Patent application number | Description | Published |
20110061397 | CIRCUMFERENTIALLY SELF EXPANDING COMBUSTOR SUPPORT FOR A TURBINE ENGINE - A bullhorn or support for a turbine combustor is provided. The support maintains proper positioning of the transition element relative to the combustor while also allowing for certain movements of the support to alleviate mechanical stresses during turbine operation. The support is constructed from at least two pieces having an interlocking and releasable connection. | 03-17-2011 |
20110271688 | Reduced Pressure Loss Transition Support - A transition piece support for a turbomachine includes one or more support arms extending across a diffuser flowpath to the transition piece. The one or more support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms. A turbomachine includes a combustor, a diffuser, a transition piece operably connected to the combustor and a transition piece support including one or more support arms extending across a flow of fluid to the transition piece. The support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms. | 11-10-2011 |
20120186260 | TRANSITION PIECE IMPINGEMENT SLEEVE FOR A GAS TURBINE - An impingement sleeve for a transition piece of a gas turbine is disclosed. The impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct. Additionally, the impingement sleeve may include a joint defined between the first and second casings. The joint may include a plurality of fasteners configured to attach the first casing to the second casing. | 07-26-2012 |
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 |
20130031783 | METHODS RELATING TO INTEGRATING LATE LEAN INJECTION INTO COMBUSTION TURBINE ENGINES - The present application thus describes a method of manufacture for a late lean injection system in a combustor of a combustion turbine engine. The method may include the steps of: a) identifying a desired position within the flow assembly for a late lean injector, wherein the late lean injector comprises a late lean nozzle and a transfer tube; b) corresponding to the desired position for the late lean injector, identifying an injection point on the inner radial wall and a late lean nozzle position on the outer radial wall; c) positioning the inner radial wall and the outer radial wall in an unassembled position; d) while in the unassembled position, forming a hole through the inner radial wall at the injection point and slideably engaging the transfer tube within the hole; e) installing the late lean nozzle in the outer radial wall at the late lean nozzle position; f) positioning the inner radial wall and the outer radial wall in an assembled position; and g) connecting the transfer tube to the late lean nozzle. | 02-07-2013 |
20130031906 | ASSEMBLIES AND APPARATUS RELATED TO INTEGRATING LATE LEAN INJECTION INTO COMBUSTION TURBINE ENGINES - An assembly for use in a late lean injection system of a combustor of a combustion turbine engine, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the assembly comprising: a boss rigidly secured to the inner radial wall, the boss being configured to define a hollow passageway through the inner radial wall; a transfer tube slideably engaged within the boss; a stop formed on the transfer tube; and damping means positioned between the boss and the stop. | 02-07-2013 |
20130031908 | ASSEMBLIES AND APPARATUS RELATED TO INTEGRATING LATE LEAN INJECTION INTO COMBUSTION TURBINE ENGINES - A transfer tube for use in a late lean injection system of a combustor, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the outer radial wall including a late lean nozzle, the transfer tube including flow directing structure that defines a fluid passageway. At a first end, the flow directing structure may include an inlet and attachment means that attach the transfer tube to the late lean nozzle. The flow directing structure may have a configuration such that the fluid passageway spans the flow annulus and positions the outlet at a desirable injection point in the inner radial wall. | 02-07-2013 |
20130067923 | COMBUSTOR AND METHOD FOR CONDITIONING FLOW THROUGH A COMBUSTOR - A combustor includes an end cover and a casing adjacent to the end cover, wherein the end cover and casing at least partially define a volume inside the combustor. The combustor further includes an end cap that extends radially across at least a portion of the combustor, at least one nozzle arranged in the end cap to provide fluid communication through the end cap, and means for conditioning flow through the volume. A method for conditioning flow through a combustor includes flowing a working fluid through a volume at least partially defined by an end cover, a casing, and an end cap that extends radially across at least a portion of the combustor and flowing the working fluid across an annular insert adjacent to the end cover. | 03-21-2013 |
20130111910 | TRANSITION PIECE AFT FRAME - A transition piece aft frame is provided and includes a manifold having an interior that is receptive of fuel and formed to define fuel injection holes configured to inject the received fuel from the manifold interior toward a main flow of products of combustion flowing through the manifold. The manifold includes a main body having an interior facing surface that faces the main flow of the products of the combustion and along which the fuel injection holes are defined. | 05-09-2013 |
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 |
20130232986 | COMBUSTOR AND METHOD FOR REDUCING THERMAL STRESSES IN A COMBUSTOR - A combustor includes a combustion chamber and a casing that circumferentially surrounds the combustion chamber to at least partially define an annular passage between the casing and the combustion chamber. A fuel plenum extends radially through the casing to provide fluid communication through the casing to the annular passage, and a liner extends inside at least a portion of the fuel plenum to prevent fuel from directly impinging upon at least a portion of the fuel plenum. A method of reducing thermal stresses in a combustor includes flowing a fuel inside a fuel plenum that extends radially through a casing, shielding at least a portion of the fuel plenum from direct impingement by the fuel radially inward of the casing, and flowing the fuel from the fuel plenum into an annular passage between the casing and a combustion chamber. | 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 |
20130269820 | Method, Systems, And Apparatuses For Transition Piece Contouring - Disclosed herein are apparatuses, methods, and systems for transition piece contouring. In an embodiment, a high thermal stress section of a transition piece and a low thermal stress section of a transition piece is a determined The low thermal stress section of the transition piece may be contoured to intercept hot gas flow. | 10-17-2013 |
20130269821 | Systems And Apparatuses For Hot Gas Flow In A Transition Piece - Disclosed herein are methods, systems, and apparatuses for hot gas flow. In an embodiment, a transition piece comprises a surface that conforms to an approximately straight line path stretching approximately from the forward end of a transition piece to the aft end of the transition piece wherein the surface may help direct the flow of gases. | 10-17-2013 |
20130272863 | Transition Piece Cross Sectional Area Convergence Reduction And Selection - Disclosed herein are apparatuses, methods, and systems for cross sectional area convergence reduction and selection. In an embodiment, an aft end cross sectional area is determined for a transition piece and a forward end cross sectional area is determined for the transition piece. The transition piece may be fabricated based on a constant slope of cross sectional area change between the aft end and the forward end. | 10-17-2013 |
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 |
20140000265 | TRANSITION DUCT FOR A GAS TURBINE | 01-02-2014 |
20140014792 | FASTENER ASSEMBLY FOR A GAS TURBINE - A fastener assembly configured for use within an opening defined in a transition piece bracket is disclosed. The fastener assembly may generally include a fastener having a head configured to be positioned proximal to a first end of the opening and a body. The body may include a shank portion, a threaded portion opposite the shank portion and a recessed portion defined between the shank portion and the threaded portion. The fastener assembly may also include a retention member configured to be positioned within the opening adjacent the recessed portion such that the retention member engages at least one of the shank portion or the threaded portion as the fastener is moved within the opening. In addition, the fastener assembly may include a biasing member engaged against the retention member. The biasing member may be configured to bias the head of the fastener away from the first end of the opening. | 01-16-2014 |
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 |
20140047846 | TURBINE COMPONENT COOLING ARRANGEMENT AND METHOD OF COOLING A TURBINE COMPONENT - A turbine component cooling arrangement includes a combustor liner defining a combustor chamber, wherein the combustor liner includes an outer surface and an inner surface. Also included is a channel disposed along the outer surface, wherein the channel is configured to receive a cooling flow through at least one aperture extending through a liner ring disposed proximate the outer surface of the combustor liner. Further included is at least one outlet orifice extending between the channel and the combustor chamber through the inner surface for routing the cooling flow along the inner surface within the combustor chamber. | 02-20-2014 |
20140069103 | SEAL FOR USE BETWEEN INJECTOR AND COMBUSTION CHAMBER IN GAS TURBINE - A seal assembly for use between an injector and a combustion chamber in a gas turbine. A liner at least partially defines the combustion chamber, and the liner has at least one tubular liner collar, through which an injector is inserted. In one embodiment, the liner collar has a partially convex outer diameter and a floating collar is positioned at least partially around the liner collar. The floating collar has a retention member having a first end fixed to the floating collar and a second end configured to abut the convex outer diameter of liner collar, wherein the retention member maintains the floating collar at a radial distance from the injector less than a radial distance between the liner collar and the injector. | 03-13-2014 |
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 |
20140123619 | COMBUSTOR ASSEMBLY - According to one aspect of the invention, a combustor assembly for a pair of adjacent combustors includes a first passage formed in a liner of a first combustor and a flow sleeve disposed outside the liner of the first combustor, wherein the flow sleeve includes a window and a second passage aligned with the first passage. The assembly also includes a cross-fire tube disposed in the first passage to provide fluid communication between the first combustor and a second combustor and a retention clip disposed through the window to urge the cross-fire tube against an outer surface of the liner to enable the cross-fire tube to receive fluid through the first passage. | 05-08-2014 |
20140123660 | SYSTEM AND METHOD FOR A TURBINE COMBUSTOR - A system includes a turbine combustor, which includes a first wall disposed about a combustion chamber, a second wall disposed about the first wall, and a third wall disposed about the second wall. The third wall is configured to combine an exhaust gas with an oxidant and the combustion chamber is configured to combust a mixture of a fuel, the oxidant, and the exhaust gas. | 05-08-2014 |
20140144122 | CROSSFIRE TUBE ASSEMBLY BETWEEN ADJACENT COMBUSTORS - A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves. | 05-29-2014 |
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 |
20140260258 | SYSTEM FOR PROVIDING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber disposed downstream from the fuel nozzle, an inner flow sleeve that circumferentially surrounds the combustion chamber and a plurality of injectors circumferentially arranged around the inner flow sleeve. The plurality of injectors provide for fluid communication through the inner flow sleeve and into the combustion chamber downstream from the fuel nozzle. The system further includes an outer air shield that defines an injection air plenum that surrounds the plurality of injectors. An inlet passage extends through the outer air shield to define a flow path into the injection air plenum. An outer sleeve is slidingly engaged with the outer air shield. The outer sleeve has a first position that restricts flow through the inlet passage and a second position that increases flow through the inlet passage. | 09-18-2014 |
20140260264 | SYSTEM FOR CONTROLLING A FLOW RATE OF A COMPRESSED WORKING FLUID TO A COMBUSTOR FUEL INJECTOR - A system for controlling air flow rate of a compressed working fluid to a fuel injector of a combustor includes an outer casing that defines a high pressure plenum around a portion of the combustor, an extraction port in fluid communication with the high pressure plenum and an inlet port. The combustor includes a plurality of fuel injectors arranged around a combustion liner, an inner flow sleeve, an outer air shield that surrounds the plurality of fuel injectors and the inner flow sleeve. The outer air shield defines an injection an air plenum between the outer air shield and the inner flow sleeve and an inlet to the injection air plenum. An external fluid circuit provides fluid communication between the extraction port and the inlet port. A baffle extends between the outer casing and the outer air shield to provide flow separation between the inlet and the high pressure plenum. | 09-18-2014 |
20140260272 | SYSTEM FOR PROVIDING FUEL TO A COMBUSTOR - A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold. | 09-18-2014 |
20140260273 | CONTINUOUS COMBUSTION LINER FOR A COMBUSTOR OF A GAS TURBINE - A combustion liner for a gas turbine combustor includes an annular main body having a forward end axially separated from an aft end, and a transitional intersection defined between the forward end and the aft end. The main body extends continuously from the forward end to the aft end. A plurality of fuel injector passages extend radially through the main body upstream from the transitional intersection. The main body comprises a conical section having a circular cross section that diverges between the forward end and the transitional intersection, and a transition section having a non-circular cross section that extends from the transitional intersection to the aft end of the main body. | 09-18-2014 |
20140260275 | FLOW SLEEVE ASSEMBLY FOR A COMBUSTION MODULE OF A GAS TURBINE COMBUSTOR - A flow sleeve assembly for a combustor of a gas turbine includes an annular support sleeve disposed at a forward end of the flow sleeve assembly. The support sleeve includes a forward portion axially separated from an aft portion. An aft frame is disposed at an aft end of the flow sleeve assembly. An annular flow sleeve extends from the aft portion of the support sleeve towards the aft frame. The flow sleeve includes a forward end that is axially separated from an aft end. The forward end of the flow sleeve circumferentially surrounds the aft end of the support sleeve. An annular impingement sleeve extends between the aft end of the flow sleeve and the aft frame. A forward end of the impingement sleeve is connected to the aft end of the flow sleeve, and an aft end of the impingement sleeve is connected to the aft frame. | 09-18-2014 |
20140260277 | FLOW SLEEVE FOR A COMBUSTION MODULE OF A GAS TURBINE - A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve. | 09-18-2014 |
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 |
20140260280 | ASSEMBLY FOR CONTROLLING CLEARANCE BETWEEN A LINER AND STATIONARY NOZZLE WITHIN A GAS TURBINE - An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell. | 09-18-2014 |
20140260318 | SIDE SEAL SLOT FOR A COMBUSTION LINER - A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall that extend outward from the first side of the aft frame. A first segment of the upstream wall extends from an inner portion of the aft frame towards an outer portion of the aft frame at a first outward distance from the first side. A second segment of the upstream wall extends from the first segment to the outer portion of the aft frame at a second outward distance from the first side. The second segment of the upstream wall at least partially defines a side seal guide feature to allow for axial insertion of a bottom portion of a side seal into the side seal slot. | 09-18-2014 |
20140260319 | COMBUSTOR SUPPORT ASSEMBLY FOR MOUNTING A COMBUSTION MODULE OF A GAS TURBINE - A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating surface. A combustion module extends through the combustor opening. The combustion module includes a forward end that is circumferentially surrounded by a mounting flange and an aft end that is circumferentially surrounded by an aft frame. The mounting flange extends circumferentially around the combustor opening. The mounting flange is coupled to the outer mating surface of the compressor discharge casing and the aft frame is coupled to the inner mating surface of the outer turbine shell. | 09-18-2014 |
20140360193 | SUPPORT FRAME AND METHOD FOR ASSEMBLY OF A COMBUSTION MODULE OF A GAS TURBINE - A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate. | 12-11-2014 |
20150082795 | INTERNALLY COOLED TRANSITION DUCT AFT FRAME - An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion. A serpentine cooling passage is defined within the main body beneath the outer surface. The serpentine cooling passage is in fluid communication with the inlet port and the exhaust port. A conduit may be connected to the exhaust port for routing a compressed working fluid away from aft frame. | 03-26-2015 |