<p>A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.</p>
申请公布号
CA2875028(A1)
申请公布日期
2013.12.19
申请号
CA20132875028
申请日期
2013.06.13
申请人
GENERAL ELECTRIC COMPANY
发明人
PEARSON, SHAWN MICHAEL;BERGHOLZ, ROBERT FREDRICK;SMITH, DOUGLAS RAY;BUCK, FREDERICK ALAN;MOLTER, STEPHEN MARK;FELDMANN, KEVIN ROBERT