Abstract: In a flange cooling structure of a gas turbine engine, one of a first flange and a second flange is a high pressure flange that faces a first region, and the other of the first flange and the second flange is a low pressure flange that faces a second region. A contact surface of the high pressure flange or a contact surface of the low pressure flange includes a cooling groove that communicates with the first region and the second region.

Abstract: A gas turbine engine including a compressor that compresses air taken in; a combustor that sprays a fuel into the compressed air and combusts the fuel; a turbine rotated by energy of the combustion gas generated by the combustor; a rotating shaft coupling the compressor and the turbine; a rear bearing that is a cageless ball bearing including an inner race, an outer race, and a ball, the inner race being fixed to a portion of the rotating shaft which portion is close to the turbine; a housing to which the rear bearing is attached; and a rear bearing holding member that is interposed between the rear bearing and the housing and holds the outer race of the rear bearing such that the outer race of the rear bearing is movable in an axial direction relative to the housing.

Abstract: A stationary blade unit including a first engaging portion projecting from an outer tube toward a first side in an axial direction; and a second engaging portion projecting from the outer tube toward a second side in the axial direction. A first outer shell includes a first flange and a first engaged portion into which the first engaging portion is slidingly inserted in the axial direction. A second outer shell includes: a second flange fastened to the first flange by a fastener; and a second engaged portion into which the second engaging portion is slidingly inserted in the axial direction. The stationary blade unit includes a projection projecting outward in a radial direction from the outer tube. One of the first outer shell and the second outer shell includes an integrated stopper arranged on a rotation trajectory of the projection around an axis.

Abstract: A gas turbine engine includes: a fan that is in front of a compressor and rotates in association with a rotating shaft; a casing including an inner shell and an outer shell and a bypass passage; bearings inside the inner shell; an oil mist generator that is outside the outer shell and generates oil mist by mixing oil with compressed air extracted through an extraction port of the compressor; an air pipe through which the compressed air extracted from the compressor is guided to the oil mist generator; and an oil mist pipe through which the oil mist generated by the oil mist generator is guided to the bearings. At least one of the air pipe and the oil mist pipe includes a heat exchanger that is in the bypass passage and is cooled by the air flowing through the bypass passage.

Abstract: A gas turbine engine including a compressor that compresses air taken in; a combustor that sprays a fuel into the compressed air and combusts the fuel; a turbine rotated by energy of the combustion gas generated by the combustor; a rotating shaft coupling the compressor and the turbine; a rear bearing that is a cageless ball bearing including an inner race, an outer race, and a ball, the inner race being fixed to a portion of the rotating shaft which portion is close to the turbine; a housing to which the rear bearing is attached; and a rear bearing holding member that is interposed between the rear bearing and the housing and holds the outer race of the rear bearing such that the outer race of the rear bearing is movable in an axial direction relative to the housing.

Abstract: In a flange cooling structure of a gas turbine engine, one of a first flange and a second flange is a high pressure flange that faces a first region, and the other of the first flange and the second flange is a low pressure flange that faces a second region. A contact surface of the high pressure flange or a contact surface of the low pressure flange includes a cooling groove that communicates with the first region and the second region.

Abstract: A gas turbine engine includes: a fan that is arranged in front of a compressor and rotates in association with a rotating shaft; a casing including an inner shell accommodating the compressor, a combustor, and a turbine, and an outer shell arranged such that a bypass passage through which part of air supplied by the fan flows exists between the inner shell and the outer shell; bearings arranged inside the inner shell; an oil mist generator that is arranged outside the outer shell and generates oil mist by mixing oil with compressed air extracted through an extraction port of the compressor; an air pipe through which the compressed air extracted from the compressor is guided to the oil mist generator; and an oil mist pipe through which the oil mist generated by the oil mist generator is guided to the bearings. At least one of the air pipe and the oil mist pipe includes a heat exchanger that is arranged in the bypass passage and is cooled by the air flowing through the bypass passage.