Abstract
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.
Highlights
The application range of gas turbine technologies tends to widen including transport and various industries [1]
Results analysis The calculations performed prove that the proposed approach to the construction of the axial compressor blade row allows to describe various defects with sufficient flexibility by changing the position of the control points
Having performed a series of numerical calculations with various axial compressor blade row defects and their combinations, a cluster analysis can be conducted in order to identify groups by the degree and nature of the defect influence on the characteristics of the axial compressor and gas turbine unit (GTU)
Summary
The application range of gas turbine technologies tends to widen including transport (air and maritime) and various industries (chemical, oil and gas) [1]. The axial compressor consumes more than half of the power generated by the turbine, which depends on the pressure ratio in the cycle, turbo-machine efficiency, incoming gas temperature (before it goes to the turbine), and incoming air temperature (before it goes to the compressor). Since the axial compressor consumes a large amount of power, it is important to achieve and maintain its high efficiency and sufficient gas-dynamic stability margin, which primarily depend on the quality of the blade row [4]. In this regard, allowable size and shape deviations are regulated during manufacturing and repair of axial compressor blades, as well as other turbines [5, 6]. Reducing the maximum airfoil thickness may serve as another example
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