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1. 发明授权

US4000610A Flight maneuverable nozzle for gas turbine engines 失效
标题翻译：燃气轮机的飞行机动喷嘴
公开(公告)号：US4000610A
公开(公告)日：1977-01-04
申请号：US572340
申请日：1975-04-28
申请人： Dudley O. Nash , Robert G. Beavers , Joseph C. Burge , Onofre T. M. Castells , Alan I. Parker
发明人： Dudley O. Nash , Robert G. Beavers , Joseph C. Burge , Onofre T. M. Castells , Alan I. Parker
IPC分类号： F02K1/78 , B64C15/02 , F02K1/00 , F02K1/12 , F02K1/20
CPC分类号： F02K1/006 , F02K1/1215
摘要： A flight maneuverable gas turbine exhaust nozzle is provided with cooperating variable internal converging-diverging flaps to provide area control. A flap downstream of the converging-diverging flap provides flight maneuver vectoring as well as external exhaust expansion control. A vertical take-off and landing capability is provided by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. The nozzle throat rotates with the deflector to produce efficient turning of the exhaust stream.
摘要翻译：飞行机动式燃气轮机排气喷嘴设有配合可变的内部会聚发散翼片，以提供区域控制。在会聚发散翼下游的翼片提供飞行机动矢量以及外部排气扩展控制。通过部署旋转阀盖型偏转器来提供垂直起降能力，其将排气流向下排放到排气喷嘴的一侧。喷嘴喉部与偏转器一起旋转以产生排气流的有效转动。

2. 发明授权

US4254619A Partial span inlet guide vane for cross-connected engines 失效
标题翻译：用于交叉连接发动机的部分跨度入口导叶
公开(公告)号：US4254619A
公开(公告)日：1981-03-10
申请号：US901934
申请日：1978-05-01
申请人： Rollin G. Giffin, III , Onofre T. M. Castells
发明人： Rollin G. Giffin, III , Onofre T. M. Castells
IPC分类号： F02K3/04 , F02K3/075 , F02K3/12 , F04D29/36
CPC分类号： F04D29/362 , F02K3/075 , F02K3/12 , Y02T50/671
摘要： A pair of turbofan engines are cross connected such that during normal-mode operation horsepower can be shared by the respective cores, and when one engine core becomes inoperative the fan of that engine can be driven by the turbine of the operative engine to thereby maintain a substantial thrust output. In order to balance the respective thrust outputs, variable inlet guide vanes are controlled to decrease the fan mass flow in the operative engine and increase the fan mass flow in the inoperative engine. The variable inlet guide vanes are so constructed as to only partially span the fan duct so as to not appreciably affect the airflow to the core when the inlet guide vane angle setting is altered to allow the core to thereby retain a high level of supercharging during this operational period of maximum power demand.
摘要翻译：一对涡轮风扇发动机是交叉连接的，使得在正常模式操作期间，功率可以由相应的核共享，并且当一个发动机核心变得不起作用时，该发动机的风扇可以由操作发动机的涡轮驱动，从而维持大推力输出。为了平衡各个推力输出，控制可变入口导向叶片以减少操作发动机中的风扇质量流量，并增加不可操作的发动机中的风扇质量流量。可变入口引导叶片被构造成仅部分跨越风扇管道，以便当入口导向叶片角度设置被改变时不会明显地影响到气流的流动，从而允许岩心在此期间保持高水平的增压最大电力需求运行期。

3. 发明授权

US4222233A Auxiliary lift propulsion system with oversized front fan 失效
公开(公告)号：US4222233A
公开(公告)日：1980-09-16
申请号：US820657
申请日：1977-08-02
申请人： James E. Johnson , Onofre T. M. Castells , Dan J. Rundell
发明人： James E. Johnson , Onofre T. M. Castells , Dan J. Rundell
IPC分类号： B64C29/00 , B64D27/20 , F02K1/00 , F02K3/02 , F02K9/06
CPC分类号： F02K3/025 , B64C29/005 , F02K1/002 , Y02T50/671
摘要： A propulsion system for use primarily in V/STOL aircraft is provided with a variable cycle, double bypass gas turbofan engine and a remote augmenter to produce auxiliary lift. The fan is oversized in air-pumping capability with respect to the cruise flight requirements of the remainder of the engine and a variable area, low pressure turbine is capable of supplying varying amounts of rotational energy to the oversized fan, thereby modulating its speed and pumping capability. During powered lift flight, the variable cycle engine is operated in the single bypass mode with the oversized fan at its maximum pumping capability. In this mode, substantially all of the bypass flow is routed as an auxiliary airstream to the remote augmenter where it is mixed with fuel, burned and exhausted through a vectorable nozzle to produce thrust for lifting. Additional lift is generated by the high energy products of combustion of the variable cycle engine which are further energized in an afterburner and exhausted through a thrust vectorable nozzle at the rear of the engine. In the cruise operating mode, the fan is driven at a slower rotational speed and all of the bypass flow is directed to a variable area bypass injector where it is mixed with the variable cycle engine products of combustion and exhausted as a mixture through the rear nozzle. The variable cycle engine can be selectively operated in the single or double bypass mode during cruise to maximize efficiency as the aircraft speed is varied. Because the total installed thrust is available in the forward cruise mode, an aircraft powered by the propulsion system of the present invention has substantially greater capabilities in the areas of excess power, acceleration time and combat ceiling when compared to prior art conceptions embodying separate lift plus lift/cruise engines. Additionally, by not having to develop and maintain a separate lift engine system, a substantially lower aircraft lift cycle cost is possible.

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