Patent application number | Description | Published |
20100089020 | METERING OF DILUENT FLOW IN COMBUSTOR - Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A circumferentially adjustable collar is located at the at least one baffle hole between the baffle plate and the at least one fuel nozzle. A plurality of openings at the collar are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed at a circumferentially adjustable collar between a baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow hole in the at least one fuel nozzle. | 04-15-2010 |
20100092896 | METHOD AND APPARATUS FOR INTRODUCING DILUENT FLOW INTO A COMBUSTOR - Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. At least one shroud is secured to the baffle plate and includes at least one piston ring disposed at the shroud. The at least one piston ring is configured to meter a flow of diluent between the at least one shroud and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a piston ring gap defined by at least one piston ring disposed at a baffle plate and a fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the piston ring gap toward at least one airflow hole in the fuel nozzle. | 04-15-2010 |
20110008614 | Electrostatic Powder Coatings - In one embodiment, a protective coating may be electrostatically applied to a rotary machine component. The powder coating includes an electrically conductive sacrificial base coat and a ceramic oxide erosion resistant top coat. | 01-13-2011 |
20120279224 | GAS TURBINE ENGINE COMBUSTOR - A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring. | 11-08-2012 |
20120294729 | COLD METAL TRANSFER HARDFACING OF BUCKETS - In one embodiment, the invention provides a method of hardfacing a portion of a bucket subject to mechanical stress, the method comprising: contacting a surface of a bucket with a hardfacing filler metal connected to a welding nozzle to establish an arc between the surface and the filler metal and form a molten weld pool comprising the filler metal and a material of the surface; extending the filler metal into the molten weld pool to short circuit the arc; withdrawing the filler metal from the molten weld pool to re-establish the arc; moving the welding nozzle along the surface; and re-extending the filler metal into the molten weld pool to short circuit the arc, deposit additional filler metal into the molten weld pool, and liquify additional material of the surface into the molten weld pool. | 11-22-2012 |
20120304659 | IMPINGEMENT SLEEVE AND METHODS FOR DESIGNING AND FORMING IMPINGEMENT SLEEVE - An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric. | 12-06-2012 |
20120304664 | SYSTEM FOR MOUNTING COMBUSTOR TRANSITION PIECE TO FRAME OF GAS TURBINE ENGINE - A system includes a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine. The combustor transition piece includes a hollow body with an internal flow passage extending from an upstream end portion to a downstream end portion. The combustor transition piece also includes an aft frame coupled to the downstream end portion of the hollow body, an aft flange coupled to the aft frame, and a mounting lug removably coupled to the aft frame at a first joint. The mounting lug is configured to removably couple to a mounting bracket at a second joint. | 12-06-2012 |
20130269351 | MICROMIXER ASSEMBLY OF A TURBINE SYSTEM AND METHOD OF ASSEMBLY - A micromixer assembly of a turbine system includes a plate having at least one aperture comprising a receiving diameter. Also included is at least one tube having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor, wherein the at least one tube includes an inner diameter and an outer diameter, wherein the outer diameter is configured to fit within the receiving diameter of the at least one aperture, wherein the at least one tube is operably coupled at a location on the outer diameter to the receiving diameter of the at least one aperture by exerting a radial force on the inner diameter of the tube. | 10-17-2013 |
20130318975 | TURBOMACHINE COMBUSTOR NOZZLE INCLUDING A MONOLITHIC NOZZLE COMPONENT AND METHOD OF FORMING THE SAME - A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements. | 12-05-2013 |