Optimization Approac H and Some Results for 2d Compressor Airfoil

Komarov, O. V.; Sedunin, Viacheslav A.; Блинов, В. Л.; Serkov, S. A.

doi:10.38036/jgpp.8.3_39

Cited by 4 publications

References 13 publications

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Validation of a CFD model of a single stage centrifugal compressor by mass-averaged parameters

Bogdanets¹,

Блинов²,

Sedunin³

et al. 2019

EPJ Web Conf.

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In this paper a validation of a computational model is presented for single-stage centrifugal compressor with an axial-flow impeller and a vaneless diffuser. The comparison was made by mass averaged performance. The paper shows that the model used is able to predict overall performance near the design operating point within 1.2% difference. However, further away the model fails to follow the experimental characteristics.

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Validation of a CFD model of a single stage centrifugal compressor by mass-averaged parameters

Bogdanets¹,

Блинов²,

Sedunin³

et al. 2019

EPJ Web Conf.

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Influence of the axial compressor blade row defects on the industrial gas turbine performance

Блинов¹,

Zubkov²

2020

J. Phys.: Conf. Ser.

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This paper presents the compressor blade algorithm for predicting the defect influence on the characteristics of the stage, axial compressor or GTU as a whole. The developed model is based on the use of Bezier curves, with the control point coordinates calculated using the main geometric parameters of the airfoil, which provides highly precise geometry of both the airfoil and the blade as a whole. The paper shows some results of verification of the developed method and the selected numerical model parameters, as well as the analysis of the defect influence on the airfoil flow conditions in order to demonstrate the capabilities of the algorithm. The main results of the study were summarized and recommendations for further research were developed.

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Mathematical model of the axial compressor blade in system assessing technical condition of the industrial gas turbine

Блинов

Zubkov

2021

IOP Conf. Ser.: Mater. Sci. Eng.

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The paper presents the key stages of developing a geometric model of the axial compressor blade. The model is based on Bezier curves, which are used to design the parts of airfoil and allow making local changes to the airfoil and blade geometry. This model is designed to assess the technical condition of the axial compressor being a part of an industrial gas turbine or gas-turbine units, depending on the defects of axial compressor blade row (in the gas-flow channel) and the turbine as a whole. As a part of the study the algorithm, which describes the process of the blade formation, were presented. Although the study presents the main equations of the model based on the key geometric parameters of the airfoil, provides examples of airfoil, blade and stage modelling using the presented method, and shows the results of model verification using numerical simulation methods.

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Optimization Approac H and Some Results for 2d Compressor Airfoil

Cited by 4 publications

References 13 publications

Validation of a CFD model of a single stage centrifugal compressor by mass-averaged parameters

Validation of a CFD model of a single stage centrifugal compressor by mass-averaged parameters

Influence of the axial compressor blade row defects on the industrial gas turbine performance

Mathematical model of the axial compressor blade in system assessing technical condition of the industrial gas turbine

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