Development of methods of modeling and computer-aided design of compressors


Discusses the methods of calculation allowing to calculate the characteristics of cascades of profiles, rows blade, the compressor as a whole. Make improvements to previously known methods of calculation. It is proposed to allocate an additional (along the surface current) elementary channels that can achieve output of rows diagrams parameters. Preparation thus permits the compressor, in turn, to calculate the characteristic of the developed engine steady and unsteady modes with high accuracy. The proposed method allows the selection of geometric parameters of blade rows, and in operation - perform account the influence on the characteristics of changes in the geometry of the blades (due to erosion, dirt, etc.). Allows you to analyze the effect of prepollution and erosion of the blades to change the characteristics of the nodes, and the results of the identification of the plant model to solve the inverse problem - to identify the actual values of pollution and erosion in specific stages and crowns. The resulting geometry of the rims may be used as an initial approximation for the boundary conditions at the solid-state 3D modeling and gas-dynamic calculations in СAE- systems such as Ansys CFX.

About the authors

I. A. Krivosheev

Ufa State Aviation Technical University, Ufa

Author for correspondence.

Doctor of Science (Engineering), Professor

Dean of the Faculty of aircraft engines

Russian Federation

K. E. Rozhkov

Ufa State Aviation Technical University, Ufa


Postgraduate student of the aviation engines department

Russian Federation


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