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MODELING AN INSTALLATION OF RECUPERATIVE HEAT EXCHANGERS FOR AN AERO ENGINE

机译：对航空发动机换热器的安装进行建模

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This work presents the complete effort to model the presence of an integrated system of heat exchangers mounted in the exhaust nozzle of an aero engine which uses an alternative but more efficient thermodynamic cycle. The heat exchangers are operating as heat recuperators exploiting part of the thermal energy of the turbine exhaust gas to preheat the compressor outlet air before combustion and to reduce pollutants and fuel consumption. The presence of the heat exchangers enforces a significant pressure drop in the exhaust gas flow which can affect the overall efficiency of the thermodynamic cycle and the potential benefit of this technology. For this reason it is important to optimize the operation of the system of heat exchangers. The main target of this optimization effort is the minimization of the pressure losses for the same amount of heat transfer achieved. The optimization is performed with the combined use of experimental measurements and CFD methods. Since the CFD modeling is taking into consideration the overall geometry of the exhaust nozzle of the aero engine where the heat exchangers are mounted, the presence of the latter is unavoidably modeled with the use of a porosity model for practical reasons, having to do with CPU and memory requirements. The porosity model is taking into account the pressure drop and heat transfer behaviour of the heat exchangers and was developed and validated with the use of detailed experimental measurements. For the validation of the CFD model, isothermal experimental measurements carried out for laboratory conditions in a 1:1 model of a quarter of the exhaust nozzle of the aero engine, including four full-scaleheat exchangers, were used. The CFD results were in good agreement with the experimental measurements and the same flow structures and problematic regions were detected. Thus, a complete 3-D CFD model of the overall exhaust nozzle of the aero engine was created and validated which at the next step formed the basis for the optimization of the overall aero engine installation for real engine operating conditions. The improved design of the aero engine installation presented decreased pressure losses in relation to the initial design and a more balanced mass flow distribution, showing the applicability of the overall methodology and its advantages for producing efficient engineering solutions for similar setups.
机译：这项工作提出了对安装在航空发动机排气喷嘴中的热交换器集成系统进行建模的全部工作，该系统使用替代方法但效率更高的热力学循环。热交换器用作换热器，利用涡轮机废气的部分热能在燃烧之前预热压缩机出口空气，并减少污染物和燃料消耗。热交换器的存在会在废气流中产生明显的压降，这会影响热力学循环的整体效率以及该技术的潜在优势。因此，优化热交换器系统的运行非常重要。该优化工作的主要目标是在达到相同热量传递的情况下将压力损失最小化。通过结合使用实验测量和CFD方法来执行优化。由于CFD建模考虑了安装热交换器的航空发动机排气喷嘴的整体几何形状，因此出于实际原因，不可避免地要使用孔隙度模型来模拟后者的存在，这与CPU有关和内存需求。孔隙率模型考虑了热交换器的压降和传热特性，并通过使用详细的实验测量值进行了开发和验证。为了验证CFD模型，在实验室条件下对航空发动机排气喷嘴的四分之一的1：1模型进行了等温实验测量，其中包括四个满量程 使用了热交换器。 CFD结果与实验测量结果非常吻合，并且检测到相同的流动结构和有问题的区域。因此，创建并验证了航空发动机整体排气喷嘴的完整3-D CFD模型，该模型在下一步为针对实际发动机工况优化整个航空发动机安装奠定了基础。航空发动机装置的改进设计相对于初始设计而言减少了压力损失，使质量流量分布更加平衡，显示了总体方法的适用性及其为类似设置提供高效工程解决方案的优势。

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