A low-pressure turbine (1) for a jet engine, said turbine being equipped with a turbine case (2), turbine blades (3) that rotate about the axis of the turbine case (2), and a shroud (4) that comprises multiple shroud segments (4A) arranged annularly along the inner peripheral surface of the turbine case (2) so as to surround the turbine blades (3), wherein an elongated protrusion (4a) and an outward groove (4b) are formed on each shroud segment (4A), each shroud segment (4A) is fixed to the turbine case (2) by engaging the elongated protrusion (4a) with a receiving groove (2a) of the turbine case (2) in the axial direction and by engaging the outward groove (4b) with an inward elongated protrusion (2b) of the turbine case (2), and each shroud segment (4A) has a pressure-receiving part (4e) formed thereon for receiving a force for releasing the engagement state of the outward groove (4b) with the inward elongated protrusion (2b) of the turbine case (2) when removing the shroud segment (4A) from the turbine case (2). The present invention enables disassembling work to be easily performed while achieving reduction of engine performance loss and reduction of thermal fatigue of the turbine case.