A system includes a gas turbine operational at a constant rated rotational speed, a speed sensor to measure an actual speed of the gas turbine, a turbine controller to control the gas turbine to the constant rated rotational speed, and a generator coupled with the gas turbine and rotatable to output electric power. The system also includes a DC to DC converter to output a load current on a load bus to supply a load. The DC to DC converter is supplied input electric power from the generator. The system also includes an energy storage device cooperative operable with the DC to DC converter to supply power on the load bus, and a controller to receive the actual speed and adjust an output electrical current set point of the DC to DC converter to compensate for deviation of the actual speed from the constant rated speed of the gas turbine.

A system includes a first controller configured to control a gas turbine to operate at a constant speed set point and a variable torque output to drive a generator. A DC to DC converter may operate as a load on a power source bus supplied by the generator. A second controller may limit a rate of change of the DC output power of the DC to DC converter during intermittent supply of a transient step change load subsequent to receipt of a transient load control signal. The transient load control signal is anticipatory of application of the transient step change load to the load bus. The rate of change is limited by the second controller to maintain the variable torque of the gas turbine below a predetermined threshold as a load ramp rate of the DC to DC converter changes on the power source bus.

A system includes a DC to DC converter coupled with a load, a power source bus coupled with an input of the DC to DC converter, and an energy storage device. The energy storage device and an output of the DC to DC converter are coupled with a load bus, which supplies the load. The power source bus is supplied power by a generator being driven by a gas turbine. During operation, an operational temperature of the gas turbine may be received by the controller. The controller may dynamically adjust a demand output of the DC to DC converter in response to the operational temperature of the gas turbine exceeding a predetermined threshold temperature value for a predetermined period of time.

A turbomachine complex includes at least one motor-generator, at least one power source coupled to the at least one motor-generator, and at least one load dissipative device coupled to the at least one motor-generator. The turbomachine complex is configured to energize the at least one motor-generator through the at least one power source. The turbomachine complex is further configured to simultaneously energize the at least one at least one load dissipative device through the at least one motor-generator.

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 control device for a gas turbine system includes a sensing unit for measuring the rotor speed and the output of the power generator; a speed regulation rate setting unit for calculating an actual speed regulation rate based on the measured rotor speed and the measured output of the power generator, and for setting a reference speed regulation rate based on the actual speed regulation rate and the target speed regulation rate; and a fuel amount control unit for controlling an amount of fuel supplied to the combustor based on the set reference speed regulation rate. Stable system operation is secured by a method of controlling the gas turbine system to satisfy a target speed regulation rate if additional power should be supplied due to sudden load fluctuations or a failure at another power plant.

Disclosed herein is an integrated power generation and load driving system, comprising in combination a multi-shaft gas turbine engine comprising a high-pressure turbine mechanically coupled to an air compressor; and a low-pressure turbine, fluidly coupled to but mechanically separated from the high-pressure turbine and mechanically coupled to an output power shaft wherein the output power shaft is connected to a shaft line an electric generator, mechanically coupled to the shaft line and driven into rotation by the gas turbine engine a rotating load, mechanically coupled to the shaft line and driven into rotation by the gas turbine engine a load control arrangement, configured for controlling at least one operating parameter of the rotating load to adapt the operating condition of the rotating load to process requirements from a process, whereof the rotating load forms part, while the low-pressure turbine and the electric generator rotate at a substantially constant speed.

A turboexpander and driven turbomachine system comprising a turboexpander configured for expanding a first fluid and comprising an expander stage with one expander impeller; a first set of moveable inlet guide vanes at the inlet of the expander stage; a driven turbomachine configured for processing a second fluid and comprising a turbomachine impeller; a second set of moveable inlet guide vanes at the inlet of the turbomachine impeller; a mechanical transmission between the turboexpander and the driven turbomachine; and a controller connected to the second set of moveable inlet guide vanes and configured for controlling the second set of moveable inlet guide vanes for adjusting the rotary speed of the driven turbomachine and said turboexpander.

An assembly including a first turbocharger, the first turbocharger including a first turbine and a first compressor, the first turbine arranged in a turbine flowpath to be driven in rotation by an exhaust gas flowing at a variable flow rate through the turbine flowpath. The first compressor arranged in a compressor flowpath to be driven by the first turbine to urge an intake gas to flow through the compressor flowpath. The first turbine and first compressor being supported for rotation in bearings supplied via an oil flowpath at an oil pressure. The assembly further including a seal arranged between the oil flowpath and the compressor flowpath to resist leakage of the oil into the compressor flowpath and a flow control means configured to control a rotational speed of the first turbine and first compressor by controlling the flow of exhaust gas in the turbine flowpath.

A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, an accessory drive gearbox a first towershaft interconnecting the accessory drive gearbox and the first or second turbine shaft, and a multispeed transmission interconnecting the accessory drive gearbox and at least one accessory component.