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公开(公告)号：US5706651A
公开(公告)日：1998-01-13
申请号：US521139
申请日：1995-08-29
CPC分类号： F02K3/06 , B64D33/06 , F02C7/045 , F02C7/24 , F02K1/386 , F02K1/48 , F02K1/60 , F05D2220/327 , Y02T50/672
摘要： A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level. There is a fan at the upstream end of the core engine for generating axial fan air flow through bypass ducts terminating at a common nozzle, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A target thrust reverser includes opposing doors rotatable into position to block and divert the flow of exhaust gas for generating reverse thrust. Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine. An acoustically dampened light bulb-shaped nose cone is provided for coaxial attachment to an upstream end of the core engine. The axial flow front fan is axially separated from the inlet guide vane is extended relatively forwardly. A bleed air valve, selectively operational to bleed air from the core engine when the valve is open, is ducted for directing bleed air to the vicinity of the common nozzle.
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公开(公告)号：US5943856A
公开(公告)日：1999-08-31
申请号：US905148
申请日：1997-08-01
CPC分类号： F02K3/06 , B64D33/06 , F02C7/045 , F02C7/24 , F02K1/386 , F02K1/48 , F02K1/60 , F05D2220/327 , Y02T50/672
摘要： A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level. There is a fan at the upstream end of the core engine for generating axial fan air flow through bypass ducts terminating at a common nozzle, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A target thrust reverser includes opposing doors rotatable into position to block and divert the flow of exhaust gas for generating reverse thrust. Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine. An acoustically dampened light bulb-shaped nose cone is provided for coaxial attachment to an upstream end of the core engine. The axial flow front fan is axially separated from the inlet guide vane is extended relatively forwardly. A bleed air valve, selectively operational to bleed air from the core engine when the valve is open, is ducted for directing bleed air to the vicinity of the common nozzle.
摘要翻译： 一种降噪套件，用于修改由多级压缩机和多级反应涡轮驱动的风扇的两（2）阀芯轴流涡扇风扇发动机，推力至少约为18,000磅。 在海平面。 在核心发动机的上游端有一个风扇，用于通过终止于公共喷嘴的旁路管道产生轴流式风机空气流，公共喷嘴具有用于每个风扇空气流和一个范围内的废气的混合平面区域 在700和800平方英寸之间。 目标推力反向器包括可旋转到位置的相对的门，以阻挡和转移废气流以产生反向推力。 用于径向转向风扇空气并允许排气径向向外膨胀的混合装置同轴地设置在核心发动机的下游。 提供了一种用于与核心发动机的上游端同轴连接的声阻尼的灯泡形鼻锥。 轴流前风扇与入口导叶轴向分离，相对向前延伸。 排气阀，当阀打开时，选择性地操作以从核心发动机排出空气，用于将排气引导到公共喷嘴附近。
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公开(公告)号：US5791138A
公开(公告)日：1998-08-11
申请号：US584342
申请日：1996-01-11
CPC分类号： F02K3/06 , F02C7/045 , F02C7/24 , F02K1/386 , F02K1/48 , F02K1/60 , F05D2220/327 , Y02T50/672
摘要： A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level. There is a fan at the upstream end of the core engine for generating axial fan air flow through bypass ducts terminating at a common nozzle, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A material layer is located in a spacing between a tip of blades for at least some of the fans and a duct for the fans, thereby to reduce a normal clearance between the tip of blades for the fan and the duct. Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine. An acoustically dampened light bulb-shaped nose cone is provided for coaxial attachment to an upstream end of the core engine. There is an inlet pressure sensing probe housed in an inlet bullet forwardly of the fans. Alternatively, there is an inlet pressure sensing probe housed at a location of an inlet guide vane forwardly of the fans, the probe being shaped for aerodynamic location in the inlet guide vane. The axial flow front fan is axially separated from the inlet guide vane is extended relatively forwardly.
摘要翻译： 一种降噪套件，用于修改由多级压缩机和多级反应涡轮驱动的风扇的两（2）阀芯轴流涡扇风扇发动机，推力至少约为18,000磅。 在海平面。 在核心发动机的上游端有一个风扇，用于通过终止于公共喷嘴的旁路管道产生轴流式风机空气流，公共喷嘴具有用于每个风扇空气流和一个范围内的废气的混合平面区域 在700和800平方英寸之间。 材料层位于用于至少一些风扇的叶片的尖端和用于风扇的管道之间的间隔中，从而减小用于风扇的叶片的尖端与管道之间的正常间隙。 用于径向转向风扇空气并允许排气径向向外膨胀的混合装置同轴地设置在核心发动机的下游。 提供了一种用于与核心发动机的上游端同轴连接的声阻尼的灯泡形鼻锥。 入口压力传感探头安装在风扇前方的入口子弹中。 或者，存在入口压力感测探头，其容纳在风扇向前的入口导向叶片的位置处，该探针成形为入口导叶中的空气动力学位置。 轴流前风扇与入口导叶轴向分离，相对向前延伸。
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