Patent ID: 11913376
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 17:
18. A gas turbine engine comprising:
a compressor section including (a) a compressor rotor shaft assembly including a plurality of compressor rotors longitudinally spaced apart from each other via respective ones of a plurality of shaft sections of a rotor shaft, each compressor rotor of the plurality of compressor rotors having a plurality of rotor vanes extending radially outward therefrom and being circumferentially spaced about the compressor rotor, and (b) a stator shroud assembly including a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing;
a pressurized air source that generates a flow of pressurized air to be provided to the compressor section; and
a plurality of pressurized airflow nozzles connected with the pressurized air source and that provide the flow of pressurized air into the compressor flow passage as a primary driver source to cause the compressor rotor shaft assembly to rotate during a shutdown phase of the gas turbine engine,
wherein the compressor rotor shaft assembly defines a pressurized cavity therewithin that is in fluid communication with the pressurized air source, and the plurality of pressurized airflow nozzles being arranged through at least one shaft section of the plurality of shaft sections, the plurality of pressurized airflow nozzles being circumferentially spaced apart and arranged to provide a tangential flow of air therefrom, with respect to a circumferential direction about the compressor rotor shaft assembly, into the compressor flow passage so as to cause the compressor rotor shaft assembly to rotate.