| 主权项 |
1. A hollow gas turbine vane comprising:
a hollow first endwall including a first endwall cooling passage configured to receive cooling air for cooling the first endwall, the first endwall cooling passage arranged in an interior of the hollow first endwall defined by spaced apart walls having spacers formed there between; an airfoil, extending radially from the first endwall, including opposite pressure and suction side walls extending chordwise between a leading edge and a trailing edge of the airfoil, and including an airfoil cooling passage radially extending between radial ends of the airfoil, configured by connection, to receive cooling air from the first endwall cooling passage; a second endwall at an airfoil end radially distal from the first endwall, having a second endwall cooling passage connected to the airfoil cooling passage to be in cooling air communication with the airfoil cooling passage, wherein the airfoil cooling passage extends from the first endwall cooling passage to the second endwall cooling passage and is configured by direct connection for exclusively receiving cooling air used to cool the first endwall; and a wall cooling passage of the airfoil extending from a region of the leading edge to the trailing edge and being configured, in the leading edge region, for receiving cooling air exclusively from the airfoil cooling passage and, at the trailing edge for ejecting cooling air therethrough such that cooling air in the wall cooling passage sequentially cools the airfoil from the leading edge to the trailing edge, wherein the second endwall cooling passage is configured by direct connection to the airfoil cooling passage so that the second endwall is cooled exclusively by cooling air received from the airfoil cooling passage, that cooling air having been exclusively used to cool the first endwall via the first endwall cooling passage prior to entering the airfoil cooling passage. |
