Abstract:
PROBLEM TO BE SOLVED: To provide an integrated rotor module that decreases hardware complexity and weight.SOLUTION: A rotor module 62 disposed in a low-pressure turbine 46 includes CMC airfoils 64A, 64B, and 64C, a CMC drum 66, vanes 68A, 68B, and a split case 60 respectively made of a ceramic composite material. The CMC airfoils 64A, 64B, and 64C form a multiple of rows and extend from the common CMC drum. The CMC airfoils 64A, 64B, and 64C are alternately arranged with the CMC vanes 68A, 68B. The rotor module 62 has a mount 70. The mount 70 extends radially inwardly from the central-axis position extending in the axial direction of the common drum 66 adjacent to the airfoil row 68B and integrally mounts the rotor module 62 to an inner shaft 40. The rotor module 62 further includes an independent feature such as a knife edge seal 72.
Abstract:
PROBLEM TO BE SOLVED: To shorten a low shaft of an engine while increasing output density of the engine.SOLUTION: A gas turbine engine 20 includes a shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure turbine 62 includes inside blade sets 120 which are connected to a low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is rotated on a rotation axis in a direction opposite to the inside blade set 120 at a speed lower than the speed of the inside blade set 120. This configuration shortens the overall length of the engine 20, and makes the engine 20 have a desirable high-pressure core ratio, while maximizing the output density of the engine.
Abstract:
PROBLEM TO BE SOLVED: To provide a gas turbine engine arrangement in an engine mounting structure for mounting a turbo fan gas turbine engine to an aircraft pylon.SOLUTION: The gas turbine engine includes a spool which drives a gear train along an engine center axis, wherein the spool includes a low pressure compressor with 4 to 8 stages.
Abstract:
PROBLEM TO BE SOLVED: To shorten the low shaft of an engine while increasing the output density of the engine.SOLUTION: A gas turbine engine 20 includes a shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure compressor 60 comprises a counter-rotating compressor hub 70 having blade stages 72, 74 and 76, and blade stages 78 and 80 of a low-speed spool 30 are inserted among the blade stages 72, 74 and 76. A transmission 82 counter-rotates the counter-rotating compressor hub 70 with respect to the low-speed spool 30. The counter-rotating low-pressure turbine 62 comprises inside blade sets 120 which are connected to a low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is rotated on a rotation axis in a direction opposite to the inside blade set 120 at a speed lower than the inside blade set 120.
Abstract:
PROBLEM TO BE SOLVED: To provide a full hoop ring structure that prevents leakage of fluid from between each segment of a vane structure.SOLUTION: A vane structure 64B includes: a ceramic matrix composite ring 66 on the outer peripheral side; a ceramic matrix composite ring 68 on the inner peripheral side; and a multiple of ceramic matrix composite airfoils 70 incorporated between the ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side. The ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side are basically wound around the multiple of incorporated airfoils 70 so as to form a full hoop. The design of the full hoop rings allows to maximize the utilization of the fiber strength of the ceramic matrix composite material in the full hoop configuration.
Abstract:
PROBLEM TO BE SOLVED: To shorten the low shaft of an engine while increasing the output density of the engine.SOLUTION: A gas turbine engine 20 includes a low shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure turbine 62 includes inside blade sets 120 which are connected to the low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is fixed to an outside rotor 126; a front end of the outside rotor 126 is supported on a central turbine frame 134 by a bearing 150; and a rear end of the outside rotor 126 is supported on the low shaft 40 by the bearing 152. In addition, the gear device 116 comprises a sun gear 140, a splitter gear 142 which is meshed with the sun gear 140, and a ring gear 148 which is meshed with the splitter gear 142.
Abstract:
PROBLEM TO BE SOLVED: To provide a gas turbine engine which has a low stage count low-pressure turbine.SOLUTION: A gas turbine engine includes a spool which drives a gear train along an engine center axis, wherein the spool includes the low-pressure turbine with 3 to 6 stages.
Abstract:
PROBLEM TO BE SOLVED: To reduce weight and cost of a gas turbine engine.SOLUTION: A turbine exhaust case (70) of the gas turbine engine includes a plurality of CMC (ceramic matrix composite) turbine exhaust case struts (72) between a CMC core nacelle aft portion (76) and a CMC tail cone (74).
Abstract:
PROBLEM TO BE SOLVED: To provide a geometry that provides continuity to fibers of a ceramic matrix composite material, and to maximize the strength per weight.SOLUTION: In each structure of the air foil segments 82, the box-shape ceramic-matrix-composite-fiber geometry 98 is used. Each of the ceramic matrix composite airfoil segments 82 defines a rectilinear pressure side bond line 100P and a rectilinear suction side bond line 100S on a circumferential segment of the ceramic matrix composite airfoil segments 82 to maintain aerodynamic performance and provide a strong bonding part. The rectilinear pressure side bond line 100P and the rectilinear suction side bond line 100S approximately align with a front edge 84L, a rear edge 84T, and respective platforms 90, 92.
Abstract:
PROBLEM TO BE SOLVED: To provide a disk that has self-retention capability in order to maintain the balance of circumferential stress.SOLUTION: Airfoils 66A, 66C define rails 80A, 80C. Respective contours of the rails 80A, 80C define an innermost bore radius B of a rail inner bore 82. That is, the rails 80A, 80C are relatively axially wide at rail platforms 84 of the contours adjacent the airfoils 66A, 66C and inclined toward the rail inner bore 82. The rail inner bore 82 defines an axial thickness of 1y while the rail platforms 84 define axial thicknesses of 1y to 6y.