIEL L , CHANDLER JESSE M
CPC分类号： F01D25/162 , F02C7/12 , F02C7/20 , F02C7/32 , F05D2220/325 , F05D2260/60 , Y02T50/675
摘要： A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.
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公开(公告)号：EP2929162A4
公开(公告)日：2016-01-06
申请号：EP13862563
申请日：2013-06-20
发明人： SUCIU GABRIEL L , CHANDLER JESSE M
CPC分类号： F02C7/052 , B01D46/0023 , F02C7/12 , F05D2220/327 , F05D2260/40311 , F05D2260/607 , Y02T50/675
摘要： A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.
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公开(公告)号：EP2820271A4
公开(公告)日：2015-11-18
申请号：EP13754271
申请日：2013-02-20
发明人： SUCIU GABRIEL L , ALVANOS IOANNIS
CPC分类号： F02C6/08 , F01D5/081 , F01D9/065 , F02C7/18 , F02C7/185 , F05B2260/205 , Y02T50/676
摘要： A gas turbine engine includes a heat exchanger, a mid-turbine frame, a passageway that extends through at least a portion of the mid-turbine frame and a first nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The mid-turbine frame is in fluid communication with the heat exchanger. The conditioned airflow is communicated through the passageway and is received by the first nozzle assembly to condition gas turbine engine hardware.
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10.发明公开GEARED TURBINE ENGINE WITH RELATIVELY LIGHTWEIGHT PROPULSOR MODULE 审中-公开带有相对轻型螺旋桨模块的GEARBURGER涡轮发动机
公开(公告)号：EP2904234A4
公开(公告)日：2015-11-04
申请号：EP13845886
申请日：2013-02-08
发明人： SCHWARZ FRED M , SUCIU GABRIEL L
CPC分类号： F02C7/36 , F02C3/10 , F02C3/107 , F02C7/20 , F02C7/32 , F05D2220/36 , F05D2260/40311 , Y02T50/672 , Y10T29/49321
摘要： An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.
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