Patent application number | Description | Published |
20100242493 | Fuel Nozzle Spring Support - The present application provides a fuel nozzle spring support system. The fuel nozzle spring support system may include a fuel nozzle, a cap assembly, and a spring support positioned between the fuel nozzle and the cap assembly. | 09-30-2010 |
20110100016 | APPARATUS AND METHODS FOR FUEL NOZZLE FREQUENCY ADJUSTMENT - A combustion liner cap assembly includes a cylindrical sleeve with a cantilevered fuel nozzle mounted therewithin; and a plurality of support rods. Each support rod has a first end supported by the cylindrical sleeve and a second end configured to contact the cantilevered fuel nozzle. Each support rod is adjustable in effective length to provide an adjustable compression force against the cantilevered fuel nozzle. A method for adjusting a resonant frequency of a cantilevered fuel nozzle mounted in a cylindrical sleeve is provided. A plurality of support rods extend between the cylindrical sleeve and the cantilevered fuel nozzle. An associated gas turbine has at least some combustion and rotor tones of interest. The method includes adjusting an effective length of the support rods to adjust compressive forces exerted against the cantilevered fuel nozzle to increase a resonant frequency of the fuel nozzle to be greater than the combustion and rotor tones of interest. | 05-05-2011 |
20110100019 | APPARATUS AND METHODS FOR FUEL NOZZLE FREQUENCY ADJUSTMENT - A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle. A mounting flange assembly concentrically surrounds the cylindrical outer sleeve. A plurality of struts on an outer surface of the cylindrical outer sleeve support the mounting flange assembly. A plurality of flanges are on the outer surface of the cylindrical outer sleeve; and a plurality of support rods having first ends are adjustably supported by respective flanges. A combustor for a gas turbine includes a combustion liner cap assembly, a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings, and a center fuel nozzle supported in the center fuel nozzle opening. Second ends of the plurality of support rods adjustably contact the center fuel nozzle. | 05-05-2011 |
20130192234 | BUNDLED MULTI-TUBE NOZZLE ASSEMBLY - A method for reducing emissions in a turbo machine is disclosed. The method includes providing fuel to a multi-tube nozzle and reducing the differences in the mass flow rate of fuel into each tube. An improved multi-tube nozzle is also disclosed. The nozzle includes an assembly that reduces the difference in the mass flow rate of fuel into each tube. | 08-01-2013 |
20130305734 | Fuel Plenum Premixing Tube with Surface Treatment - The present application provides a micro-mixer fuel plenum for mixing a flow of fuel and a flow of air in a combustor. The micro-mixing fuel plenum may include an outer barrel and a number of mixing tubes positioned within the outer barrel. The mixing tubes may include one or more heat transfer features thereon. | 11-21-2013 |
20140053571 | SEAL FOR A PERFORATED PLATE - A cooling circuit of a gas turbine passes an airflow through a combustor section that includes a plurality of mixing tubes for transporting a fuel/air mixture and a perforated plate including a plurality of impingement holes and a plurality of tube holes for accommodating the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the perforated plate and the mixing tubes. The impingement holes and the annulus areas are configured to pass the airflow through the perforated plate. A flow management device modifies an effective size of the annulus areas to control a distribution of the airflow through the impingement holes and the annulus areas of the perforated plate to enhance cooling efficiency. | 02-27-2014 |
20140083110 | SEAL FOR FUEL DISTRIBUTION PLATE - A fuel flow passes through a micromixer section of a gas turbine that includes a plurality of mixing tubes for transporting a fuel/air mixture and a distribution plate including a plurality of distribution holes and a plurality of tube holes for accommodating the mixing tubes. Each of the mixing tubes includes a plurality of fuel holes through which fuel enters the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the distribution plate and the mixing tubes. The distribution holes and the annulus areas are configured to pass the fuel flow through the distribution plate toward the fuel holes. A flow management device modifies an effective size of the annulus areas to control a distribution of the fuel flow through the distribution holes and the annulus areas of the distribution plate to provide a uniform fuel/air composition in each of the mixing tubes. | 03-27-2014 |
20140202163 | EFFUSION PLATE USING ADDITIVE MANUFACTURING METHODS - Additive manufacturing techniques may be utilized to construct effusion plates. Such additive manufacturing techniques may include defining a configuration for an effusion plate having one or more internal cooling channels. The manufacturing techniques may further include depositing a powder into a chamber, applying an energy source to the deposited powder, and consolidating the powder into a cross-sectional shape corresponding to the defined configuration. Such methods may be implemented to construct an effusion plate having one or more channels with a curved cross-sectional geometry. | 07-24-2014 |
20140216038 | Variable Volume Combustor with Cantilevered Support Structure - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within an end cover, a common fuel tube extending through the end cover and in communication with the micro-mixer fuel nozzles, a linear actuator to maneuver the common fuel tube and the micro-mixer fuel nozzles, and a sealing support structure positioned between the end cover and the common fuel tube. | 08-07-2014 |
20140216039 | Variable Volume Combustor with Aerodynamic Fuel Flanges for Nozzle Mounting - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts. | 08-07-2014 |
20140216041 | Variable Volume Combustor with Center Hub Fuel Staging - The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle. | 08-07-2014 |
20140216048 | Variable Volume Combustor - The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner. | 08-07-2014 |
20140216049 | Variable Volume Combustor with Pre-Nozzle Fuel Injection System - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system. | 08-07-2014 |
20140216050 | Variable Volume Combustor with Nested Fuel Manifold System - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system. | 08-07-2014 |
20140216051 | Variable Volume Combustor with an Air Bypass System - The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles. | 08-07-2014 |
20140216054 | Variable Volume Combustor with Aerodynamic Support Struts - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles. | 08-07-2014 |