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    • 6. 发明申请
    • COMBINED CYCLE INTEGRATED COMBUSTOR AND NOZZLE SYSTEM
    • 组合式循环混合气体和喷嘴系统
    • WO2008076318A2
    • 2008-06-26
    • PCT/US2007/025522
    • 2007-12-12
    • AEROJET-GENERAL CORPORATIONBULMAN, Melvin, J.
    • BULMAN, Melvin, J.
    • F02K7/08
    • F02K7/18F02K7/10F02K7/14F02K7/16F05D2220/10Y02T50/67
    • An engine (20) that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine (20) is a combined cycle engine having both a booster (30) and a dual mode ramjet (DMRJ). The booster (30) and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster (30) accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air (28) delivered to the DMRJ is accelerated by primary ejector thrusters (34) that may receive oxidizer from either on-board oxidizer tanks (31) or from booster (30) compressor discharge air. As the Combined Cycle Engine further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the booster (30) and exhaust from the DMRJ are combined in a common nozzle (42) disposed downstream of a combustor portion (32) of said DMRJ functioning as an aerodynamic choke.
    • 通过节省车辆和发动机开发成本,在Hypersonic联合循环车辆上操作并产生整个所需车辆推力的发动机(20)在Mach4以下。 一个这样的发动机(20)是具有增压器(30)和双模式冲压喷气发动机(DMRJ)的组合循环发动机。 增压器(30)和DMRJ被一体化以提供从马赫0到超过马赫数4的有效推力。随着助力器(30)将车辆从马赫0加速到超过马赫数4,从马赫0到大约马赫数2 传送到DMRJ的进入空气(28)通过可从车载氧化剂罐(31)或增压器(30)压缩机排出空气接收氧化剂的主喷射推进器(34)加速。 当组合循环发动机进一步将车辆从大约马赫0加速到来自增压器(30)的超过马赫4排气时,并且来自DMRJ的排气被组合在设置在燃烧器部分(32)的下游的公共喷嘴(42)中, DMRJ表现为空气动力学扼流圈。
    • 7. 发明申请
    • NOZZLE WITH TEMPERATURE-RESPONSIVE THROAT DIAMETER
    • 喷嘴与温度响应的直径
    • WO2008033699A2
    • 2008-03-20
    • PCT/US2007/077533
    • 2007-09-04
    • AEROJET-GENERAL CORPORATIONLYNCH, Michael, D.BARR, Dustin, C.
    • LYNCH, Michael, D.BARR, Dustin, C.
    • E03C1/02
    • F02K9/97F02K9/86F02K9/978F05D2250/70F05D2250/71F05D2300/505
    • Nozzles that offer shape variability to maintain or purposely change the pressure drop across the throat are obtained by constructing the nozzles with components that change their shape, angle, or curvature in response to temperature changes that occur during the flow of combustion products through the nozzle. The temperature change may be the gradual heating of the nozzle wall from hot combustion gases, and the shape change may result in a decrease in the throat diameter or an expansion of the throat diameter. A decrease in throat diameter will be useful when the depletion of propellant as burning proceeds causes a drop in the pressure or flow rate of the combustion gas and there is a need to compensate for this drop to maintain the pressure drop across the throat. An increase in throat diameter will be useful when an initial high thrust is no longer needed and depletion of the fuel by itself is insufficient to lower the thrust to its desired reduced level. An example of a temperature-responsive material is a shape memory alloy; other examples are presented as well.
    • 提供形状可变性以保持或有意地改变喉部上的压降的喷嘴是通过根据在通过喷嘴的燃烧产物流动期间发生的温度变化来构造具有改变其形状,角度或曲率的部件的喷嘴而获得的。 温度变化可能是来自热燃烧气体的喷嘴壁的逐渐加热,并且形状变化可能导致喉部直径的减小或喉部直径的膨胀。 喉咙直径的减小将是有用的,当作为燃烧进行的推进剂的消耗导致燃烧气体的压力或流速的下降,并且需要补偿该下降以维持喉部上的压降。 当不再需要初始高推力并且燃料本身的耗尽不足以将推力降低到其期望的减小水平时,喉管直径的增加将是有用的。 温度响应材料的一个例子是形状记忆合金; 还提供了其他示例。