| 摘要 |
An airfoil (10) in a gas turbine engine includes a substrate (12) having an inner surface (14), an opposed outer surface (16), and pluralities of radially outer cooling passages (20), radially inner cooling passages (22), and mid-span cooling passages (24), each for delivering cooling fluid (CF) from a cooling fluid source (15) to the outer surface (16) of the substrate (12). The cooling passages (20, 22, 24) are shaped/configured such that the cooling fluid (CF) passing out of the respective cooling passages (20, 22, 24) matches a flow direction of hot combustion gases (HG) passing by the airfoil (10) during operation of the engine to increase engine efficiency. |
