METHOD OF OPERATING GAS-TURBINE ENGINE AND GAS-TURBINE ENGINE Russian patent published in 1994 - IPC

Abstract RU 2009350 C1

FIELD: heat power engineering. SUBSTANCE: fuel is fed through a shaft, disk and nozzle blade of the first stage of a multistage turbine, discharged toward air compressed in the compressor, and burnt out within inter-blade passages. Additional fuel supply from the blades of the last stage of the turbine, air supply from outer contour, and burning out the fuel in nozzle array positioned downstream of the blades are provided at reheating regimes of operation. EFFECT: improved method. 3 cl, 4 dwg

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RU 2 009 350 C1

Authors

Serkov Anatolij Gavrilovich

Dates

1994-03-15—Published

1991-06-14—Filed