Abstract: A gas turbine engine E includes a compressor wheel 9 and a turbine wheel 10 fixed to a rotary shaft 8, a can-type combustor 18 disposed on an extension of the axis L of the rotary shaft 8, and an circular plate-type heat exchanger 12 disposed to surround a radially outer portion of the can-type combustor 18. The compressor wheel 9, the turbine wheel 10, the can-type combustor 18 and the plate-type heat exchanger 12 are disposed coaxially with the axis L of the rotary shaft 8. Therefore, the flows of compressed air and combustion gas are symmetrized with respect to the axis L, and the distribution of temperature within a casing is also symmetrized with respect to the axis L. Thus, the flows of compressed air and combustion gas within the gas turbine engine E can be axially symmetrized, and the generation of a thermal distortion can be prevented.