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

Claim 7:
8. 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;
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;
a core engine outer casing arranged radially outward of the stator shroud casing, the pressurized air source being arranged between the stator shroud casing and the core engine outer casing;
an air intake duct connected to an inlet through the core engine outer casing and connected to the pressurized air source; and
a pressurized air duct connecting the pressurized air source to the plurality of pressurized airflow nozzles.