ASSEMBLY, COMPRESSOR AND COOLING SYSTEM

摘要

A gas turbine engine (20;100) may comprise a first rotor (206) with a primary flowpath (201) along an outer diameter of the first rotor (206). A secondary flowpath (202) may be radially inward from the primary flowpath (201). The secondary flowpath (202) may pass through an opening (208) through the first rotor (206). A blade (252) may be disposed on a distal end of the first rotor (206). The blade (252) may extend into the primary flowpath (201). A bleed tube (204) may be in a wall of the primary flowpath (201) and forward of the blade (252). The bleed tube (204) may extend radially inward from the primary flowpath (201). The bleed tube (204) may fluidly connect to the opening (208) through the first rotor (206). A plenum (210) may be aft of the blade (252) and radially inward from the primary flowpath (201). The plenum (210) may be fluidly connected to the opening (208) through the first rotor (206). A second rotor (216) may be aft of the plenum (210).