Patent application number | Description | Published |
20090255267 | COMUBSTOR SEAL HAVING MULTIPLE COOLING FLUID PATHWAYS - A combustor for a gas turbine includes a first combustor component and a second combustor component. The second combustor component is at least partially insertable into the first combustor component, and the first combustor component and second combustor component define a combustion fluid pathway. A combustor seal is located between the first combustor component and the second combustor component. The combustor seal defines at least one inner cooling pathway between the combustor seal and the second combustor component and at least one outer cooling pathway between the combustor seal and the first combustor component for cooling the first combustor component and second combustor component. A method for cooling a first combustor component and a second combustor component is also disclosed. | 10-15-2009 |
20100005804 | COMBUSTOR STRUCTURE - A combustor includes at least one combustor liner defining a combustion chamber capable of directing combustion products toward a turbine. At least one combustor sleeve is located outside of the combustion chamber and is capable of reducing a magnitude of acoustic waves in the combustion chamber. The at least one combustor liner and the at least one combustor sleeve define at least one flow channel therebetween. Further, a combustor includes at least one combustor liner defining a combustion chamber capable of directing combustion products toward turbomachinery. At least one combustor sleeve disposed outside of the combustion chamber and is capable of controlling distribution of fluid flow in the combustor to modify a uniformity of the fluid flow to the combustion chamber. | 01-14-2010 |
20100037622 | Contoured Impingement Sleeve Holes - A combustor for use with a gas turbine. The combustor may include liner, an impingement sleeve, and with the liner and the impingement sleeve defining an airflow channel. The impingement sleeve may include a number of contoured holes therethrough. | 02-18-2010 |
20100170249 | METHOD AND APPARATUS TO FACILITATE COOLING OF A DIFFUSION TIP WITHIN A GAS TURBINE ENGINE - A method and apparatus for a diffusion tip for use with a fuel nozzle is described. The diffusion tip has a substantially circular body including an outer surface and an opposite inner surface. The diffusion tip body extends from a discharge end to an inlet end. The diffusion tip includes an inlet surface adjacent to the discharge end and defined within the body. A discharge surface is defined opposite the inlet surface. A plurality of diffusion apertures each extend between the discharge surface and the inlet surface, each aperture is oriented relative to the body to discharge a diffusion flow outward therefrom at an angle γ (gamma) measured in an X-Z plane between a centerline of the aperture and an X-axis extending tangentially to the outer surface, and at an angle θ (theta) measured in a Y-Z plane between the centerline of the aperture and a Y-axis extending radially outward from the centerline. | 07-08-2010 |
20100186416 | FLOW CONDITIONER FOR USE IN GAS TURBINE COMPONENT IN WHICH COMBUSTION OCCURS - A gas turbine component in which combustion occurs. The gas turbine component includes a liner, including a first surface facing a first space and a second surface facing a second space, the liner being interposed between the first and second spaces and having a through-hole defined therein extending from the first to the second surface by which incoming flows proceed from the first space and to the second space. At least the first surface is formed to flow condition the incoming flows to resist separating from sidewalls of the through-hole. | 07-29-2010 |
20100251723 | THIMBLE, SLEEVE, AND METHOD FOR COOLING A COMBUSTOR ASSEMBLY - A method for cooling a combustor assembly having a cooling passage. The method includes providing at least one thimble including an inner surface that defines a first opening, a second opening that is downstream from the first opening, and a flow channel that extends between the first opening and the second opening. The flow channel has a converging portion and a recovery portion that is downstream from the converging portion. The method also includes inserting the at least one thimble into at least one inlet that is defined in at least one sleeve such that cooling air is discharged from the flow channel into the cooling passage. | 10-07-2010 |
20100293957 | SYSTEM AND METHOD FOR COOLING A WALL OF A GAS TURBINE COMBUSTOR - A system, in one embodiment, includes an engine wall. The engine wall includes a cold-side and a hot-side. The engine wall includes one or more dilution holes, wherein each of the one or more dilution holes includes a first opening on the cold-side, a second opening on a hot-side, and a section of thermal barrier coating (TBC) applied on the cold-side and having an opening that generally circumscribes the first opening. | 11-25-2010 |
20110162378 | TUNABLE TRANSITION PIECE AFT FRAME - A tunable transition piece aft-frame is disclosed for tuning the exit profile of combustion products as such products flow from a transition piece to a combustion product receiving apparatus. The aft-frame includes a generally rectilinear shaped body which has a laterally extending flange. Dilution holes are formed in the flange and are configured to allow dilution air to penetrate into the flow of the combustion products to shape the exit temperature profile of the combustion products. | 07-07-2011 |
20120279226 | HULA SEAL WITH PREFERENTIAL COOLING - An annular seal for use between coupled combustor components includes a segmented annular solid edge portion and a plurality of alternating spring fingers and slots extending from the solid edge portion and arranged about a circumference of the solid edge portion, wherein one or more of the plurality of spring fingers or one or more of the plurality of straight and angled slots have non-uniform width dimensions. | 11-08-2012 |
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 |
20130086920 | COMBUSTOR AND METHOD FOR SUPPLYING FLOW TO A COMBUSTOR - A device for supplying flow to a combustor includes a flow sleeve configured to circumferentially surround the combustor, wherein the flow sleeve defines a first annular passage around the combustor. A first section of the first annular passage converges at a first convergence rate. A second section of the first annular passage downstream from the first section converges at a second convergence rate that is less than the first convergence rate. A method for supplying flow to a combustor includes flowing a first portion of a working fluid substantially axially through a first annular passage, converging the first annular passage at a first convergence rate, and converging the first annular passage at a second convergence rate downstream from the first convergence rate, wherein the second convergence rate is less than the first convergence rate. | 04-11-2013 |
20130089823 | COMBUSTOR - A combustor includes a combustion chamber and at least one group of at least two burner jets disposed circumferentially about the combustor. The at least two burner jets within a group are generally coplanar and are spaced about equal distances circumferentially. Each of the at least two burner jets within a group is oriented to direct a flow of a fluid at a corresponding tangential point of an associated imaginary circle within the combustion chamber to induce a generally cyclonic flow pattern within the combustion chamber. | 04-11-2013 |
20130091847 | COMBUSTOR LINER - A combustor liner is provided. The combustor liner has a first end, including a forward end liner formed to define a converging interior through which a main flow is directed to flow and a second end. The second end is fluidly coupled to an aft portion of the first end and includes an aft end liner formed to define a diverging interior receptive of the main flow and through which the main flow is directed to continue to flow. | 04-18-2013 |
20130232980 | SYSTEM FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for the working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube spirals between the flow sleeve and the liner. | 09-12-2013 |
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 |
20130239575 | SYSTEM FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a combustion chamber and a flow sleeve that circumferentially surrounds at least a portion of the combustion chamber. A tube provides fluid communication for the working fluid to flow through the flow sleeve and into the combustion chamber, wherein the tube comprises an axial centerline. A first set of injectors are circumferentially arranged around the tube and angled radially with respect to the axial centerline of the tube, wherein the first set of injectors provide fluid communication for the working fluid to flow through a wall of the tube. | 09-19-2013 |
20130318991 | Combustor With Multiple Combustion Zones With Injector Placement for Component Durability - A combustion system including a combustor; a combustor liner disposed within the combustor is provided. At least one primary fuel nozzle is provided to provide fuel to a primary combustion zone disposed proximate to the upstream end of the combustor liner. A transition duct is coupled to the downstream end of the combustor liner. A secondary nozzle assembly is disposed proximate to the downstream end of the combustor to provide fuel to a secondary combustion zone at locations predetermined to reduce peak thermal loads on the surface area of the transition duct. | 12-05-2013 |
20140013758 | SYSTEM FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a plurality of fuel injectors circumferentially arranged around the combustion chamber. The plurality of fuel injectors provide fluid communication into the combustion chamber, and a separate cap for each fuel injector defines a separate volume around a different fuel injector outside of the combustion chamber. | 01-16-2014 |
20140033725 | INJECTOR SEAL FOR A GAS TURBOMACHINE - An injector seal for a gas turbomachine includes a seal body having a first surface, an opposing second surface, a central opening configured and disposed to receive a gas turbomachine injector, an outer edge, and a plurality of passages extending through the seal body. The plurality of passages are configured and disposed to guide a fluid at the first surface through the second surface. | 02-06-2014 |
20140033726 | LINER COOLING ASSEMBLY FOR A GAS TURBINE SYSTEM - A liner cooling assembly for a gas turbine system includes a liner having an outer surface and an inner surface, the inner surface defining an interior region. Also included is a sleeve disposed radially outwardly of the outer surface of the liner, the sleeve and the outer surface of the liner defining a channel configured to receive a cooling flow. Further included is a cooling jacket extending circumferentially around at least a portion of the outer surface of the liner and disposed between the liner and the sleeve, wherein the cooling jacket comprises at least one support operably coupled to the cooling jacket and the outer surface of the liner. | 02-06-2014 |
20140041391 | APPARATUS INCLUDING A FLOW CONDITIONER COUPLED TO A TRANSITION PIECE FORWARD END - An apparatus is provided and includes a combustor, a transition piece and a flow conditioner. The combustor has a head end and defines a first flowpath along which a main flow is directable to flow in a downstream direction from the head end. The transition piece is disposable downstream from the combustor, has a forward end and defines a second flowpath along which the main flow is directable to flow in the downstream direction from the forward end. The flow conditioner includes an inner member coupled to the transition piece forward end, an outer member and aerodynamic elements supportively disposed between the inner and outer members to be interactive with a flow of fluid proceeding toward the combustor head end. | 02-13-2014 |
20140096530 | AIR MANAGEMENT ARRANGEMENT FOR A LATE LEAN INJECTION COMBUSTOR SYSTEM AND METHOD OF ROUTING AN AIRFLOW - An air management arrangement for a late lean injection combustor system includes a combustor liner defining a combustor chamber. Also included is a sleeve surrounding at least a portion of the combustor liner, the combustor liner and the sleeve defining a cooling annulus for routing a cooling airflow from proximate an aft end of the combustor liner toward a forward end of the combustor liner. Further included is a cooling airflow divider region configured to split the cooling airflow into a first cooling airflow portion and a second cooling airflow portion, wherein the first cooling airflow portion is directed to at least one primary air-fuel injector, wherein the second cooling airflow portion is directed to at least one lean-direct injector extending through the sleeve and the cooling annulus for injection of the second cooling airflow portion into the combustor chamber. | 04-10-2014 |
20140116053 | FUEL INJECTION ASSEMBLIES IN COMBUSTION TURBINE ENGINES - An assembly for use in a fuel injection system within a combustor of a combustion turbine engine is described. The assembly may include: a first port formed through an outer radial wall of the combustor and a second port formed through an inner radial wall. A plenum may be formed about the first port. A tube may be formed that has a first end positioned within the first port and a second end positioned within the second port. At the first end, the tube may be sized smaller than the first port such that two passages are defined therethrough: a first passage defined about an exterior of the tube; and a second passage defined through an interior of the tube. | 05-01-2014 |
20140116058 | ASSEMBLIES AND APPARATUS RELATED TO COMBUSTOR COOLING IN TURBINE ENGINES - A combustor of a combustion turbine engine is described. The combustor may include an inner radial wall, which defines a combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall so to form a flow annulus therebetween, and the combustor may include a socket extending from the outer radial wall into the flow annulus. The socket may include: a mouth formed through the outer radial wall; a floor offset a predetermined distance from an outboard surface of the inner radial wall; impingement ports formed through the floor; and an axial nozzle. | 05-01-2014 |
20140123653 | ENHANCEMENT FOR FUEL INJECTOR - A fuel injector is provided and includes a surface disposed proximate to a flow of a first fluid and a delta wing feature. The surface has upstream and downstream portions defined relative to the flow and defines an injector hole in the downstream portion by which a jet of a second fluid is injectable into the flow. The delta wing feature is disposed on the surface at the upstream portion and is configured to lift an oncoming portion of the flow off the surface and to cause the oncoming portion of the flow to form a pair of counter-rotating vortices that respectively co-rotate with the jet in a cross-flow direction. | 05-08-2014 |
20140130477 | TURBOMACHINE AND STAGED COMBUSTION SYSTEM OF A TURBOMACHINE - A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes. | 05-15-2014 |
20140130504 | SYSTEM FOR COOLING A HOT GAS COMPONENT FOR A COMBUSTOR OF A GAS TURBINE - A system for cooling a hot gas path component for a combustor generally includes an impingement sleeve that circumferentially surrounds an outer surface of the hot gas path component. A first cooling chamber is defined between the impingement sleeve and a first portion of the outer surface of the hot gas path component. A second cooling chamber is disposed downstream from the first cooling chamber. The second cooling chamber is defined between the impingement sleeve and a second portion of the outer surface of hot gas path component. An inlet extends through the impingement sleeve so as to define a first flow path into the first cooling chamber. An outlet defines a second flow path between the first cooling chamber and the second cooling chamber. | 05-15-2014 |
20140174090 | SYSTEM FOR SUPPLYING FUEL TO A COMBUSTOR - A system for supplying fuel to a combustor includes a combustion chamber and a liner that circumferentially surrounds at least a portion of the combustion chamber. A plurality of fuel nozzles are radially arranged across the combustor upstream from the combustion chamber to supply a swirling flow of fuel into the combustion chamber. A first fuel injector downstream from the plurality of fuel nozzles provides fluid communication for fuel to flow through the liner and into the combustion chamber. The first fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber. | 06-26-2014 |
20140260279 | HOT GAS PATH DUCT FOR A COMBUSTOR OF A GAS TURBINE - A hot gas path duct or unibody liner for a gas turbine includes a main body having a forward end and an aft end. The main body defines a cross-sectional flow area and an axial flow length that extends between the forward end and the aft end. The main body further defines a fuel injection portion disposed downstream from the forward end and upstream from the aft end. The cross-sectional flow area decreases along the axial flow length between the forward end and the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion. | 09-18-2014 |
20150059348 | SYSTEM AND METHOD FOR CONTROLLING FUEL DISTRIBUTIONS IN A COMBUSTOR IN A GAS TURBINE ENGINE - The present disclosure relates to a gas turbine engine system having a plurality of combustors, wherein a first combustor includes one or more fuel nozzles and one or more fuel injectors positioned downstream from the fuel nozzles. The gas turbine engine may also include a first valve disposed along a fuel delivery line between a fuel circuit and the first combustor to adjust a first flow of the fuel to the first combustor. The gas turbine engine may also include a second valve disposed along a fuel delivery line between the first valve and at least one of the one or more fuel injectors to adjust a second flow of the fuel to at least one of the one or more fuel injectors. | 03-05-2015 |