TAKING INTO ACCOUNT THE BLADES EROSIVE WEAR IN THE MODELING OF CHARACTERISTICS OF THE AIRCRAFT ENGINE MULTISTAGE AXIAL COMPRESSOR

Елена Серафимовна Барышева, Александр Евгеньевич Дёмин, Роман Леонидович Зеленский

Abstract


In developing of methods for diagnostic based on the parameters of the working process of the flow-through part of aviation gas turbine engines, the development of the working process thermogasdynamic model for the engine is the main task. Math modeling of various types of defects of engine elements is carried out by introducing into the model the changed characteristics of these units, which makes it possible to determine the change of parameters which are recorded in operation. With the help of such a model it is possible to assess the technical state de the deviations of the measured parameters. The ability to determination and using of the multistage axial compressor characteristics with taking into account the erosive wear of its elements during operation significantly enhances the capabilities of such models, since the erosion wear of the flowing part, the blades of the impellers and the guide vanes of the multistage compressor is one of the most frequent cause of early removal of the gas turbine engine from the aircraft. The mathematical model of the multistage axial compressor is created and the results of its verification according to experimental data are given. The correspondence of the obtained compressor mathematical model to the real object is shown in a wide range of regimes in terms of rotation frequency and flow rate. In accordance with the level of the compressor model, the authors proposed a method for taking into account the abrasive wear of the blades and its implementation is carried out. The proposed approach is open for making changes as data is accumulated during operation. Influence on the compressor characteristic of various factors arising in the course of operation, such as changing the chord and geometric angles of the profile, is considered and the results of are shown. Calculations of compressor characteristics with taking into account erosion wear in a wide range of operating conditions are carried out and the obtained results are presented. The obtained characteristics of the compressor allow to form a diagnostic mathematical model of the engine. With the help of this model, it is possible to select the most informative parameters recorded for use in diagnosing the development of such a defect as erosion wear.

Keywords


GTD diagnostic systems, calculation of the multistage axial compressor characteristics, blade row description, erosion wear

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DOI: https://doi.org/10.32620/aktt.2017.6.08