A turbine airfoil for a gas turbine engine includes: (a) spaced-apart pressure and suction sidewalls extending between a leading edge and a trailing edge; (b) a first cavity disposed between the pressure and suction sidewalls, the first cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates with an exterior surface of the airfoil; (c) a second cavity disposed between the pressure and suction sidewalls, the second cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates solely with the suction sidewall of the airfoil; and (d) a metering structure adapted to substantially restrict air flow into the second cavity.
申请公布号
WO2009148655(A2)
申请公布日期
2009.12.10
申请号
WO2009US35976
申请日期
2009.03.04
申请人
GENERAL ELECTRIC COMPANY;CORREIA, VICTOR HUGO, SILVA;DEMERS, DANIEL, EDWARD;MANNING, ROBERT, FRANCIS
发明人
CORREIA, VICTOR HUGO, SILVA;DEMERS, DANIEL, EDWARD;MANNING, ROBERT, FRANCIS