US 11,939,871 B1
Abradable material and design for jet engine applications
Kerry E. Muenchow, West Hartford, CT (US); Georgios S. Zafiris, Glastonbury, CT (US); Raymond P. Martina, Jr., Manchester, CT (US); John Harner, Florence, MA (US); Imad Hanhan, Newington, CT (US); Darin S. Lussier, Guilford, CT (US); Scott A. Smith, Plantsville, CT (US); Mark W. Costa, Storrs, CT (US); and Michael R. LaFavor, Manchester, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Oct. 28, 2022, as Appl. No. 17/976,210.
Int. Cl. F01D 11/12 (2006.01); F01D 25/24 (2006.01)
CPC F01D 11/122 (2013.01) [F01D 25/24 (2013.01); F05D 2300/506 (2013.01); F05D 2300/522 (2013.01); F05D 2300/601 (2013.01); F05D 2300/61 (2013.01); F05D 2300/615 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An abradable material for a rub strip of a gas turbine engine component, comprising:
a polymer matrix, and
an organic or inorganic filler distributed through the matrix, wherein the abradable material has a compression spring rate profile comprising:
less than 50,000 lb/in at −65° F.,
less than 35,000 lb/in at room temperature, and
less than 35,000 lb/in at 200° F.