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A numerical study of anti-vortex film-cooling holes designs in a 1-1/2 turbine stage using LES

Propulsion and Power Research 2019年第4期8卷 275-299页

作者： Nabeel Al-Zurfi Ali Turan Adel Nasser Ahmed Alhusseny Department of Mechanical Engineering Faculty of EngineeringUniversity of KufaNajafIraq Visiting Researcher Department of MechanicalAerospace and Civil EngineeringSchool of EngineeringFaculty of Science and EngineeringThe University of ManchesterManchesterM139PLUK Department of Mechanical Aerospace and Civil EngineeringSchool of EngineeringFaculty of Science and EngineeringThe University of ManchesterManchesterM139PLUK

The primary focus of the present study is to investigate the impact of anti-vortex holes design on the film-cooling performance in a film-cooled rotor blade model using the large eddy simulation method(LES).One row of the film holes was positioned on the pressure surface of the rotor *** row had three cylindrical holes(the main hole in the present study)with a diameter(D)of 4 mm and a tangential injection angle of 28 *** main hole supplemented with the addition of two symmetrical side holes(anti-vortex holes),which branch out from the same main *** positions for the anti-vortex side holes were considered;namely:upstream to the outlet of the main hole;in line with the main hole;and downstream of the main *** Reynolds number was fixed at Re Z 1.92105 and the speed of the rotor blade was taken to be 1800 *** blowing ratio varied from 1.0 to 5.0 and the density ratio of coolant to mainstream was *** to the base hole,the film cooling performance of the all anti-vortex cases showed obvious improvement at all blowing *** middle stream side holes and downstream side holes each demonstrated good film cooling performance at all blowing ratios,while the upstream side holes perform well only at a lower blowing *** presence of side holes can restrain the CRVP(counter rotating vortex pairs)intensity of the main hole and reduce the coolant lift-off,improving the film coverage and film cooling *** downstream side holes can perform better in reducing the CRVP intensity.

关键词： Rotor blade Large eddy simulation Film-cooling effectiveness Turbulence Rotation anti-vortex hole

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