FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: proposed diaphragm of guide-vane assembly of high-pressure turbine in gas-turbine engine has inner side carrying at least one guide vane, and outer side opposite to inner side, from which flange extends radially to form cooling air channel at front side, and space at other, rear side. Trailing of guide vane is pointed to rear edge of diaphragm in direction flow. Inner side of diaphragm has coating applied between trailing edge of guide vane and rear edge of diaphragm to form heat barrier increasing temperature gradient produced in diaphragm by circular movement of air in said space.
EFFECT: provision of thermal protection of diaphragm in part where other cooling means cannot be used.
12 cl, 5 dwg
