Aircraft gas turbine

Abstract

An aircraft gas turbine is constituted by accommodating a compressor (14), a combustor (15), and a turbine (16) in a cylindrical main unit casing (12). A thick wall part (52) is provided on an outer periphery side of rotor blades (34) in the main unit casing (12), a cooling passage (53) for cooling the thick wall part (52) by circulating compressed air compressed by the compressor (14) is provided in the thick wall part (52), and a discharge passage (55) for discharging compressed air having circulated in the cooling passage (53) to a combustion gas passage A is provided, and therefore the structural strength of the thick wall part is ensured by appropriately cooling the thick wall part of the casing, while simplifying the structure and preventing a decrease in efficiency, thereby enabling to ensure effective containment performance and an appropriate clearance between the casing and the rotor blades.

Dependencies are inferred from the claim text.