FEATURES OF THE AERODYNAMIC OPTIMIZATION OF THE SPATIAL SHAPE OF AXIAL-FLOW COMPRESSOR BLADES

• Datum: 2026
• Hauptverfasser: KVASHA, Yu. O., ZINEVYCH, N. A., PETRUSHENKO, N. V.
• Format: Artikel
• Veröffentlicht: текст 3 2026
• Online Zugang: https://journal-itm.dp.ua/ojs/index.php/ITM_j1/article/view/186
• Назва журналу: Technical Mechanics

This paper is concerned with the choice of rational methods for the aerodynamic improvement of blade rows of gas-turbine engines’ highly loaded axial-flow compressor stages. The paper presents an assessment of capabilities of an approach to the aerodynamic optimization of compressor blade rows developed at the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine. Its major constituents are a numerical simulation of a 3D blade row flow based on the сcomplete averaged Navier-Stokes and a two-parameter turbulence model; the use of sufficiently “coarse” computational grids, for which, however, the computed results are sensitive to blade shape variation; the formulation of quality criteria as aerodynamic characteristics of blade rows averaged over the airflow rate; a search for an optimum spatial blade shape using the points of sequences evenly distributed in the space of variables; and a simple method of blade shape variation for which the blade shape remains aerodynamically acceptable in the optimization process. The goal of the work is to identify the features that manifest themselves in that approach and assess the possibility of optimization time reduction by accounting for them. Use was made of numerical data obtained earlier in the aerodynamic stabilization of compressor impeller blades. An information-analytical assessment of the data is presented. It is shown that the optimization improves the aerodynamic characteristics of cascades for the hub, the middle, and the peripheral region of the blade row channel, Varying the blade shape in the course of the optimization process keeps it aerodynamically acceptable too. The results obtained show the advisability of using small sets of pre-optimized 2D cascades in 3D compressor blade shaping to reduce the optimization time. REFERENCES 1. Ashihara K., Goto A. Turbomachinery blade design using 3-D inverse design method, CFD and optimization algorithm. Proc. of ASME TURBO EXPO 2001. (New Orleans, Louisiana, USA, June 4-7, 2001). New Orleans (USA), 2001. 9 pp. https://doi.org/10.1115/2001-GT-0358 2. Chan-Sol Ahn, Kwang-Yong Kim. Aerodynamic design optimization of an axial flow compressor rotor. Proc. of ASME TURBO EXPO 2002. (Amsterdam, The Netherlands, June 3-6, 2002). Amsterdam (The Netherlands), 2002. 7 pp. 3. 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