| Patent application number | Description | Published |
|---|
| 20080289314 | METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES - A fuel delivery system for a gas turbine engine includes one or more subsets of combustors, and at least two fuel manifolds including a fuel manifold coupled to each combustor subset and configured to deliver fuel to only the subset of combustors during a predetermined gas turbine engine operating mode. A gas turbine engine assembly including a fuel delivery system and a method of operating a gas turbine engine is also described herein. | 11-27-2008 |
| 20090249794 | Systems and Methods for Augmenting Power Output of a Turbine During a Transient Event - Systems and methods for augmenting power output of a turbine during a transient event are provided. A cooling substance may be provided and at least a portion of the cooling substance may be directed to a compressor inlet of the turbine for a predefined time in order to augment power output of the turbine. | 10-08-2009 |
| 20100043387 | METHODS AND SYSTEMS FOR OPERATING GAS TURBINE ENGINES - Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation. | 02-25-2010 |
| 20100257837 | SYSTEMS INVOLVING HYBRID POWER PLANTS - A system comprises, a first heat recovery steam generator (HRSG) having an upstream intake duct portion, a first gas turbine engine connected to a first exhaust duct operative to output exhaust from the first gas turbine engine to the upstream intake duct portion of the first HRSG, and a second gas turbine engine connected to a second exhaust duct operative to output exhaust from the second gas turbine engine to the upstream intake duct portion of the first HRSG. | 10-14-2010 |
| 20100269481 | SYSTEMS AND METHODS FOR PROVIDING SURGE PROTECTION TO A TURBINE COMPONENT - Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component. | 10-28-2010 |
| 20100275609 | HYBRID WOBBE CONTROL DURING RAPID RESPONSE STARTUP - According to one aspect, the subject application involves a method of controlling a transition of a gas turbine. The method includes receiving a request of the gas turbine to drive an increased load. The increased load is greater than a load being driven by the gas turbine when the request is received. The method further includes determining that a temperature of a fuel to be ignited within a combustor of the gas turbine is less than a target temperature of the fuel to be introduced into the combustor for driving the increased load. Responsive to this determination, the method also includes controlling introduction of an additive into the combustor of the gas turbine when the temperature of the fuel is less than the target temperature to establish a suitable Wobbe Index of a fuel combination to promote a substantially continuous transition of the gas turbine to drive the increased load, wherein the fuel combination includes the fuel and the additive. | 11-04-2010 |
| 20100280731 | SYSTEMS AND METHODS FOR CONTROLLING FUEL FLOW TO A TURBINE COMPONENT - Systems and methods for controlling fuel flow to a turbine component are provided. One or more parameters associated with a fuel flow to a turbine component may be monitored. The fuel flow may be modeled based at least in part on the one or more monitored parameters. The fuel flow may be adjusted to a target flow based at least in part on the modeling of the fuel flow. | 11-04-2010 |
| 20100280733 | GAS TURBINE SHUTDOWN - A gas turbine includes a rotor, and a controller for controlling a shutdown of the gas turbine based on a target fuel-to-air ratio profile and/or controlling a rotor speed according to a target speed schedule to attain a specified duration for the shutdown. The controller controls the rotor speed by engaging the starting system to turn the rotor. | 11-04-2010 |
| 20100287944 | AVAILABILITY IMPROVEMENTS TO HEAVY FUEL FIRED GAS TURBINES - Maintenance operations for a hot gas path of a gas turbine require shutdown and cooled down conditions. When a gas turbine is shut down, thermal gradients in the rotor cause stresses that limit the life of the major components. As the cooling rate is increased to reduce the time, the stresses are increased, reducing rotor life. A method and equipment are provided to reduce the overall cycle time for the maintenance, yet mitigate the life penalties, thereby providing greater power production while maintaining (or potentially extending) rotor life. The method includes small hold times during the turbine shutdown and startup and slower turbine ramp rates during cooldown and startup, which more than offset thermal stresses from a forced cooldown, considerably shortening the overall operation. | 11-18-2010 |
| 20100296912 | Active Rotor Alignment Control System And Method - A rotating machine, such as a gas turbine, includes an active rotor alignment clearance control system wherein a plurality of actuators are circumferentially spaced around at least one rotor shaft bearing. The actuators are configured to eccentrically displace the bearing, and thus the rotor shaft, relative to stationary outer casing structure. A plurality of sensors are circumferentially spaced around a component of the casing structure, such as an inner shroud, and measure a parameter indicative of an eccentricity, such as blade tip clearance between the rotor blades and the structure, as the rotor rotates within the structure. A control system in communication with the sensors and actuators is configured to control the actuators to eccentrically displace the rotor by moving the shaft bearing to compensate for eccentricities detected between the rotor and casing structure. | 11-25-2010 |
