PURPOSE: To reduce the generation of vibration stress by connecting a first spool constituting a part of a rotor of a turbine having a double reverse moving airfoil row with a second spool constituting a shroud of a blade body by a plurality of blades extending in the radial direction to constitute a vibration damping airfoil row.

CONSTITUTION: This gas turbine engine 60 is provided with a thruster (fan part) 61 including a power turbine 50 having a first turbine 72 and a second turbine 74 which are reversed mutually in the rear of a gas generator 62 having a compressor part 22 and a combustor part 36. Fan moving airfoils 64 in a front row and fan moving airfoils 68 in a rear row are driven by each turbine 72, 74 in a double reverse manner. In this case, a first spool 77 constituting a part of an outer rotor 76 of the first turbine 72 and a second spool 78 constituting an inner shroud band 79 at an airfoil tip are mutually connected by a plurality of airfoils 102 extending in the radial direction to constitute an annular airfoil row casting 100 which is a vibration damping airfoil row and connect it to an engine in flanges 104, 106 provided in the first spool 77.