Patent ID: 6510684
Filing Date: 2003-01-28
Classification: F02C,F04D,F05D

Abstract:
A gas turbine engine comprising a centrifugal compressor for compressing air that is drawn into the compressor, a compressed air passage, a burner, the burner being supplied with air compressed by the compressor through the compressed air passage, a turbine, the turbine being driven by combustion gas generated in the burner, a rotating shaft, the compressor and the turbine being positioned on the rotating shaft adjacent to each other in an axial direction of the rotating shaft, and a plurality of radially-arranged heat pipes, wherein each heat pipe has an evaporation section on a radially inner part thereof which faces an outer periphery of the rotating shaft between the compressor and the turbine and a condensation section on a radially outer part thereof which faces the compressed air passage.