摘要
介绍了某型航改燃气轮机空气系统的设计方法和准则,通过典型流动单元建立了1维空气系统设计网络,采取1元等熵不可压流方法完成了燃气轮机空气系统设计与计算分析;通过空气系统整机试验,获得了关键部位的压力温度分布,根据试验验证完成了该系统设计方案。
The methods and criterion of the secondary flow system design were introduced for an aeroderivative gas turbine.One dimension design network of the secondary flow system design was built by the typical flow units.The design and calculation analysis of the system were completed using the unitary constant entropy incompressible method.The pressure temperature distribution of the key parts was obtained by the overall test and the design plans were accomplished according to the test verification.
出处
《航空发动机》
2011年第2期25-28,共4页
Aeroengine
关键词
航改燃气轮机
空气系统
试验
aeroderivative gas turbine
secondary flow system
test
