Patent ID: 8402771

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; and (c) a turbine rotated by the hot gas, wherein the combustor is installed adjacent to the turbine opposite to the compressor, and a heat insulation device is installed between the combustor and the compressor, and between the turbine and the compressor, to reduce conduction of heat from a high-temperature side to a low-temperature side of the gas turbine engine, wherein the heat insulation device includes a heat-insulation heat exchange plate that includes 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 the flow path forming plate from a periphery, wherein the pressurized air flows in the inside along the low-temperature side outer plate, and the pressurized air flows in the high-temperature side at an inner end portion, and the pressurized air flows outwardly along the high-temperature side outer plate, and is discharged from the periphery to the combustor, wherein a compressor impeller of the compressor is connected to a turbine impeller of the turbine via a connection shaft; and the connection shaft is provided with an axial hole opened towards an inlet side of the compressor and that axially extends to a vicinity of the turbine impeller, and a radial hole opened towards an outside of the connection shaft adjacent to the turbine impeller and extending radially, wherein the radial hole is in communication with the axial hole.