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公开(公告)号：US4142365A
公开(公告)日：1979-03-06
申请号：US737786
申请日：1976-11-01
CPC分类号： F02K3/077 , F02K1/386 , F02K3/04 , Y02T50/671
摘要： A high bypass ratio gas turbofan engine provided with a hybrid mixer for mixing that portion of the bypass stream equivalent to a bypass ratio of substantially two with the core engine hot gas stream. The mixture is passed through a common exhaust nozzle.
摘要翻译： 具有混合混合器的高旁路比气体涡轮风扇发动机，用于将相当于二级旁路比的旁路流的那部分与核心发动机热气流混合。 混合物通过一个普通的排气喷嘴。
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公开(公告)号：US4951463A
公开(公告)日：1990-08-28
申请号：US421905
申请日：1989-10-16
CPC分类号： F02K9/52 , F02K7/10 , F23R3/28 , F05D2260/20
摘要： A hypersonic scramjet engine fuel injector and a hypersonic scramjet engine having such a fuel injector. The engine has a serially connected inlet, combustor, and exhaust nozzle. Multiple, horizontally-spaced-apart fuel injectors are positioned in and connected to the combustor's top portion. Each fuel injector has a hollow wedge shape housing. To improve fuel-air mixing for better combustion, the housing's end wall has multiple, discrete, convergent-divergent fuel outlet nozzles and its side walls have horizontally-extending exterior grooves. Fuel is used to cool the fuel injector housing with the housing's bottom and side walls having fuel-exit holes and the housing having an interior serpentine fuel passageway.
摘要翻译： 超音速冲击式发动机燃料喷射器和具有这种燃料喷射器的超音速冲击式发动机。 发动机具有串联连接的入口，燃烧器和排气喷嘴。 多个水平间隔开的燃料喷射器位于并连接到燃烧器顶部。 每个燃料喷射器具有中空楔形壳体。 为了改善燃料 - 空气混合以改善燃烧，壳体的端壁具有多个分立的会聚发散燃料出口喷嘴，其侧壁具有水平延伸的外部凹槽。 燃料用于冷却燃料喷射器壳体，壳体的底部和侧壁具有燃料出口孔，并且壳体具有内部蛇形燃料通道。
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公开(公告)号：US4903480A
公开(公告)日：1990-02-27
申请号：US245181
申请日：1988-09-16
CPC分类号： F23R3/28 , F02K7/10 , F02K9/52 , F05D2260/20
摘要： A hypersonic scramjet engine fuel injector and a hypersonic scramjet engine having such a fuel injector. The engine has a serially connected inlet, combustor, and exhaust nozzle. Multiple, horizontally-spaced-apart fuel injectors are positioned in and connected to the combustor's top portion. Each fuel injector has a hollow wedge shape housing. To improve fuel-air mixing for better combustion, the housing's end wall has multiple, discrete, convergent-divergent fuel outlet nozzles and its side walls have horizontally-extending exterior grooves. Fuel is used to cool the fuel injector housing with the housing's bottom and side walls having fuel-exit holes and the housing having an interior serpentine fuel passageway.
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公开(公告)号：US4993663A
公开(公告)日：1991-02-19
申请号：US359556
申请日：1989-06-01
CPC分类号： B64D33/02 , B64C21/06 , B64D29/00 , F01D5/145 , F02C7/04 , B64C2230/04 , B64C2230/06 , B64D2033/0226 , Y02T50/166 , Y02T50/671 , Y02T50/673
摘要： A hybrid laminar flow nacelle for housing an engine of an aircraft includes an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at the leading lip. The nacelle incorporates a suction bleed system between the surfaces and a tailored outer surface geometry shape for producing reduced friction drag laminar flow over the outer cowl at cruise operation of the aircraft and producing separation-free flow over the inner surface of the cowl at off-cruise operation of the aircraft.
摘要翻译： 用于容纳飞行器的发动机的混合层流机舱包括具有前缘和径向间隔开并且轴向延伸的环形外部和内部前表面部分的外部环形罩，其在前缘处合并。 机舱结合了表面之间的抽吸排放系统和适合的外表面几何形状，用于在飞行器的巡航操作下在外罩上产生减小的摩擦阻力层流，并在离合器的整个外罩的内表面上产生无分离的流动， 巡航操作的飞机。
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公开(公告)号：US4799633A
公开(公告)日：1989-01-24
申请号：US77963
申请日：1987-07-27
CPC分类号： B64D29/00 , B64D33/02 , B64D2033/0226
摘要： An improved nacelle is provided for housing an aircraft engine and reducing aerodynamic drag during aircraft operation. In one embodiment, the nacelle houses a gas turbine engine and comprises a leading edge and a trailing edge, having a reference chord extending therebetween, and an outer surface which is continuous from the leading edge to the trailing edge. The outer surface includes a forward portion, an intermediate portion and an aft portion that has a profile defined by a varying thickness measured perpendicularly from the chord to the outer surface. The profile has a maximum thickness at the intersection of the forward and intermediate portions, which intersection is located greater than about 36% of the chord from the leading edge, and is effective for increasing laminar flow over the nacelle for reducing aerodynamic drag.
摘要翻译： 提供了一种改进的机舱，用于容纳飞行器发动机并在飞行器运行期间减少气动阻力。 在一个实施例中，机舱容纳燃气涡轮发动机，并且包括前缘和后缘，其具有在其间延伸的参考弦和从前缘到后缘连续的外表面。 外表面包括前部，中间部分和后部，其具有由垂直于弦到外表面测量的变化厚度限定的轮廓。 该轮廓在前部和中间部分的交叉点处具有最大厚度，该交叉点位于大于前缘的约36％的弦处，并且有效地增加机舱上的层流以减小气动阻力。
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公开(公告)号：US4969327A
公开(公告)日：1990-11-13
申请号：US422178
申请日：1989-10-16
CPC分类号： F02K9/52 , F02K7/10 , F23R3/28 , F05D2260/20
摘要： A hypersonic scramjet engine fuel injector and a hypersonic scramjet engine having such a fuel injector. The engine has a serially connected inlet, combustor, and exhaust nozzle. Multiple, horizontally-spaced-apart fuel injectors are positioned in and connected to the combustor's top portion. Each fuel injector has a hollow wedge shape housing. To improve fuel-air mixing for better combustion, the housing's end wall has multiple, discrete, convergent-divergent fuel outlet nozzles and its side walls have horizontally-extending exterior grooves. Fuel is used to cool the fuel injector housing with the housing's bottom and side walls having fuel-exit holes and the housing having an interior serpentine fuel passageway.
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公开(公告)号：US4410150A
公开(公告)日：1983-10-18
申请号：US368242
申请日：1982-04-14
申请人： Daniel J. Lahti
发明人： Daniel J. Lahti
CPC分类号： B64D29/02 , B64C23/00 , B64D33/02 , F02K1/52 , F02K3/04 , B64C2230/20 , Y02T50/166
摘要： A wing-mounted gas turbofan engine is provided with an exhaust system that reduces airflow drag during subsonic aircraft flight operation. The system reduces drag by turning the engine bypass exhaust stream away from the underside of the airplane wing to lessen its tendency to reduce air pressure under the wing. Low pressure below the airplane wing has a detrimental effect on wing lift which, in turn, causes greater airflow drag. The exhaust system construction lessens its pressure lowering influence by first, inwardly curving the exhaust system exit to turn the bypass flow away from the airplane wing; second, by predetermining the location of a nozzle throat within the bypass stream to control exit exhaust pressure so as to match outside air pressure and third, by decreasing the diameter of a portion of the engine nacelle just downstream of the bypass exhaust stream exit to provide a flow region for the exhaust that is further from the airplane wing.
摘要翻译： 机翼式涡轮风扇发动机配有排气系统，可在亚音速飞行器飞行操作期间减少气流阻力。 该系统通过将发动机旁通排气流转移离开飞机机翼的下侧来减少阻力，以减少其降低机翼下方气压的趋势。 飞机机翼下方的低压对机翼升力有不利影响，这又会导致更大的气流阻力。 排气系统结构通过首先使排气系统出口向内弯曲，使旁路流离开飞机机翼，从而降低其降压影响; 第二，通过预先确定旁路流内的喷嘴喉部的位置来控制出口排气压力，以便匹配外部空气压力和第三，通过在旁路排气流出口下游减小发动机舱的一部分的直径以提供 用于更远离飞机机翼的排气的流动区域。
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