IMPINGEMENT AND FILM COOLING FOR GAS TURBINE COMBUSTOR WALLS

摘要

The invention provides a cold combustor wall for lining the hot combustor wall of a gas turbine engine, disposed at a distance from the outer surface of the hot combustor wall. Improved cooling of the the hot combustor wall results from the addition of impingement cooling air injected through orifices in the cold combustion wall directed at the hot combustion wall. The cold combustor wall has an outer surface in contact with cool compressed air and includes a pattern of air impingement inlet orifices through the cold combustor wall for conducting compressed air from the outer surface of the cold combustor wall in compressed air jets directed at the outer surface of the hot combustor wall. The provision of a cold combustor wall improves conventional air film cooling by adding impingement cooling and reusing the air after impingement to form the conventional air film. The invention is equally applicable to hot combustor walls using conventional effusion cooling and splash louver cooling film systems as well.