DEVICE FOR STARTING GAS TURBINE ENGINE Russian patent published in 2017 - IPC F02C7/26 

FIELD: engine devices and pumps.

SUBSTANCE: device for starting the gas turbine engine comprises a rotor formed by a compressor, a turbine and a shaft connecting thereof, a combustion chamber, an auxiliary power plant, a pipeline connecting the auxiliary power plant with a turbine cooling system incorporating nozzle vanes with inner duct connected with turbine flow passage portion through slots in outlet edges of the nozzle vanes, and a working wheel with a disc and working blades. The inner cavity of the working blades is connected through slots in outlet edges with the turbine flow passage portion with air ducts provided in the working wheel, and a device for twsting the stator. The device is provided with a control valve positioned in the pipeline connecting the auxiliary power plant with the turbine cooling system, the air duct installed in the inner duct of turbine nozzle vanes. The air duct is communicated with the auxiliary power plant and the stator twisting device. The channels of the stator twisting device are directed towards rotation direction of the working wheel.

EFFECT: allows to simplify and increase the reliability of the start-up and also to considerably extend the range of engine start-up, in particular, in case of engine failure in flight conditions, reduce weight of launch system due to elimination of elements for additional mechanical rotor spin-up.

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