METHOD FOR LOWERING TEMPERATURE AT TIP AREA OF TURBINE BLADE, AIRFOIL PORTION, AND TURBINE ENGINE

摘要

PROBLEM TO BE SOLVED: To provide a rotor blade for a gas turbine engine including a tip area that can lower an operating temperature of the rotor blade. SOLUTION: The tip area includes a first tip wall 64 and a second tip wall 62 extending outward in a radial direction from a tip plate 54 of an airfoil portion 42. The tip walls extend from near an airfoil front edge 48 and are brought into contact with each other at an airfoil rear edge 50. A part of the first tip wall is depressed to form a tip shelf portion 90 extending from the airfoil front edge to the airfoil rear edge.