An example embodiment of a turbine engine assembly includes a low spool including a low spool accessory drive gear driven by a low rotor shaft, a high spool including a high spool accessory drive gear driven by a high rotor shaft concentric around a portion of the low rotor shaft, and a differential gear assembly adapted to offtake power from rotation of one or both of the low spool and the high spool to drive one or more accessory loads. The differential gear assembly includes a differential bullgear and one or more idler gears each including a plurality of teeth meshed with the low spool accessory drive gear and the high spool accessory drive gear, and a bearing surface. The differential bull gear includes a plurality of teeth and a corresponding at least one bearing surface engaging with the bearing surface of each of the one or more idler gears. The plurality of teeth are adapted to mesh with an accessory drive system to transfer the power offtake and drive the one or more accessory loads.

Systems and methods for operating an engine of a rotorcraft are described herein. An engine parameter indicative of torque of the engine is obtained. A decrease of the torque of the engine is detected. At least one rotorcraft parameter indicative of at least one command to control the rotorcraft is obtained and evaluated to determine whether one of an autorotation mode and a powered flight mode of the rotorcraft has been commanded. When the powered flight mode of the rotorcraft has been commanded and the decrease of the torque has been detected, a shaft shear of the engine is detected and a signal indicative of the shaft shear is transmitted. When the autorotation mode of the rotorcraft has been commanded and the decrease of the torque has been detected, detection of the shaft shear is disabled during operation in the autorotation mode.

A system for operating a turbo machine to maintain bearing engagement, the system including a bearing assembly; a first displacement device adjacent a bearing race; a second displacement device disposed adjacent the bearing race opposite of the first displacement device; an effort supply system disposed adjacent to the first and/or second displacement devices; and one or more controllers configured to perform operations. The operations include generating a first effort input at the first and/or second displacement devices; adjusting a thrust loading at the bearing assembly; generating a second effort input at the first displacement device greater than the first effort input; and displacing the bearing race opposite of the thrust loading at the bearing assembly via the generated second effort input at the first displacement device.

An axial load management system for a turbomachine including a rotating drivetrain, a thrust bearing assembly, a sensor, and a valve supply line. The rotating drivetrain includes a compressor section and an expander section fluidly coupled together by a closed flowpath. The thrust bearing assembly includes a thrust runner, a thrust bearing housing, and a gas thrust bearing extending between the thrust runner and the thrust bearing housing. Further, the gas thrust bearing supports the rotating drivetrain. The sensor is attached to at least one of the thrust bearing housing or the gas thrust bearing. The valve supply line is fluidly coupled to the closed flowpath. A valve positioned within the valve supply line selectively allows a working fluid to flow between the closed flowpath and a thrust chamber defined by a rotating surface and a fixed surface to modify an axial load on the rotating drivetrain.

An operation control device for a single shaft gas turbine selects an operation mode based on a load state of a power generator, and controls the turbine based on the operation mode. In a first operation mode, a rotational speed of the turbine is maintained within a first rotational speed range, and in a second operation mode, the rotational speed is maintained within a second rotational speed range set on a lower rotational speed side than the first rotational speed range. The second rotational speed range is set on the lower rotational speed side than the first rotational speed range with a first non-selection rotational speed range set therebetween.

A turbine section for a gas turbine engine includes a variable reaction free wheel downstream of the first static vane structure and a turbine rotor downstream of the variable reaction free wheel. A method of generating thrust for a gas turbine engine, includes rotating a variable reaction free wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.

A dry gas seal for sealing the shaft of a turbomachinery, provided with means for the continuous health monitoring of the dry gas seal comprising one or more sensors adapted to measure strains and/or loads induced to the primary ring of the dry gas seal and/or strains induced to one or more of the elastic elements coupled to the primary ring and/or adapted to measure displacements of the primary ring or of an element coupled to the primary ring, for an early detection of failure of the seal, thus enabling main failures early detection capability and proactive maintenance actions.

The invention relates to an assembly for monitoring and/or controlling a wind turbine. The assembly includes a first strain sensor for measuring a first blade bending moment of a rotor blade of a wind turbine in a first spatial direction; a second strain sensor for measuring a second blade bending moment of a rotor blade of a wind turbine in a second spatial direction, which differs from the first spatial direction; an arrangement for determining constant components of forces and moments of the rotor blades provided in the wind turbine; and a controller for combining the first blade bending moment, the second blade bending moment and the constant components.

A gas turbine cooling system includes: a cooling air line that guides compressed air; a cooler that cools the compressed air; a flow rate adjuster that adjusts the flow rate of the cooling air; and a control device. The control device includes: a load change determination unit that determines whether a load indicated by a load command of the gas turbine has changed; a first command generation section that generates a first command indicating such an operation amount of the flow rate adjuster as allows the flow rate of the cooling air to meet a target flow rate; and a second command generation section that, when it is determined that the load indicated by the load command has changed, generates a second command indicating such an operation amount of the flow rate adjuster as allows a change-adapted flow rate higher than the target flow rate to be met.

A load adjustment method, comprising: a step of acquiring a warm-up parameter indicating the degree of warm-up of a gas turbine during operation under load; a step of determining an upper limit of a load increase rate in accordance with the warm-up parameter; and a step of increasing the load of the gas turbine at or below the upper limit of the load increase rate.