US 12,428,969 B1
Seal assembly for a gas turbine engine
Prateek Jalan, Bangalore (IN); Steven Douglas Johnson, Milford, OH (US); Rajesh Kumar, Bangalore (IN); Tajinder Singh, Bangalore (IN); Alok Kumar, Bangalore (IN); Lucas Parisot, Boston, MA (US); and Jonathan Russell Ratzlaff, Loveland, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Cincinnati, OH (US)
Filed on Aug. 7, 2024, as Appl. No. 18/796,888.
Int. Cl. F01D 11/00 (2006.01); F01D 11/06 (2006.01)
CPC F01D 11/001 (2013.01) [F01D 11/06 (2013.01); F05D 2240/55 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator;
a seal assembly defining a primary seal at an interface of the rotor and the stator, the seal assembly separating an inlet plenum from an outlet plenum, the seal assembly comprising one or more aspiration conduits fluidly connected to the primary seal; and
one or more flingers positioned at least partially between the seal assembly and the inlet plenum, the one or more flingers defining one or more passageways fluidly connecting the inlet plenum to the one or more aspiration conduits, the one or more flingers positioned to direct at least a portion of an airflow within the inlet plenum away from the one or more passageways.