GAS TURBINE ENGINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering; gas turbine engines. SUBSTANCE: engine contains combustion chamber, compressor connected through shaft with cooled turbine, space located behind last stage of compressor being separated by labyrinth seal from compressor setting and communicating with inlet of air feed duct. Space is limited by first stage of turbine, shaft and combustion chamber. Turbine is made with at least two stages with cooled nozzle assembly placed between stages which forms interdisk space. Outlet of air feed duct communicates with interdisk space through nozzle assembly cooling duct. EFFECT: reduced fuel consumption and increased reliability, efficiency and gas- dynamic stability of compressor. 3 cl, 3 dwg