Transactions of Nanjing University of Aeronautics & Astronautics
Study on Anti-icing Heat Load Distribution for a Three-Dimensional Propeller
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Abstract:
At present， research on the anti-icing heat loads of propeller aircraft is inadequate， while predicting the distribution of anti-icing heat loads is crucial for designing propeller aircraft anti-icing systems. A three-dimensional propeller is simulated based on the multiple reference frame and Messinger thermodynamic model to analyze the effect of the anti-icing heat load. The results indicate that the majority of the anti-icing heat loads concentrates at the leading edge of the blade， with an initial increase and subsequent decrease along the spreading direction. As the incoming flow speed increases， both the value and range of anti-icing power initially increase and then decrease. The influence of the angle of attack is negligible due to the rotating effect. The anti-icing power increases linearly as the temperature drops. Considering the provisions in Appendix C of CCAR-25， when the rotation speed is 660 r/min， the chordwise upward limit is 12.1%， the chordwise downward limit is 6.7%， and the maximum anti-icing power density is 9.5 kW/m2. The anti-icing power of the single propeller exceeds 1.96 kW. This study provides a scientific explanation for the surface anti-icing of propeller aircraft and a theoretical basis for the installation of anti-icing systems on propeller aircraft.
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Project Supported:
This work was supported by the National Natural Science Foundation of China （No.12072213）， the National Science and Technology Major Project from Ministry of Science and Technology of China （No?.J2019-Ⅲ-0010-0054）， and the National Numerical Windtunnel from China Aerodynamics Research and Center （No.NNW2019-JT01-023）.
Clc Number:
V211.3
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