Patent application number | Description | Published |
20090053036 | Systems and Methods for Extending Gas Turbine Emissions Compliance - A gas turbine system for operation at low loads. The gas turbine system may include a number of inlet guide vanes, a compressor, a turbine, and an air movement system for maintaining an emission from the gas turbine system below a predetermined level. | 02-26-2009 |
20110072779 | SYSTEM AND METHOD USING LOW EMISSIONS GAS TURBINE CYCLE WITH PARTIAL AIR SEPARATION - A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone. | 03-31-2011 |
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 |
20120131923 | SYSTEM AND METHOD FOR PREMIXER WAKE AND VORTEX FILLING FOR ENHANCED FLAME-HOLDING RESISTANCE - A combustion system premixer includes one or more streamwise vortex generators configured to passively redirect surrounding high velocity air into at least one of wake and vortex regions within a combustion system fuel nozzle in response to air passing through the premixer. The streamwise vortex generators operate to minimize turbulent flow structures, thus improving air/fuel mixing, and enhancing resistance to flame-holding and flash-back within the premixer. | 05-31-2012 |
20130006581 | COMBUSTOR HEALTH AND PERFORMANCE MONITORING SYSTEM FOR GAS TURBINES USING COMBUSTION DYNAMICS - A system and method each utilize combustion dynamics data to monitor and assess gas turbine combustor health and performance. The system and method each employ a physics-based model to differentiate changes in the spectral features attributable to variations in the operating conditions from differences caused from changes in the hardware. | 01-03-2013 |
20130145771 | SYSTEM AND METHOD USING LOW EMISSIONS GAS TURBINE CYCLE WITH PARTIAL AIR SEPARATION - A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone. | 06-13-2013 |
20130167545 | COMBUSTOR SYSTEM FOR USE IN TURBINE ENGINES AND METHODS OF OPERATING A TURBINE ENGINE - A combustor system for use in a turbine engine is provided. The turbine engine includes turbine assembly that includes a fluid inlet, a fluid outlet, and a combustion gas path defined therebetween. The combustor system includes a first combustor assembly and a second combustor assembly. The first combustor assembly is coupled to the turbine assembly for channeling a first flow of combustion gases through the turbine assembly. The first combustor assembly is oriented adjacent to the turbine assembly inlet to channel the first flow of combustion gases to the turbine assembly through the turbine assembly inlet. The second combustor assembly is coupled to the turbine assembly along the combustion gas path for channeling a second flow of combustion gases through the turbine assembly. | 07-04-2013 |
20140157792 | SYSTEM AND METHOD FOR REMOVING HEAT FROM A TURBINE - A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum. | 06-12-2014 |