COOLING SYSTEM FOR GAS TURBINE ENGINES

摘要

A cooling system for gas turbine engines (100) includes a turbine rotor compartment (106) defining a cooling air plenum (120). A plurality of turbine discs (130,132) are rotatably housed within the rotor compartment (106). A cooling air inlet (122) is in fluid communication with the plenum (120). Each turbine disc includes a cooling outlet (138) in fluid communication with the plenum for cooling the rotor compartment.