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首页> 外文期刊>The Aeronautical Journal >Design optimisation of separate- jet exhausts for the next generation of civil aero-engines
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Design optimisation of separate- jet exhausts for the next generation of civil aero-engines

机译：下一代民用航空发动机的分离喷气排气设计优化

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The next generation of civil large aero-engines will employ greater bypass ratios compared with contemporary architectures. This results in higher exchange rates between exhaust performance and specific fuel consumption (SFC). Concurrently, the aerodynamic design of the exhaust is expected to play a key role in the success of future turbofans. This paper presents the development of a computational framework for the aerodynamic design of separate-jet exhaust systems for civil aero-engines. A mathematical approach is synthesised based on class-shape transformation (CST) functions for the parametric geometry definition of gas-turbine exhaust components such as annular ducts and nozzles. This geometry formulation is coupled with an automated viscous and compressible flow solution method and a cost-effective design space exploration (DSE) approach. The framework is deployed to optimise the performance of a separate-jet exhaust for very-high-bypass ratio (VHBR) turbofan engine. The optimisations carried out suggest the potential to increase the engine's net propulsive force compared with a baseline architecture, through optimum exhaust redesign. The proposed method is able to identify and alleviate adverse flow-features that may deteriorate the aerodynamic behaviour of the exhaust system.
机译：与当代建筑相比，下一代民用大型航空发动机将采用更大的旁通比。这导致排气性能与比燃料消耗（SFC）之间的汇率更高。同时，排气的空气动力学设计有望在未来涡轮风扇的成功中发挥关键作用。本文介绍了用于民用航空发动机的独立喷射排气系统的空气动力学设计计算框架的发展。基于类形状变换（CST）函数的数学方法综合在一起，用于燃气轮机排气组件（例如环形管道和喷嘴）的参数几何定义。这种几何结构公式与自动粘性和可压缩流求解方法以及经济高效的设计空间探索（DSE）方法结合在一起。部署该框架可优化超高旁路比（VHBR）涡扇发动机的独立喷射排气的性能。进行的优化表明，通过优化排气设计，与基准架构相比，有可能增加发动机的净推进力。所提出的方法能够识别并减轻可能使排气系统的空气动力学性能恶化的不利的流动特征。

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