| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine blade with reduced tipflow leakage, improved turbine efficiently, and improved tip cooling, in a gas turbine engine. SOLUTION: This turbine blade (10) includes an airfoil (12), a platform (14) on a root of the airfoil, and a support dovetail (16). The airfoil (12) has opposite positive pressure and negative pressure side surfaces (20, 22) extending chordally between leading and trailing edges (24, 26) and extending in span from the root (28) to a tip (30). The tip (30) includes first and second ribs (36, 38) conforming with the positive pressure and negative pressure side surfaces (20, 22), arranged interspecially in a blade thickness direction between the leading and tailing edges (24, 26), and forming a tip cavity (40) having a tip floor (42) surrounding the airfoil (12). The second rib (38) includes an outer surface flare (44) enlarging laterally outwardly from the negative pressure side surface (22). COPYRIGHT: (C)2008,JPO&INPIT |
