| Patent application number | Description | Published |
|---|
| 20080282667 | METHOD AND APPARATUS TO FACILITATE COOLING TURBINE ENGINES - A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly. | 11-20-2008 |
| 20090056336 | Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine - A burner for use in a combustion system of an industrial gas turbine. The burner includes a fuel/air premixer including a splitter vane defining a first, radially inner passage and a second, radially outer passage, the first and second passages each having air flow turning vane portions which impart swirl to the combustion air passing through the premixer. The vane portions in each passage are commonly configured to impart a same swirl direction in each passage. A plurality of splitter vanes may be provided to define three or more annular passages in the premixer. | 03-05-2009 |
| 20090064682 | METHOD AND SYSTEM TO DETERMINE COMPOSITION OF FUEL ENTERING COMBUSTOR - Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (A | 03-12-2009 |
| 20100011770 | Gas Turbine Premixer with Cratered Fuel Injection Sites - A premixer for a gas turbine combustor includes a swirler including a plurality of turning vanes that impart swirl velocity to airflow through the premixer, and at least one fuel injection site enabling fuel to mix with the airflow in the premixer. The fuel injection site terminates in a cratered hole. The cratered hole increases mixing efficiency and increases flashback/flameholding resistance. | 01-21-2010 |
| 20100011851 | METHOD AND SYSTEM TO DETERMINE COMPOSITION OF FUEL ENTERING COMBUSTOR - Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (A | 01-21-2010 |
| 20100058766 | Segmented Combustor Cap - A combustor cap is cooperable with an impingement plate in a turbine fuel nozzle and includes a plurality of cap segments independently securable to the impingement plate. The plurality of cap segments are radially and tangentially movable relative to the impingement plate. | 03-11-2010 |
| 20100319353 | Multiple Fuel Circuits for Syngas/NG DLN in a Premixed Nozzle - A fuel/air premixer for use in a burner in a combustion system of an industrial gas turbine includes an air inlet, a fixed nozzle geometry, and an annular mixing passage. The fuel/air premixer mixes fuel and air in the annular mixing passage for injection into a combustor reaction zone. A plurality of fuel sources are connected with the fixed nozzle geometry, and each of the fuel sources is cooperable with the fixed nozzle geometry to effect multiple fuel flow variations including variations in fuel type, fuel blend, volumetric flow, and pressure ratios. | 12-23-2010 |
| 20110072824 | APPARTUS AND METHOD FOR A GAS TURBINE NOZZLE - A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downstream of the inlet, and the circumference at the first point downstream of the inlet is less than the circumference at a second point downstream of the first point. A method for supplying a fuel through a nozzle directs a first airflow along a first path and a second airflow along a second path separate from the first path. The method further includes injecting the fuel into at least one of the first path or the second path and accelerating at least one of the first airflow or the second airflow. | 03-31-2011 |
| 20110094235 | COMBUSTOR HEADEND GUIDE VANES TO REDUCE FLOW MALDISTRIBUTION INTO MULTI-NOZZLE ARRANGEMENT - A combustor for a gas turbine includes a plurality of nozzles provided in an array; a baffle plate configured to provide a desired air flow distribution to the array of nozzles; and a casing comprising a plurality of holes in an outer surface. The casing extends from a headend of the combustor to the baffle plate. A method of distributing an air flow in a combustor of a gas turbine includes providing an air flow to the outer surface of the casing; directing the air flow around the baffle plate; and distributing the air flow through the baffle plate to the array of nozzles. | 04-28-2011 |
