US 12,385,417 B2
Disrupting flow vortices to attenuate resonant tones within a gas turbine engine
Ignatius Theratil, Mississauga (CA); and Daniel Alecu, Brampton (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Jul. 28, 2023, as Appl. No. 18/227,645.
Prior Publication US 2025/0035012 A1, Jan. 30, 2025
Int. Cl. F01D 25/04 (2006.01); F01D 11/00 (2006.01); F01D 25/18 (2006.01)
CPC F01D 25/04 (2013.01) [F01D 11/00 (2013.01); F01D 25/18 (2013.01); F01D 25/183 (2013.01); F05D 2220/323 (2013.01); F05D 2240/55 (2013.01); F05D 2260/96 (2013.01); F05D 2260/98 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An assembly for a gas turbine engine, comprising:
a rotating structure of the gas turbine engine rotatable about an axis, the rotating structure including a seal land, an engine shaft, and a plurality of fluid nozzles, the plurality of fluid nozzles including a first nozzle and a second nozzle, the seal land connected to and rotatable with the engine shaft;
a stationary structure of the gas turbine engine comprising a seal element, the seal element arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure; and
a volume formed by and extending between the rotating structure and the stationary structure, the volume adjacent the seal element and the seal land;
each of the plurality of fluid nozzles configured to direct a respective fluid jet out from the rotating structure and into the volume,
wherein each of the plurality of fluid nozzles is mounted to and/or included as part of the rotating structure, and
wherein the first nozzle is configured to direct the respective fluid jet into the volume in a radial direction towards the seal assembly, and the second nozzle is configured to direct the respective fluid jet into the volume in an axial direction away from the seal assembly.