Patent ID: 8225615

Claim:
A gas turbine engine including: (a) a compressor for compressing air; (b) a combustor for burning a fuel in pressurized air compressed by the compressor to generate hot gas; (c) a turbine rotated by the hot gas, wherein the combustor is installed adjacent to the turbine opposite to the compressor; (d) a heat insulation device installed between the compressor and both the combustor and the turbine to reduce conduction of heat from a high-temperature side of the heat insulation device to a low-temperature side of the heat insulation device; wherein the heat insulation device includes a heat-insulation heat exchange plate for partitioning the compressor from both the combustor and the turbine; and wherein the heat-insulation heat exchange plate comprises (i) a low-temperature side outer plate, (ii) a high-temperature side outer plate, and (iii) a flow path forming plate, for partitioning an inside of the heat-insulation heat exchange plate, wherein the pressurized air compressed by the compressor flows in from a periphery the low-temperature side outer plate into the inside of the heat-insulation heat exchange plate along the low-temperature side outer plate, flows into the high-temperature side of the heat-insulation device at an inner end portion of the high-temperature side, outwardly along the high-temperature side outer plate, and is discharged from a periphery of the high-temperature side outer plate to the combustor.