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Cycle Improvement in the Cooled Turbine Nozzle with Asymmetric End Surfaces
Russian Aeronautics Pub Date : 2020-09-16 , DOI: 10.3103/s1068799820020166 A. E. Remizov , V. V. Vyatkov , R. V. Kharchenko , E. S. Osokina
中文翻译:
具有不对称端面的冷却涡轮喷嘴的循环改进
更新日期:2020-09-16
Russian Aeronautics Pub Date : 2020-09-16 , DOI: 10.3103/s1068799820020166 A. E. Remizov , V. V. Vyatkov , R. V. Kharchenko , E. S. Osokina
Abstract
The paper deals with the analysis of cycle features in the cooled turbine nozzle with asymmetric end surfaces. Influence of asymmetric end surfaces, which have been obtained in the course of turbine stage optimization, on the structure and dynamics of secondary flows in the blade passage is shown. Features of film cooling arrangement on the nozzle asymmetric end surface are analyzed. The method to ensure thermal state of end surfaces by arranging the convective heat transfer from the inside of the end surface is shown.中文翻译:
具有不对称端面的冷却涡轮喷嘴的循环改进