A hybrid engine concept for multi-fuel blended wing body
A hybrid engine concept for multi-fuel blended wing body
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DOI：
10.1108/aeat-04-2014-0054
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发表时间：
2014-10
影响因子：
1.5
通讯作者：
A. Rao;F. Yin;J. V. Buijtenen
中科院分区：
文献类型：
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作者：
A. Rao;F. Yin;J. V. Buijtenen
目的-本文的目的是提出一种用于多燃料混合翼身(MFBWB)飞机的新型混合发动机概念，并对该发动机概念的性能进行评估。设计/方法/方法-拟议的混合动力发动机概念有几个新的特点，包括一个用于实现边界层吸入的反向旋转风扇，在涡轮间燃烧器中使用低温燃料(液化天然气[LNG]或液氢[LH2])和煤油的双燃烧室(在无焰燃烧模式下)，以及利用低温燃料进行排气冷却的冷却系统。利用燃气轮机模拟程序建立了混合动力发动机的零维热力学模型，对各种可能的发动机结构进行了性能参数分析。此外，使用开发的内部热力发动机模型和遗传算法，在循环参考点对所选发动机结构进行了优化。研究结果--使用液化氢和煤油，混合动力引擎。
Purpose – The purpose of this paper is to present a novel hybrid engine concept for a multi-fuel blended wing body (MFBWB) aircraft and assess the performance of this engine concept. Design/methodology/approach – The proposed hybrid engine concept has several novel features which include a contra-rotating fan for implementing boundary layer ingestion, dual combustion chambers using cryogenic fuel (liquefied natural gas [LNG] or liquid hydrogen [LH2]) and kerosene in the inter-turbine burner (in flameless combustion mode) and a cooling system for bleed air cooling utilizing the cryogenic fuel. A zero-dimensional thermodynamic model of the proposed hybrid engine is created using Gas Turbine Simulation Program to parametrically analyse the performance of various possible engine architectures. Furthermore, the chosen engine architecture is optimized at a cycle reference point using a developed in-house thermodynamic engine model coupled with genetic algorithm. Findings – Using LH2 and kerosene, the hybrid eng...