The present application relates to cooling of an exhaust frame (4) of a gas turbine and attempts to solve the problem of stagnation zones in the cooling path, in particular downstream of struts (11). The exhaust frame includes: inner and an outer casing (9A, 9B), inner and outer diffuser walls (10A, 10B) located between the inner and outer casings, thereby defining an inner cooling passage, an exhaust passage and an outer cooling passage; a strut (11) which connects the inner casing (9A) and the outer casing (9B) to each other; a strut cover (12) defining an annular connection passage (22) connecting the inner cooling passage (16) and the outer cooling passage (19) to each other; and a communication hole (24; 28; 29) provided in a wall of the outer cooling passage (19) at a position downstream of a center line (X) of the strut (11) in the flow direction of a combustion gas (7).