Patent application number | Description | Published |
20110005334 | TUNABLE FLUID FLOW CONTROL SYSTEM - A tunable fluid flow control system includes a fluidic oscillator having a movable boundary wall. A pressurized gas source is coupled to the movable boundary wall and configured to supply a stream of pressurized gas to the movable boundary wall to actuate the boundary wall. The boundary wall is actuatable to vary a cavity volume in the fluidic oscillator so as to control frequency of flow of a pulsating fluid generated by the fluidic oscillator. A portion of a fluid is bypassed the fluidic oscillator so as to control amplitude of flow of a pulsating fluid generated by the fluidic oscillator. | 01-13-2011 |
20120023952 | FUEL NOZZLE AND ASSEMBLY AND GAS TURBINE COMPRISING THE SAME - A nozzle for assemblies and gas turbines is provided. The nozzle exhibits destabilized flame holding characteristics, i.e., the nozzle is unable to stabilize flame up to an equivalence ratio of about 0.65. As a result, flame heat release is delayed resulting in lower peak flame temperatures and correspondingly lower NOx levels. Flame stabilization capability is retained for higher equivalence ratios to support operation of the combustor in other regions of the load range. | 02-02-2012 |
20130036745 | GAS TURBINE COMBUSTOR HAVING COUNTERFLOW INJECTION MECHANISM AND METHOD OF USE - In accordance with certain embodiments, a system and method of use includes a counterflow injection mechanism. The counterflow injection mechanism includes a fuel-air injection mechanism having fuel and air passages leading to fuel and air injection openings, wherein the fuel and air injection openings are disposed at an off-center position and a generally counterflow direction relative to a generally lengthwise flow axis of a gas turbine combustor. | 02-14-2013 |
20130160457 | SYSTEM AND METHOD FOR IMPROVED COMBUSTOR TEMPERATURE UNIFORMITY - A combustor and a method for reducing a temperature gradient of a combustor component are provided. The combustor includes a coating applied to at least a portion thereof with the coating serving to alter the emissivity of the at least a portion to which it is applied. The method includes applying a coating on at least one of a combustor liner and a flow sleeve, wherein the coating alters the emissivity exhibited where applied. | 06-27-2013 |
20140007584 | SYSTEM AND METHOD FOR REDUCING PRESSURE OSCILLATIONS WITHIN A GAS TURBINE ENGINE - In one embodiment, a system for reducing pressure oscillations within a gas turbine engine includes at least one fuel injector configured to inject fuel into a combustor. The system also includes a valve fluidly coupled to the at least one fuel injector. The system further includes a controller communicatively coupled to the valve. The controller is configured to cycle the valve between an open position and a closed position at a first frequency and a first duty cycle while a magnitude of pressure oscillations within the combustor is less than a threshold value, to cycle the valve between the open position and the closed position at a second frequency and a second duty cycle while the magnitude of the pressure oscillations within the combustor is greater than or equal to the threshold value, and to adjust the second frequency based on a measured frequency of the pressure oscillations. | 01-09-2014 |
Patent application number | Description | Published |
20100175379 | PRE-MIX CATALYTIC PARTIAL OXIDATION FUEL REFORMER FOR STAGED AND REHEAT GAS TURBINE SYSTEMS - A gas turbine system includes a fuel reformer comprising: a fuel inlet; an oxygen inlet; a pre-mixing zone configured to mix the fuel and the oxygen in a pre-mixing device to form a gaseous pre-mix; wherein the pre-mixing device comprises a flow conditioning device configured to pre-condition the fuel stream, wherein the flow conditioning device is disposed upstream of the oxygen inlet; a diffuser disposed downstream of the flow conditioning device; a catalytic partial oxidation zone disposed downstream of the diffuser, wherein the catalytic partial oxidation zone comprises a catalyst composition configured to react the fuel and the oxygen to generate a syngas. The generated syngas is then mixed with rest of the fuel to form a hydrogen-enriched fuel mixture, which is then sent to the combustion chamber of a gas turbine to reduce the NOx emission and extend the lean blow out limit. | 07-15-2010 |
20100175386 | PREMIXED PARTIAL OXIDATION SYNGAS GENERATION AND GAS TURBINE SYSTEM - A gas turbine system includes a fuel reformer system comprising a fuel inlet configured to receive a fuel slipstream; an oxygen inlet configured to introduce an oxygen slipstream; a preconditioning zone configured to pretreat the fuel slipstream; a mixing zone comprising a premixing device configured to facilitate mixing of the fuel slipstream and the oxygen slipstream to form a gaseous premix; a reaction zone configured to generate a syngas from the gaseous premix; a quench zone configured to mix a fuel stream into the syngas to form a hydrogen-enriched fuel mixture; and a gas turbine configured to receive the fuel mixture. | 07-15-2010 |
20100223933 | System for controlling combustion dynamics and method for operating the same - A method for controlling combustion dynamics is provided. The method includes providing a flow of partially premixed, premixed, or lean premixed fuel-air into a combustion chamber. The method also includes monitoring the combustion system for combustion dynamics. The method further includes actuating a system to control and abate combustion dynamics. | 09-09-2010 |
20120266602 | Aerodynamic Fuel Nozzle - The present application and the resultant patent provide a combustor for a turbine engine. The combustor may include a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly. The swirler assembly may include a number of stages with a number of fueled structures and a number of unfueled structures. | 10-25-2012 |
20130298563 | Secondary Combustion System - The present application provides a secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine. The secondary combustion system may include a manifold ring and a number of injectors extending from the manifold ring. Each of the injectors may include a number of jets in communication with the manifold ring. One or more of the jets may include an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle. | 11-14-2013 |
20140283524 | NOZZLE SYSTEM AND METHOD FOR STARTING AND OPERATING GAS TURBINES ON LOWBTU FUELS - A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided. | 09-25-2014 |
20140352321 | GAS TURBINE ENGINE SYSTEM AND AN ASSOCIATED METHOD THEREOF - A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine. | 12-04-2014 |