초록 ▼

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

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.

대표청구항 ▼

1. 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

1. 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. 2. A gas turbine engine according to claim 1, wherein an air bearing is formed between an inner periphery of the evaporation sections of the heat pipes and the outer periphery of the rotating shaft. 3. A gas turbine engine according to claim 2, wherein a plurality of channels inclined towards or orthogonal to the circumferential direction, are formed on the inner periphery of the evaporation sections of the heat pipes. 4. A gas turbine engine according to claim 3, wherein a width of the inner periphery of the evaporation sections of the heat pipes facing the outer periphery of the rotating shaft is increased in the axial direction of the rotating shaft. 5. A gas turbine engine according to claim 2, wherein a width of the inner periphery of the evaporation sections of the heat pipes facing the outer periphery of the rotating shaft is increased in the axial direction of the rotating shaft. 6. A gas turbine engine according to any one of claims 1 to 5, wherein the evaporation sections of at least two adjacent heat pipes communicate with each other. 7. A gas turbine engine according to any one of claims 1 to 5, wherein the evaporation sections of all the heat pipes communicate with each other. 8. A gas turbine engine according to any one of claims 1 to 5, wherein the condensation sections of the heat pipes in the compressed air passage, form diffusers. 9. A gas turbine engine according to any one of claims 1 to 5, wherein the evaporation sections of the heat pipes extending radially between the compressor and the turbine, are curved in the circumferential direction. 10. A gas turbine engine according to any one of claims 1 to 5, wherein the condensation sections of the heat pipes in the compressed air passage, are curved in the circumferential direction. 11. A gas turbine engine according to any one of claims 1 to 5, wherein the compressed air passage and the heat pipes are divided into a plurality of modules.