US 12,338,737 B1
Seal assembly for a turbine engine
Rahul Anil Bidkar, Clifton Park, NY (US); Christopher Walter Falcone, Schenectady, NY (US); Grant Robert Portune, Cincinnati, OH (US); Nora Marie Molino, Schenectady, NY (US); and Matthew James Misch, Cincinnati, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Dec. 18, 2023, as Appl. No. 18/543,591.
Int. Cl. F01D 11/00 (2006.01); F01D 17/16 (2006.01); F02C 7/28 (2006.01)
CPC F01D 11/001 (2013.01) [F01D 17/162 (2013.01); F02C 7/28 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A turbine engine, comprising:
a rotor;
a stator;
a circumferential seal assembly comprising a plurality of seal segments, the plurality of seal segments disposed between the rotor and the stator, wherein the rotor, the stator, and the plurality of seal segments are arranged together to define a high pressure region and a low pressure region; and
a biasing member engaged with the seal assembly,
wherein the stator comprises at least one feature formed therein,
wherein a pressurized fluid engaging with the at least one feature provides an aft-to-forward axial force that reduces friction between interfacing aft surfaces of the plurality of seal segments and the stator,
wherein the at least one feature comprises a recess formed in a surface of the stator that creates an intermediate pressure region between the high pressure region and the low pressure region, and
wherein the high pressure region is located forward of the low pressure region and the intermediate pressure region is forward of the seal assembly.