Class / Patent application number | Description | Number of patent applications / Date published |
060390230 | With variable oxidizer control | 25 |
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 |
20090100820 | Oxidizing Fuel - A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system. The oxidation of the fuel is initiated by raising the temperature of the mixture to or above an auto-ignition temperature of the fuel. In some cases, the reaction chamber may be provided without a fuel oxidation catalyst material. | 04-23-2009 |
20090205309 | Method for controlling the combustion in a combustion chamber and combustion chamber device - There is provided a method for controlling the combustion in a combustion chamber with a combustion space, wherein fuel in fluid form and oxidiser in fluid form are blown into the combustion space, in which at least one control jet is generated in the combustion space, which influences the flow of fuel and/or oxidiser in the combustion space, wherein the mass flow component of the at least one control jet lies between 1% and 7% of the total mass flow, the at least one control jet is generated such that it varies over time, the at least one control jet is generated by being blown in or extracted through one or more ports in a combustion chamber wall, which coincide with one or more ports for blowing in and/or extracting fuel and/or oxidiser, and the at least one control jet is generated so that a degree of swirl of the fuel flow and/or oxidiser flow is reduced by means thereof. | 08-20-2009 |
20090260340 | Combustor of a Turbine, a Method of Retro-Fitting a Combustor of a Turbine and a Method of Building a Combustor of a Turbine - A combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine are each provided. The combustor includes a combustion chamber along which a dilution breach is defined, a casing perimetrically surrounding the combustion chamber so as to define an airflow between the casing and the combustion chamber, the airflow being configured to supply dilution air to the combustion chamber via the dilution breach, and an easy to adjust dilution airflow tuning part disposed on the casing and in communication with the airflow. The dilution airflow tuning part is configured to increase and/or decrease an available amount of the dilution air to be supplied to the combustion chamber. | 10-22-2009 |
20090293446 | Method for low NOx combustion with low pressure drop - The present invention provides a method for the reduction of pressure drop in low NOx combustion of fuel and air, maximizing energy efficiency. A supply of fuel and a supply of air form a fuel rich mixture that is reacted to produce partial reaction products and heat. A portion of the heat is transferred to a second supply of air. The partial reaction products are mixed with heated air and with a third supply of air to form a fuel lean admixture that is passed to a combustion zone for low NOx combustion. | 12-03-2009 |
20100018181 | CENTERBODY CAP FOR A TURBOMACHINE COMBUSTOR AND METHOD - A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage defined by a gap between the wall of the centerbody and the external turbulator. The external turbulator member includes a step positioned at the second end of the centerbody. The step defines a radial distance about the second end of the centerbody. The external turbulator member is formed having a step-to-gap ratio relative to the centerbody in a range of about 0.8 to about 1.2. | 01-28-2010 |
20110072779 | SYSTEM AND METHOD USING LOW EMISSIONS GAS TURBINE CYCLE WITH PARTIAL AIR SEPARATION - A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone. | 03-31-2011 |
20110203250 | COMBUSTION DEVICE FOR A GAS TURBINE - A combustion device for a gas turbine includes an interior portion, an inner wall having a plurality of first passages and an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into a third passage. An intermediate layer is disposed between the inner wall and the outer wall and defines a plurality of chambers, each chamber forming a Helmholtz damper and being connected to the interior portion by at least one of the plurality of first passages and being connected to at least one of the plurality of second passages by at least one of the plurality of third passages | 08-25-2011 |
20110225947 | SYSTEM AND METHODS FOR ALTERING AIR FLOW IN A COMBUSTOR - A combustor assembly of a turbine engine is provided with a mechanical air regulation unit which selectively varies the amount of air being delivered into a combustion zone of the combustor based upon a pressure of a fuel being supplied to the combustor. A first type of air regulation unit would act to increase the amount of air entering the combustion zone when greater amounts of a high heat value fuel are being delivered to the fuel nozzles of the combustor. A second type of air regulation unit could act to decrease the amount of air entering the combustion zone when greater amounts of a low heat value fuel are being delivered into the combustor through fuel nozzles. | 09-22-2011 |
20110252763 | Turbine Inlet Heat Transfer System - A heat transfer system is provided for a filter house. The filter house is configured to channel air into a turbine engine. The heat transfer system includes at least one of an expansion device and a compressor, a circuit coupled to at least one of the expansion device and the compressor, at least one sensor that detects a parameter of at least one of air channeled through a filter house and the fluid channeled through the circuit, and a controller coupled to the at least one sensor. The controller is configured to selectively control flow of fluid through the circuit to change the parameter of air channeled through the filter house based on the parameter detected by the sensor. | 10-20-2011 |
20110265443 | SYSTEM AND METHOD FOR ADJUSTING COMPRESSOR INLET FLUID TEMPERATURE - A system includes a radiation detector array directed toward a fluid flow into a compressor. The radiation detector array is configured to output a signal indicative of a two-dimensional temperature profile of the fluid flow. The system also includes a controller communicatively coupled to the radiation detector array. The controller is configured to detect a temperature variation across the fluid flow based on the signal, and to adjust a parameter of a temperature control device to compensate for the detected temperature variation. | 11-03-2011 |
20130025253 | REDUCTION OF CO AND O2 EMISSIONS IN OXYFUEL HYDROCARBON COMBUSTION SYSTEMS USING OH RADICAL FORMATION WITH HYDROGEN FUEL STAGING AND DILUENT ADDITION - A method for reducing the amount of carbon monoxide and oxygen emissions in an oxyfuel hydrocarbon combustion system, comprising the steps of feeding defined amounts of hydrocarbon fuel and an oxidizer (e.g., air) to one or more combustors in the engine and igniting the mixture to form a first combustor exhaust stream; determining the amount of carbon monoxide present at the head end of a combustor in the initial combustor exhaust stream; identifying one or more target locations within the combustor at a point downstream from the first exhaust stream for injecting free hydrogen and a supplemental oxidizer; injecting hydrogen and the supplemental oxidizer into the combustor at specified downstream locations based on the amount of detected carbon monoxide; and injecting a diluent (e.g., CO | 01-31-2013 |
20130145741 | TWO-STAGE COMBUSTOR FOR GAS TURBINE ENGINE - A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. A first and a second combustion stages are defined between the liners, each said combustion stage having a plurality of fuel injection bores distributed in a liner wall defining the respective stage. Valves at the fuel injection bores of one of the combustion stages, the valves each defining an air passage from an exterior to an interior of the combustion stage, the valves each having an actuatable member for adjusting a size of a respective air passage for air staging the combustor. | 06-13-2013 |
20130160423 | CAN ANNULAR COMBUSTION ARRANGEMENT WITH FLOW TRIPPING DEVICE - A can annular combustion arrangement ( | 06-27-2013 |
20130232939 | GRADUAL OXIDATION WITH ADIABATIC TEMPERATURE ABOVE FLAMEOUT TEMPERATURE - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20130232940 | GRADUAL OXIDATION BELOW FLAMEOUT TEMPERATURE - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20130283762 | ROTARY VANE ACTUATOR OPERATED AIR VALVES - Rotary vane actuator operated air valves associated with gas turbine engines are disclosed. An example gas turbine engine may include a fan, a compressor, a combustor, and a turbine in a serial flow relationship; a supply pipe arranged to convey compressed air from one or more of the fan and the compressor; a valve operatively disposed in the supply pipe, the valve including a rotatable valve member arranged to modulate flow of the compressed air through the supply pipe based upon an angular position of the valve member, the valve member being rotatable between an open position and a shut position; and/or a hydraulically operated rotary vane actuator operatively coupled to rotate the valve member. | 10-31-2013 |
20130312385 | GAS TURBINE SYSTEM HAVING A PLASMA ACTUATOR FLOW CONTROL ARRANGEMENT - A gas turbine system having a plasma actuator flow control arrangement including a compressor section for compressing an airstream, wherein the compressor section includes at least one inlet guide vane for controlling the airstream proximate an inlet portion of the compressor section. Also included is a turbine inlet assembly for ingesting the airstream to be routed to the compressor section. Further included is a plasma actuator disposed within at least one of the inlet portion of the compressor section and the turbine inlet assembly for controllably producing an electric field to manipulate a portion of the airstream. | 11-28-2013 |
20140237987 | GAS TURBINE ENGINE VARIABLE GEOMETRY FLOW COMPONENT - A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle. | 08-28-2014 |
20140290208 | AIRCRAFT PROPULSION ARCHITECTURE INTEGRATING AN ENERGY RECOVERY SYSTEM - A drive system of at least one rotor of an aircraft via electrical energy in addition to or as a replacement of a mechanical system. The electrical energy is provided at least in part by at least one device for recovering thermal energy from hot gases of an internal combustion engine of the aircraft. | 10-02-2014 |
20140338304 | AIR REGULATION FOR FILM COOLING AND EMISSION CONTROL OF COMBUSTION GAS STRUCTURE - A gas turbine engine compressed air flow control arrangement, including: a combustion gas structure having an acceleration geometry ( | 11-20-2014 |
20140338305 | PROVIDING OXIDATION TO A GAS TURBINE ENGINE - A gas turbine engine includes a compressor for compressing air from an environment; a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel; a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor; and an injector coupled with a source of oxidizer for injecting the oxidizer into the combustor. A method for operating a gas turbine engine includes compressing air from an environment; receiving the compressed air at a combustor; mixing the compressed air with fuel; injecting oxidizer into the combustor in addition to the air from the environment; combusting the fuel with the compressed air and the oxidizer; receiving exhaust gas from the combusted fuel; and powering the compression of the air from the environment using the exhaust gas. | 11-20-2014 |
20150020497 | GAS TURBINE FACILITY - A gas turbine facility | 01-22-2015 |
20150027099 | GAS TURBINE FACILITY - A gas turbine facility | 01-29-2015 |
20150369135 | DEVICE FOR IMPROVED AIR AND FUEL DISTRIBUTION TO A COMBUSTOR - A flow conditioning device ( | 12-24-2015 |