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公开(公告)号：WO2013141934A3
公开(公告)日：2013-09-26
申请号：PCT/US2012/071946
申请日：2012-12-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F01D25/24
Abstract: A nacelle assembly for a high-bypass gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, and a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, the fan variable area nozzle operable to vary the fan nozzle exit area by about 20%.
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2.发明申请GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO 审中-公开具有风扇变风量的气体涡轮发动机，用于低风扇压力比
公开(公告)号：WO2013141932A1
公开(公告)日：2013-09-26
申请号：PCT/US2012/071928
申请日：2012-12-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F02K1/06
Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, the fan pressure ratio less than about 1.45. In a further embodiment of any of the foregoing nacelle assembly for a gas turbine engine embodiment, the assembly further includes a controller operable to control the fan variable area nozzle.
Abstract translation: 用于高旁通燃气涡轮发动机的机舱组件包括围绕发动机中心线轴线限定的核心机舱，至少部分地安装在核心机舱周围的风扇机舱，以限定用于风扇旁路气流的风扇旁路流动路径，风扇可变区域 喷嘴可以相对于风扇机舱轴向移动，以改变风扇喷嘴出口面积，并且在发动机运行期间调节风扇旁路气流的风扇压力比，风扇压力比小于约1.45。 在用于燃气涡轮发动机实施例的任何前述的机舱组件的另一实施例中，组件还包括可操作以控制风扇可变区域喷嘴的控制器。
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3.发明申请GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO 审中-公开具有风扇变风量的气体涡轮发动机，用于低风扇压力比
公开(公告)号：WO2013147951A1
公开(公告)日：2013-10-03
申请号：PCT/US2012/071954
申请日：2012-12-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F02K3/075
CPC classification number: F02K3/06 , F02K1/09 , F02K3/075 , F05D2270/10
Abstract: A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.
Abstract translation: 燃气涡轮发动机包括具有二十（20）个或更少风扇叶片的风扇部分和小于约1.45的风扇压力比。
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4.发明申请GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE TO REDUCE FAN INSTABILITY 审中-公开具有风扇变化范围的气体涡轮发动机减少风扇不稳定性
公开(公告)号：WO2013141933A1
公开(公告)日：2013-09-26
申请号：PCT/US2012/071937
申请日：2012-12-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F02K3/075
Abstract: A nacelle assembly for a high-bypass gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, and a controller operable to control the fan variable area nozzle to vary a fan nozzle exit area and adjust the pressure ratio of the fan bypass airflow.
Abstract translation: 根据本公开的示例性方面的用于高旁路燃气涡轮发动机的机舱组件包括围绕发动机中心线轴线限定的核心机舱，至少部分地围绕所述核心机舱安装的风扇机舱，以限定用于 风扇旁路气流，风扇可变区域喷嘴可相对于风扇机舱轴向移动以改变风扇喷嘴出口区域，并且在发动机运行期间调节风扇旁路气流的风扇压力比，以及控制器，其可操作以控制风扇可变区域喷嘴 改变风扇喷嘴出口区域并调节风扇旁路气流的压力比。
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公开(公告)号：WO2013126123A1
公开(公告)日：2013-08-29
申请号：PCT/US2012/068336
申请日：2012-12-07
Applicant: UNITED TECHNOLOGIES CORPORATION , KOHLENBERG, Gregory A. , ZAMORA, Sean P.
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P.
IPC: F02K3/075
Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle axially movable relative the fan nacelle to define an auxiliary port to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
Abstract translation: 用于高旁通燃气涡轮发动机的机舱组件包括可相对于风扇机舱轴向移动的风扇可变区域喷嘴，以限定辅助端口以改变风扇喷嘴出口区域并调节发动机运行期间风扇旁路气流的压力比。
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Patent Agency Ranking6.发明公开GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO 审中-公开具有可变鼓风口区用于低风扇压力比燃气涡轮发动机
公开(公告)号：EP2798188A1
公开(公告)日：2014-11-05
申请号：EP12872986.0
申请日：2012-12-28
Applicant: United Technologies Corporation
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F02K3/075
CPC classification number: F02K3/06 , F02K1/09 , F02K3/075 , F05D2270/10
Abstract: A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.
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7.发明公开GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE TO REDUCE FAN INSTABILITY 审中-公开具有可变喷嘴鼓风机AREA燃气涡轮发动机降低风扇不稳定性
公开(公告)号：EP2798187A1
公开(公告)日：2014-11-05
申请号：EP12872220.4
申请日：2012-12-28
Applicant: United Technologies Corporation
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F02K3/075
Abstract: A nacelle assembly for a high-bypass gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, and a controller operable to control the fan variable area nozzle to vary a fan nozzle exit area and adjust the pressure ratio of the fan bypass airflow.
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8.发明公开GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO 审中-公开具有可变鼓风口区用于低风扇压力比燃气涡轮发动机
公开(公告)号：EP2798184A1
公开(公告)日：2014-11-05
申请号：EP12871743.6
申请日：2012-12-28
Applicant: United Technologies Corporation
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F02K1/06
Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, the fan pressure ratio less than about 1.45. In a further embodiment of any of the foregoing nacelle assembly for a gas turbine engine embodiment, the assembly further includes a controller operable to control the fan variable area nozzle.
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公开(公告)号：EP2798162A2
公开(公告)日：2014-11-05
申请号：EP12871636.2
申请日：2012-12-28
Applicant: United Technologies Corporation
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P. , SCHWARZ, Frederick M.
IPC: F01D25/24
Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
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10.发明公开
公开(公告)号：EP2788609A1
公开(公告)日：2014-10-15
申请号：EP12869088.0
申请日：2012-12-07
Applicant: United Technologies Corporation
Inventor： KOHLENBERG, Gregory A. , ZAMORA, Sean P.
IPC: F02K3/075
Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle axially movable relative the fan nacelle to define an auxiliary port to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
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