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1. 发明申请

WO2008045058A1 OPERATIONAL LINE MANAGEMENT OF LOW PRESSURE COMPRESSOR IN A TURBOFAN ENGINE 审中-公开
标题翻译：涡轮发动机低压压缩机的运行管理
公开(公告)号：WO2008045058A1
公开(公告)日：2008-04-17
申请号：PCT/US2006/039808
申请日：2006-10-12
申请人： UNITED TECHNOLOGIES CORPORATION , HURWITZ, Wayne , MCVEY, William, J.
发明人： HURWITZ, Wayne , MCVEY, William, J.
IPC分类号： F02K1/16 , F02K1/06 , F02K1/15 , F02K3/06
CPC分类号： F01D17/08 , F01D17/141 , F01D21/00 , F02K1/1207 , F02K1/15 , F02K1/16 , F02K3/06 , F02K3/075 , F05D2250/52 , F05D2270/101 , F05D2270/301 , F05D2270/3013 , F05D2270/304
摘要： A turbofan engine control system is provided for managing a low pressure compressor operating line. The engine includes a low spool having a low pressure compressor housed in a core nacelle. A turbofan is coupled to the low spool. A fan nacelle surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area. A controller is programmed to effectively change the nozzle exit area in response to an undesired low pressure compressor stability margin which can result in a stall or surge condition. In one example, the physical nozzle exit area is decreased at the undesired stability condition occurring during engine deceleration. A low pressure compressor pressure ratio, low spool speed and throttle position are monitored to determine the undesired stability margin.
摘要翻译：提供一种用于管理低压压缩机操作线的涡轮风扇发动机控制系统。发动机包括具有容纳在核心机舱中的低压压缩机的低阀芯。涡轮风扇联接到低阀芯。风扇机舱围绕涡轮风扇和核心机舱，并提供具有喷嘴出口区域的旁路流动路径。控制器被编程为响应于可能导致失速或喘振状况的不期望的低压压缩机稳定裕度来有效地改变喷嘴出口面积。在一个示例中，物理喷嘴出口面积在发动机减速期间发生的不期望的稳定性条件下减小。监测低压压缩机压力比，低阀芯速度和节气门位置以确定不期望的稳定裕度。

2. 发明申请

WO2008063152A3 TURBOFAN ENGINE 审中-公开
标题翻译：涡轮发动机
公开(公告)号：WO2008063152A3
公开(公告)日：2008-10-30
申请号：PCT/US2006039942
申请日：2006-10-12
申请人： UNITED TECHNOLOGIES CORP , GRABOWSKI ZBIGNIEW M , MCVEY WILLIAM J
发明人： GRABOWSKI ZBIGNIEW M , MCVEY WILLIAM J
IPC分类号： F02K3/02 , F02K3/075
CPC分类号： F02K3/06 , F02C7/36 , F02K1/1207 , F05D2220/36 , F05D2260/40311
摘要： A turbofan engine (10) is provided that includes a fan nacelle (34) surrounding a core nacelle (12). The core nacelle (12) houses a spool (14). The fan (34) and core (12) nacelles provide a bypass flow path (39) having a nozzle exit area (40). A turbofan (20) is arranged within the fan nacelle (34) upstream from the core nacelle (12). A flow control device (41) is adapted to effectively change the nozzle exit area (40) to obtain a desired operating condition for the turbofan engine (10). A gear train (22) couples the spool (14) and turbofan (20) for reducing a turbofan rotational speed relative to a spool rotational speed. A controller (50) is programmed to respond to at least one sensor (52-60). The controller (50) is programmed to effectively control the nozzle area (40).
摘要翻译：提供一种涡轮风扇发动机（10），其包括围绕核心机舱（12）的风扇机舱（34）。核心机舱（12）容纳线轴（14）。风扇（34）和核心（12）机舱提供具有喷嘴出口区域（40）的旁路流路（39）。涡轮风扇（20）布置在风扇机舱（34）内部的核心机舱（12）的上游。流量控制装置（41）适于有效地改变喷嘴出口区域（40）以获得用于涡轮风扇发动机（10）的期望的操作条件。齿轮系（22）联接滑阀（14）和涡轮风扇（20），用于相对于滑阀旋转速度减小涡轮风扇转速。控制器（50）被编程为响应于至少一个传感器（52-60）。控制器（50）被编程为有效地控制喷嘴区域（40）。

3. 发明申请

WO2008063152A2 EFFECTIVELY VARIABLE AREA NOZZLE TURBOFAN ENGINE INTEGRATION 审中-公开
标题翻译：有效的可变区域喷气涡轮发动机整合
公开(公告)号：WO2008063152A2
公开(公告)日：2008-05-29
申请号：PCT/US2006/039942
申请日：2006-10-12
申请人： UNITED TECHNOLOGIES CORPORATION , GRABOWSKI, Zbigniew M. , MCVEY, William J.
发明人： GRABOWSKI, Zbigniew M. , MCVEY, William J.
IPC分类号： F02K1/06 , F02K3/06 , F02C7/36
CPC分类号： F02K3/06 , F02C7/36 , F02K1/1207 , F05D2220/36 , F05D2260/40311
摘要： A turbofan engine is provided that includes a fan nacelle surrounding a core nacelle. The core nacelle houses a spool. The fan and core nacelles provide a bypass flow path having a nozzle exit area. A turbofan is arranged within the fan nacelle upstream from the core nacelle. A flow control device is adapted to effectively change the nozzle exit area to obtain a desired operating condition for the turbofan engine. A gear train couples the spool and turbofan for reducing a turbofan rotational speed relative to a spool rotational speed. A controller is programmed to respond to at least one sensor. The controller is programmed to effectively control the nozzle area.
摘要翻译：提供了一种涡轮风扇发动机，其包括围绕核心机舱的风扇机舱。核心机舱装有一个线轴。风扇和核心机舱提供具有喷嘴出口区域的旁路流动路径。涡轮风扇布置在机舱上游的风扇机舱内。流量控制装置适于有效地改变喷嘴出口区域以获得用于涡轮风扇发动机的期望的操作条件。齿轮系将线轴和涡轮风扇相结合，以相对于阀芯旋转速度降低涡轮风扇转速。控制器被编程为响应于至少一个传感器。控制器被编程为有效地控制喷嘴面积。

4. 发明申请

WO2008063153A2 MANAGING LOW PRESSURE TURBINE MAXIMUM SPEED IN A TURBOFAN ENGINE 审中-公开
标题翻译：在涡轮发动机中管理低压涡轮机的最大转速
公开(公告)号：WO2008063153A2
公开(公告)日：2008-05-29
申请号：PCT/US2006/039947
申请日：2006-10-12
申请人： UNITED TECHNOLOGIES CORPORATION , MCVEY, William J.
发明人： MCVEY, William J.
IPC分类号： F02K1/06 , F02K3/06 , F02C7/36
CPC分类号： F02K1/15 , F02K1/06 , F02K3/06 , F05D2270/021 , F05D2270/304
摘要： A turbofan engine control system for managing a low pressure turbine speed is provided. The turbofan engine control system includes a low spool having a low pressure turbine that are housed in a core nacelle. The low pressure turbine is adapted to rotate at a speed and includes a maximum design speed. A turbofan is coupled to the low spool. A fan nacelle surrounds the turbofan and core nacelle and provides a bypass flow path. The bypass flow path includes a nozzle exit area. A controller is programmed to command a flow control device adapted to effectively decrease the nozzle exit area in response to a condition. Reducing the nozzle exit area, either physically or otherwise, maintains the speed below the maximum design speed.
摘要翻译：提供了一种用于管理低压涡轮机转速的涡轮风扇发动机控制系统。涡轮风扇发动机控制系统包括具有容纳在核心机舱中的低压涡轮机的低阀芯。低压涡轮机适于以一定速度旋转并且包括最大设计速度。涡轮风扇联接到低阀芯。风扇机舱围绕涡轮风扇和核心机舱，并提供旁路流路。旁路流路包括喷嘴出口区域。控制器被编程为命令流量控制装置，其适于响应于条件有效地减小喷嘴出口面积。物理上或其他方面减少喷嘴出口区域将速度保持在最大设计速度以下。

5. 发明申请

WO2008063153A3 MANAGING LOW PRESSURE TURBINE MAXIMUM SPEED IN A TURBOFAN ENGINE 审中-公开
标题翻译：管理涡轮发动机中的低压涡轮最大速度
公开(公告)号：WO2008063153A3
公开(公告)日：2008-10-30
申请号：PCT/US2006039947
申请日：2006-10-12
申请人： UNITED TECHNOLOGIES CORP , MCVEY WILLIAM J
发明人： MCVEY WILLIAM J
IPC分类号： F02K1/15 , F02K3/06
CPC分类号： F02K1/15 , F02K1/06 , F02K3/06 , F05D2270/021 , F05D2270/304
摘要： A turbofan engine control system for managing a low pressure turbine speed is provided. The turbofan engine control system includes a low spool having a low pressure turbine that are housed in a core nacelle. The low pressure turbine is adapted to rotate at a speed and includes a maximum design speed. A turbofan is coupled to the low spool. A fan nacelle surrounds the turbofan and core nacelle and provides a bypass flow path. The bypass flow path includes a nozzle exit area. A controller is programmed to command a flow control device adapted to effectively decrease the nozzle exit area in response to a condition. Reducing the nozzle exit area, either physically or otherwise, maintains the speed below the maximum design speed.
摘要翻译：提供了用于管理低压涡轮机速度的涡轮风扇发动机控制系统。涡轮风扇发动机控制系统包括具有容纳在核心机舱中的低压涡轮机的低线轴。低压涡轮适于以一定速度旋转并包括最大设计速度。涡轮风扇连接到低速轴。风扇机舱围绕涡轮风扇和核心机舱，并提供旁路流路。旁路流路包括喷嘴出口区域。控制器被编程以命令流量控制装置适于响应于条件有效地减小喷嘴出口面积。减少喷嘴出口面积，无论是物理还是其他方式，都将速度保持在最大设计速度以下。

6. 发明申请

WO2008045079A1 TURBOFAN ENGINE OPERATION CONTROL 审中-公开
标题翻译：涡轮发动机运行控制
公开(公告)号：WO2008045079A1
公开(公告)日：2008-04-17
申请号：PCT/US2006/040064
申请日：2006-10-12
申请人： UNITED TECHNOLOGIES CORPORATION , MCVEY, William J.
发明人： MCVEY, William J.
IPC分类号： F02K1/12 , F02K1/16 , F02K3/075
CPC分类号： F02K1/16 , F02K1/1207 , F02K3/075 , F05D2220/327
摘要： A turbofan engine (10) is provided that includes a spool (14). The spool (14) supports a turbine (18) and is housed within a core nacelle (12). A fan (20) is coupled to the spool (14) and includes a target operability line. The target operability line provides desired fuel consumption, engine performance, and/or fan operability margin. A fan nacelle (34) surrounds the fan (20) and core nacelle (12) to provide a bypass flow path (39) having a nozzle exit area (40). A controller (50) is programmed to command a flow control device (41) for changing the nozzle exit area (40). The change in nozzle exit area (40) achieves the target operability line in response to an engine operating condition that is a function of airspeed and throttle position. A change in the nozzle exit area (40) is used to move the operating line toward a fan stall or flutter boundary by manipulating the fan pressure ratio.
摘要翻译：提供一种涡轮风扇发动机（10），其包括阀芯（14）。阀芯（14）支撑涡轮（18）并且容纳在核心机舱（12）内。风扇（20）联接到卷轴（14）并且包括目标可操作性线。目标可操作性线提供所需的燃料消耗，发动机性能和/或风扇可操作性裕量。风扇机舱（34）围绕风扇（20）和核心机舱（12），以提供具有喷嘴出口区域（40）的旁路流动路径（39）。控制器（50）被编程为命令用于改变喷嘴出口区域（40）的流量控制装置（41）。喷嘴出口区域（40）的变化响应于作为空速和节气门位置的函数的发动机操作条件而实现目标可操作性线。喷嘴出口区域（40）的变化用于通过操纵风扇压力比将操作线移向风扇失速或颤动边界。

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