US 9,810,087 B2
Reversible blade rotor seal with protrusions
Christopher Corcoran, Manchester, CT (US); and Daniel A. Snyder, Manchester, CT (US)
Assigned to UNITED TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed by United Technologies Corporation, Hartford, CT (US)
Filed on Jun. 24, 2015, as Appl. No. 14/748,876.
Prior Publication US 2016/0376903 A1, Dec. 29, 2016
Int. Cl. F01D 11/00 (2006.01); F01D 5/08 (2006.01); F01D 5/22 (2006.01); F01D 5/30 (2006.01); F02C 7/18 (2006.01); F16J 15/02 (2006.01)
CPC F01D 11/006 (2013.01) [F01D 5/081 (2013.01); F01D 5/22 (2013.01); F01D 5/3015 (2013.01); F01D 11/008 (2013.01); F02C 7/18 (2013.01); F16J 15/02 (2013.01); F05D 2220/32 (2013.01); F05D 2240/24 (2013.01); F05D 2240/55 (2013.01); F05D 2250/72 (2013.01); F05D 2260/20 (2013.01); Y02T 50/676 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A sealing structure for a gas turbine engine, comprising:
a rotor that has a rim with slots and a cooling passage, the rotor rotatable about an axis;
a first and second blades arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage, the first and second shelves forming an opening; and
a reversible seal arranged within the pocket and having a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a second condition, the seal includes first and second protrusions respectively extending from first and second faces opposing one another, the first protrusions supported on the rim in a first condition.