Abstract: In a part-fastening structure, one of respective threads of a first nut member for fastening a first part and a second nut member for fastening a second part, is a right-hand thread, and the other is a left-hand thread. The members are connected together by a connecting member against relative rotation. Thus, rotation of the first member in its loosening direction acts in a direction of fastening the second member via the connecting member, and rotation of the second member in its loosening direction acts in a direction of fastening the first member via the connecting member, so that looseness of both the members is prevented, while reducing the number of locking parts to minimize an increase in an axial dimension.

Abstract: In a part-fastening structure, one of respective threads of a first nut member for fastening a first part and a second nut member for fastening a second part, is a right-hand thread, and the other is a left-hand thread. The members are connected together by a connecting member against relative rotation. Thus, rotation of the first member in its loosening direction acts in a direction of fastening the second member via the connecting member, and rotation of the second member in its loosening direction acts in a direction of fastening the first member via the connecting member, so that looseness of both the members is prevented, while reducing the number of locking parts to minimize an increase in an axial dimension.

Abstract: To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

Abstract: In a device for supplying secondary air in a gas turbine engine provided with an inner shaft (8) and a hollow outer shaft (7) coaxially nested with each other, a seal air introduction passage (71, 85, 88) is defined inside the engine for introducing a part of high pressure air drawn from a high pressure compressor into a seal section provided in each of the bearing boxes for supporting the inner and outer shafts; and a swirl air cooling turbine (59) is provided in the seal air introduction passage and attached to a part attached to the outer shaft in a rotationally fast manner. The swirl air cooling turbine (59) is formed around a section of the outer shaft intermediate between the high pressure compressor and the high pressure turbine, the swirl air cooling turbine including a spiral flow path extending in a substantially cylindrical plane coaxial with the outer shaft.

Abstract: [Object] To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. [Means] The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

Abstract: In a device for supplying secondary air in a gas turbine engine provided with an inner shaft (8) and a hollow outer shaft (7) coaxially nested with each other, a seal air introduction passage (71, 85, 88) is defined inside the engine for introducing a part of high pressure air drawn from a high pressure compressor into a seal section provided in each of the bearing boxes for supporting the inner and outer shafts; and a swirl air cooling turbine (59) is provided in the seal air introduction passage and attached to a part attached to the outer shaft in a rotationally fast manner. The swirl air cooling turbine (59) is formed around a section of the outer shaft intermediate between the high pressure compressor and the high pressure turbine, the swirl air cooling turbine including a spiral flow path extending in a substantially cylindrical plane coaxial with the outer shaft.

Abstract: In a device for supplying secondary air in a gas turbine engine provided with an inner shaft (8) supporting a low pressure compressor and a low pressure turbine and a hollow outer shaft (7) coaxially nested with the inner shaft and supporting a high pressure compressor and a high pressure turbine, a seal air introduction passage (41, 45, 48) for introducing a part of high pressure air drawn from the high pressure compressor into a seal section provided in each of the bearing boxes is provided with a high pressure air introduction turbine (62) attached to the outer shaft in a rotationally fast manner.

Abstract: In a device for supplying secondary air in a gas turbine engine provided with an inner shaft (8) supporting a low pressure compressor and a low pressure turbine and a hollow outer shaft (7) coaxially nested with the inner shaft and supporting a high pressure compressor and a high pressure turbine, a seal air introduction passage (41, 45, 48) for introducing a part of high pressure air drawn from the high pressure compressor into a seal section provided in each of the bearing boxes is provided with a high pressure air introduction turbine (62) attached to the outer shaft in a rotationally fast manner.

Abstract: Provided is a device for supplying seal air to the bearings of a gas turbine engine which allows the seal pressure to be kept even between the front and rear gear boxes without complicating the passages for supplying the seal air to the bearing boxes. Sealing air drawn from a part of high pressure compressor is conducted through passages defined between the inner periphery of the rotors of the high pressure compressor and a high pressure turbine and the outer periphery of the outer shaft, and is distributed to the front and rear bearing boxes. By appropriately providing narrowed parts in these passages, seal air is evenly distributed between the front and rear bearing boxes. Thus, even in case of a failure of one of the oil seals, any concentrated leakage of the lubricating oil can be avoided.

Abstract: Provided is a device for supplying seal air to the bearings of a gas turbine engine which allows the seal pressure to be kept even between the front and rear gear boxes without complicating the passages for supplying the seal air to the bearing boxes. Sealing air drawn from a part of high pressure compressor is conducted through passages defined between the inner periphery of the rotors of the high pressure compressor and a high pressure turbine and the outer periphery of the outer shaft, and is distributed to the front and rear bearing boxes. By appropriately providing narrowed parts in these passages, seal air is evenly distributed between the front and rear bearing boxes. Thus, even in case of a failure of one of the oil seals, any concentrated leakage of the lubricating oil can be avoided.