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.

The operation and maintenance of gas pumping units at the Gazprom transport systems are carried according to the current number of equivalent working hours of the gas turbine and the centrifugal natural gas compressor. Modern concepts of lean production requires maintenance procedures are to be done according to the current technical operating performance of units and its parametrical diagnostics. To meet these requirements an appropriate research project is ongoing at Ural Federal University. In this article a methodology for the technical performance estimation of GTU’s is proposed, verified and discussed. The method is based on processing of data gathered from standard thermodynamic measurements and therefore is applicable in the frame of most gas turbine units without major modifications. The method includes a verified high-order mathematical model based on the Gas dynamic function for the precise analytical description of turbomachinery aerodynamics. A correction factor is introduced for adjusting the mathematical model in case of a non-traditional (not optimised) design applied in the exact turbine design. Models are defined for different types of multi-shaft GT’s and an automated algorithm for calculation of the coefficients of technical performance of the overall unit is provided. A series of experiments showed convergence between traditional and new methods in effective power output and efficiency of units does not exceed 2%. Special software is designed for online monitoring of technical performance.

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This paper contains on-site test data of an axial compressor as part of an industrial gas turbine, as well as the process of Computational Fluid Dynamics (CFD) modelling, verification, research and modernization. The research method has been verified with actual test data gathered from the real gas turbine unit (GTU) test. The computational studies showed significant potential for improving aerodynamic efficiency and the surge margin of a compressor by better matching of inlet and outer groups of stages. A special design approach was used to improve aerodynamic parameters of the inlet system and certain middle stages. Computations made for the improved compressor model showed a 3% efficiency gain and 5% stall margin gain with possibilities for further modernization. Keywords: axial compressor of gas turbine, CFD computations, profiling of compressor blades, verification of computational model.

In large pipeline gas transport systems the operation and maintenance of gas pumping units are carried according to the current number of equivalent working hours of centrifugal gas compressors and gas turbines. Modern terms of lean production require the maintenance procedure to be done according to the current technical performance of equipment. The paper presents a designed and verified methodology of technical performance estimation of gas turbine units using the standard measuring systems. This method includes a verified high-order mathematical model based on the gas dynamic function for the precise analytical description of turbomachinery aerodynamics. The models are defined for different types of multi-shaft gas turbines. In this article the results of technical performance estimation of different gas turbine units are discussed.