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| Application No. | Application Title | Issue Date |
| 20120102956 | TURBINE EXHAUST DIFFUSION SYSTEM AND METHOD A system includes multiple blades coupled to a rotor, a stationary shroud disposed about the multiple blades, and a clearance between the stationary shroud and each blade end of the multiple blades, wherein the clearance is configured to enable over tip leakage flow. Th... | 05/03/2012 |
| 20120079830 | SENSOR COMMUNICATION SYSTEM AND MACHINE HAVING THE SAME A sensor communication system includes an electromagnetic waveguide disposed adjacent to at least one component of a machine. The electromagnetic waveguide can be configured to convey a fluid within the machine. The sensor communication system can also include a sensor ... | 04/05/2012 |
| 20120067053 | COMBUSTOR SYSTEM A gas turbine engine having a ramburner is disclosed. The ramburner is disposed downstream of a gas turbine engine combustor and receives an engine exhaust flow from the gas turbine engine combustor. The ramburner also accepts a bypass air. Fuel is injected into the ram... | 03/22/2012 |
| 20120047895 | SYSTEMS AND APPARATUS RELATING TO COMBUSTOR COOLING AND OPERATION IN GAS TURBINE ENGINES A combustor for a gas turbine engine that includes first and second combustion chambers interconnected by a throat region that includes a converging wall section, a diverging wall section, and a throat apex between the diverging wall section and the converging wall sect... | 03/01/2012 |
| 20120023949 | APPARATUS AND FILTERING SYSTEMS RELATING TO COMBUSTORS IN COMBUSTION TURBINE ENGINES A combustor for a combustion turbine engine that includes: a chamber defined by an outer wall and forming a channel between windows defined through the outer wall toward a forward end of the chamber and at least one fuel injector positioned toward an aft end of the cham... | 02/02/2012 |
| 20120023950 | CONTROLLABLE FLAMEHOLDER The present invention relates to a flameholder (1) for holding a flame (84) comprising a flow of combusting fluid. The flameholder (1) comprises an inlet (32) and an outlet (34) which defines a flow path between them. A magnetic-field ... | 02/02/2012 |
| 20120017594 | SEAL ASSEMBLY FOR CONTROLLING FLUID FLOW A seal assembly (50, 60) for a gas turbine engine for controlling air flow between a diffuser (48) and rotor disks comprising first and second annular flange ends (52, 54) and an annular seal mid-section (56) between and operatively connected... | 01/26/2012 |
| 20120000203 | Method for operating a burner and burner, in particular for a gas turbine A method for operating a burner comprising a burner axis and at least one jet nozzle is provided. The nozzle or nozzles include a central axis, a jet nozzle outlet, a wall that runs in a radial direction starting from the central axis and that faces the burner axis and ... | 01/05/2012 |
| 20110296845 | Combined heat and power with a peak temperature heat load A combined heat and power plant in which air is compressed in a compressor, the compressed air is reacted with a fuel, producing high temperature, high pressure combustion products, the combustion products heat a first heat load whereby the combustion products are coole... | 12/08/2011 |
| 20110289926 | EXTRUDED FLUID MANIFOLD FOR GAS TURBOMACHINE COMBUSTOR CASING A turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage. The combustor casin... | 12/01/2011 |
| 20110271678 | TURBOMACHINE COMBUSTION CHAMBER WALL HAVING A SINGLE ANNULAR ROW OF INLET ORIFICES FOR PRIMARY AIR AND FOR DILUTION AIR A turbomachine combustion chamber including coaxial walls forming surfaces of revolution that include inlet orifices for admitting primary air and dilution air into the chamber, the orifices in each wall being substantially in alignment with one another along the longit... | 11/10/2011 |
| 20110265481 | DUAL FUEL CAN COMBUSTOR WITH AUTOMATIC LIQUID FUEL PURGE A lean, low NOx gas-fired can combustor having liquid fuel operation capability includes a housing, a combustor liner disposed within the housing and defining a combustion zone for combusting fuel with air, and a head assembly for joining the longitudinal housing and li... | 11/03/2011 |
| 20110232288 | METHOD OF REDUCING COMBUSTION INSTABILITIES BY CHOOSING THE POSITION OF A BLEED AIR INTAKE ON A TURBOMACHINE Method of reducing acoustic vibratory phenomena in the environment of a combustion chamber of a turbomachine, said chamber being positioned in a cavity delimited by an exterior casing and an interior chamber casing, characterized in that it includes at least the followi... | 09/29/2011 |
| 20110209481 | Turbine Combustor End Cover An end cover assembly for a combustor includes a first plate receptive of one of more combustor fuel nozzles and a second plate. One or more intermediate plates are located between the first plate and the second plate and define one or more cavities to distribute fuel t... | 09/01/2011 |
| 20110203281 | ARTICLE FOR HIGH TEMPERATURE SERVICE An article comprises a substrate and a coating disposed over the substrate, wherein the coating comprises a monoclinic silicate phase that undergoes no solid state phase transformation reaction in the temperature range from about 1100 degrees Celsius to about 1275 degre... | 08/25/2011 |
| 20110203282 | ASSEMBLY FOR DIRECTING COMBUSTION GAS An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (<... | 08/25/2011 |
| 20110197586 | Systems and Methods of Providing High Pressure Air to a Head End of a Combustor A combustor includes a first flow path and a second flow path. The first flow path places a diffuser in indirect fluid communication with a combustor cap assembly by way of an intervening lower combustor annular passageway. The second flow path places the diffuser in di... | 08/18/2011 |
| 20110179794 | PRODUCTION PROCESS A transition duct (94) for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct (94) may have an internal passage (102) extending between an inlet (98) to... | 07/28/2011 |
| 20110179803 | BLED DIFFUSER FED SECONDARY COMBUSTION SYSTEM FOR GAS TURBINES The present subject matter provides a system for modifying static pressure recoveries and emissions formation within a gas turbine. The system includes a bled diffuser positioned downstream from a compressor section of the gas turbine and a bleed duct extending from the... | 07/28/2011 |
| 20110162369 | Gas Turbine, Exhaust Diffuser, and Method of Modifying Gas Turbine Plant A method of modifying a gas turbine plant which is provided with a one-shaft gas turbine having a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a one-shaft turbine driven by the comb... | 07/07/2011 |
| 20110113748 | GUIDING AN IGNITION SPARK PLUG IN A TURBOMACHINE COMBUSTION CHAMBER The invention relates to a turbomachine combustion chamber including at least one ignition spark plug carried by an outer casing and extending in guide means carried by a wall of the chamber, the wall forming a body of revolution, the guide means comprising a tubular gu... | 05/19/2011 |
| 20110094235 | COMBUSTOR HEADEND GUIDE VANES TO REDUCE FLOW MALDISTRIBUTION INTO MULTI-NOZZLE ARRANGEMENT A combustor for a gas turbine includes a plurality of nozzles provided in an array; a baffle plate configured to provide a desired air flow distribution to the array of nozzles; and a casing comprising a plurality of holes in an outer surface. The casing extends from a ... | 04/28/2011 |
| 20110083443 | STORAGE OF ELECTRICAL ENERGY WITH THERMAL STORAGE AND RETURN THROUGH A THERMODYNAMIC CYCLE A device and a method for using overcapacities in the power grid is provided. In case of an oversupply of energy, the energy is transferred to a thermal storage device directly via a heating element and in the discharge case of the thermal storage device the heat is rem... | 04/14/2011 |
| 20110079016 | Compact aircraft combustor The present invention provides a combustor for an aerospace gas turbine engine comprising two stages wherein each stage defines an inlet and an exit. The second stage inlet is in fluid communication with the first stage exit such that a first flowpath is defined and it ... | 04/07/2011 |
| 20110048017 | METHOD OF DEPOSITING PROTECTIVE COATINGS ON TURBINE COMBUSTION COMPONENTS A method is provided for high velocity air plasma spraying (APS) application of a protective coating system, such as a bond coat with or without an overlying ceramic thermal barrier coat, to a superalloy metal substrate. Application of MCrAlY alloy bond particles (where... | 03/03/2011 |
| 20110048019 | TURBINE ENHANCEMENT SYSTEM The present invention is concerned with a system and method for enhancing the performance of a wind turbine, which involves injecting air from an array of nozzles into the airflow upstream of the turbine in order to reduce the turbulence and/or increase the velocity and... | 03/03/2011 |
| 20110048018 | COMBUSTION DEVICE OF A GAS TURBINE A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the insi... | 03/03/2011 |
| 20110016865 | GAS TURBINE AND METHOD OF FORMING COMBUSTOR INSERTION HOLE OF GAS TURBINE A gas turbine includes a combustor, a combustor casing formed in a cylindrical shape to house the combustor therein, and a combustor insertion hole, which is a hole formed on a side periphery of the combustor casing, where a size thereof in a direction orthogonal to a c... | 01/27/2011 |
| 20110011095 | WASHER WITH COOLING PASSAGE FOR A TURBINE ENGINE COMBUSTOR A washer for a turbine engine combustor comprises a first surface, a second surface facing generally opposite from the first surface, a bore communicating through the first and second surfaces, and a cooling passage separate from the bore and communicating through the f... | 01/20/2011 |
| 20110000221 | Low Emission Power Generation and Hydrocarbon Recovery Systems and Methods Methods and systems for low emission power generation in hydrocarbon recovery processes are provided. One system includes integrated pressure maintenance and miscible flood systems with low emission power generation. An alternative system provides for low emission power... | 01/06/2011 |
| 20100313567 | GAS TURBINE In a gas turbine that generates rotational power by supplying fuel to compressed air compressed by a compressor and burning the fuel in a combustor and supplying resultant combustion gas to a turbine, a circumferential distance starting from a leading edge of a turbine ... | 12/16/2010 |
| 20100281868 | GAS TURBINE ENGINE COMBUSTER A combustor for a gas turbine engine, and including an integrated dome and deflector having a conical shape optimized for each individual combustor cup in an array of combustor cups, as determined by CFD analysis for eliminating combustor air recirculation zones and swi... | 11/11/2010 |
| 20100247323 | Erosion barrier for thermal barrier coatings A workpiece, such as a turbine engine component, comprises a substrate, a thermal barrier coating on the substrate, and a hard erosion barrier deposited over the thermal barrier coating. The erosion barrier preferably has a Vickers hardness in the range of from 1300 to ... | 09/30/2010 |
| 20100205969 | Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner The invention relates to a burner for a turbomachine, comprising a guide plate that is arranged in a flame chamber and engages a wall section via spacers. The invention further relates to a guide plate, the fastening section of which comprises a plurality of raised area... | 08/19/2010 |
| 20100175384 | Optical Flame Holding And Flashback Detection Optical flame holding and flashback detection systems and methods are provided. Exemplary embodiments include a combustor including a combustor housing defining a combustion chamber having combustion zones, flame detectors disposed on the combustor housing and in optica... | 07/15/2010 |
| 20100170248 | COMBUSTOR AND COMBUSTION METHOD FOR COMBUSTOR A combustor and a combustion method for the combustor, which can suppress backfire and ensure stable combustion. The combustor comprises a mixing-chamber forming member for forming therein a mixing chamber in which air for combustion and fuel are mixed with each other, ... | 07/08/2010 |
| 20100154425 | STRAIN TOLERANT THERMAL BARRIER COATING SYSTEM A method for forming a thermal barrier coating on a combustor panel or a fuel nozzle comprises the steps of: providing a component selected from the group consisting of a combustor panel, a bulkhead heat shield, and a fuel nozzle; optionally depositing a first layer of ... | 06/24/2010 |
| 20100154422 | CMAS MITIGATION COMPOSITIONS, ENVIRONMENTAL BARRIER COATINGS COMPRISING THE SAME, AND CERAMIC COMPONENTS COMPRISING THE SAME Calcium magnesium aluminosilcate (CMAS) mitigation compositions selected from zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof wherein the CMAS mitigation composition is included as a separat... | 06/24/2010 |
| 20100139286 | BURNER AND FUEL SUPPLY FOR A GAS TURBINE A burner including a pressure measurement device for pressure measurement in a combustion medium inside a gas turbine is provided. The burner supplies the combustion medium in an uncombusted state to a combustion chamber of the gas turbine. The pressure measurement devi... | 06/10/2010 |
| 20100107647 | TOROIDAL BOUNDARY LAYER GAS TURBINE A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion toroid.... | 05/06/2010 |
