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首页> 外文期刊>The Aeronautical Journal >Potential of surrogate modelling in compressor casing design focussing on rapid tip clearance assessments
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Potential of surrogate modelling in compressor casing design focussing on rapid tip clearance assessments

机译：压缩机套管设计中替代模型的潜力焦点快速提示清关评估

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Losses induced by tip clearance limit decisive improvements in the system efficiency and aerodynamic operational stability of aero-engine axial compressors. The tendency towards even lower blade heights to compensate for higher fluid densities aggravates their influence. Generally, it is emphasised that the tip clearance should be minimised but remain large enough to prevent collisions between the blade tip and the casing throughout the entire mission. The present work concentrates on the development of a preliminary aero-engine axial compressor casing design methodology involving meta-modelling techniques. Previous research work at the Institute for Turbomachinery and Flight Propulsion resulted in a Two-Dimensional (2D) axisymmetric finite element model for a generic multi-stage high-pressure axial compressor casing. Subsequent sensitivity studies led to the identification of significant parameters that are important for fine-tuning the tip clearance via specific flange design. This work is devoted to an exploration of the potential of surrogate modelling in preliminary compressor casing design with respect to rapid tip clearance assessments and its corresponding precision in comparison with finite element results. Reputed as data-driven mathematical approximation models and conceived for inexpensive numerical simulation result reproduction, surrogate models show even greater capacity when linked with extensive design space exploration and optimisation algorithms. Compared with high-fidelity finite element simulations, the reductions obtained in computational time when using surrogate models amount to 99.9%. Validated via statistical methods and dependent on the size of the training database, the precision of surrogate models can reach down to the range of manufacturing tolerances. Subsequent inclusion of such surrogate models in a parametric optimisation process for tip clearance minimisation rapidly returned adaptions of the geometric design variables.
机译：尖端间隙诱导的损失限制了航空发动机轴流压缩机的系统效率和空气动力运行稳定性的决定性改进。甚至降低叶片高度以补偿更高的流体密度的趋势加剧了它们的影响。通常，强调尖端间隙应最小化但保持足够大，以防止在整个任务中的叶片尖端和壳体之间的碰撞。目前的工作专注于开发初步航空发动机轴向压缩机套管设计方法，涉及元建模技术。以前在涡轮机械和飞行推进研究所的研究工作导致通用多级高压轴向压缩机壳体的二维（2D）轴对称有限元模型。随后的灵敏度研究导致了通过特定法兰设计微调尖端间隙的重要参数。这项工作探讨了关于快速尖端间隙评估的初步压缩机壳体设计中替代模型的潜力及其相应的精度与有限元结果相比。被誉为数据驱动的数学近似模型，并构思了廉价的数值模拟结果再现，代理模型在与广泛的设计空间探索和优化算法相关时表现出更大的容量。与高保真有限元模拟相比，使用替代模型的计算时间在计算时间内获得的额度为99.9％。通过统计方法验证并取决于培训数据库的大小，代理模型的精度可以达到制造公差范围。随后在参数化优化过程中包含这种代理模型，用于尖端清除最小化的快速返回几何设计变量的自适应。

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