Patent application number | Description | Published |
20090293444 | GAS TURBINE INTEGRATED WITH FUEL CATALYTIC PARTIAL OXIDATION - A system and method for removing at least carbon from a fuel/air mixture prior to injection of the fuel/air mixture into a combustion system is disclosed. The system fully integrates the combined cycle power plant with carbon scrubbing of the fuel/air mixture to increase overall cycle efficiency while capturing carbon from the cycle. A portion of the compressed air source generated by the gas turbine compressor is provided to a premixer where it is mixed with a natural gas to form a fuel/air mixture. The fuel/air mixture passes through a catalytic partial oxidation (CPOX) reactor, which utilizes a precious metal to partially oxidize the hydrocarbons into carbon monoxide. The mixture passes through a shift reactor to complete generation of carbon dioxide and raise hydrogen yield of the fuel/air mixture. Carbon constituents are then removed from the mixture by a separator. | 12-03-2009 |
20140090389 | VARIABLE LENGTH COMBUSTOR DOME EXTENSION FOR IMPROVED OPERABILITY - The present invention discloses a novel apparatus and method for operating a gas turbine combustor having a structural configuration proximate a pilot region of the combustor which seeks to minimize the onset of thermo acoustic dynamics. The pilot region of the combustor includes a generally cylindrical extension having an outlet end with an irregular profile which incorporates asymmetries into the system so as to destroy any coherent structures. | 04-03-2014 |
20140090390 | FLAMESHEET COMBUSTOR DOME - The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture. | 04-03-2014 |
20140090396 | COMBUSTOR WITH RADIALLY STAGED PREMIXED PILOT FOR IMPROVED - The present invention discloses a novel apparatus and method for a mixing fuel and air in a gas turbine combustion system. The mixer helps to mix fuel and air while being able to selectively increase the fuel flow to a shear to a shear layer of a pilot flame in order to reduce polluting emissions. The mixer directs a flow of air radially inward into the combustion system and includes two sets of fuel injectors within each radially-oriented vane. A first plurality of fuel injectors operate independent of a second plurality of fuel injectors and the second plurality of fuel injectors are positioned to selectively modulate the fuel flow to the shear layer of the resulting pilot flame. | 04-03-2014 |
20140090400 | VARIABLE FLOW DIVIDER MECHANISM FOR A MULTI-STAGE COMBUSTOR - The present invention discloses a novel apparatus and way for altering the airflow to a gas turbine combustion system. The apparatus comprises a flow divider mechanism which splits the airflow surrounding a combustion liner into two distinct portions, one directed towards a pilot and one directed towards a main stage combustion. The flow divider mechanism is interchangeable so as to provide a way of altering airflow splits between stages of the combustion system. | 04-03-2014 |
20140200721 | Stabilizing A Gas Turbine Engine Via Incremental Tuning During Transients - Methods and systems are provided for automatically tuning a combustor of a gas turbine engine during a transient period, such as when a state of the gas turbine engine is changing. Once it has been determined whether the state of the gas turbine engine is changing, it is then determined whether a lean blowout is imminent, which is based conditions being monitored. A stability bias is applied to the system if either the state is changing or if lean blowout is imminent until the lean blowout is no longer determined to be imminent. The stability bias monitors operating conditions of the gas turbine engine and determines when one of the operating conditions has overcome a threshold value. Once a threshold value is overcome, a fuel flow fraction is adjusted by a predefined increment. The application of the stability bias is gradually terminated once it is determined that the lean blowout is no longer imminent. | 07-17-2014 |
20140208756 | System For Reducing Combustion Noise And Improving Cooling - A novel and improved system for cooling and reducing combustion noise in a gas turbine combustor is disclosed. The system includes a flow sleeve for a gas turbine combustor comprising a tubular portion and a conical portion, with a plurality of flow straighteners extending radially inward and between the tubular and conical portions and a plurality of rows of cooling holes extending about the flow sleeve, and an aft ring secured to the outlet end of the conical portion, where the aft ring includes an overlapping piston ring that is able to expand or contract in diameter. A combustion liner extends through the flow sleeve and engages an inlet of a transition duct while the piston ring of the flow sleeve also engages the transition duct to form a seal. | 07-31-2014 |
20140277789 | DYNAMIC TUNING OF A GAS TURBINE ENGINE TO DETECT AND PREVENT LEAN BLOWOUT - A method for tuning a combustor of a gas turbine engine based on one or more monitored operating conditions is provided. One or more operating conditions of the gas turbine engine are monitored. The monitored operating conditions may include, for example, a low frequency tone, a high frequency tone, and a ratio of the low frequency tone to the high frequency tone. It is determined whether the ratio of the low frequency tone to the high frequency tone is within a first predefined normal range. If the ratio of the low frequency tone to the high frequency tone is within the first predefined normal range, a determination is made not to tune the gas turbine engine. But, if the ratio of the low frequency tone to the high frequency tone is not within the first predefined normal range, a determination is made to tune the gas turbine engine. | 09-18-2014 |
20140277790 | ENSURING NON-EXCESSIVE VARIATION OF GRADIENTS IN AUTO-TUNING A GAS TURBINE ENGINE - Methods are provided for ensuring non-excessive variation of a gradient of an applied split bias versus firing temperature of a gas turbine engine. It is determined that an incremental split bias step is to be taken, and a current firing temperature of the gas turbine engine is identified on a graph. A first difference between a split schedule and an applied schedule gradient is calculated using lower firing temperatures than the current firing temperature, and a second difference is calculated using higher firing temperatures. If the first difference exceeds a predetermined limit, the incremental split bias step is not allowed at a lower firing temperature, and similarly, if the second difference exceeds a predetermined limit, the incremental split bias step is not allowed at a higher firing temperature. | 09-18-2014 |
20150075172 | FLAMESHEET COMBUSTOR CONTOURED LINER - The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wall thickness and a tapering of the thermal barrier coating to reduce the bluff body effect at the combustion liner inlet end. | 03-19-2015 |