Abstract: This invention relates to cooling a section of a split shaft gas turbine engine. Because combustion takes place in the region of the shaft-split, overheating may occur and care must be taken to ensure that this portion of the turbine is sufficiently cooled. This invention is concerned with bleeding a portion of the compressed air from an intermediate stage of the compressor turbine and feeding the compressed air into a manifold. Next the air is fed by means of suitable conduit members into the split-shaft region of the turbine. Provision is made to feed this air to the faces of the power disc for the compressor section and the face of the power disc for the output power section of the turbine. Various other parts of the turbine are also cooled in the split shaft region of the turbine.