US 12,486,779 B2
Seal support assembly for a turbine engine
Ravindra Shankar Ganiger, Bengaluru (IN); Vidyashankar Ramasastry Buravalla, Bengaluru (IN); David Raju Yamarthi, Bengaluru (IN); Rajesh Kumar, 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. 8, 2023, as Appl. No. 18/180,449.
Prior Publication US 2024/0301801 A1, Sep. 12, 2024
Int. Cl. F01D 11/08 (2006.01); F03G 7/06 (2006.01)
CPC F01D 11/08 (2013.01) [F03G 7/0614 (2021.08); F05D 2220/30 (2013.01); F05D 2240/55 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A turbine engine defining an axial direction, comprising:
a rotor;
a stator comprising a carrier;
a seal support assembly coupled to the carrier; and
a seal assembly disposed between the rotor and the stator and supported by the seal support assembly, the seal assembly defining a high pressure side and a low pressure side and comprising a plurality of seal segments, the plurality of seal segments including a first seal segment, the first seal segment having a seal face configured to form a fluid bearing with the rotor, a lip assembly, and a body, the lip assembly positioned on the high pressure side and defining an outer pressurization surface in a radially outward direction in fluid communication with the high pressure side, the lip assembly including a seal lip having a high pressure surface defining a first angle with the axial direction and a low pressure surface defining a second angle with the axial direction, wherein the second angle is greater than 0 degrees and less than 90 degrees, the second angle being greater than the first angle,
wherein the lip assembly includes a seal body having the seal lip, and wherein the seal body is cantilevered from the body of the first seal segment.