18357410. GAS TURBINE ENGINE DEFINING A ROTOR CAVITY (General Electric Company)
Contents
GAS TURBINE ENGINE DEFINING A ROTOR CAVITY
Organization Name
Inventor(s)
Rajesh Kumar of Bengaluru (IN)
Sesha Subramanian of Bengaluru (IN)
Vaishnav Raghuvaran of Bengaluru (IN)
Ravindra Shankar Ganiger of Bengaluru (IN)
Adam Tomasz Pazinski of Warsaw (PL)
GAS TURBINE ENGINE DEFINING A ROTOR CAVITY
This abstract first appeared for US patent application 18357410 titled 'GAS TURBINE ENGINE DEFINING A ROTOR CAVITY
Original Abstract Submitted
A gas turbine engine includes a compressor section comprising a compressor, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, the compressor comprising an aft-most compressor stage; a spool drivingly coupled to the compressor; a stage of stator vanes located downstream of the aft-most compressor stage; and a stator case, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the stage of stator vanes including a first stator vane defining a fluid passage, and the stator case defining a plenum and a supplemental airflow passage, the plenum in fluid communication with the fluid passage in the first stator vane, the supplemental airflow passage in fluid communication with the plenum and the rotor cavity for proving an airflow to the rotor cavity
