Patent ID: 10753212

Abstract:
A turbine blade, installed on a rotor disk of a turbine and configured to rotate the turbine by a force of flowing gas, includes a root configured to be coupled to the rotor disk; a platform integrally formed with an upper portion of the root, the platform having opposite sides respectively extending in an axial direction of the rotor disk; an airfoil integrally formed with an upper portion of the platform; and an angel wing configured to be removably coupled to each of the opposite sides of the platform. When coupled, the angel wing protrudes from the platform in the axial direction. The turbine blade, which may be included in the turbine of a gas turbine, is capable of improving the castability and adjusting a clearance between an airfoil and a turbine rotor disk such that space between the airfoil and the turbine rotor disk can be reliably sealed.