232results about "Burner cooling" patented technology

An injection nozzle for a turbomachine includes a main body having a first end portion that extends to a second end portion defining an exterior wall having an outer surface. A plurality of fluid delivery tubes extend through the main body. Each of the plurality of fluid delivery tubes includes a first fluid inlet for receiving a first fluid, a second fluid inlet for receiving a second fluid and an outlet. The injection nozzle further includes a coolant delivery system arranged within the main body. The coolant delivery system guides a coolant along at least one of a portion of the exterior wall and around the plurality of fluid delivery tubes.

A fuel nozzle with active cooling is provided. It includes an outer peripheral wall, a nozzle center body concentrically disposed within the outer wall in a fuel and air pre-mixture. The fuel and air pre-mixture includes an air inlet, a fuel inlet and a premixing passage defined between the outer wall in the center body. A gas fuel flow passage is provided. A first cooling passage is included within the center body in a second cooling passage is defined between the center body and the outer wall.

A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly and simplify fuel nozzle manufacturing.

Inorganic fiber production burner apparatus and methods of use are disclosed. One burner includes a refractory block adapted to be in fluid connection with sources of primary oxidant and fuel, the refractory block having a fuel and primary oxidant entrance end and a flame exit end, the flame exit end having a substantially rectangular flame exit having a width greater than its height, the refractory block defining a combustion chamber and a second chamber fluidly connecting the combustion chamber and the flame exit end; and an oxygen manifold fluidly connected to the combustion chamber and adapted to route oxygen to the combustion chamber through a plurality of passages through the refractory block. This abstract allows a searcher or other reader to quickly ascertain the subject matter of the disclosure. It will not be used to interpret or limit the scope or meaning of the claims. 37 CFR 1.72(b).

The present invention provides a fuel spray apparatus for a gas turbine engine, including: a pilot part configured to spray a fuel to be used for a diffusion combustion; a main part provided so as to surround the pilot part and configured to inject a pre-mixed gas only upon a high power operation; and a shield body constituting a purge air passage which is configured to take therein an air flowed on an upstream side relative to a fuel injection port of the main part as a purge air, and to blow off a fuel dripping from the fuel injection port toward a main air passage of the main part. The purge air passage is provided in a position opposite to a main fuel passage communicated with the fuel injection port across the shield body.

A combustor has a combustion zone and a liner bounding the combustion zone. The liner has a first end portion and a second end portion spaced a defined distance from the first end portion. The combustor has a convector spaced apart from the liner. The convector has a first end portion and a second end portion spaced a defined distance of the first end portion. A plurality of passages are located between the liner and the convector. One of the passages has a length that is longer than at least one of the defined distance of the liner and the defined distance of the convector.

A combustor-to-transition seal (301) includes a spring clip assembly (322, 422, 522) and a first spring metal ring (340, 441) or a ring assembly (440,540) that includes the first spring metal ring (441) and a second spring metal ring (442). Such combustor-to-transition seal (301) provides a first seal (321) and a second seal (331, 531) when at a junction of a combustor (108, 308, 508) and a transition (114, 314, 514). In an embodiment, the first spring metal ring (340) has a plurality of apertures (342) through the ring (340) that provide effusion cooling of the ring (340). The plurality of apertures (342) regulates a flow of cooling fluid to maintain an acceptable temperature of the ring (340). In an alternative embodiment, the second spring metal ring (442) has grooves (446) that regulate a flow of cooling fluid to maintain an acceptable temperature of the ring assembly (440).

A fuel injector includes a fuel delivery tube; a plurality of pre-mixing tubes, each pre-mixing tube comprising at least one fuel injection hole; an upstream tube support plate that supports upstream ends of the plurality of pre-mixing tubes; a downstream tube support plate that supports downstream ends of the plurality of pre-mixing tubes; an outer wall connecting the upstream tube support plate and the downstream tube support plate and defining a plenum therewith; and a baffle provided in the plenum. The baffle includes a radial portion. A fuel delivered in the upstream direction by the fuel delivery tube is directed radially outwardly in the plenum between the radial portion of the baffle and the downstream tube support plate, then in the downstream direction around an outer edge portion of the radial portion, and then radially inwardly between the radial portion and the upstream tube support plate.

A system includes a gasification fuel injector, which includes a first fuel conduit configured to inject a first fuel flow from a first fuel tip, a second fuel conduit configured to inject a second fuel flow from a second fuel tip, a first gas conduit configured to inject a first gas flow from a first gas tip, a second gas conduit configured to inject a second gas flow from a second gas tip, and a third gas conduit configured to inject a third gas flow from a third gas tip. At least one of the first fuel tip, the second fuel tip, the first gas tip, the second gas tip, or the third gas tip is recessed a distance away from an outlet of the gasification fuel injector. The first and second fuel conduits and the first, second, and third gas conduits are coaxial with one another.

A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly.

An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion liner seal is in contact with an inner wall of the transition duct inlet ring. Increasing the dedicated cooling air supply to the combustion liner aft end, coupled with a modified combustion liner aft end geometry, significantly reduces turbulence and flow re-circulation, thereby resulting in lower metal temperatures and increased component life. Multiple embodiments of the interface region are disclosed depending on the amount of cooling required.

An apparatus having a flame bowl, a shroud surrounding the flame bowl, and a fitting connected to an underside of the flame bowl is disclosed. At least two wick holders are disposed in the flame bowl. The shroud connects to the flame bowl along a top thereof and is spaced apart from the flame bowl along a bottom thereof.

An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion liner seal is in contact with an inner wall of the transition duct inlet ring. Increasing the dedicated cooling air supply to the combustion liner aft end, coupled with a modified combustion liner aft end geometry, significantly reduces turbulence and flow re-circulation, thereby resulting in lower metal temperatures and increased component life. Multiple embodiments of the interface region are disclosed depending on the amount of cooling required.

A gas turbine engine fuel nozzle includes an axis of symmetry extending therethrough, the nozzle body including a first passage extending coaxially therethrough, a second passage, and a third passage, the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, and a nozzle tip coupled to the nozzle body, the nozzle tip including at least one primary discharge opening in flow communication with the first passage, at least one secondary discharge opening in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage.

According to various embodiments, a system includes a gasification fuel injector. The gasification fuel injector includes a tip portion, an annular coolant chamber disposed in the tip portion, a recessed surface for cooling control and a first structural support extending through the annular coolant chamber. The first structural support divides the annular coolant chamber into a first passage and a second passage.

A system includes a multi-tube fuel nozzle including a fuel nozzle head that includes an outer wall surrounding a chamber. The outer wall includes a downstream wall portion configured to face a combustion region. The multi-tube fuel nozzle also includes multiple tubes extending through the chamber to the downstream wall portion. Each tube of the multiple tubes includes an upstream portion, a downstream portion, and at least one fuel inlet disposed at the upstream portion, and is configured to receive air and mix the air with fuel from the at least one fuel inlet. The multi-tube fuel nozzle includes a fuel conduit extending through the chamber crosswise to and around the multiple tubes. The fuel conduit includes multiple impingement cooling orifices. A fuel flow path extends through the fuel conduit, through the impingement cooling orifices, through the chamber, and into the at least one fuel inlet of each tube.

A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and / or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body.

An assembly method in which a brazing metal is initially filled into radial wells pierced in an annular injection piece having first injection orifices for discharging a primary fuel, and in a cylindrical endpiece surrounding the annular injection piece and having secondary injection orifices for discharging a secondary fuel; thereafter the annular injection piece is fitted inside the cylindrical endpiece and these pieces are together fitted on a first tube for feeding primary fuel and a second tube for feeding secondary fuel and surrounding the first tube, and also to an outer wall of the injector; finally, the end portion of the injector as assembled in this way is placed in an enclosure where it is heated so as to melt the brazing metal to unite the parts.

A fuel nozzle with active cooling is provided. It includes an outer peripheral wall, a nozzle center body concentrically disposed within the outer wall in a fuel and air pre-mixture. The fuel and air pre-mixture includes an air inlet, a fuel inlet and a premixing passage defined between the outer wall in the center body. A gas fuel flow passage is provided. A first cooling passage is included within the center body in a second cooling passage is defined between the center body and the outer wall.

The present invention relates to an arrangement comprising an igniter plug of the semiconductor in shell type, a duct secured to a combustion chamber of a gas turbine engine, a floating sleeve via which the igniter plug is mounted in the duct, in order to accommodate expansion along an axis perpendicular to the axis of the igniter plug. It notably comprises means for guiding air to cool the semiconductor of the igniter plug, the shell and the semiconductor defining, at their combustion-chamber end, an annular igniter plug cavity, and the shell comprising orifices in the region of the igniter plug annular cavity that communicate with the annular cavity of the sleeve and orifices on its planar surface.

A pilot nozzle heat shield includes a generally cylindrical body having a first end for receiving a pilot nozzle. The body includes a plurality of radial retention pin cavities for receiving retention pins. A frustoconical flow tip is located at a second end of the body that includes a proximal periphery and a distal periphery. A plurality of flow jets are circumferentially spaced about the proximal periphery of the frustoconical flow tip which further includes a plurality of slots extending distally from the plurality of flow jets. The plurality of slots define a plurality of tangs and the plurality of tangs define an aperture at the distal periphery of the flow tip. At least two of the tangs are connected about the distal periphery of the flow tip and the pilot nozzle heat shield generally includes at least two sets of connected tangs.

An injector of a two-headed combustion chamber of a turbomachine has a first feed tube which is connected to an annular injection piece for discharging primary fuel into the combustion chamber. It also has a second feed tube surrounding the first feed tube and connected to a cylindrical endpiece for discharging secondary fuel into said combustion chamber. This endpiece has an annular channel of diameter that is greater than the diameter of the second feed tube and that extends over its entire length. A third tube is provided that surrounds the second tube and that is connected to a tubular separation element which is inserted in the annular channel of the cylindrical endpiece so as to form two annular spaces in which a cooling fluid can flow over 360° all the way to the end of the injector.

A gas turbine engine fuel nozzle includes an axis of symmetry extending therethrough, the nozzle body including a first passage extending coaxially therethrough, a second passage, and a third passage, the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, and a nozzle tip coupled to the nozzle body, the nozzle tip including at least one primary discharge opening in flow communication with the first passage, at least one secondary discharge opening in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage.

A combustor for a gas turbine engine includes a plurality of primary nozzles configured to diffuse or premix fuel into an air flow through the combustor; and a secondary nozzle configured to premix fuel with the air flow. Each premixing nozzle includes a center body, at least one vane, a burner tube provided around the center body, at least two cooling passages, a fuel cooling passage to cool surfaces of the center body and the at least one vane, and an air cooling passage to cool a wall of the burner tube. The cooling passages prevent the walls of the center body, the vane(s), and the burner tube from overheating during flame holding events.

In a gas turbogroup, which comprises a compressor, a first combustion chamber, a first turbine, a second combustion chamber, and a second turbine, the first combustion chamber is arranged downstream of the compressor, the first turbine is arranged downstream of the first combustion chamber, the second combustion chamber is arranged downstream of the first turbine, and the second turbine is arranged downstream of the second combustion chamber, wherein the second combustion chamber has a convectively cooled wall. A cooling air feed line for the second combustion chamber branches from the main flow path of the gas turbogroup downstream of the compressor and upstream of the first combustion chamber. A return line for heated cooling air leads from the second combustion chamber upstream of the first turbine to the main flow path.

A method for cooling an igniter lead is provided. The method includes coupling an assembly to the igniter lead such that a portion of the assembly rotates circumferentially around the igniter lead, and channeling cooling air through the assembly to facilitate cooling the igniter lead.

A combustor generally includes a shroud that that defines at least one inlet passage extends circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port, at least one outlet port and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve may extend through the fuel nozzle passage. The tube, the sleeve, and the first plate may at least partially define an outlet passage. A first fluid flow path generally extends from the at inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.

Submerged combustion burners having a burner body and a burner tip connected thereto. The burner body has an external conduit and first and second internal conduits substantially concentric therewith, forming first and second annuli for passing a cooling fluid therethrough. A burner tip body is connected to the burner body at ends of the external and second internal conduits. The burner tip includes a generally central flow passage for a combustible mixture, the flow passage defined by an inner wall of the burner tip. The burner tip further has an outer wall and a crown connecting the inner and outer walls. The inner and outer walls, and the crown are comprised of same or different materials having greater corrosion and / or fatigue resistance than at least the external burner conduit.

A pilot nozzle heat shield includes a generally cylindrical body having a first end for receiving a pilot nozzle. The body includes a plurality of radial retention pin cavities for receiving retention pins. A frustoconical flow tip is located at a second end of the body that includes a proximal periphery and a distal periphery. A plurality of flow jets are circumferentially spaced about the proximal periphery of the frustoconical flow tip which further includes a plurality of slots extending distally from the plurality of flow jets. The plurality of slots define a plurality of tangs and the plurality of tangs define an aperture at the distal periphery of the flow tip. At least two of the tangs are connected about the distal periphery of the flow tip and the pilot nozzle heat shield generally includes at least two sets of connected tangs.