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1.发明授权Gas turbine engine with pylon mounted accessory drive 有权Gasturbinenmotor mit Pylon-montiertemHilfsgeräteantrieb
公开(公告)号：EP2065585B1
公开(公告)日：2017-01-04
申请号：EP08253758.0
申请日：2008-11-19
发明人： Winter, Michael
CPC分类号： F02C7/32 , F02C7/36 , F02K3/06 , F05D2260/4031 , Y02T50/671
摘要： A gas turbine engine includes an accessory gearbox (60) within an engine pylon (P). The accessory components (66) may be mounted within the engine pylon (P) to save weight and space within the core nacelle (12) as well as provide a relatively lower temperature operating environment.
摘要翻译： 燃气涡轮发动机包括在发动机塔架（P）内的附件齿轮箱（60）。 辅助部件（66）可以安装在发动机塔架（P）内，以减轻核心机舱（12）内的重量和空间，并提供相对较低温度的操作环境。
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2.发明授权
公开(公告)号：EP1992810B1
公开(公告)日：2014-05-28
申请号：EP08251743.4
申请日：2008-05-19
发明人： Jain, Ashok K. , Winter, Michael
CPC分类号： F02K3/06 , F02C7/042 , F02C7/057 , F05D2300/505 , Y02T50/671
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公开(公告)号：EP0707206B1
公开(公告)日：2002-05-29
申请号：EP95115964.9
申请日：1995-10-10
发明人： Haas, Robert J. , Winter, Michael , Annigeri, Balkrishna S. , Favrow, Leroy H. , Wegge, Jason S.
CPC分类号： G01N3/068 , G01N21/33 , G01N2021/8838 , G01N2203/0005 , G01N2203/0016 , G01N2203/0066 , G01N2203/0073 , G01N2203/0226 , G01N2203/0647
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公开(公告)号：EP2282016A3
公开(公告)日：2014-04-16
申请号：EP10251190.4
申请日：2010-06-30
发明人： Winter, Michael
IPC分类号： F01D17/16 , F01D17/08 , F02C9/20 , F02K1/08 , F02C9/22 , F02C9/28 , F02K3/06 , F01D25/34 , F02K1/06 , F02K1/09
CPC分类号： F01D17/162 , F01D17/085 , F01D25/34 , F02C9/20 , F02C9/22 , F02C9/28 , F02K1/06 , F02K1/08 , F02K1/09 , F02K3/06 , F05D2270/303
摘要： A control system (40) for a turbofan (10) comprises a variable area nozzle (26) for regulating core flow ( Fc ) through the turbofan, an actuator (27), a temperature sensor (42), a flight controller (44) and a nozzle control (47). The actuator (27) is coupled to the variable area nozzle (26) to regulate the core flow by positioning the variable area nozzle. The temperature sensor (42) is positioned in the turbofan to sense a gas path temperature of the core flow ( Fc ). The flight controller (44) is connected to the turbofan to make a thrust demand based on a flight condition of the turbofan (10). The nozzle control (47) is connected to the flight controller (44) and the actuator for directing the actuator based on the gas path temperature and the flight condition, such that the gas path temperature is controlled by adjusting the variable area nozzle (26) to regulate the core flow ( Fc ) while the turbofan meets the thrust demand.
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5.发明授权Control system of the axial bearing load of a gas turbine engine and corresponding method of regulating this load 有权的燃气涡轮发动机的推力轴承的负荷的控制系统和用于控制该负载对应的方法
公开(公告)号：EP2009249B1
公开(公告)日：2013-10-23
申请号：EP08252056.0
申请日：2008-06-16
CPC分类号： F02K1/12 , F01D21/04 , F01D25/16 , F02K1/70 , F05D2270/114 , F05D2270/30 , F05D2270/304
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公开(公告)号：EP1988266A3
公开(公告)日：2011-10-05
申请号：EP08251047.0
申请日：2008-03-25
发明人： Jain, Ashok K. , Winter, Michael
CPC分类号： F02C7/042 , B64C23/00 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F02K3/00 , F05D2270/17
摘要： A nacelle assembly (26) includes an inlet lip section (38) and an airfoil (50) adjacent to the inlet lip section (38). The airfoil (50) is selectively moveable between a first position (X) and a second position (X') to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly (26).
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7.发明公开Control system of the axial bearing load of a gas turbine engine and corresponding method of regulating this load 有权Kontollsystem的燃气涡轮发动机的推力轴承的负荷和相应的方法，用于控制该负载
公开(公告)号：EP2009249A3
公开(公告)日：2010-12-15
申请号：EP08252056.0
申请日：2008-06-16
CPC分类号： F02K1/12 , F01D21/04 , F01D25/16 , F02K1/70 , F05D2270/114 , F05D2270/30 , F05D2270/304
摘要： A turbine engine (10) provides a spool (14) supporting a turbine (18). The spool (14) is arranged in a core nacelle (12) and includes a thrust bearing (49). A fan (20) is arranged upstream from the core nacelle (12) and is coupled to the spool (14). A fan nacelle (34) surrounds the fan (20) and core nacelle (12) and provides a bypass flow path (39) that includes a fan nozzle exit area (40). A flow control device is adapted to effectively change the fan nozzle exit area (40). A controller (50) is programmed to monitor the thrust bearing (49) and command the flow control device in response to an undesired load on the thrust bearing (49). Effectively changing the fan nozzle exit area (40) with the flow control device actively manages the bearing thrust load to desired levels.
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8.发明公开Nacelle assembly having inlet airfoil for a gas turbine engine 有权Gondelanordnung mit Einlassprofilfürein Gasturbinentriebwerk
公开(公告)号：EP1988266A2
公开(公告)日：2008-11-05
申请号：EP08251047.0
申请日：2008-03-25
发明人： Jain, Ashok K. , Winter, Michael
IPC分类号： F02C7/042
CPC分类号： F02C7/042 , B64C23/00 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F02K3/00 , F05D2270/17
摘要： A nacelle assembly (26) includes an inlet lip section (38) and an airfoil (50) adjacent to the inlet lip section (38). The airfoil (50) is selectively moveable between a first position (X) and a second position (X') to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly (26).
摘要翻译： 机舱组件（26）包括邻近入口唇部（38）的入口唇部（38）和翼型件（50）。 翼型件50可以在第一位置（X）和第二位置（X'）之间选择性地移动，以调节迎面而来的气流的流动并影响机舱组件（26）的有效边界层厚度。
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9.发明授权Fan nacelle flow control and method of controlling a boundary layer at the inlet of a fan nacelle 有权风扇机舱和流量控制方法用于在风扇机舱的入口控制边界层
公开(公告)号：EP2072779B1
公开(公告)日：2014-07-09
申请号：EP08253893.5
申请日：2008-12-05
发明人： Winter, Michael
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/0226 , F02C7/057 , F05D2270/1022 , F05D2270/17 , Y02T50/671
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10.发明公开Gas turbine engine with pylon mounted accessory drive 审中-公开Gasturbinenmotor mit Pylon-montiertz Zusatzantrieb
公开(公告)号：EP2617965A2
公开(公告)日：2013-07-24
申请号：EP13150504.2
申请日：2013-01-08
发明人： Winter, Michael
IPC分类号： F02C7/32
CPC分类号： F02C7/32 , Y02T50/671
摘要： A gas turbine engine (10) includes an accessory gearbox (60) within an engine pylon (P). The accessory components (66) may be mounted within the engine pylon (P) to save weight and space within the core nacelle (12) as well as provide a relatively lower temperature operating environment.
摘要翻译： 燃气涡轮发动机（10）包括在发动机塔架（P）内的附件齿轮箱（60）。 辅助部件（66）可以安装在发动机塔架（P）内，以减轻核心机舱（12）内的重量和空间，并提供相对较低温度的操作环境。
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