Patent ID: 6966191

Claim:
A device for supplying secondary air in a gas turbine engine, comprising: an inner shaft ( 8 ) connected to a low pressure compressor (LC) and a low pressure turbine (LT); an outer shaft ( 7 ), coaxially disposed with respect to the inner shaft, connected to a high pressure compressor (HC) and a high pressure turbine (HT); at least a pair of bearing boxes ( 21 , 25 ) which are spaced from each other in an axial direction each accommodating a bearing ( 5 f , 5 r , 6 f , 6 r ) for supporting an end of the inner or outer shaft; a seal air introduction passage ( 41 , 45 , 48 ) 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 ( 62 ) provided in the seal air introduction passage and attached to a part attached to the outer shaft in a rotationally fast manner.