An approach to multi-fidelity optimization of aeroengine compression systems
An approach to multi-fidelity optimization of aeroengine compression systems
复制标题
航空发动机压缩系统多保真度优化方法
DOI：
10.2514/6.2012-5634
复制
发表时间：
2012
期刊：
影响因子：
2.5
通讯作者：
T. Ghisu
中科院分区：
文献类型：
--
作者：
J. Jarrett;T. Ghisu
叶轮机械的气动设计给设计优化团体带来了许多精致的挑战。其中最主要的是设计空间的大小和其中不连续的程度。这种不连续性可能会限制高保真计算流体力学(CFD)的充分利用：这类代码需要详细的几何信息，通常只有在通过其他方法设置了机器的基本配置后才能获得。本文的前提是，通过利用多保真技术在设计过程的早期有效地利用CFD，特别是通过促进其参与配置选择，应该能够在更短的时间内产生更高性能的设计。采用按需生成的局部多保真修正策略，结合自适应信赖域的全局搜索算法，首先在一个适度、光滑的外部气动问题上进行了测试。速度提高了一个数量级，可与应用于平滑问题的既定技术相媲美。然后，一些主要旨在快速有效地评估各种配置的增强措施被应用于基本战略，并在通用航空发动机核心压缩系统上测试了这项新技术。在这个相对较大且高度不连续的问题上，实现了类似数量级的加速。观察到用CFD评估的配置数量增加了五倍。由于该技术既不限制成分分析代码的基本物理模型，也不限制这些代码之间的一阶一致性，因此它有可能适用于一系列多学科的设计挑战。2012Jerome Jarrett和Tiziano Ghisu。
The aerodynamic design of turbomachinery presents the design optimisation community with a number of exquisite challenges. Chief among these are the size of the design space and the extent of discontinuity therein. This discontinuity can serve to limit the full exploitation of high-fidelity computational fluid dynamics (CFD): such codes require detailed geometric information often available only sometime after the basic configuration of the machine has been set by other means. The premise of this paper is that it should be possible to produce higher performing designs in less time by exploiting multi-fidelity techniques to effectively harness CFD earlier in the design process, specifically by facilitating its participation in configuration selection. The adopted strategy of local multi-fidelity correction, generated on demand, combined with a global search algorithm via an adaptive trust region is first tested on a modest, smooth external aerodynamic problem. Speed-up of an order of magnitude is demonstrated, comparable to established techniques applied to smooth problems. A number of enhancements aimed principally at effectively evaluating a wide range of configurations quickly is then applied to the basic strategy, and the emerging technique is tested on a generic aeroengine core compression system. A similar order of magnitude speed-up is achieved on this relatively large and highly discontinuous problem. A five-fold increase in the number of configurations assessed with CFD is observed. As the technique places constraints neither on the underlying physical modelling of the constituent analysis codes nor on first-order agreement between those codes, it has potential applicability to a range of multidisciplinary design challenges. © 2012 by Jerome Jarrett and Tiziano Ghisu.