Combined method of cooling shroud platforms of high-temperature turbine blades

被引：0
|
作者：
Gorelov, YG [1 ]
Kopylov, IS [1 ]
Matveev, AS [1 ]
机构：
[1] ND Kuznetsov Sci Tech Complex, Samara, Russia
来源：
IZVESTIYA VYSSHIKH UCHEBNYKH ZAVEDENII AVIATSIONAYA TEKHNIKA | 1999年 / 02期
关键词：
D O I：
暂无
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
We have presented the results of experimental comparison study made by application of an one-stage gas generator. We analyze the efficiency of cooling shroud platforms under combined shroud cooling together with conventional jet air flow cooling from above and organization of barrier cooling out of inner blade cavity.
引用
收藏
页码：37 / 40
页数：4
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