Abstract: This invention relates to a method of thermally isolating a bearing located near the combustion region in a gas turbine. Air is bled from an intermediate stage of the compressor turbine and is arranged to be fed to the central pipe of a coaxial piping arrangement which leads to the bearing housing. The housing for the bearing is arranged to have cooling air passages located therein to allow the air to circulate around and thus isolate the various parts of the bearing from the hot ambient. The air which has thereby acquired heat is subsequently lead back to the coaxial piping arrangement and is fed outwardly through the turbine in the space between the outer pipe and the central pipe.