| 主权项 |
1. A combustor for a gas turbine engine comprising: inner and outer liners spaced apart from each other to define a chamber therebetween including a primary zone adjacent an upstream end of the chamber and a secondary zone downstream of the primary zone, the upstream end being closed by a dome, a dome heat shield disposed within the chamber, adjacent and spaced apart from the dome, an inner liner heat shield disposed within the chamber, adjacent and spaced apart from the inner liner, an outer liner heat shield disposed within the chamber, adjacent and spaced apart from the outer liner, the inner and outer liner heat shields extending from the upstream end of the chamber over the primary zone and terminating at the secondary zone, the inner and outer liners and the inner and outer liner heat shields defining a plurality of apertures therein for introducing dilution air jets into the chamber, the combustor including a plurality of impingement holes defined in the dome and inner and outer liners for directing impingement cooling air therethrough and into the combustor to impinge on a cold side of the respective heat shields, and a discharging apparatus to direct exhausted impingement cooling air discharged from the cold side of the respective heat shields to flow along and substantially parallel to a hot side of the respective inner and outer liner heat shields, the combustor further including a plurality of effusion holes defined in a section of the inner and outer liners free of coverage by the respective inner and outer liner heat shields, the effusion holes directing effusion cooling air therethrough and into the combustor to effusion cool said section of the inner and outer liners. |
