US 9,810,087 B2
Reversible blade rotor seal with protrusions
Christopher Corcoran, Manchester, CT (US); and Daniel A. Snyder, Manchester, 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.