GAS TURBINE ENGINE WITH HIGH TEMPERATURE SPOOL AND ASSOCIATED COOLING SYSTEM

摘要

A gas turbine engine (20) includes a turbine section (54) that includes a turbine rotor (132) arranged in a plenum (180). A compressor section (54) includes a compressor rotor assembly (60) that has spaced apart inner and outer portions (71, 73) that provide an axially extending cooling channel (84). Compressor blades (78) extend radially outward from the outer portion (73) which provides an inner core flow path (C). A rotor spoke is configured to receive a first cooling flow (76) and fluidly connect the outer portion (73) to the cooling channel (84). The compressor rotor assembly (60) has a coolant exit (90) that is in fluid communication with the cooling channel (84). The compressor rotor assembly (60) is configured to communicate the first cooling flow (76) to the turbine rotor (132). A bleed source (91) is configured to provide a second cooling flow (190). A combustor section (56) includes an injector (120) in fluid communication with the bleed source (91). The tangential onboard injector (120) is configured to communicate the second cooling flow (190) to the turbine rotor (132).