GAS TURBINE NOZZLE UNIT Russian patent published in 1999 - IPC

FIELD: mechanical engineering; gas turbines. SUBSTANCE: lip exit, forming together with one of shells slot channel for cooling air, is arranged in vane channel. Longitudinal ribs are installed in circular slot channel at both sides of vane leading edges. Areas of passage cross sections of circular slot channel located opposite to leading edges and between the edges are in definite relation with lengths of section arcs. Arrangement of lip exit in vane channel and provision of longitudinal ribs at both sides from vane leading edges makes required portion of cooling air, coming out of lip exit, get into vane leading edge being most heated. This provides decreasing nonuniformly of distribution of cooling air in circumferential direction in vane cooling system without increasing total consumption of cooling air and thus increasing efficiency of cooing of nozzle unit section adjoining vane leading edges. EFFECT: enhanced cooling of nozzle unit. 3 dwg