COOLING SYSTEM FOR AIRCRAFT GAS TURBINE ENGINE

A cooling system includes: a core casing (18) configured to house a compressor (12, 13), a combustion chamber (14), and a turbine (15, 16); a tail cone (28) configured to form at least part of an exhaust passage (23) of the turbine (15, 16) together with the core casing (18); struts (27) configured to connect the core casing (18) with a support body (26) of the tail cone (28); a housing (31) installed in the tail cone (28), configured to house an electrical apparatus; and at least one primary duct (40) configured to connect between an internal space of the housing (31) and an outlet passage (12a) of the compressor (12) or a discharge port of a blower (34) installed in a gas turbine engine via at least one of the struts (27) and a radial outside of the core casing (18).