Cooled two-stage GTE turbine with a tubular or tubular-annular combustion chamber

被引：0
|
作者：
Agachev R.S. [1 ]
Sychenkov V.A. [1 ]
Stepanov P.A. [1 ]
机构：
[1] Tupolev State Technical University, Kazan
来源：
Russian Aeronautics | 2008年 / 51卷 / 01期
关键词：
Combustion chambers - Nozzles - Temperature distribution - Turbomachine blades;
D O I：
10.3103/S1068799808010157
中图分类号：
学科分类号：
摘要：
A scheme of the nozzle blade arrangement in the two-stage GTE turbine is described taking into account peripheral periodic inhomogeneity of the temperature field. © Allerton Press, Inc. 2008.
引用
收藏
页码：90 / 93
页数：3
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