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Investigations of Synergistic Combination of the Composite Cycle and Intercooled Recuperation

机译:复合循环和中间冷却恢复协同组合的研究

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The synergistic combination of two promising engine architectures for future aero engines is presented. The first is the Composite Cycle Engine, which introduces a piston system in the high pressure part of the core engine, to utilize closed volume combustion and high temperature capability due to instationary operation. The second is the Intercooled Recuperated engine that employs recuperators to utilize waste heat from the core engine exhaust, and intercooler to improve temperature levels for recuperation and to reduce compression work. Combinations of both architectures are presented and investigated for improvement potential with respect to specific fuel consumption, engine weight and fuel burn against a turbofan. Intercooler options were screened, and a benefit of up to 1.9% fuel burn could be shown for installation in front of piston system through a significant, efficiency-neutral weight decrease. Waste heat can be utilized by means of classic recuperation to the entire core mass flow before the combustor, or alternatively on the turbine cooling bleed or a piston engine bypass flow that is mixed again with the main flow before the combustor. As further permutation, waste heat can be recovered either after the low pressure turbine - with or without sequential combustion - or between the high pressure and low pressure turbine. Waste heat recovery after the low pressure turbine was found to be not easily feasible or tied to high fuel burn penalties due to unfavourable temperature levels, even when using sequential combustion or intercooling. Feasible temperature levels could be obtained with inter-turbine waste heat recovery, but always resulted in higher fuel burn compared to the non-recuperated baseline under the given assumptions. Consequently, only the application of an intercooler appears to provide a considerable benefit for the examined thermodynamic conditions in the low fidelity analyses of various engine architecture combinations with the specific heat exchanger design. Since the obtained drawbacks of some waste heat utilization concepts are small, innovative waste heat management concepts coupled with the further extension of the design space and the inclusion of higher fidelity models may achieve a benefit and motivate future investigations.
机译:提出了两个有前途发动机架构为未来航空发动机的协同组合。首先是复合循环发动机,其在芯发动机的高压部分引入活塞系统,以利用由于航空运行而采用闭合的体积燃烧和高温能力。第二是采用恢复器利用来自芯发动机排气的储存和中冷却器来改善恢复的温度水平并减少压缩工作的恢复器的倒闭发动机。展示和研究了这两种架构的组合,用于对特定燃料消耗,发动机重量和燃料燃烧的改进潜力。筛选了中间冷却器选项,可以通过显着的效率 - 中性重量减少在活塞系统前面安装高达1.9%的燃料燃烧的益处。废热可以通过经典的恢复来利用燃烧器之前的整个核心质量流动,或者在涡轮机冷却出止血或燃烧器之前再次混合的活塞发动机旁路流动。作为进一步排列,可以在低压涡轮机之后回收废热 - 或者没有连续燃烧 - 或在高压和低压涡轮机之间。在低压涡轮机中发现余热恢复是由于使用顺序燃烧或中冷却,由于不利的温度水平,由于不利的温度水平而不易得到可靠或与高燃料烧伤造成的。通过涡轮机垃圾热回收可以获得可行的温度水平,但与在给定假设下的非恢复基线相比,总是导致更高的燃料燃烧。因此,仅似乎仅应用中间冷却器的应用对于具有特定热交换器设计的各种发动机架构组合的低保真分析中的检查热力学条件的相当大的益处。由于一些废热利用概念的所获得的缺点是小的,创新的废热管理概念与设计空间的进一步延伸,并且包含更高的保真模型可以实现益处和激励未来的研究。

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