Design and Optimization of Compressor Airfoils by Using Class Function / Shape Function Methodology
| Autor: | Giesecke, Daniel, Stark, Udo, Harms, Rubén, Friedrichs, Jens |
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| Přispěvatelé: | Legrand, Mathias, Technische Universität Braunschweig = Technical University of Braunschweig [Braunschweig] |
| Jazyk: | angličtina |
| Rok vydání: | 2017 |
| Předmět: | |
| Zdroj: | 17th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery (ISROMAC2017) 17th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery (ISROMAC2017), Dec 2017, Maui, United States |
| Popis: | International audience; This paper describes a new design method for high Reynolds number subsonic compressor blade sections for industrial gas turbines and compressors. The focus is on the middle and end stages, where the Reynolds numbers are about 2 to 6 × 10 6 and the Mach numbers between 0.4 and 0.8. The new design method combines i) a parametric geometry definition method, ii) a fast blade-to-blade flow solver, and iii) an optimization tool with a suitable objective function. The development of a new blade section is based on a conventional NACA-65 design, subsequently modified to an optimized CSM profile, where CSM means Class Function / Shape Function Methodology. The new profile shapes are obtained by superimposing a camber line and a thickness distribution. Both the camber line and the thickness distribution are prescribed as analytical functions to cut down the CPU-time for geometry set up and to guarantee smooth geometries. Numerical calculations are performed by applying the two-dimensional blade-to-blade solver MISES. The optimization method used in this paper is the single-objective genetic algorithm (SOGA) from the DAKOTA library. The objective function consists of 5 components and takes into account the whole loss polar. The corresponding computing time is relatively short-that is 1 to 2 days. At high Reynolds number, the new profiles show decreased design point losses and increased operating limits compared to corresponding results using conventional NACA-65 profiles. In addition, the present results show close agreement with those produced by so-called high performance profiles of the relevant literature. |
| Databáze: | OpenAIRE |
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