| 摘要 |
A thermal insulator between the turbine and the compressor of a gas turbine engine is provided and at the same time it enables the air that has passed through the compressor to be heated by the heat of the hot turbine. A gas turbine engine comprises a centrifugal compressor for compressing air that is drawn or sucked into the compressor, a compressed air passage supplying the air compressed by the compressor to a burner, and a turbine driven by means of combustion gas generated in the burner. The compressor and the turbine are provided on a rotating shaft adjacent to each other in the axial direction. Evaporation sections on the radially inner side of a plurality of heat pipes provided in a radial form face towards the outer periphery of the rotating shaft between the compressor and the turbine, and condensation sections on the radially outer side of the heat pipes face towards the compressed air passage.
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