| Patent application number | Description | Published |
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| 20090068007 | Mounting System for Impingement Cooling Manifold - A manifold mounting system for mounting an impingement cooling manifold to a casing of a turbine including a mounting pin affixed to a shroud pin of the turbine wherein the mounting pin extends through the impingement cooling manifold wherein the mounting pin comprises a securing device operable for securing the mounting pin to the impingement cooling manifold, and a leveling support leg affixed to the impingement cooling manifold wherein the mounting pin, securing device, and leveling support leg are operable for adjusting the gap distance between the impingement cooling manifold and the casing of the turbine. | 03-12-2009 |
| 20090320440 | WET COMPRESSION SYSTEMS IN TURBINE ENGINES - A wet compression system for a gas turbine compressor having a bellmouth that includes a plurality of nozzles for spraying a fine spray of liquid disposed within an aft section of the bellmouth. The aft section of the bellmouth may include a downstream half of the bellmouth, and the nozzles may be connected to a plurality of struts, each of the struts comprising a structural member that connects an inner diameter casing of the bellmouth to an outer diameter casing of the bellmouth. In some embodiments, the nozzles may be positioned on a leading edge of at least one of the struts and a minimum clearance of at least approximately 0.2 m may be maintained between the nozzles and the inner diameter casing of the bellmouth. In other embodiments, the nozzles may be positioned on a trailing edge of at least one of the struts and a minimum clearance of at least approximately 0.05 m may be maintained between the nozzles and the inner diameter casing of the bellmouth. | 12-31-2009 |
| 20100034635 | Predictive Model Based Control System for Heavy Duty Gas Turbines - A system for controlling the clearance between a turbine blade and the turbine casing that includes an impingement cooling manifold attached to a turbine casing, a temperature sensing device for determining the temperature of the turbine casing, a blower, a control system logic for determining the setting temperature of the casing, and a controller for controlling the blower, wherein the blower forces air onto the impingement cooling manifold to cool the casing towards the setting temperature and control the clearance. | 02-11-2010 |
| 20110056212 | SYSTEM AND METHOD FOR APPLYING ENERGY EXTERNALLY FOR FUEL GAS FOR DEW POINT HEATING IN GAS TURBINE POWER PLANT - In a gas turbine power plant, pressurized fuel gas undergoes pressure reduction and gas expansion before being provided to a gas turbine. Condensations, which can damage the turbine, can form as the fuel gas cools when the fuel gas undergoes the pressure reduction and expansion. An electric startup heater is used to superheat the fuel gas to substantially prevent the condensations from forming. The electric startup heater includes band heaters wrapped externally to a fuel gas pipe to heat the fuel gas from outside in. Compared to conventional heaters which provide superheating through internal heating elements, the electric startup heater reduces costs and provides increased safety, flexibility, operational efficiency and ability to adapt to varying fuel gas characteristics. | 03-10-2011 |
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| 20100162708 | METHODS, APPARATUS AND/OR SYSTEMS RELATING TO FUEL DELIVERY SYSTEMS FOR INDUSTRIAL MACHINERY - An assembly for delivering a supply of liquid fuel and a supply of purge air to a gas turbine engine, the assembly comprising: an annular dual-flow check valve for controlling the flow through concentric channels that have a common outlet, the annular dual-flow check valve comprising: an outer body and an inner body that define the concentric channels, which include an outer channel and an inner channel formed therein; a spring activated annular poppet that resides in the outer channel and has a range of motion in the axial direction; and an opening through the inner body that connects the outer channel to the inner channel; wherein the axial movement of the annular poppet is regulated by the pressure of the flow upstream of the annular poppet in the outer channel; and the axial range of motion of the annular poppet includes at least two axial positions. | 07-01-2010 |
| 20100163120 | METHODS, APPARATUS AND/OR SYSTEMS RELATING TO CONTROLLING FLOW THROUGH CONCENTRIC PASSAGES - An annular dual-flow check valve for controlling the flow through concentric channels that have a common outlet, comprising: an outer body and an inner body that define the concentric channels, which include an outer channel and an inner channel formed therein; a spring activated annular poppet that resides in the outer channel and has a range of motion in the axial direction; and an opening through the inner body that connects the outer channel to the inner channel; wherein: the axial movement of the annular poppet is regulated by the pressure of the flow upstream of the annular poppet in the outer channel; and the axial range of motion of the annular poppet includes at least two axial positions: a closed position where the annular poppet substantially covers the opening and a open position where at least a portion of the opening is not covered by the annular poppet. | 07-01-2010 |
| 20100307157 | METHODS RELATING TO TURBINE ENGINE CONTROL AND OPERATION - A method of controlling a combustion turbine engine, wherein the engine includes: a fuel line including a heat exchange portion; a heating value meter; a cold leg bypass comprising an alternate fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction, the fuel mixing junction being positioned such that a length of fuel line between it and the inlet to the combustor is short; and valves for controlling the amount of fuel being directed through the heat exchange portion; the method comprising: measuring the heating value of the fuel; determining a target fuel temperature range based on the heating value and a target Modified Wobbe Index range; and controlling the fuel that bypasses the heat exchange portion such that the temperature of the fuel is within the target temperature range. | 12-09-2010 |
| 20100307158 | SYSTEMS RELATING TO TURBINE ENGINE CONTROL AND OPERATION - A combustion turbine engine that includes: a compressor; a combustor that receives fuel from a fuel line; a turbine; a heat exchange portion comprising a portion of the fuel line in heat transfer relationship with a heat source for heating the fuel; a rapid heating value meter disposed to test the heating value of the fuel that is configured to provide heating value test results within approximately 1 minute; a cold leg bypass comprising a fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction; and valves for controlling the fuel being directed through the heat exchange portion and the fuel being direct through the cold leg bypass; wherein the length of fuel line between the fuel mixing junction and the combustor is less than 20 meters. | 12-09-2010 |
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| 20090053035 | APPARATUS AND METHOD FOR REDUCING ECCENTRICITY AND OUT-OF-ROUNDNESS IN TURBINES - A turbine includes: a plurality of turbine blades arranged within a casing, the arrangement including a clearance between tips of the blades and the casing; a plurality of manifolds disposed proximate to the casing opposite the clearance, wherein each of the manifolds includes a plurality of impingement holes in the surface thereof; a source of clearance information; and a source of cooling air for supplying cooling air through a plurality of flow control devices to selected ones of the manifolds according to the clearance information. A system and a method are also provided. | 02-26-2009 |
| 20100024429 | APPARATUS, SYSTEM AND METHOD FOR HEATING FUEL GAS USING GAS TURBINE EXHAUST - An apparatus, a system and a method by which fuel gas to drive a heat source is heated are provided. The apparatus includes a first gas passage by which at least a portion of the fuel gas is transported from an inlet to an outlet, the outlet being fluidly coupled to the heat source, a plurality of heat pipes in thermal communication, at respective first ends thereof, with the portion of the fuel gas transported by the first gas passage, and a heating element, fluidly coupled to the heat source to receive exhaust of the heat source, through which respective second ends of the heat pipes extend to be in position to be heated by the exhaust. | 02-04-2010 |
| 20100040482 | EJECTORS WITH SEPARABLY SECURED NOZZLES, ADJUSTABLE SIZE NOZZLES, OR ADJUSTABLE SIZE MIXING TUBES - An ejector comprising a motive inlet, a motive nozzle separably secured to the motive inlet, a suction chamber about the motive nozzle, a suction fluid inlet to the suction chamber, a mixing tube in fluid communication with the suction chamber and the motive nozzle, a diffuser in fluid communication with the mixing tube and distal the suction chamber and the motive nozzle, and an outlet from the diffuser is provided. A nozzle comprising at least two concentric arc nozzle portions is also provided. An ejector comprising a mixing tube including a flexible layer adapted to compress or stretch, thereby allowing a mixing tube diameter to change is further provided. | 02-18-2010 |
| 20100118914 | EXTERNALLY ADJUSTABLE IMPINGEMENT COOLING MANIFOLD MOUNT AND THERMOCOUPLE HOUSING - A mount includes a mounting bolt attached to a casing; an internal bushing that engages the casing at a distal end of the internal bushing; and an external bushing that engages a manifold and engages the internal bushing. The internal bushing is adjustable with respect to the external bushing thereby allowing the manifold to be adjustable with respect to the casing. | 05-13-2010 |
| 20100170265 | Variable Geometry Ejector - An ejector for a turbine engine is described herein. The ejector may include a variable geometry motive nozzle and a variable geometry mixing tube positioned downstream of the variable geometry motive nozzle. | 07-08-2010 |
