Distributed cooling for gas turbine engine combustor

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专利权人:

United Technologies Corporation

发明人:

Cunha, Frank J.

申请号：

EP20120178491

公开号：

EP2551593(A3)

申请日:

2012.07.30

申请国别(地区):

欧洲专利局

年份:

2017

代理人:

摘要：

A combustor component of a gas turbine engine includes a refractory metal core (RMC) microcircuit (90) in a liner (72,74) for self-regulating a cooling flow. The liner (72,74) includes an inlet (92), first and second divergent islands (94A,94B), a flow separator island (98), first and second feedback features (100A,100B) and exit slots (102A,102B).

来源网站：

中国工程科技知识中心

来源网址：

http://www.ckcest.cn/home/