Patent application number | Description | Published |
20110283707 | System for Cooling Turbine Combustor Transition Piece - An air cooling hood offset from an exterior of the transition piece to define an air cooling passage between the air cooling hood and the exterior of the transition piece, wherein the air cooling hood comprises a plurality of air outlets disposed along the exterior of the transition piece, and the plurality of air outlets is configured to expel an airflow from the air cooling passage away from the exterior of the transition piece. | 11-24-2011 |
20120167571 | COMBUSTOR ASSEMBLIES FOR USE IN TURBINE ENGINES AND METHODS OF ASSEMBLING SAME - A method of assembling a combustor assembly for use in a turbine engine is provided. A combustor liner that defines a combustion chamber therein is provided. The liner includes a forward end and an aft end, wherein the aft end includes at least one channel extending therethrough. The channel is aligned obliquely with respect to a centerline extending through the aft end. A plurality of fuel nozzles are coupled to the forward end such that the fuel nozzles extend through the forward end. An annular sleeve that includes at least one opening extending radially therethrough is coupled to the aft end, wherein the sleeve substantially circumscribes the aft end such that a cavity is defined therebetween and such that a fluid channeled through the at least one opening impinges against a surface of the aft end prior to the fluid being channeled into the combustion chamber. | 07-05-2012 |
20120180492 | APPARATUS FOR VIBRATION SUPPORT IN COMBUSTORS AND METHOD FOR FORMING APPARATUS - A sleeve component assembly for a combustor, and a method for forming the sleeve component assembly for the combustor, are disclosed. The sleeve component assembly includes a sleeve component, the sleeve component comprising one of an inner sleeve component or an outer sleeve component. The sleeve component assembly further includes at least one support feature extending from the sleeve component, the at least one support feature configured to contact and provide vibratory support to an adjacent sleeve component. The at least one support feature is integral with the sleeve component. | 07-19-2012 |
20120186269 | SUPPORT BETWEEN TRANSITION PIECE AND IMPINGEMENT SLEEVE IN COMBUSTOR - A support between a transition piece and an impingement sleeve in a combustor is disclosed. The support includes a resilient portion, the resilient portion configured to provide dampening between the transition piece and the impingement sleeve. The support further includes a mount portion configured for mounting the support to one of the transition piece or the impingement sleeve. The support further includes a contact portion configured for contacting the other of the transition piece or the impingement sleeve. | 07-26-2012 |
20120198855 | METHOD AND APPARATUS FOR COOLING COMBUSTOR LINER IN COMBUSTOR - A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner. | 08-09-2012 |
20120210729 | METHOD AND APPARATUS FOR MOUNTING TRANSITION PIECE IN COMBUSTOR - A bracket for a combustor, and a method for mounting a transition piece in a combustor, are disclosed. The combustor has an impingement sleeve at least partially surrounding a transition piece and an outer casing at least partially surrounding the impingement sleeve. The bracket is mounted to the transition piece and connected to the outer casing. The method includes mounting a bracket to the transition piece, extending the bracket through an impingement sleeve, the impingement sleeve at least partially surrounding the transition piece, and connecting the bracket to an outer casing, the outer casing at least partially surrounding the impingement sleeve. | 08-23-2012 |
20120234012 | 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, a method for designing an impingement sleeve is disclosed. The method includes determining a desired operational value for a transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value. | 09-20-2012 |
20120234018 | AFT FRAME AND METHOD FOR COOLING AFT FRAME - An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough. | 09-20-2012 |
20120280460 | TWO-PIECE SIDE SEAL WITH COVERS - A side seal assembly is provided for sealing gaps between adjacent transition ducts in a gas turbine combustor arrangement. The side seal assembly includes a first elongated plate mounting an outer seal and a first fastening element at one end thereof; a second elongated plate mounting a second fastening element at one end thereof and an inner seal at an opposite end thereof. The first and second elongated plates are adapted to be joined in back-to-back relationship by means of the first and second fastening elements, such that in use, the outer and inner seals extend substantially parallel to, but offset from, the first and second elongated plates. The first elongated plate and the inner and outer seals substantially cover three radial gaps between the adjacent transition ducts. | 11-08-2012 |
20120297782 | SYSTEM AND METHOD FOR TURBINE COMBUSTOR MOUNTING ASSEMBLY - A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape. | 11-29-2012 |
20120297783 | SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE - A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure. | 11-29-2012 |
20120297784 | SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE - A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an airflow guide vane disposed in the air passage. The airflow guide vane includes an upstream vane portion and a downstream vane portion. The upstream vane portion is oriented at an angle from an axial axis of the gas turbine combustor. The downstream vane portion is aligned with the axial axis. The airflow guide vane is configured to remove a circumferential swirl of an airflow upstream of the airflow guide vane to straighten the airflow downstream of the airflow guide vane along the axial axis. | 11-29-2012 |
20120297786 | SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE - A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, a fuel injector disposed downstream of the combustion liner and the flow sleeve, a liner mount extending between the combustion liner and the flow sleeve, and a crossfire tube extending between the combustion liner and the flow sleeve. The fuel injector, the liner mount, and the crossfire tube are aligned with one another in a flow enhancing arrangement along a common axis in an axial direction relative to an axis of the gas turbine combustor. The flow enhancing arrangement reduces an air flow disturbance caused by the fuel injector, the liner mount, and the crossfire tube. | 11-29-2012 |
20120304648 | INTEGRATED LATE LEAN INJECTION ON A COMBUSTION LINER AND LATE LEAN INJECTION SLEEVE ASSEMBLY - A late lean injection sleeve assembly allows the injection of fuel at the aft end of a gas turbine liner, before the transition piece, into the combustion gases downstream of a turbine combustor's fuel nozzles. The late lean injection enables fuel injection downstream of the fuel nozzles to create a secondary/tertiary (with quaternary injection upstream of the fuel nozzles) combustion zone while reducing/eliminating the risk of fuel leaking into the combustion discharge case. The fuel is delivered by the flow sleeve into one or more nozzles that mix the fuel with CDC air before injecting it into the combustor's liner. | 12-06-2012 |
20120304652 | INJECTOR APPARATUS - An injector apparatus is provided and includes an annular inlet in which a first fluid traveling in a first direction is mixable with a second fluid to form a mixture, an annular outlet disposed downstream from the inlet from which the mixture is injectable into a main flow in a third direction and an annular intermediate section fluidly interposed between the inlet and the outlet and along which the mixture is re-directable from the inlet to the outlet. | 12-06-2012 |
20120304654 | COMBUSTION LINER HAVING TURBULATORS - A combustor for a turbine is provided. The combustor includes a plurality of fuel nozzles and a combustion zone is aligned with a combustion process associated with each of the fuel nozzles. A combustion liner includes a plurality of turbulator groups, and each of the turbulator groups has or more individual turbulators. Each of the turbulator groups is aligned with a hot streak caused by the combustion zone associated with the fuel nozzle. Each of the turbulator groups are circumferentially spaced from a neighboring turbulator group. | 12-06-2012 |
20120304655 | TURBOMACHINE COMBUSTOR ASSEMBLY INCLUDING A LINER STOP - A turbomachine combustor assembly includes a combustor housing and a combustor body. The combustor body defines a combustor liner having a first end portion that extends to a second end portion through a combustion chamber. A cap assembly is mounted at the combustor housing. The cap assembly includes an endcover, a plurality of fuel nozzles supported by the end cover, and an outer barrel member. The outer barrel member extends about the plurality of fuel nozzles. A liner stop is arranged on one of the outer barrel member and the first end portion of the combustor liner. The liner stop includes a stepped lip portion that receives the other of the outer barrel member and the first end portion of the combustor liner to form substantially smooth liner to outer barrel interface. The liner stop restricts axial movement of the combustor liner relative to the outer barrel member. | 12-06-2012 |
20120304656 | COMBUSTION LINER AND TRANSITION PIECE - An apparatus is disclosed. The apparatus may include a body configured to flow hot gases of combustion between a forward end and an aft end. Additionally, the body may include a plurality of raised sections spaced apart circumferentially around an outer perimeter of the body. The raised sections may generally extend lengthwise between the forward and aft ends. | 12-06-2012 |
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 |
20120306166 | SEAL ASSEMBLY FOR GAS TURBINE - A seal assembly is provided having a retention assembly attached to a first component, and a seal element secured by the retention assembly. The seal element comprises at least one leaf seal, and the leaf seal is comprised of a plurality of tabs in series with a plurality of slots. The seal assembly forms a flexible seal between the first component and a second component. | 12-06-2012 |
20130074471 | TURBINE COMBUSTOR AND METHOD FOR TEMPERATURE CONTROL AND DAMPING A PORTION OF A COMBUSTOR - According to one aspect of the invention, a turbine combustor includes an outer member coupled to a wall of the combustor, wherein there is at least one damping hole formed in outer member. The turbine combustor further includes at least one temperature control hole formed in the wall wherein the at least one temperature control hole is formed at an angle with respect to a line perpendicular to a hot gas path in the combustor. | 03-28-2013 |
20130086915 | FILM COOLED COMBUSTION LINER ASSEMBLY - A combustion liner assembly is provided and includes a combustion liner and a transition piece. A portion of the transition piece is circumferentially disposed around a portion of the combustion liner. A seal is attached to the transition piece, and the seal is configured to apply a compressive force to an aft end of the combustion liner. | 04-11-2013 |
20130111909 | Combustion System Having A Venturi For Reducing Wakes In An Airflow - A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow. | 05-09-2013 |
20130227964 | TRANSITION PIECE AFT FRAME ASSEMBLY HAVING A HEAT SHIELD - A transition piece aft frame assembly is provided, and includes a transition piece aft frame and a heat shield. The transition piece aft frame has an aft face. At least a portion of the aft face is exposed to an exhaust gas stream. The heat shield is connected to the transition piece aft frame. The heat shield is oriented to generally deflect the exhaust gas stream away from the aft face of the transition piece aft frame. | 09-05-2013 |
20130333389 | CROSS FIRE TUBE RETENTION SYSTEM FOR A GAS TURBINE ENGINE - A cross fire retention system for a gas turbine engine includes a retention system housing operably coupled to a radially outer surface of a flow sleeve surrounding a combustion chamber, wherein the retention system housing includes a central aperture relatively aligned with a flow sleeve channel and is configured to receive a cross fire tube. Also included is a locking element extending through a side aperture of the retention system housing and having a first end configured to fittingly engage a first portion of an outer surface of the cross fire tube. Further included is a resilient member disposed within the retention system housing and configured to engage a second portion of the outer surface of the cross fire tube. | 12-19-2013 |
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 |
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 |
20150292438 | METHOD AND APPARATUS FOR COOLING COMBUSTOR LINER IN COMBUSTOR - A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner. | 10-15-2015 |
20150308349 | FUEL DELIVERY SYSTEM - A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor. | 10-29-2015 |
20160040882 | FUEL NOZZLE TUBE RETENTION - A system for retaining a fuel nozzle premix tube includes a retention plate and a premix tube which extends downstream from an outlet of a premix passage defined along an aft side of a fuel plenum body. The premix tube includes an inlet end and a spring support feature which is disposed proximate to the inlet end. The premix tube extends through the retention plate. The spring retention feature is disposed between an aft side of the fuel plenum and the retention plate. The system further includes a spring which extends between the spring retention feature and the retention plate. | 02-11-2016 |
20160047314 | NOZZLE HAVING AN ORIFICE PLUG FOR A GAS TURBOMACHINE - A gas turbomachine nozzle includes a base portion having a first fluid inlet and a second fluid inlet, and an outlet portion having one or more outlets. A connection section fluidically connects the base portion and the outlet portion. An orifice plug is arranged in the base portion at the second fluid inlet. The orifice plug includes one or more openings fluidically connecting the second fluid inlet and the connection section. | 02-18-2016 |