US 11,867,082 B2
Rotor blade with detachable tip
Abhijeet Jayshingrao Yadav, Karad (IN); Nitesh Jain, Bangalore (IN); and Nicholas Joseph Kray, Mason, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Apr. 21, 2021, as Appl. No. 17/236,236.
Prior Publication US 2022/0341329 A1, Oct. 27, 2022
Int. Cl. F01D 5/14 (2006.01); F01D 5/02 (2006.01); F01D 5/28 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/02 (2013.01); F01D 5/28 (2013.01); F05D 2220/32 (2013.01); F05D 2230/80 (2013.01); F05D 2240/307 (2013.01); F05D 2300/17 (2013.01)] 17 Claims
OG exemplary drawing
 
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.