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 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 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 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.
Abstract:
An engine includes a duct containing a flow of cool air and a pump system for providing air to an environmental control system. The pump system has an impeller having an inlet for receiving cool air from the duct and an outlet for discharging air to the environmental control system.
Abstract:
A gas turbine engine has an impeller pump for delivering air to an environmental control system and a speed control pump connected to the impeller pump for driving the impeller pump at a constant speed.
Abstract:
motor de turbina a gás. é descrito um motor de turbina a gás que inclui um eixo do conjunto compressor-turbina ao longo de um eixo geométrico da linha central do motor que aciona um trem de engrenagem, o dito eixo do conjunto compressor-turbina inclui um compressor de baixa pressão com quatro a oito (4-8) estágios
Abstract:
A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.