Cycle Improvement in the Cooled Turbine Nozzle with Asymmetric End Surfaces

A. E. Remizov; V. V. Vyatkov; R. V. Kharchenko; E. S. Osokina

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Cycle Improvement in the Cooled Turbine Nozzle with Asymmetric End Surfaces

机译：具有不对称末端表面的冷却涡轮喷嘴的循环改进

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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.

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来源
《Russian Aeronautics》 |2020年第2期|共7页
作者
A. E. Remizov; V. V. Vyatkov; R. V. Kharchenko; E. S. Osokina;
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作者单位

P.A. Soloviev Rybinsk State Aviation Technical University;

P.A. Soloviev Rybinsk State Aviation Technical University;

P.A. Soloviev Rybinsk State Aviation Technical University;

P.A. Soloviev Rybinsk State Aviation Technical University;

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原文格式 PDF
正文语种 eng
中图分类航空;
关键词
cooled gas turbine; efficiency; optimization; asymmetric end surfaces;

机译：冷却燃气轮机;效率;优化;不对称的终点;

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Cycle Improvement in the Cooled Turbine Nozzle with Asymmetric End Surfaces

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