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Methods and Programs for Aerodynamic Computation and Design of Turbomachnes’ Working Elements

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Abstract

To increase the efficiency of turbomachines, further development of methods and programs for their aerodynamic calculation is necessary. Investigations in this direction were actively conducted in the joint-stock company NIIturbocompressor named after V.B. Shnepp for several decades. This article gives a brief overview of the methods and programs for aerodynamic calculation and design of working elements of turbomachinery, developed within the framework of a quasi-three-dimensional model. The introductory part briefly describes the history of the development of methods for calculating the flow through the flow path of turbomachines for various purposes. In this case, the main attention is paid to the model based on the division of the spatial flow into two two-dimensional ones. The first two-dimensional problem is to calculate the averaged axisymmetric flow in the flow path of a turbomachine. The second problem allows one to determine the characteristics of the flow on the constructed axisymmetric current surfaces. In particular, the velocity and pressure fields are found in the interblade space and on the surfaces of the impeller blades and other blade elements. Initially, the corresponding mathematical apparatus was developed in relation to the flow of an ideal incompressible fluid. The further development of the model was to take into account the compressibility of the gas in the subsonic flow regime and viscosity in the framework of the boundary layer model. At the same time, these factors were taken into account in both two-dimensional problems. Also, the model under consideration was extended to the case of blade elements of turbomachines with a multi-row structure. The software package compiled on this basis, which takes into account the mutual influence of the solutions of two-dimensional problems on each other, made it possible to demonstrate, using various examples, the nature of the influence of compressibility, viscosity, and multirowness on the flow characteristics. The paper also describes a technique for solving the inverse problem, which consists in profiling turbomachine blades according to the velocity distributions specified on their surfaces. The effectiveness of the inverse problem is demonstrated by an example of its application to the design of the impeller of a centrifugal compressor. In conclusion, it was noted that despite the apparent simplicity of this model, it can be successfully applied at the initial stage of designing turbomachines.

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Authors and Affiliations

  1. Kazan National Research Technological University, 420111, Kazan, Russia

    A. V. Potashev, I. G. Khisameev & T. N. Mustafin

  2. Kazan Cooperative Institute, Branch of the Russian University of Cooperation, 420045, Kazan, Russia

    E. V. Potasheva

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  1. A. V. Potashev
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  2. E. V. Potasheva
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  3. I. G. Khisameev
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  4. T. N. Mustafin
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Correspondence to A. V. Potashev, E. V. Potasheva, I. G. Khisameev or T. N. Mustafin.

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(Submitted by A. M. Elizarov)

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Potashev, A.V., Potasheva, E.V., Khisameev, I.G. et al. Methods and Programs for Aerodynamic Computation and Design of Turbomachnes’ Working Elements. Lobachevskii J Math 43, 3005–3019 (2022). https://doi.org/10.1134/S1995080222130376

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  • DOI: https://doi.org/10.1134/S1995080222130376

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