Patent ID: 11867082
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A rotor blade for a gas turbine engine, the rotor blade comprising:
a blade body formed of a first material, wherein the blade body defines a leading edge, a trailing edge, a root, a tip, a pressure-side surface, a suction-side surface, and a slot that extends between the pressure-side surface and the suction-side surface between the leading edge and the trailing edge of the blade body;
a cap portion disposed over a portion of the leading edge; and
a tip component defining an abradable exterior surface at a radial extremity of the rotor blade with respect to the root of the blade body, wherein the tip component is positioned in the slot and removably connected to the blade body, the tip component formed of a second material that is different than the first material, wherein the cap portion extends radially across the tip component to the radial extremity.