Patent application number | Description | Published |
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 |
20130036742 | COMBUSTOR LINER COOLING SYSTEM - A turbine engine with a combustor that includes a hollow wall about a combustor liner. The combustor liner includes an inner surface facing inwardly toward a combustion chamber. The turbine engine includes a first air flow path in an upstream direction through the hollow wall toward a head end of the combustor. The first air flow path includes a plurality of bypass openings extending through the combustor liner to the inner surface to supply a first cooling film to a downstream end portion of the combustor liner. The turbine engine further includes a second flow path in a second direction opposite the upstream direction through the hollow wall. The second flow path includes a plurality of film holes extending through the combustor liner to the inner surface to supply a second cooling film to the downstream end portion of the combustor liner downstream of the first cooling film. | 02-14-2013 |
20130086921 | COMBUSTOR AND METHOD FOR SUPPLYING FLOW TO A COMBUSTOR - A device for supplying flow across a combustor includes an axial fluid injector configured to circumferentially surround at least a portion of the combustor. An inner annular passage extends through the axial fluid injector and provides fluid communication through the axial fluid injector and into a first annular passage that surrounds the combustor. An outer annular passage extends through the axial fluid injector radially outward from the inner annular passage and provides axial flow into the first annular passage. A method for supplying flow to a combustor includes flowing a first portion of a working fluid through a first axial flow path and flowing a second portion of the working fluid through a second axial flow path. | 04-11-2013 |
20130167543 | METHODS AND SYSTEMS FOR COOLING A TRANSITION NOZZLE - A transition nozzle for use with a turbine assembly is provided. The transition nozzle includes a liner defining a combustion chamber therein, a wrapper circumscribing the liner such that a cooling duct is defined between the wrapper and the liner, a cooling fluid inlet configured to supply a cooling fluid to the cooling duct, and a plurality of ribs coupled between the liner and the wrapper such that a plurality of cooling channels are defined in the cooling duct. | 07-04-2013 |
20130174563 | COMBUSTOR FUEL NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor fuel nozzle includes a center body and an inner shroud that circumferentially surrounds at least a portion of the center body. The inner shroud has a downstream surface. The fuel nozzle includes an inner passage between the center body and the inner shroud, an outer passage that circumferentially surrounds at least a portion of the inner shroud and a first plurality of fuel ports extending substantially radially outward through the center body. The first plurality of fuel ports is upstream from the downstream surface of the inner shroud. A method for supplying fuel to a combustor fuel nozzle includes flowing a working fluid through an inner passage between a center body and an inner shroud, injecting a fuel from the center body against the inner shroud, and flowing a portion of the working fluid through an outer passage that surrounds at least a portion of the inner shroud. | 07-11-2013 |
20130209250 | TRANSITION PIECE SEAL ASSEMBLY FOR A TURBOMACHINE - A transition piece seal assembly includes a first seal, and a second seal joined to the first seal. The second seal being spaced from the first seal to define a coolant passage. | 08-15-2013 |
20130236301 | Apparatus And System For Directing Hot Gas - Disclosed herein are apparatuses and systems for directing the flow of hot gas exiting a transition piece. In an embodiment, an aft frame an aft frame has an exit face that has an airfoil shape. In an embodiment, a transition piece aft exit has an airfoil shape. | 09-12-2013 |
20140060063 | Systems and Methods For Suppressing Combustion Driven Pressure Fluctuations With a Premix Combustor Having Multiple Premix Times - A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles. | 03-06-2014 |
20140238026 | FUEL NOZZLE FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS - A fuel nozzle includes a center body that extends axially along an axial centerline for a length. A shroud circumferentially surrounds the center body for at least a portion of the length of the center body. A plurality of helical passages circumferentially surround the center body along at least a portion of the length of the center body, and a fuel port in each helical passage has a different convective time. | 08-28-2014 |
20140260300 | AIR DIFFUSER FOR COMBUSTOR - A system includes a multi-tube fuel nozzle of a turbine combustor. The multi-tube fuel nozzle includes a support structure defining an interior volume configured to receive an air flow; a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector; and an outer annular wall configured to direct an air flow from an annulus between a liner and a flow sleeve of the turbine combustor at least partially radially inward into the interior volume through an air inlet and toward the plurality of mixing tubes, wherein the outer annular wall at least partially defines an air flow passage extending from the annulus to the interior volume. | 09-18-2014 |
20140338338 | SYSTEM AND METHOD FOR TUBE LEVEL AIR FLOW CONDITIONING - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple mixing tubes. Each mixing tube includes an annular wall disposed about a central passage and an air inlet region configured to be disposed about a fuel injector extending into the central passage. The central passage extends from an upstream end to a downstream end of the annular wall relative to a direction of flow through the central passage. The air inlet region includes an air entry surface of the annular wall that gradually decreases in diameter in the direction of flow. | 11-20-2014 |
20140338339 | SYSTEM AND METHOD HAVING MULTI-TUBE FUEL NOZZLE WITH MULTIPLE FUEL INJECTORS - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube. | 11-20-2014 |
20140338340 | SYSTEM AND METHOD FOR TUBE LEVEL AIR FLOW CONDITIONING - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple tubes. Each tube includes a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be disposed about a fuel injector. Each tube also includes an air flow conditioner having multiple air ports disposed adjacent the first end. The multiple air ports extend through the wall into the central passage. | 11-20-2014 |