US 11,913,343 B2
Replaceable rotor blade tip clearance measurement device for a gas turbine engine
Jose R. Paulino, Saco, ME (US); Veronika Reynolds, Lawrence, MA (US); and Jason David Liles, Port Saint Lucie, FL (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by United Technologies Corporation, Farmington, CT (US)
Filed on Oct. 3, 2019, as Appl. No. 16/592,001.
Prior Publication US 2021/0102474 A1, Apr. 8, 2021
Int. Cl. F01D 21/00 (2006.01); F01D 11/12 (2006.01); B33Y 80/00 (2015.01)
CPC F01D 21/003 (2013.01) [F01D 11/122 (2013.01); B33Y 80/00 (2014.12); F05D 2230/80 (2013.01); F05D 2240/55 (2013.01); F05D 2250/141 (2013.01); F05D 2250/15 (2013.01); F05D 2250/283 (2013.01); F05D 2270/821 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A replaceable rotor blade tip clearance measurement device for a gas turbine engine, consisting of:
a threaded section along an axis, the threaded section having a first end and a second end opposite from the first end along the axis;
an integral abradable tip with an internal lattice geometry that extends from the first end of the threaded section along the axis; and
a bolt head at the second end of the threaded section along the axis.