直升机休养飞行条件下的节油潜力评价

Chengyu Zhang, M. Kerler, V. Gümmer
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引用次数: 3

摘要

将回热器集成到涡轮发动机中,使废气和压缩空气之间的热量传递成为可能,这表明在降低排放和SFC(比燃料消耗)方面具有相当大的潜力。然而,事实上,它们尚未在飞机应用中得到广泛接受。其中一个主要的潜在缺点是,在这种情况下,系统的总重量需要严格控制,而且人们担心,有益的燃油节省可能无法抵消回热器的额外体积和重量。为了评估回收旋翼机的性能,研究回收器对整个系统的影响,开发了一个综合的仿真框架,主要包含三个不同飞行条件的模块:直升机性能模块(HPM)、GasTurb发动机仿真模块和回收器重量估计模块。具体来说,HPM计算直升机在不同飞行条件(高度、速度等)下的动力需求,利用GasTurb对常规涡轮发动机和再生涡轮发动机的性能进行模拟,计算出满足动力需求的相应发动机作用点。回收器重量的估计主要是基于以往的研究,作为质量流量和有效性的函数。该方法被用于典型的双发轻型直升机配置。通过与常规非回热循环的比较,研究了不同回热效能下的回热循环在不同飞行条件下的燃油节约潜力,并进行了权衡分析,以确定补偿额外回热重量所需的飞行时间。研究结果表明,在长航程、大航程任务中,回收循环具有很大的潜力,但不一定适用于所有类型的直升机任务。
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Evaluation of the Fuel Saving Potential Regarding Recuperated Helicopter Flight Conditions
Incorporating recuperators into turbine engines which enables the heat transfer between exhaust gas and compressed air, indicates considerable potential for lower emissions and SFC (specific fuel consumption). However as a matter of fact, they have not yet found wide acceptance in aircraft applications. One of the main potential disadvantages is because in such situations system overall weight needs to be strictly controlled, and there are concerns that the beneficial fuel saving may not offset the additional bulk and weight of the recuperator. In this work, aimed at evaluating the performance of the recuperated rotorcraft and investigating the influence of a recupeator on the whole system, a comprehensive simulation framework has been developed which mainly contains three modules for various flight conditions: Helicopter performance module (HPM), GasTurb engine simulation module and the recuperator weight estimation. Specifically, HPM calculates the helicopter power requirement for different flight conditions (altitude, speed, etc.), and GasTurb is used to simulate the performance of conventional and recuperated turbine engine, and compute the corresponding engine operating point to meet the power demand. The recuperator weight estimation is mainly based on previous studies as a function of mass flow and effectiveness. The methodology is adopted for a typical twin engine light helicopter configuration. In comparison with the conventional non-recuperated cycle, the authors studied the fuel saving potential of the recuperated cycle for different recuperator effectiveness under various flight conditions, and a trade-off analysis was also conducted to identify the flight time required to compensate the additional recuperator weight. The obtained results suggested that the recuperated cycle possesses great potential, especially for long duration and large range mission, but it may not be necessarily suitable for all types of helicopter missions.
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