Abstract
In view of the rotor icing problems, the influence of centrifugal force on rotor blade icing is investigated. A numerical simulation method of three-dimensional rotor blade icing is presented. Body-fitted grids around the rotor blade are generated using overlapping grid technology and rotor flow field characteristics are obtained by solving N-S equations. According to Eulerian two-phase flow, the droplet trajectories are calculated and droplet impingement characteristics are obtained. The mass and energy conservation equations of ice accretion model are established and a new calculation method of runback water mass based on shear stress and centrifugal force is proposed to simulate water flow and ice shape. The calculation results are compared with available experimental results in order to verify the correctness of the numerical simulation method. The influence of centrifugal force on rotor icing is calculated. The results show that the flow direction and distribution of liquid water on rotor surfaces change under the action of centrifugal force, which lead to the increasing of icing at the stagnation point and the decreasing of icing on both frozen limitations.
Highlights
The helicopters are most likely to encounter icing problems due to the lower flight height and slower flight speed
Its calculation method is as follows: the two-dimensional flow field results are obtained from the three-dimensional rotor flow field and ice accretion is simulated based on fixed wing icing calculation method; the differential geometric method is used to expand the two-dimensional ice shape into three-dimensional
In order to verify the correctness of the numerical simulation method used in this paper, rotor blade icing under three conditions is simulated and the calculation results are compared with the experimental results and the ARISP icing model in [16]
Summary
The helicopters are most likely to encounter icing problems due to the lower flight height and slower flight speed. With the development of computer technology, researchers have explored the use of numerical simulation technology to solve helicopter rotor icing problem. Its calculation method is as follows: the two-dimensional flow field results are obtained from the three-dimensional rotor flow field and ice accretion is simulated based on fixed wing icing calculation method; the differential geometric method is used to expand the two-dimensional ice shape into three-dimensional. This method does not realize the three-dimensional rotor icing numerical simulation [5]. The other scholars have carried out the related researches on the icing simulation of rotor blade airfoil, which is similar to the NASA research method, but its calculation accuracy still needs to be improved [6, 7]
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