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公开(公告)号：US3879941A
公开(公告)日：1975-04-29
申请号：US36238073
申请日：1973-05-21
Applicant: GEN ELECTRIC
Inventor： SARGISSON DONALD FARLEY
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/026 , F02K3/06 , F02K3/075 , F02K3/11 , Y10T137/0536
Abstract: A variable cycle gas turbine engine for commercial supersonic aircraft is provided with variable geometry means to simultaneously control the bypass and pressure ratios for different engine flight conditions wherein the engine may be operated at supersonic speed with a lower bypass and higher pressure ratio than at subsonic speed. The relatively high noise levels generally associated with the supersonic mode of operation for conventional supersonic engines can be significantly reduced by controlling the variable geometry means in a manner which increases the bypass ratio and decreases the pressure ratio of the fan section of the engine. In this manner, supersonic aircraft may approach and take off from airports situated adjacent densely populated areas without unduly disturbing the local residents.
Abstract translation: 用于商用超音速飞机的可变循环燃气涡轮发动机设置有可变几何装置，以同时控制不同发动机飞行条件的旁路和压力比，其中发动机可以以比亚音速更低的旁路和更高压力比在超音速下操作 。 通常通过以增加旁路比并降低发动机的风扇部分的压力比的方式控制可变几何装置，通常与常规超音速发动机的超音速操作模式相关联的相对较高的噪声水平可以显着降低。 以这种方式，超音速飞机可以靠近人口稠密地区的机场接近起飞，而不会不当地扰乱当地居民。
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公开(公告)号：US3915413A
公开(公告)日：1975-10-28
申请号：US45475174
申请日：1974-03-25
Applicant: GEN ELECTRIC
Inventor： SARGISSON DONALD FARLEY
CPC classification number: B64D33/02 , B64D2033/026 , F02C7/042 , F05D2220/80 , Y02T50/671 , Y10T137/0645
Abstract: A variable geometry inlet system is provided for a subsonic/supersonic gas turbine engine wherein a secondary inlet airflow is selectively ejected into a primary inlet airflow in order to augment the overall mass airflow to the engine and increase inlet pressure recovery. A plurality of foils are cooperatively disposed in rotatable connection with respect to a nacelle in order to modulate the secondary inlet airflow and match the velocity of the secondary airstream to that of the primary airstream thus reducing the mixing loss which would otherwise occur if the two streams commingled at different velocities. The primary and secondary inlet airstreams may also be maintained at a sufficiently high velocity to reduce the forward propagation of engine generated noise. The foils may also be rotated to define an outlet whereby a portion of the primary inlet airflow may be ejected overboard during supersonic operation to reduce aerodynamic drag as might otherwise result from a malfunctioning engine.
Abstract translation: 提供了用于亚音速/超音速燃气涡轮发动机的可变几何入口系统，其中次级入口气流被选择性地喷射到主入口气流中，以便增加到发动机的总质量气流并增加入口压力恢复。 多个箔片相对于机舱以可旋转的方式相互配合地设置，以便调节次级入口气流并使二次气流的速度与主要气流的速度相匹配，从而减少如果两个流 混合在不同的速度。 主入口气流和次级入口气流也可以以足够高的速度保持，以减少发动机产生的噪声的正向传播。 箔也可以旋转以限定出口，由此在超音速操作期间，主入口气流的一部分可能被外侧喷射，以减少否则可能由故障发动机引起的气动阻力。
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公开(公告)号：US3465950A
公开(公告)日：1969-09-09
申请号：US3465950D
申请日：1968-01-22
Applicant: GEN ELECTRIC
Inventor： FREID WILBERT BERNARD , DUFFY ROBERT JOSEPH , SARGISSON DONALD FARLEY
CPC classification number: F02C7/05
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