GAS TURBINE DISK CAVITY INGESTION INHIBITOR

摘要

A supplemental air cooling system for use in gas turbine engines to inhibit the ingestion of hot flow path gases into circumferential locations of turbine disk cavities is provided. The supplemental air cooling is provided through a simple set of cooling air holes located on each side of the turbine nozzle airfoil trailing edges, and proximately placed to be below the turbine nozzle structural element flow discouragers. Turbine disk cavity cooling purge air entering the disk cavity through the cooling air holes produces dynamic pressure cooling air jets which force the incoming hot ingestion air to turn circumferentially and go back out in the flow path before it enters the turbine disk cavity. The result is a decrease in hot gas ingestion, a reduction in disk rotor and static structural metal temperatures, a reduction in the amount of required cooling air flow, and enhanced performance of the gas turbine engine by virtue of improved specific fuel consumption.