A gas turbine engine , comprising: an exhaust diffuser connected to a turbine outlet and including an inner tube and an outer tube to form therebetween an annular exhaust passage through which an exhaust gas (EG) from a turbine passes; a strut extending across the exhaust diffuser from a housing disposed radially outward of the outer tube and configured to support a bearing inside the inner tube ; a strut cover , disposed in the exhaust passage , configured to cover an outer circumference of the strut ; and a connecting member connecting the housing and the inner tube , the connecting member being disposed downstream of the strut cover in the exhaust passage and including therein a hollow portion in which an accessory is inserted, wherein the housing includes a first intake port to introduce a first air (VA) for ventilation from outside, the strut cover has a plurality of discharge holes at a rear edge portion thereof, configured to discharge ventilation air (VA) inside the strut cover to the outside into the exhaust passage , the discharge holes being provided so as to be spaced apart from each other along a direction in which the strut cover extends across the exhaust passage the gas turbine engine further comprising a first ventilation passage (VP1) extending from the first intake port through the hollow portion of the connecting member into a cavity (S1) inside the inner tube , then extending from an inner end portion of the strut through a gap (S) between the strut and the strut cover , and the discharge holes of the strut cover , into the exhaust passage , wherein the rear edge portion of the strut cover has a flat surface portion facing a downstream side of the exhaust gas (EG), and a portion of the strut cover other than the rear edge portion is formed as a curved portion having an airfoil-shaped transverse cross section, characterized in that the discharge holes are provided in only one of two corner portions each corresponding to the boundary between the curved portion and the flat surface portion . an exhaust diffuser connected to a turbine outlet and including an inner tube and an outer tube to form therebetween an annular exhaust passage through which an exhaust gas (EG) from a turbine passes; a strut extending across the exhaust diffuser from a housing disposed radially outward of the outer tube and configured to support a bearing inside the inner tube ; a strut cover , disposed in the exhaust passage , configured to cover an outer circumference of the strut ; and a connecting member connecting the housing and the inner tube , the connecting member being disposed downstream of the strut cover in the exhaust passage and including therein a hollow portion in which an accessory is inserted, wherein the housing includes a first intake port to introduce a first air (VA) for ventilation from outside, the strut cover has a plurality of discharge holes at a rear edge portion thereof, configured to discharge ventilation air (VA) inside the strut cover to the outside into the exhaust passage , the discharge holes being provided so as to be spaced apart from each other along a direction in which the strut cover extends across the exhaust passage the gas turbine engine further comprising a first ventilation passage (VP1) extending from the first intake port through the hollow portion of the connecting member into a cavity (S1) inside the inner tube , then extending from an inner end portion of the strut through a gap (S) between the strut and the strut cover , and the discharge holes of the strut cover , into the exhaust passage , <EOS>