METHODS AND APPARATUS FOR COOLING GAS TURBINE ENGINE BLADE TIPS

摘要

A turbine (20) for a gas turbine engine (10) including a turbine nozzle assembly (42) that facilitates reducing an operating temperature of rotor blades (56) in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity to a shroud (80) that extends circumferentially around the rotor assembly (40). The turbine nozzle assembly includes a plurality of turbine vane segments (92) that channel combustion gases to downstream rotor blades. Each turbine vane segment extends radially outward from an inner platform (96) and includes a tip (100), a root (102), and a body (94) that extends therebetween . The turbine vane segment tip is formed integrally with an outer band (150) that mounts the vane segments within the gas turbine engine. The outer band is in flow communication with a cooling fluid source, and includes at least one opening (158).