US 12,241,375 B2
Seal support assembly for a turbine engine
Ravindra Shankar Ganiger, Bengaluru (IN); David Raju Yamarthi, Bengaluru (IN); Chandrashekhar Kandukuri, Bengaluru (IN); Deepak Trivedi, Halfmoon, NY (US); Narendra Anand Hardikar, Bengaluru (IN); Vidyashankar Ramasastry Buravalla, Bengaluru (IN); Steven Douglas Johnson, Milford, OH (US); Amit Goyal, Bengaluru (IN); Grant Robert Portune, Cincinnati, OH (US); Himanshu Gupta, Bengaluru (IN); Srinivasan Swaminathan, Bengaluru (IN); Shalini Thimmegowda, Bengaluru (IN); Guru Venkata Dattu Jonnalagadda, Ponnur (IN); Shalabh Saxena, Bengaluru (IN); and Prateek Jalan, Bengaluru (IN)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 24, 2023, as Appl. No. 18/189,379.
Prior Publication US 2024/0318570 A1, Sep. 26, 2024
Int. Cl. F01D 11/02 (2006.01)
CPC F01D 11/025 (2013.01) [F05D 2240/53 (2013.01); F05D 2240/55 (2013.01); F05D 2260/38 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A turbine engine defining an axial direction and a radial direction, the turbine engine comprising:
a rotor;
a stator comprising a carrier;
a seal assembly disposed between the rotor and the stator, 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 seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and
a seal support assembly comprising a spring arrangement extending between the carrier and the seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine, wherein the spring arrangement comprises a plurality of spring extensions extending between the carrier and the seal segment, wherein the seal segment defines a slot extending along the axial direction and a circumferential direction of the turbine engine, and wherein the plurality of spring extensions each includes a distal end positioned in the slot of the seal segment.