Patent application number | Description | Published |
20090308077 | HOLE PATTERN FOR GAS TURBINE COMBUSTOR - A combustor for a turbine engine includes an outer liner having a row of circumferentially distributed outer combustion air holes and an inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners each include at least a major air hole having a first hole size, an intermediate air hole having a second hole size, and a minor air hole having a third hole size. The first, second, and third hole sizes are all different from each other. | 12-17-2009 |
20100050643 | Gas Turbine Engine Systems and Methods Involving Enhanced Fuel Dispersion - Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased. | 03-04-2010 |
20100223849 | METHOD OF CATALYTIC REACTION - A method of combusting a catalyzed hydrocarbon fuel comprising providing a first fluid and a second fluid, at least one of said fluids comprising a mixture of a hydrocarbon fuel with an air stream, passing the first fluid into one or more catalytic tubes of a catalytic reactor, and passing the second fluid adjacent the catalytic tubes in a chamber of a catalytic reactor. A varying tube cross section to modify the flow of one of the fluids is provided for at least a portion of the tube. The flow of the first fluid leaving the catalytic tubes is mixed with the second fluid and combusted. | 09-09-2010 |
20120017599 | ANNULAR GAS TURBINE COMBUSTOR - A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly. | 01-26-2012 |
20130091849 | AUGMENTOR SPRAY BAR WITH TIP SUPPORT BUSHING - An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage. | 04-18-2013 |
20130256993 | SEAL WITH NON-METALLIC INTERFACE - A seal for use between a first duct and a second duct and, the ducts having relative motion therebetween, includes a first plurality of fingers for attachment to the first duct to be disposed about one of the first duct and the second duct, a seal land attaching to about an other of the first duct and the second duct, and a seal attaching to the seal land and in contact with the plurality of fingers wherein one of the plurality of fingers and the seal is metallic and an other of the seal land or the plurality of fingers is non-metallic. | 10-03-2013 |
20130323405 | COATING FOR COOLING AIR HOLES - A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture. | 12-05-2013 |
20140090391 | COMBUSTER WITH RADIAL FUEL INJECTION - A combustor for a gas turbine engine includes an forward fuel injection system in communication with a combustion chamber and a downstream fuel injection system that communicates with the combustion chamber downstream of the forward fuel injection system. | 04-03-2014 |
20140099182 | DUCT DAMPER - An example damper includes a damping member configured to damp a duct wall at an interface between a duct band and the duct wall | 04-10-2014 |
20140147271 | Pressure Seal With Non-Metallic Wear Surfaces - A gas turbine engine has a pair of components having a high-pressure chamber on one side, and a low pressure chamber on an opposed side. A three-sided seal has one side in sealing contact with each of said components. A third side is associated with a third component. At least one non-metallic wear surface is positioned between one of the three sides of the seal and its respective component. | 05-29-2014 |
20140150915 | OSCILLATING TUBE HAVING A SEGMENTED COATING FOR DAMPING THE TUBE - The oscillating tube ( | 06-05-2014 |
20140165578 | Ovate Swirler Assembly for Combustors - In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter greater than that of a minor diameter such that the shrouds define an ovate shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds. | 06-19-2014 |
20140165585 | Oblong Swirler Assembly for Combustors - In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter which is larger than a minor diameter such that the shrouds define an oblong shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds. | 06-19-2014 |
20140255158 | COATING PROCESS FOR GAS TURBINE ENGINE COMPONENT WITH COOLING HOLES - A method of coating a component having a multiple of cooling holes includes removing at least a portion of a prior coating; directing a gas through at least one of the multiple of cooling holes; and applying a coat layer while directing the gas through at least one of the | 09-11-2014 |
20140349029 | COATING FOR COOLING AIR HOLES - A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture. | 11-27-2014 |