Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.

Abstract: A helix amplifier pipe fitting may include an elbow or straight pipe fitting including an expanded helix portion, a plurality of helix vanes at an angle of incidence to the incoming fluid flow to impart rotational velocity on the fluid. A helix amplifier may include a helix discharge amplifier having a tapered canister, a tapered helix portion including a plurality of helix vanes, and a tapered mixing chamber.

Abstract: A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.

Abstract: A combustor of an embodiment includes: a cylindrical combustor liner; and a fuel nozzle which is provided at one end of the combustor liner and jets a fuel and an oxidant into the combustor liner. The fuel nozzle includes: a plurality of fuel supply passages which each supply the fuel; and a plurality of oxidant supply passages which each supply the oxidant. Flow rates of the fuel supplied to the respective fuel supply passages and flow rates of the oxidant supplied to the respective oxidant supply passages are each individually regulated.

Abstract: A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer air flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.

Abstract: A fuel nozzle for a turbomachine includes a centerbody that extends axially with respect to a centerline of the fuel nozzle. A confining tube is positioned radially outward of the centerbody. A plurality of swirler vanes is disposed between the centerbody and the confining tube. Each of the plurality of swirler vanes includes a radially inner base and a radially outer tip. Each of the swirler vanes further includes an upstream portion that extends generally axially from a leading edge. A downstream portion extends from the upstream portion to a trailing edge. The downstream portion defines a bend length between the upstream portion and the trailing edge. The bend length at the radially outer tip is greater than the bend length at the radially inner base.

Abstract: Fuel spray nozzle for generating a spray of atomised liquid fuel in a combustor of a gas turbine engine. The nozzle includes a flow circuit that has in flow series: a gallery that receives fuel flow, plural circumferentially-spaced restrictor passages arranged in a row around the nozzle, plural conditioning passages configured to impart a circumferential component to their respective portions of the fuel flow, and an annular spin chamber which forms a swirling fuel flow which is discharged at an exit port. The restrictor passages form flow restrictions which in use produce a pressure differential between the gallery and the spin chamber to evenly circumferentially distribute the fuel flow between the restrictor passages. The conditioning passages have increased flow cross-sectional areas relative to the flow cross-sectional areas of the restrictor passages, such that the restrictor passages produce substantially all of the pressure differential between the gallery and the spin chamber.

Abstract: A method for reducing NOx emissions in a gas turbine in which a flow of primary air and a flow of fuel are fed into a dual annular counter rotating swirler, the primary air flow being fed into the inner and outer annular chambers, wherein the method comprises the step of injecting the flow of fuel into the inner annular chamber; another embodiment is a gas turbine air fuel mixer comprising a dual annular counter rotating swirler comprising a fuel supplying element adapted to supplying fuel inside the inner chamber of the swirler; another embodiment is a gas turbine provided by such air fuel mixer.

Abstract: A cement kiln burner device includes a powdered-solid-fuel flow channel having means for swirling a powdered-solid-fuel flow; a first air flow channel placed outside the powdered-solid-fuel flow channel having means for swirling an air flow; a second air flow channel placed outside the first air flow channel having means for straightly forwarding an air flow; a third air flow channel placed inside the powdered-solid-fuel flow channel having means for swirling an air flow; and a combustible-solid-waste flow channel placed inside the third air flow channel. The second air flow channel includes an opening portion forming a port for injecting an air flow, and a closed portion covered for preventing an air flow from passing therethrough. The opening portion and the closed portion are alternately arranged in a circumferential direction.

Abstract: A nozzle for a combustion chamber of an engine for providing a fuel-air mixture at a nozzle exit opening of the nozzle includes a nozzle main body including the nozzle exit opening and extends along a nozzle longitudinal axis. The nozzle main body has a first air guiding channel, a fuel guiding channel and a further, radially outwardly second air guiding channel. One end of the fuel guiding channel is positioned in front of the end of the second air guiding channel. A tapering channel portion with a shell surface inclined with respect to a nozzle longitudinal axis in the axial direction and connects to a radially outer shell surface of the fuel guiding channel is formed between the end of the fuel guiding channel and the end of the second air guiding channel at the nozzle.

Abstract: A combustor includes a plurality of fuel nozzles arranged in a nozzle casing. Each fuel nozzle includes a first fuel injection passage disposed at the axial center of the fuel nozzle and configured to inject liquid fuel into a combustion chamber. A second fuel injection passage encloses the first fuel injection passage and injects liquid fuel into the combustion chamber at a predetermined spray angle with respect to a center line of the fuel nozzle. A first air injection passage encloses the second fuel injection passage and injects air to be mixed with the injected liquid fuel from the second fuel injection passage. At the combustion chamber end, opposing surfaces of the first and second fuel injection passages are each inclined with respect to the center line and are separated by a space through which the liquid fuel of the second fuel injection passage is injected.

Abstract: There is provided a combustible waste injection device and a method for operating the same which can suppress a landing combustion of a combustible waste and suppress excessive change of a flame state from a cement kiln burner even if a rate of using the combustible waste fluctuates. A combustible waste injection device according to the present invention has a combustible waste flow channel which is arranged in an inner side of the air flow channel in an innermost shell, is installed in parallel to an axial direction of the cement kiln burner device and is provided for flow feeding a combustible waste flow, and the combustible waste flow channel has an inclined surface having a rising slope toward the injection port near the injection port in such a manner that a flow channel width in a vertical direction is narrowed toward the injection port.

Abstract: A combustion liner or component produced through the use of additive manufacturing techniques. The combustion liner or other component may be formed having a feature based optimized cooling circuit at least partially embedded in the thickness of the material. The internal cooling circuit, may be used, along with other benefits, to control the temperature of the component and prevent hot-spots and uneven heat distribution across the surface of the component.

Abstract: A nozzle, a combustor, and a gas turbine are capable of uniformly pre-mixing fuel and air. The nozzle includes an integrated swirler comprising an inner tube configured to provide a first pre-mixing passage through which pre-mixed air flows, an outer tube configured to partially enclose the inner tube and form an outer fuel passage through which fuel flows, and a plurality of vanes coupled with the outer tube, each vane having an exhaust hole through which fuel exits; a fuel injector including an inner fuel passage through which fuel flows and being configured to be inserted into the inner tube of the integrated swirler; and a peg having an outer surface in which are formed a plurality of injection holes communicating with the inner fuel passage, the injection holes configured to inject the fuel of the inner fuel passage into the first pre-mixing passage.

Abstract: A fluid atomizer and methods of atomizing fluids are disclosed. The fluid atomizer may comprise an inner member and one or more outer members. The inner member defines an interior conduit for providing a first-fluid flowpath from a supply end of the atomizer to a discharge end of the atomizer along a central axis. The one or more outer members are positioned radially outward of the inner member from the central axis. The inner and outer members define a second-fluid flowpath extending from a second-fluid supply conduit to a second-fluid discharge plenum. The second-fluid flowpath comprises a tangential conduit spiraling along the axis from the second-fluid supply conduit to a terminal end; an annulus downstream from and in fluid communication with the tangential conduit; and a second-fluid discharge plenum downstream from and in fluid communication with the annulus.

Abstract: A combustor for a gas turbine engine having a central axis about which is arranged in flow sequence a radial swirler, a pre-chamber partly defined by a wall and a combustion chamber. The radial swirler has a base plate having an annular array of vanes and fuel injectors arranged to direct an air/fuel mixture radially inwardly and tangentially to create a vortex that flows through the pre-chamber and into the combustion chamber. The pre-chamber has a portion which is convergent in a downstream direction.

Abstract: The present invention is concerned with improved swirl burners, particularly, but not limited to, swirl burners used in fuel cell systems.

Abstract: A pre-film liquid fuel cartridge (20) includes a primary liquid fuel passage (106), a plurality of inner fuel ports (116) and a plurality of outer fuel ports (124) that are in fluid communication with the primary liquid fuel passage. An inner pre-filming surface (142) is defined downstream from the plurality of inner fuel ports. The inner pre-filming surface (142) terminates at a first shear edge (140). An outer pre-filming surface (152) is defined downstream from the plurality of outer fuel ports. The outer pre-filming surface (152) terminates at a second shear edge (154). The first and second shear edges are relatively oriented so that a first pre-filmed liquid fuel sheet exiting the first shear edge intersects with a second pre-filmed liquid fuel sheet exiting the second shear edge, thereby atomizing the first and second pre-filmed liquid fuel sheets.

Abstract: The present disclosure is directed to a fuel injector assembly of a gas turbine engine, including a centerbody, an outer sleeve surrounding the centerbody, an inner sleeve disposed between the centerbody and at least a section of the outer sleeve, and at least one axially oriented vane defined between the centerbody and a section of the inner sleeve. A section of the outer sleeve includes at least one radially oriented vane. A portion of the inner sleeve includes a contoured shroud and defines at least one fuel injection port disposed upstream of the contoured shroud. The axially oriented vane is disposed upstream of the fuel injection port.

Abstract: The hydration apparatus includes an air augmentation feature that intersects the ingredients. The air augmentation inlet is positioned to cause turbulence in the ingredients prior to the ingredients passing a liquid discharge nozzle that hydrates them.

Abstract: A staged fuel injector comprises a pilot inner air swirler arranged along a centre axis of the injector, a pilot fuel swirler arranged radially outboard of the pilot inner air swirler, a main inner air swirler arranged radially outboard of the pilot fuel swirler and a main fuel swirler arranged radially outboard of the pilot fuel swirler. A fuel feed arm is arranged in fluid communication with the pilot fuel swirler and the main fuel swirler for delivering fuel to the pilot fuel swirler and the main fuel swirler and a heat protective casing enclosing the fuel feed arm, the pilot fuel swirler and the main fuel swirler.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. In embodiments, the fuel injector includes an injector head adjoining a stem. The injector head includes a main premix passage, a main air inlet, vanes, and a main premix resonator. The main premix passage extends through the injector head and the main air inlet directs compressed air into the main premix passage. The vanes are located within the main premix passage for swirling the compressed air. The main premix resonator is located adjacent to and downstream of the vanes.

Abstract: A helix amplifier pipe fitting may include an elbow or straight pipe fitting including an expanded helix portion, a plurality of helix vanes at an angle of incidence to the incoming fluid flow to impart rotational velocity on the fluid. A helix amplifier may include a helix discharge amplifier having a tapered canister, a tapered helix portion including a plurality of helix vanes, and a tapered mixing chamber.

Abstract: A gas-only cartridge for a fuel nozzle includes a flange that defines a plurality of apertures for receiving a gaseous fuel, an outer tube that is coupled to the flange and an inner tube that extends axially within the outer tube. The inner tube and the outer tube define a fuel passage therebetween and the fuel passage is in fluid communication with the plurality of apertures of the flange. A fuel distribution tip is disposed at a downstream end of the gas-only cartridge and defines a plurality of fuel ports circumferentially spaced along and annularly arranged about an outer surface of the fuel distribution tip. The fuel ports are in fluid communication with the fuel passage.

Abstract: An injector includes a fuel distributor with a first fluid inlet and a first fluid outlet, with a first fluid circuit for fluid communication between the first fluid inlet and the first fluid outlet. The fuel distributor includes a second fluid inlet and a second fluid outlet, with a second fluid circuit for fluid communication between the second fluid inlet and outlet. The fuel distributor defines a spray axis. The first and second fluid outlets can be radially adjacent and/or can be substantially aligned axially relative to the spray axis, e.g., for issuing multiple different fuels from substantially the same outlet.

Abstract: A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. A nozzle cap (50) may be disposed at a downstream end of the nozzle. A heat shield (60) is mounted onto the nozzle cap. A plurality of cooling channels (62) is arranged between a forward face of the nozzle cap and a corresponding back side of the heat shield. The plurality of cooling channels may be arranged to discharge cooling air over a forward face of an atomizer assembly in the multi-functional fuel nozzle.

Abstract: A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.

Abstract: A fuel injector for injecting fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) and a second fuel supply channel (20) may be coaxially arranged in a fuel delivery structure (12). A first set of vanes 22 includes a radial passage (24) in fluid communication with the first channel (18) to receive a first fuel. Passage (24) branches into passages (26) each having an aperture (28) to inject the first fuel without jet in cross-flow injection. A second set of vanes (32) includes a radial passage (34) in fluid communication with the second channel (20) to receive a second fuel. Passage (34) branches into passages (36) each having an aperture (38) arranged to inject the second fuel also without jet in cross-flow injection. This arrangement may be effective to reduce flashback that otherwise may be encountered in fuels having a relatively high flame speed.

Abstract: A center body assembly for a fuel injector is disclosed. The center body assembly defines a primary liquid passage, a liquid gallery, swirl slots, and a prefilm passage. The primary liquid passage supplies liquid fuel to the liquid gallery. The liquid gallery includes a gallery discharge end and a gallery inlet end that aligns with the primary liquid passage. The liquid gallery tapers down from the gallery inlet end to the gallery discharge end. The swirl slots extend from the liquid gallery to the prefilm passage in a helical pattern. The prefilm passage includes an annular shape that turns inward towards an assembly axis of the center body assembly.

Abstract: In one aspect, a fuel supply system may include a fuel injector having a primary and a secondary pilot fuel nozzle in fluid communication with a primary and a secondary fuel circuit, respectively, and a main fuel nozzle in fluid communication with a main fuel circuit. The fuel injector may also define a by-pass fuel circuit connected between the primary circuit and the secondary circuit and/or the main circuit. The system may also include a primary fuel manifold configured to be fluidly connected to the primary pilot fuel nozzle via the primary fuel circuit. Moreover, the system may include a by-pass valve provided in operative association with the by-pass fuel circuit. The by-pass valve may be configured to be opened such that a portion of the fuel flowing through the primary circuit from the primary fuel manifold is directed to the secondary circuit and/or the main circuit.

Abstract: The present invention discloses a fuel nozzle assembly and method for axially staging fuel injection. The fuel nozzle assembly comprises a plurality of vanes connected to a core, with an annular ring connectedly surrounding the plurality of vanes. Fuel is directed through the core and then through the vanes and is injected at different axial planes generally perpendicular to an oncoming air stream to obtain a broad spectrum of gas residence time between the point of fuel injection and the flame.

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, a primary air passageway centrally defined axially in the body, and a plurality of concentrically-arranged nozzle tip projections disposed at a downstream portion of the body. Each of the plurality of nozzle tip projections has a radially inwardly facing fuel filming surface communicating with respective fuel passages. The fuel filming surfaces are disposed radially outwardly of an outlet of the primary air passageway. A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine is also presented.

Abstract: In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.

Abstract: An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.

Abstract: A gaseous fuel-oxygen burner is described herein. One device includes a flame zone in which combustion of gaseous fuel and oxygen occurs to form a flame, a coaxial gaseous fuel jet configured to provide the flame zone with gaseous fuel, and a coaxial oxygen jet configured to provide the flame zone with oxygen, wherein the coaxial gaseous fuel jet and the coaxial oxygen jet are separate such that the gaseous fuel from the coaxial gaseous fuel jet and the oxygen from the coaxial oxygen jet do not mix before entering the flame zone.

Abstract: The invention refers to burner arrangement for producing hot gases to be expanded in a gas turbine, including a burner inside a plenum, where the burner has means for fuel injection, means for air supply and means for generating an ignitable fuel/air mixture inside the burner, and a combustion chamber following downstream said burner having an outlet being fluidly connected to the gas turbine. The invention is characterized in that the means for air supply includes at least two separate flow passages, and that the one of the two flow passages is fed by a first supply pressure and the other flow passage is fed by a second supply pressure.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas outer tube, a gas inner tube, a liquid tube, and a heat shield. The gas outer tube and the gas inner tube form a gas fuel annulus. The gas inner tube and the liquid tube form a liquid fuel annulus. The liquid tube forms an air cavity. The heat shield extends within the liquid tube forming an insulating gap between the heat shield and the liquid tube.

Abstract: A method of aerosolizing a liquid by generating an aerosol from a liquid fluid and a gas with a nozzle having a cone-shaped gas exit channel, the method including the method steps of: ejecting a nozzle gas jet through an orifice at the cone apex; generating a zone of low pressure by the ejected nozzle gas jet, the zone of low pressure augmenting a flow of liquid fluid in a direction from a nozzle cone base towards the orifice at the cone apex; and aerosolizing the liquid fluid at the aerosolizing perimeter where the liquid fluid that flows towards the orifice is sheared by the nozzle gas jet.

Abstract: An injector for mixing two propellants upstream of a combustion chamber. The injector includes: at least one injection element with a tricoaxial structure installed between two plates which between them delimit a space; and coaxial ducts including an internal coaxial duct and an external coaxial duct that are supplied in parallel with a same propellant, for example via the space.

Abstract: A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section.

Abstract: The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover. The fuel nozzle may include a pilot system in communication with the end cover passage.

Abstract: 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.

Abstract: A gas turbine combustor includes a combustion cylinder and a premixing tube. A protruding wall of the tube has an inner diameter enlarging portion with a chamfer at an open end thereof. A swirl flow in the tube is guided outward along the chamfer, so that the cross-section area of a straight flow in the tube is expanded to have a lower flow velocity, and the distance between a flame in the cylinder and the enlarging portion is shortened. When using the fuel with high heat radiation upon combustion, the enlarging portion is replaced with the one having a smaller chamfer. The cross-section area of the straight flow is reduced to increase the flow velocity, and the lift distance becomes longer. Therefore, the damage to the combustion cylinder owing to the intensified heat radiation is prevented. The flame lift position retained in the cylinder is easily set and changed.

Abstract: A fuel-air premixer for a combustor of a gas turbine engine includes a central passage disposed along an axis and operable to communicate a first airflow and an outer annular passage about the axis operable to communicate a second airflow. The fuel-air premixer further includes an inner annular passage about the axis and between the central passage and the outer annular passage for communicating fuel flow. The inner annular passage including an inner exit angled for directing fuel flow toward the axis into a mixer passage downstream of the outer and inner exits for mixing the fuel flow with the first and second airflows.

Abstract: Generation of cavitation jet in air on a surface of a work roll provides a higher cleaning force than squirting of only high pressure fluid, so that sticking substances on the surface of the work roll are reliably removable. When a distance between a cleaning nozzle and the surface of the work roll and pressure of the high pressure fluid are controlled within a predetermined range, sticking substances are efficiently removable while roughness of the surface of the work roll is maintained.

Abstract: A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the main injector includes: a first inflow channel through which the air having a major flow component in an axial direction is taken; a second inflow channel through which the air having a major flow component in a radial direction is taken and which causes the air therein to meet the air from the first inflow channel; and a main fuel injecting portion configured to inject the fuel only to the second inflow channel.

Abstract: A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof.

Abstract: A gas turbine engine device is disclosed for mixing fuel and air prior to a combustion. The device includes a pilot mixer and a main mixer each having a fuel opening for the delivery of fuel to one or more passages. In one form the main mixer includes an inner passage and an outer passage and in which a fuel opening delivers fuel to the inner passage. The main mixer can include swirlers in the inner and/or outer passages. The pilot mixer can also include a swirler. In one embodiment the main mixer includes a converging flow path and/or a diverging flow path. The pilot mixer can also include a converging and/or diverging flow path and in one form is sheltered from an exit of the device. The main mixer fuel opening can be disposed between an upstream end and a downstream end of the mixer.

Abstract: A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage. The first swirler vane provides a first wake region within the flow segment. The second swirler vane provides a second wake region within the flow segment. A fuel injection peg is disposed downstream from the first swirler vane and the second swirler vane. The fuel injection peg is positioned within the flow segment between the first wake region and the second wake region.

Abstract: A combustion chamber for a gas turbine is proposed. The combustion chamber has a wall section and a brim element. The wall section has an inlet aperture for injecting a cooling medium into the combustion chamber. The brim element is mounted to an inner face of the wall section. The brim element is formed in such a way that a projected area of the brim element onto the inner face along a direction of a normal of the inner face at least partially covers the inlet channel.