| 摘要 |
PROBLEM TO BE SOLVED: To provide turbine blade cooling configurations that provide a high cooling effect while maintaining a structural support of a component.SOLUTION: An airfoil of a blade for a turbine of a gas turbine engine has a leading edge, a trailing edge, an outboard tip, and an inboard end. The airfoil may further include a cooling configuration that includes a plurality of cooling channels for receiving and directing a coolant. The cooling channels may include a linear cooling channel and a curved cooling channel. The blade may also include a contoured shape defined by the airfoil between the inboard end and the outboard tip, with the contoured shape being configured so to include a target area inaccessible to a linear reference line extending radially from a position at the inboard end of the airfoil. The curved cooling channels may be configured to extend between an upstream end and a downstream end so as to intersect the target area therebetween.SELECTED DRAWING: Figure 1 |
