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Intercooler parametric analysis for the IRA engine cycle performance augmentation

机译：IRA发动机循环性能增强的中间冷却器参数分析

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Aiming in the direction of designing, high efficiency aircraft engines, various concepts have been developed in recent years, among which is the concept of the intercooled and recuperative aero engine (IRA engine). This concept is based on the use of a system of heat exchangers (recuperator) mounted inside the hot-gas exhaust nozzle, as well as a system of heat exchangers (intercooler) mounted between the intermittent-pressure compressor (IPC) and the high-pressure compressor (HPC) compressor modules. Through the operation of the system of recuperator module, the heat from the exhaust gas, downstream the LP turbine of the aero engine is driven back to the combustion chamber. Thus, the preheated air enters the engine combustion chamber with increased enthalpy, providing higher combustion efficiency and consequently reduced thrust specific fuel consumption (TSFC) and low-level emissions. Additionally, by integrating the intercooler module between the compressor stages of the aero engine, the compressed air is cooled, leading to less required compression work to reach the compressor target pressure and significant improvements can be achieved in the overall engine efficiency and the specific fuel consumption hence, contributing to the reduction of CO_2 and NO_x emissions. The present work is focused on the optimization of the performance characteristics of an intercooler specifically designed for aero engine applications, working cooperatively with a novel design recuperator module targeting the reduction of specific fuel consumption and taking into consideration aero engine geometrical constraints and limitations for two separate operating scenarios. The intercooler design was based on the elliptically profiled tubular heat exchanger which was developed and invented by MTU Aero Engines AG. For the specific fuel consumption investigations, the Intercooled Recuperated Aero engine cycle that combines both intercooling and recuperation was considered. The optimization was performed with the development of an intercooler surrogate model, capable to incorporate major geometrical features. A large number of intercooler design scenarios was assessed, in which additional design criteria and constraints were applied. Thus, a significantly large intercooler design space was covered resulting to the identification of feasible designs providing beneficial effect on the Intercooled Recuperated Aero engine performance leading to reduced specific fuel consumption, reduced weight and extended aircraft range.
机译：旨在沿着设计，高效飞机发动机的方向，近年来已经开发了各种概念，其中包括间隙和恢复航空发动机（IRA发动机）的概念。该概念基于使用安装在热气排气喷嘴内的热交换器（恢复器）的系统，以及安装在间歇压力压缩机（IPC）和高的热交换器（中间冷却器）的系统系统。压力压缩机（HPC）压缩机模块。通过恢复器模块系统的操作，来自废气的热量，下游航空发动机的LP涡轮机被驱动回燃烧室。因此，预热空气进入发动机燃烧室，增加焓，提供更高的燃烧效率，从而降低推力特定燃料消耗（TSFC）和低级排放。另外，通过将中间冷却器模块集成在Aero发动机的压缩机级之间，冷却压缩空气，导致较少所需的压缩工作，以达到压缩机目标压力，并且可以在整体发动机效率和特定燃料消耗中实现显着的改进因此，有助于减少CO_2和NO_X排放。本工作的重点是优化专门设计用于Aero发动机应用的中间冷却器的性能特性，与针对特定燃料消耗的减少的新颖设计恢复器模块合作，同时考虑Aero发动机几何约束和两个单独的限制操作场景。中间冷却器设计基于椭圆形状的管状热交换器，由MTU Aero发动机AG开发和发明。对于特定的燃料消耗调查，考虑了结合中间冷却和恢复的间隙恢复的Aero发动机循环。通过开发中间冷却器代理模型的开发进行了优化，能够包含主要的几何特征。评估了大量的中间冷却器设计方案，其中应用了额外的设计标准和约束。因此，覆盖了显着大的中间冷却器设计空间，从而识别可行的设计，为中间冷却的恢复航空发动机性能提供有益效果，导致特定的燃料消耗，减轻重量和扩展飞机范围。

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