| Patent application number | Description | Published |
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| 20090183511 | SWOZZLE DESIGN FOR GAS TURBINE COMBUSTOR - Disclosed is a fuel nozzle for a combustor of a gas turbine engine includes a nozzle inlet, a combustion area and a swirler disposed between the nozzle inlet and combustion area. The swirler includes a plurality of swirler vanes, each swirler vane capable of creating a pressure difference in fluid flow through the swirler between a pressure side and suction side of the swirler vane. The swirler further includes at least one through airflow hole located in at least one swirler vane of the plurality of swirler vanes. The at least one through airflow hole is capable of utilizing the pressure difference between the pressure side and suction side to promote fluid flow through the at least one airflow hole. Also disclosed is a method for operating a combustor. | 07-23-2009 |
| 20090241505 | RE-HEAT COMBUSTOR FOR A GAS TURBINE ENGINE - A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor. | 10-01-2009 |
| 20100170266 | METHOD AND APPARATUS FOR CONTROLLING A HEATING VALUE OF A LOW ENERGY FUEL - In an embodiment, a method includes determining a first heating value of a low BTU fuel, determining a target fuel quality level based on a state of a turbine system, controlling a second heating value of a high BTU fuel, and injecting the high BTU fuel into the low BTU fuel to achieve the target fuel quality level. | 07-08-2010 |
| 20100199675 | FUEL INJECTION FOR GAS TURBINE COMBUSTORS - An injector includes a surface and an injector hole formed in the surface. The injector also includes a groove formed in the surface, the groove surrounding the injector hole. | 08-12-2010 |
| 20110056181 | CONTROL SYSTEMS AND METHOD FOR CONTROLLING A LOAD POINT OF A GAS TURBINE ENGINE - Control systems and a method for controlling a load point of a gas turbine engine are provided. A control system includes a controller that receives a temperature signal and a pressure signal associated with exhaust gases from the gas turbine engine. The controller is further configured to generate the fuel control signal. The controller is further configured to generate an actuator control signal such that flow restriction member is moved from the first operational position to the second operational position to restrict the flow path such that the exhaust gases have a temperature level within a desired turndown temperature range, the pressure level in the exhaust gases is less than a threshold pressure level, and the load point of the gas turbine engine is adjusted to toward a target load point. | 03-10-2011 |
| Patent application number | Description | Published |
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| 20100229556 | TURBINE FUEL NOZZLE HAVING HEAT CONTROL - In one embodiment, a system includes a turbine engine fuel nozzle having an air path, a fuel path, and a surface along the air path. The fuel path may be directed toward the surface. The turbine engine fuel nozzle also may include a heating element configured to heat the surface. | 09-16-2010 |
| 20100288474 | METHOD AND SYSTEM FOR SEALING AN ANNULUS - A method and systems for a purged seal for an annular space are provided. The purged seal includes a first baffle element that extends from an inner surface of the annular space into the annular space at an oblique angle and a second baffle element that extends from an outer surface of the annular space above the first baffle element in a direction opposite gravity flow into the annular space wherein the second baffle element extends at an oblique angle. The system also includes a third baffle element that extends from the inner surface above the first baffle element in a direction of gravity flow into the annular space wherein the third baffle element extends into the annular space at an oblique angle with respect to the inner surface and wherein a distal end of the third baffle element is positioned proximate a distal end of the second baffle element. | 11-18-2010 |
| 20100325956 | COOLING CHAMBER ASSEMBLY FOR A GASIFIER - A gasifier includes a combustion chamber in which a combustible fuel is burned to produce a syngas and a particulated solid residue. A cooling chamber having a liquid coolant is disposed downstream of the combustion chamber. A dip tube is disposed coupling the combustion chamber to the cooling chamber. The syngas is directed from the combustion chamber to the cooling chamber via the dip tube to contact the liquid coolant and produce a cooled syngas. An asymmetric or symmetric liquid separator is disposed proximate to an exit path of the cooling chamber and configured to remove entrained liquid content from the cooled syngas directed through the annular passage to the exit path. | 12-30-2010 |
| 20100325957 | GASIFICATION SYSTEM FLOW DAMPING - In one embodiment, a gasification system component, such as a quench unit or scrubber may retain of pool of a cooling fluid for cooling another fluid. The gasification system component includes a flow damping mechanism designed to dampen flow of the cooling fluid, the other fluid, or both, within the gasification system component. The flow damping mechanism may be disposed in an inner chamber formed between a dip tube and a draft tube or disposed in an outer chamber formed between the walls of the gasification system component and the draft tube. The flow damping mechanism also may be disposed between the inner chamber and the outer chamber. | 12-30-2010 |
| 20110120010 | GASIFICATION QUENCH CHAMBER AND SCRUBBER ASSEMBLY - A gasification quench chamber is disclosed. The gasification quench chamber includes a reservoir that contains liquid coolant in its lower portion and an exit for the cooled syngas in its upper portion; a dip tube that is configured to introduce a syngas mixture to contact the liquid coolant which produces the cooled syngas; a cooling device configured to further cool the cooled syngas in its upper portion; and a stability device in the lower portion that is configured to mitigate coolant level fluctuation and sloshing. In an embodiment of the quench chamber, the cooling device includes a heat exchanger pipe. A quench chamber and scrubber assembly is also disclosed. | 05-26-2011 |
