2488results about "Turbine/propulsion fuel control" patented technology

A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.

An electrical power generating system is driven by a multi-spool gas turbine engine including at least first and second spools. The first spool comprises a turbine and a compressor mounted on a first shaft; the second spool has at least a turbine mounted on a second shaft that is not mechanically coupled to the first shaft. A main generator is coupled with one of the spools, and an auxiliary generator/motor is also coupled with one of the spools. Speed control of each of the generators is employed for controlling operation of the engine. The auxiliary generator/motor can operate in either a generation mode to extract power from its spool or a motor mode to inject power into its spool.

A method and system of controlling a gas turbine engine is disclosed. The engine has sensors to detect one or more parameters and actuators adapted to respond to commands. The method includes receiving data from the sensors of the engine for one or more measured or sensed parameters, estimating a state of the engine by estimating one or more unmeasured or unsensed parameters using the data from the sensors and a predictive model of the engine, generating commands for the actuators based on the state using an optimization algorithm; and transmitting the commands to the engine. The system includes a state estimator adapted to estimate a state of the engine by estimating one or more unmeasured or unsensed parameters using data from the sensors of the engine for one or more measured or sensed parameters. The estimator includes a model of the engine. The system also includes a control module adapted to generate commands for the actuators based on the state. The control module includes an optimization algorithm for determining the commands.

In one embodiment, a combustor (28) for a gas turbine engine is provided comprising a primary combustion chamber (30) for combusting a first fuel to form a combustion flow stream (50) and a transition piece (32) located downstream from the primary combustion chamber (30). The transition piece (32) comprises a plurality of injectors (66) located around a circumference of the transition piece (32) for injecting a second fuel into the combustion flow stream (50). The injectors (66) are effective to create a radial temperature profile (74) at an exit (58) of the transition piece (32) having a reduced coefficient of variation relative to a radial temperature profile (64) at an inlet (54) of the transition piece (32). Methods for controlling the temperature profile of a secondary injection are also provided.

A system includes a radiation detector array directed toward a fluid flow into a compressor. The radiation detector array is configured to output a signal indicative of a two-dimensional temperature profile of the fluid flow. The system also includes a controller communicatively coupled to the radiation detector array. The controller is configured to detect a temperature variation across the fluid flow based on the signal, and to adjust a parameter of a temperature control device to compensate for the detected temperature variation.

Ambient air is compressed into a compressed ambient gas flow with a main air compressor. The compressed ambient gas flow having a compressed ambient gas flow rate is delivered to a turbine combustor and mixed with a fuel stream having a fuel stream flow rate and a portion of a recirculated gas flow to form a combustible mixture. The combustible mixture is burned and forms the recirculated gas flow that drives a turbine. The recirculated gas flow is recirculated from the turbine to the turbine compressor using a recirculation loop. At least one emission level is measured by at least a first emission sensor in the recirculated gas flow and at least a first control signal is generated. The fuel stream flow rate is adjusted based on the at least a first control signal to achieve substantially stoichiometric combustion.

A digital engine controller compatible with multiple variants of gas turbine engine is programmed to receive identification of a variant of gas turbine engine coupled to the digital controller and thereafter to automatically determine and adjust inputs to the engine, according to the received identification of engine variant, to meet user-specified output.

An engine power extraction control system controls the main propulsion engines and the electrical machines that are coupled thereto to supply an appropriate amount of aircraft thrust and electrical energy to the aircraft. The engines and electrical machines are also controlled so that the propulsion thrust that is generated is split between the various turbines in the main propulsion engines to maintain an adequate surge margin and to minimize residual thrust generation.

A power controller controls the turbine of a turbine powered generating system regardless of the load on the system to maximize the efficiency of the turbine and maintains the turbine at a substantially constant temperature during a system load change by using an energy storage device to provide power to the load while the turbine is changing speed to meet the new load demand.

A drive system for driving a load by a gas turbine. The gas turbine comprises a gas generator having a gas-generator rotor and comprising at least one gas-generator compressor and one high-pressure turbine driving the gas-generator compressor. The gas turbine further comprises a power turbine having a power-turbine rotor, which is torsionally independent of the gas-generator rotor. The load is connected to the power-turbine rotor. The system further comprises an electric motor/generator mechanically connected to the gas-generator rotor and electrically connected to an electric power grid. The electric motor/generator is adapted to function alternatively: as a generator for converting mechanical power from the gas turbine into electrical power; and as a motor for supplementing driving power to the load. A set of movable nozzle guide vanes is arranged at the inlet of the power turbine.

A combustor nozzle is provided. The combustor nozzle includes a first fuel system configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fuel system configured to introduce the syngas fuel, or a hydrocarbon fuel, or diluents, or combinations thereof into the combustion chamber to enable diffusion combustion within the combustion chamber.

In one embodiment, a system may include a gas turbine system. the gas turbine system includes a gas turbine, an after-treatment system that may receive exhaust gases from the gas turbine system, and a controller that may receive inputs and model operational behavior of an industrial plant based on the inputs. The industrial plant may include the gas turbine and the after-treatment system. The controller may also determine one or more operational parameter setpoints for the industrial plant, select the one or more operational parameter setpoints that reduce an output of a cost function, and apply the one or more operational parameter setpoints to control the industrial plant.

A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location.

A gas turbine control apparatus, etc. are provided by which combustion fluctuation, even if arising in plural frequency bands, can be effectively suppressed. If the combustion fluctuation arises in plural frequency bands, corresponding to a predetermined priority order, adjustment is done so that the combustion fluctuation of the frequency band of a high priority order is suppressed. If the gas turbine state changes after the adjustment, this is reflected on a data base 30. If no sufficient data is stored yet in the data base 30 for any the reason, such as immediately after installation of the gas turbine, correction is made using data of countermeasures based on data of another same type gas turbine contained in a basic data base 31 and data of countermeasures based on experiences of skilled adjusting operators contained in a knowledge data base 32. Also, in a stabilized operation, operation condition may be varied so that an optimal operation condition is automatically searched.

A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.

A power controller controls the turbine of a turbine powered generating system regardless of the load on said system to maximize the efficiency of the turbine and maintains the turbine at a substantially constant temperature during a system load change by using an energy storage device to provide power to the load while the turbine is changing speed to meet the new load demand.

Ambient air is compressed into a compressed ambient gas flow with a main air compressor. The compressed ambient gas flow having a compressed ambient gas flow rate is delivered to a turbine combustor and mixed with a fuel stream having a fuel stream flow rate and a portion of a recirculated low oxygen content gas flow to form a combustible mixture. The combustible mixture is burned and forms the recirculated low oxygen content gas flow that drives a turbine. A portion of the recirculated low oxygen content gas flow is recirculated from the turbine to the turbine compressor using a recirculation loop. The compressed ambient gas flow rate and the fuel stream flow rate are adjusted to achieve substantially stoichiometric combustion. An excess portion, if any, of the compressed ambient gas flow is vented. A portion of the recirculated low oxygen content gas flow is extracted using an extraction conduit.

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.

A power generation system and method includes a first gas turbine system comprising a first combustion chamber configured to combust a first fuel stream of primarily hydrogen that is substantially free of carbon-based fuels. The first gas turbine system also includes a first compressor configured to supply a first portion of compressed oxidant to the first combustion chamber and a first turbine configured to receive a first discharge from the first combustion chamber and generate a first exhaust and electrical energy. The power generation system further includes a second gas turbine system comprising a second combustion chamber configured to combust a second fuel stream to generate a second discharge. The first compressor of the first gas turbine system is configured to supply a second portion of compressed oxidant to the second combustion chamber. The second turbine system also includes a second turbine configured to receive the second discharge from the second combustion chamber to generate a second exhaust and electrical energy and a second compressor configured to receive the second discharge comprising carbon dioxide. The second compressor is also configured to discharge a recycle stream to the second combustion chamber and a split stream to a separator system adapted to recover carbon dioxide.