18362341. GAS TURBINE ENGINE DEFINING A ROTOR CAVITY (General Electric Company)
Contents
GAS TURBINE ENGINE DEFINING A ROTOR CAVITY
Organization Name
Inventor(s)
Narendra Anand Hardikar of Bengaluru (IN)
GAS TURBINE ENGINE DEFINING A ROTOR CAVITY
This abstract first appeared for US patent application 18362341 titled 'GAS TURBINE ENGINE DEFINING A ROTOR CAVITY
Original Abstract Submitted
A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, a compressor of the compressor section comprising an aft-most compressor stage; a stage of stator vanes located downstream of the aft-most compressor stage; a stator case including a seal pad; and a spool drivingly coupled to the compressor, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the spool comprising a seal tooth assembly, the seal tooth assembly including a seal support extension, a seal tooth extending from the seal support extension toward the seal pad, and a dampener operable with the seal support extension.
