HIGH-TEMPERATURE GAS TURBINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering. SUBSTANCE: proposed high-temperature gas turbine contains nozzle blades whose airfoil portions are divided by rids into radial spaces communicating at outlet with turbine setting. Nozzle blades are installed with their upper edges in outer race forming front and rear closed spaces with the race which communicate at inlet through channels with cooling air supply space and at outlet, with radial spaces of nozzle blades at F₁:F ₂ = 1,1...3, where F₁ and F₂ are areas of channels connecting, respectively, front and rear closed spaces with cooling air supply space. EFFECT: improved reliability of high-temperature gas turbine owing to intensification of convective cooling of turbine nozzle blades. 3 dwg