Patent ID: 7624580

Claim:
A device for supplying secondary air in a gas turbine engine, comprising: an inner shaft connected to a low pressure compressor and a low pressure turbine; an outer shaft coaxially disposed with respect to the inner shaft, connected to a high pressure compressor and a high pressure turbine; at least a pair of bearing boxes which are spaced from each other in an axial direction each accommodating a bearing for supporting an end of the inner or outer shaft; a seal air introduction passage for introducing a part of high pressure air drawn from the high pressure compressor into a seal section provided in each of the bearing boxes; and a high pressure air introduction turbine provided in the seal air introduction passage and attached to a part attached to the outer shaft in a rotationally fast manner, the high pressure air introduction turbine including a swirl air cooling turbine formed around a section of the outer shaft intermediate between the high pressure compressor and the high pressure turbine, and including a spiral flow path extending in a substantially cylindrical plane coaxial with the outer shaft.