A turbine engine includes a compressor, a combustion chamber, first and second turbines downstream from the combustion chamber, a first rotary shaft constrained to rotate at least with the compressor and the first turbine, a second rotary shaft constrained to rotate with the second turbine, the second rotary shaft nevertheless being free to rotate relative to the first rotary shaft, and a regulator for controlling the feed of fuel to the combustion chamber. The regulator cuts off the feed of fuel to the combustion chamber if the speed of rotation of the second rotary shaft exceeds a maximum threshold that varies as a function of at least one indicative physical parameter associated with mechanical power being extracted from the combustion gas by the second turbine. A method of regulating the turbine engine is also presented.

This invention provides a gas turbine power generation equipment adapted to prevent step out of an electric power generator due to a system trouble such as a momentary power failure in a local grid including intermittent renewable energy generation equipment and the gas turbine power generation equipment. The gas turbine power generation equipment that supplies electric power in cooperation with the intermittent renewable energy generation equipment in the local grid interconnected to a power grid includes: a fuel flow control valve that controls a flow rate of fuel supplied to a combustor; a bleed valve or inlet air flow control valve that controls a flow rate of air compressed by a compressor and supplied to the combustor; and a control unit configured so that if voltage on the power grid decreases below a threshold V(t), the control unit outputs a control signal to at least one of the fuel flow control valve, the bleed valve, and the inlet air flow control valve. The control unit thereby reduces instantaneously at least one of the fuel flow rate and the compressed air flow rate. After an elapse of a predetermined time, the control unit instantaneously returns the reduced flow rate to its original level.

Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

A gas turbine drive system in mechanical drive configuration is described. The gas turbine drive system comprises a gas turbine engine drivingly connected to a driven turbomachine. The gas turbine engine includes a dry low NOx emission combustor. A gas turbine controller is further provided. The gas turbine controller is arranged and configured for regulating the combustion temperature according to at least one control parameters of the turbomachine so that a lean blowout of the combustor is prevented when a transient event involving the driven turbomachine occurs.

A method of stopping an engine of a rotorcraft in overspeed, the engine comprising a gas generator and a power assembly. When the engine is in operation, the engine is automatically stopped when the following three conditions are satisfied simultaneously: a torque (Tq) measured on the power assembly is below a predetermined torque threshold (Tq1); and a speed of rotation referred to as a first speed of rotation (N1) of the gas generator is above a threshold referred to as a first speed threshold (S1); and a speed of rotation referred to as a second speed of rotation (N2) of the power assembly is above a threshold referred to as a second speed threshold (S2).

A system for discharging compressed air from a compressor includes a air distribution manifold that is in fluid communication with the compressor via a conduit and at least one discharge line that is in fluid communication with the air distribution manifold. The discharge line defines a flow path from the air distribution manifold to atmosphere. The discharge line comprises a coupling pipe that is coupled to the air distribution manifold, a sparger section that is disposed downstream from the coupling pipe and at least one restrictor plate that is disposed between the coupling pipe and the sparger section within the flow path. The restrictor plate comprises at least one aperture that provides a pressure drop of the compressed air between the air distribution manifold and the sparger section.

A dual trip manifold assembly (TMA) includes an isolation valve assembly having a first valve configured to receive a flow of fluid from a hydraulic system fluid supply. The first valve is configured to channel the flow of fluid to at least one hydraulic circuit. The isolation valve assembly also includes a second valve configured to receive the flow of fluid from the at least one hydraulic circuit. The second valve is further configured to channel the fluid flow to a trip header. The first valve and the second valve are synchronized to each other such that rotation of one valve causes a substantially similar rotation in the other valve.

A turbofan engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a shaft configured to be driven by the turbine section and coupled to the compressor section through a first torque load path, and a speed reduction mechanism configured to be driven by the shaft through a second torque load path separate from the first load path for rotating the fan.

A dual trip manifold assembly (TMA) includes an isolation valve assembly having a first valve configured to receive a flow of fluid from a hydraulic system fluid supply. The first valve is configured to channel the flow of fluid to at least one hydraulic circuit. The isolation valve assembly also includes a second valve configured to receive the flow of fluid from the at least one hydraulic circuit of the at least two hydraulic circuits. The second valve is further configured to channel the fluid flow to a trip header and to receive the fluid flow from the trip header. The first valve and the second valve are synchronized to each other such that rotation of one of said first and second valves causes a substantially similar rotation in the other of said first and second valves header.

An improved closed loop Brayton cycle for a power plant is provided that includes a heater, at least one turbine, a recuperator, at least one cooler, at least one compressor, a bypass line and a flap valve arrangement in a closed circuit in which working fluid is circulated to produce electricity via a generator. Depending upon the requirement, such as, in case of gird load disconnection, speed of a shaft-line to which the turbine, the compressor and the generator are configured is also required to be reduced without any impact on the pressure drop in the cycle. For that the non-tight flap valve arrangement is configured on each conduit between the heater and the at least one turbine in a closest possible proximity to each turbine inlet.