Gas turbine engine with cooling arrangement

A gas turbine engine has an exhaust diffuser. The diffuser has inner and outer cones both arranged coaxially with a central axis to define an annular exhaust channel there between and a central cavity within the inner cone. A first path is provided to extend radially through the outer and inner cones. The first path has a radially inward end and a radially outward end and the inward end s fluidly connected to the central cavity. An air supply is fluidly connected to the radially outward end of the first path, for supplying cooling air through the first path into the central cavity. An air supply or ejector is fluidly connected to the radially outward end of the first path, for drawing air by using the compressed air through the first path into the central cavity. A first opening is defined in the inner cone to fluidly connect between the exhaust channel and the central cavity. The first path and the first opening are so positioned that the cooling air is delivered from the air supply through the first path, the central cavity, and the first opening into the exhaust channel as it makes thermal contact with an object positioned in the central cavity to cool the object.