US 12,241,373 B1
Seal for a wave rotor disk engine
Christopher Tait, San Mateo, CA (US); Pejman Akbari, Pasadena, CA (US); Brian Sell, Oakwood, OH (US); and Marc Polanka, Wright-Patterson AFB, OH (US)
Assigned to United States of America as represented by the Secretary of the Air Force, Wright-Patterson AFB, OH (US)
Filed by Government of the United States, as represented by the Secretary of the Air Force, Wright-Patterson AFB, OH (US)
Filed on Jul. 7, 2022, as Appl. No. 17/859,043.
Application 17/859,043 is a division of application No. 16/736,223, filed on Jan. 7, 2020, granted, now 11,459,902.
Int. Cl. F01D 11/00 (2006.01); F01D 11/08 (2006.01); F01D 11/16 (2006.01); F01D 25/24 (2006.01); F02C 7/28 (2006.01)
CPC F01D 11/001 (2013.01) [F01D 11/005 (2013.01); F01D 11/08 (2013.01); F01D 11/16 (2013.01); F01D 25/246 (2013.01); F02C 7/28 (2013.01); F05D 2230/60 (2013.01); F05D 2240/11 (2013.01); F05D 2240/55 (2013.01)] 5 Claims
OG exemplary drawing
 
1. A seal system for an engine rotor comprising:
a rotor case having at least one seal region and at least one nozzle exit region having a plurality of nozzle vanes extending through the rotor case;
a rotor having a plurality of rotor blades rotatable within the rotor case;
a plurality of combustion channels formed within the rotor between adjacent rotor blades;
a movable seal positioned between the rotor case and the rotor operable to prevent combustion gases from passing through the rotor case at the at least one seal region; and
wherein the movable seal is passively biased toward the rotor such that a seal surface engages a tip of the rotor continuously during operation.