US 12,215,588 B2
Seal assembly for a gas turbine engine
Tajinder Singh, Bengaluru (IN); Rajesh Kumar, Bengaluru (IN); David Raju Yamarthi, Bengaluru (IN); Bryan Jung Woo Hong, Blue Ash, OH (US); Narendra Anand Hardikar, Bengaluru (IN); Ravindra Shankar Ganiger, Bengaluru (IN); and Jeffrey Douglas Rambo, Mason, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 27, 2023, as Appl. No. 18/190,403.
Prior Publication US 2024/0328325 A1, Oct. 3, 2024
Int. Cl. F01D 11/10 (2006.01)
CPC F01D 11/10 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/55 (2013.01)] 5 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
a rotor;
a stator;
a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor, wherein a lift channel extends within the seal segment from an opening on the seal face; and
a spring assembly disposed within the lift channel, the spring assembly including a biasing element and a piston element coupled to the biasing element, wherein the lift channel includes a lift volume portion extending between the opening and the piston element, and wherein the piston element is movable within the lift channel based on a pressure within the fluid bearing to adjust a size of the lift volume portion, wherein the lift channel extends between a radially inner surface and an annular side surface, and wherein the biasing element extends between a first end coupled to the annular side surface and a second end coupled to the piston element.