The influence of blade row temperature on the aerodynamic characteristics of an axial compressor impeller

2024

Авіаційно-космічна техніка та технологія, Vol 0, Iss 4sup2, Pp 18-24 (2024)

The subject of this study was the characteristics of the compressor impeller regarding the heating of the blade row. The object of this study was the blade row of an axial compressor impeller. The purpose of this study was to evaluate the effect of the blade row temperature on the characteristics of the axial compressor impeller. The following tasks were set and solved in the study: modeling the flow in the compressor impeller considering even heating of the blade row to a temperature in the range of Tb/Ta = 1...2 with a step of 0.25 at different values of the axial flow velocity at the inlet from 100 to 140 m/s with a step of 10 m/s; calculating the degree of pressure increase and efficiency of the compressor impeller in the range of blade rim heating Tb/Ta = 1...2 with a step of 0.25; the effect of heating the compressor impeller blade row on the flow pattern in the interblade channel of the impeller was evaluated. The study was carried out by the method of numerical experimentation in the Ansys Workbench Student software environment. Results: The influence of the temperature of the impeller blade row on the compressor impeller characteristics was evaluated. The dependences of the efficiency η and the degree of pressure increase π of the compressor impeller on the speed coefficient Ca were obtained at different values of the blade rim temperature in the range Tb/Ta = 1...2. The results show that the temperature of the blade row does not significantly affect the impeller characteristics. Thus, with an increase in the ratio of the blade row temperature to the ambient temperature, the efficiency η increases by 0.06...0.173%. At the same time, the degree of pressure increase π hardly changes. With an increase in the Ca velocity coefficient, the degree of pressure increase π initially decreases by 0.001...0.003, but then at Tb/Ta = 1.25...2 gradually increased by 0.005 compared with the results obtained when calculating the characteristics of the compressor impeller at Tb/Ta = 1. The scientific novelty and practical significance of the conducted research is that new data on the influence of the impeller blade row temperature on the characteristics of the compressor impeller were obtained. The obtained results can be used to optimize the turbofan attachment of gas turbine engines and to create promising three-circuit gas turbine engines.

article

English
Ukrainian

National Aerospace University «Kharkiv Aviation Institute», 2024.

газотурбінний двигун, температура, ккд, ступінь підвищення тиску, триконтурний двигун, турбовентиляторна приставка, робоче колесо, лопатковий вінець, характеристика робочого колеса, чисельний експеримент, Motor vehicles. Aeronautics. Astronautics, TL1-4050