TURBINE

A low-pressure turbine 1 of a jet engine includes: a turbine case 2; turbine blades 3 rotatable about an axis of the turbine case 2; and a shroud 4 including a plurality of shroud segments 4A annularly placed along an inner peripheral surface of the turbine case 2 while surrounding the turbine blades 3. Each shroud segment 4A is provided with a projection 4a and an outward groove 4b. The shroud segment 4A is fixed to the turbine case 2 by allowing the projection 4a to engage with a receiving groove 2a of the turbine case 2 in an axial direction, and allowing the outward groove 4b to engage with an inward projection 2b of the turbine case 2 in a radial direction. The shroud segment 4A is provided with a pressure receiving portion 4e that receives a force to release an engaged state of the outward groove 4b with the inward projection 2b of the turbine case 2 in a step of removing the shroud segment 4A from the turbine case 2. This enables disassembling work to be performed easily, while realizing reduction of engine performance loss and mitigation of thermal fatigue of the turbine case.