An unsteady numerical simulation of turbine stage on the S1 flow surface with hot streak was performed firstly.After analysis of the results
some assumptions for the hot streak migration were made.And then a separate section calculation method and an integral calculation method for the hot streak migration avenue were presented.Comparison with the unsteady calculation
the results show that
these two methods have high precision on the prediction of the hot streak migration avenue
and the differences of migration in circumferential direction are within one degree.
Numerical Simulation of Unsteady Hot Streak Migration in a 1-1/2 Stage Turbine
Multipassage Unsteady Simulation of Flow and Temperature Fields in a Turbine Stage
Numerical simulation of effects of contoured slot seal configuration on turbine performance
Study of unsteady tip leakage flow characteristic in high pressure turbine stage
Investigation on clocking effect of 1.5-stage transonic compressor
Related Author
LIU Gao-wen
LIU Song-ling
DONG Su yan
LIU Song ling
ZHU Hui ren
ZHANG Jing-hui
MA Hong-wei
WANG Da-lei
Related Institution
College of Propulsion and Energy, Northwestern Polytechnical University
Northwest Polytechnic University
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics
School of Aerospace, Tsinghua University
Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering,School of Mechanical Engineering, Tsinghua University