386results about "Combustion control" patented technology

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.

The present invention relates to methods and systems for controlling a combustion reaction and the products thereof. One embodiment includes a combustion control system having an oxygenation stream substantially comprising oxygen and CO₂ and having an oxygen to CO₂ ratio, then mixing the oxygenation stream with a combustion fuel stream and combusting in a combustor to generate a combustion products stream having a temperature and a composition detected by a temperature sensor and an oxygen analyzer, respectively, the data from which are used to control the flow and composition of the oxygenation and combustion fuel streams. The system may also include a gas turbine with an expander and having a load and a load controller in a feedback arrangement.

According to one aspect, a method of controlling a multi-combustor catalytic combustion system is provided for determining a characteristic of a fuel-air mixture downstream of a preburner associated with a catalytic combustor and adjusting the fuel flow to the preburner based on the characteristic. The characteristic may include, for example, a measurement of the preburner or catalyst outlet temperature or a determination of the position of the homogeneous combustion wave in the burnout zone of the combustor.

A recuperated gas turbine engine system and associated method employing catalytic combustion, wherein the combustor inlet temperature can be controlled to remain above the minimum required catalyst operating temperature at a wide range of operating conditions from full-load to part-load and from hot-day to cold-day conditions. The fuel is passed through the compressor along with the air and a portion of the exhaust gases from the turbine. The recirculated exhaust gas flow rate is controlled to control combustor inlet temperature.

Tuning processes implemented by an auto-tune controller are provided for measuring and adjusting the combustion dynamics and the emission composition of a gas turbine (GT) engine via a tuning process. Initially, the tuning process includes monitoring parameters, such as combustion dynamics and emission composition. Upon determining that one or more of the monitored parameters exceed a critical value, these “out-of-tune” parameters are compared to a scanning order table. Upon comparison, the first out-of-tune parameter that is matched within the scanning order table is addressed. The first out-of-tune parameter is then plotted as overlaid slopes on respective graphs, where the graph represents a fuel-flow split. Typically, the slopes are plotted as a particular out-of-tune parameter against a particular fuel-flow split. The slopes for each graph are considered together by taking into account the combined impact on each out-of-tune parameter when a fuel-flow split is selected for adjustment.

In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (λ) of the operative burners (9) of the second combustor (15) is kept below a maximum air ratio (λ_max) at part load In order to reduce the maximum air ratio (λ), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes (14) before engaging the second combustor (15). For engaging the second combustor, the row of variable compressor inlet guide vanes (14) is quickly closed and fuel is introduced in a synchronized manner into the burner (9) of the second combustor (15). A further modification is the deactivating of individual burners (9) at part load.

A dual fuel vent free gas heater having at least one gas burner with a plurality of gas outlet ports in an upper surface thereof. The gas outlet ports are in flow communication with at least one pilot flame burner. An adjustable fuel injector or at least two fuel injectors feed fuel to the burner providing for introduction of more than one fuel to the burner. Optionally, an oxygen detection system, manual fuel selection control valve, and/or temperature shut off control system may be incorporated into the dual fuel vent free heater.

A method for operating a gas turbine engine including a combustor assembly is provided. The method includes channeling a first fluid through a first nozzle into the combustor assembly, igniting the first fluid within the combustor assembly downstream from the first nozzle, channeling a second fluid through a second nozzle into the combustion assembly when the gas turbine engine attains a speed of greater than 85% of rated speed, igniting the second fluid within the combustor assembly downstream from the second nozzle, terminating a flow of the first fluid through the first nozzle, and channeling the second fluid to the first nozzle.

An intelligently controlled catalytic converter automatically monitors various operating parameters, such as water jacket temperature, catalytic input temperature, catalytic converter output temperature, oxygen level, ambient temperature, ambient humidity and/or ambient barometric air pressure, of a biofuel-fired device and automatically controls dampers, blowers and electric heaters in the device.

A multiple gas pilot burner assembly for a household heating appliance. The pilot burner includes an injector having a first conduit for receiving a flow of a first combustible fluid, a second conduit for receiving a flow of a second combustible fluid and a third conduit connected to and in fluid communication with the first and second conduits which is configured to receive the flow of the first combustible fluid from the first conduit or the flow of the second combustible fluid from the second conduit. A single nozzle at the outlet of the third conduit is provided for supplying a pilot flame. The assembly also includes a single flame igniter positioned to cause an ignition of the pilot flame at the nozzle and also a single thermocouple positioned to be heated by the pilot flame and to generate an electrical current when heated.

A temperature control system for safely controlling the rate of flow of a flammable fluid at generally constant pressure is disclosed. The system may include a flow control apparatus that is free of a regulator mechanism, for affecting the flow of the fluid. The flow control apparatus may be operable between at least a first flow rate and a second flow rate, and may have at least one upstream opening and at least one downstream opening. The system may also include a first burner in fluid communication with the downstream opening of the flow control apparatus and a conduit in fluid communication at one end thereof with the upstream opening of the flow control apparatus, and configured at the other end thereof for connection to a fuel supply. A thermocouple may be located in the vicinity of the burner or an appliance used in conjunction with the burner. The thermocouple converts a sensed thermal state into an electrical signal. An electronic controller, in communication with the flow control apparatus, for activating the flow control apparatus to one of said first and second flow rates, and being in communication with the thermocouple for receiving the electrical signal from the thermocouple is also provided. An interface connected to the controller for manually inputting a desired temperature may be included, wherein the controller is operable to automatically cycle the flow control apparatus between the first and second flow rates until the temperature sensed by the thermocouple is similar to the desired temperature.

A gas turbine combustion system having: a plurality of combustion chambers; a plurality of fuel nozzles for each of combustion chamber; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers; each of the manifolds having fuel trim control valves for the fuel nozzles, wherein the fuel trim control valves are mounted on the multiple manifolds for metering the fuel to the fuel nozzles in the combustion chambers, and a trim valve controller automatically actuates one or more of the fuel trim valves to adjust fuel to the fuel nozzles based on gas turbine operating conditions.

A dual fuel heating source can have a fuel selector valve for selecting between a first fuel and a second fuel different from the first. The dual fuel heating source may selectively have a regulator unit, and an outlet valve. The regulator unit can be configured to regulate the pressure of two different fuels. The outlet valve can be connected to the fuel selector valve such that selecting a fuel can determine the path fuel will flow through the outlet valve and also out of the heating source.