Вплив температурного нагріву поверхні лопатки на аеродинамічні характеристики профілю

The subject of the study is the aerodynamic characteristics of the compressor blade concerning the effect of its surface thermal heating. The object of this study is the compressor grid of an axial compressor impeller. This study aims to evaluate the influence of blade surface temperature on the aerodynamic characteristics of the profile. The following tasks were set and solved in the study: flow modelling in the compressor impeller considering uniform heating of the blade to temperatures in the range of Tb/Ta = 1...3 with a step of 1 at various values of the axial inlet flow velocity from 70 m/s to 140 m/s with a step of 10 m/s; calculation of the flow deflection angles for each case and construction of corresponding dependencies; and assessment of the blade heating impact of the compressor impeller on the aerodynamic characteristics of the profile. The study was carried out using the numerical experiment method in the Ansys Workbench Student software environment. Results: The influence of the uniform heating of the blade surface on the aerodynamic characteristics of the profile was evaluated. The flow deflection angles were calculated at different ratios of blade surface temperature to ambient temperature, Tb/Ta = 1...3, and axial flow velocities from 70 m/s to 140 m/s with a step of 10 m/s. A decrease in the flow deflection angle was observed with increasing temperature, which leads to reduced air compression efficiency. At the same time, at an angle of attack of 5° and a blade temperature of Tb/Ta = 2, the flow turning angle is significantly lower than other values. With the increasing temperature ratio of the blade surface to ambient air, the flow deflection angle decreases. Blade surface heating leads to the formation of flow stagnation zones. Sudden jumps in the graphs of dependencies are difficult to interpret clearly and unambiguously.The scientific novelty and practical significance: New data on the influence of blade surface temperature on the aerodynamic characteristics of the profile have been obtained. The obtained results can be used to optimize the turbofan stage of gas turbine engines and in the development of advanced three-stream gas turbine engines. Sudden value jumps on the resulting dependency graphs are difficult for clear and correct interpretation.