Abstract: A pilot cone for use in a burner arrangement having a pilot burner includes a casing which widens downstream along a burner axis and has a plurality of cooling air passages passing through it; an inner wall which extends upstream starting from the upstream end of the casing; an annular gap which runs along the inner wall on the radially outer side; and a plurality of cooling air openings which establish a connection between the annular gap and the cooling air passages. Another wall extends upstream at a distance from the inner wall starting from the casing and delimits the annular gap on the radially outer side, the inner wall having a plurality of holes.

Abstract: The present invention relates to a method for producing an engine component having a cooling duct arrangement which has a plurality of cooling ducts, each having an inflow opening, the inflow openings being arranged according to a predefined pattern in an inflow surface of the engine component, and each cooling duct opening into a recess in a wall of the engine component, along which wall a cooling film is to be formed. According to the invention, the pattern is formed in at least one subregion of defined size of the inflow surface, from a plurality of identical isosceles triangles, which are defined by a minimum spacing (k) and by a mean diameter (a) of the inflow openings correlating to the minimum spacing (k). This procedure reduces the complexity of the design process.

Abstract: A combustion chamber assembly includes a through hole on the combustion chamber wall bounded on an outer side of the wall by a hole edge and a combustion chamber shingle having a collar bounding a mixing air hole on the outer side of the wall and protruding with a first collar portion beyond the hole edge on the outer side of the wall. A cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of a combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air is guided out of the mixing air hole in a direction of a hot side of the shingle facing the combustion space.

Abstract: A gas turbine engine including a core having a compressor section fluidly connected to a combustor via a primary flowpath and a turbine section connected to the combustor via the core flow path. An assembly is disposed within the gas turbine engine and includes a first part connected to a second part via a radial stack joint. The first part includes a radially inward facing surface contacting a corresponding radially outward facing surface of the second part. A fastener protrudes through the first part and the second part and is configured to maintain the relative positions of the first part and the second part. A channel is disposed on at least one of the radially inward facing surfaces and is positioned between the fastener and a circumferential edge of the first part. The channel is connected to at least one cooling air source.

Abstract: A high-temperature component according to an embodiment is a high-temperature component which requires to be cooled by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; and a first partition wall disposed inside each of the cooling passages to partition the cooling passage into a plurality of first branch flow passages. The first partition wall includes an oblique portion formed such that, in an upstream side region of the first partition wall, a flow-passage cross-sectional area of the cooling passage as seen in an extension direction of the cooling passage gradually decreases from an upstream side toward a downstream side.

Abstract: Provided is a transition piece including a first flow path group formed by arraying a plurality of in-wall flow paths that extend inside a plate material forming the transition piece and a second flow path group that is positioned on a side closer to a combustor liner than the first flow path group is. Each in-wall flow path in the first flow path group and the second flow path group has an inlet that is located at one end section in a flow direction of a combustion gas and that faces a compressed air main flow path, and an outlet that is located at the other end section in the flow direction of the combustion gas and that faces a combustion gas flow path.

Abstract: A combustor including a skeleton structure. The combustor further includes at least one liner operably coupled to the skeleton structure to at least partially define a combustion chamber, and a plurality of first planks mounted to a first side of the at least one liner and a plurality of second planks mounted to a second side of the at least one liner. The combustor also includes at least one dilution hole structure provided with a portion of the skeleton structure, and including at least one dilution hole configured to allow fluid to pass therethrough into the combustion chamber.

Abstract: A combustion chamber for a turbomachine including an annular casing delimiting an inner volume of the combustion chamber and provided with a chimney extending to the outside of the inner volume and delimiting a passage for a penetrating part, and a bushing mounted floating on the chimney, further includes: a main air collection chamber open to the upstream arranged facing the downstream portion of the chimney; and a through-opening of the annular casing, connecting the inner volume to the main air collection chamber. The air collected by the main air collection chamber is injected into the inner volume via the through-opening and can cool an annular casing zone downstream of the chimney.

Abstract: An outlet seal connects a combustor that combusts a fuel to generate combustion gas and a shroud for a stator. The outlet seal has a gas path surface, a first connection section, and a second connection section. The shape of the gas path surface in a cross section perpendicular to an axis is an arc centered on the axis. The first connection section is formed at a first side in an axial direction and is connected to the combustor. The second connection section is formed at a second side in the axial direction and is connected to the shroud. The gas path surface has an inclined surface that is inclined with respect to the axis in a cross section including the axis, such that the flow-path area of a combustion-gas flow path is reduced toward the second side.

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

Abstract: An impingement baffle for directing a cooling fluid onto a target surface includes a baffle body having a first end opposite a second end, and a first side opposite a second side. The second side is spaced a distance apart from the target surface, with the distance varying from the first end to the second end. The baffle body defines impingement holes that extend through the baffle body from the first side to the second side. The impingement holes are spaced apart along the baffle body to receive the cooling fluid. The impingement baffle includes tubular extensions coupled to the second side. Each tubular extension is in fluid communication with a respective one of the impingement holes to direct the cooling fluid onto the target surface. Each tubular extension extends for a length from the second side, and the length of each tubular extension is based on the distance.

Abstract: An assembly is provided for a gas turbine engine. This assembly includes a multi-walled structure including a cold wall, a hot wall and a cooling cavity vertically between the cold wall and the hot wall. The cold wall includes a plurality of cold wall apertures fluidly coupled with the cooling cavity. The cold wall apertures are configured to subject the cold wall to a cold wall pressure drop vertically across the cold wall. The hot wall includes a plurality of hot wall apertures fluid coupled with the cooling cavity. The hot wall apertures are configured to subject the hot wall to a hot wall pressure drop vertically across the hot wall that is greater than or equal to the cold wall pressure drop.

Abstract: To suppress separation of air flows in air holes that are positioned in the outermost circumferential row in an air hole plate, but are far from a turn guide.

Abstract: A component for a gas turbine engine includes an outer surface bounding a hot gas path of the gas turbine engine, and a cooling passage configured to deliver a cooling airflow therethrough. The cooling passage includes a passage wall located opposite the outer surface to define a component thickness and a plurality of protrusions located along the passage wall. Each protrusion has a protrusion height extending from the passage wall and a protrusion streamwise width extending along the passage wall in a flow direction of the cooling airflow through the cooling passage. One or more cooling holes extend from the passage wall to the outer surface. A cooling hole inlet of a cooling hole is located at the passage wall, in a protrusion wake region downstream of a protrusion of the plurality of protrusions.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

Abstract: An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.

Abstract: A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.

Abstract: An acoustic device includes: a perforated plate that has a plurality of holes penetrating in a plate thickness direction of the perforated plate and in which a main flow is to flow on a first side of the perforated plate in the plate thickness direction; and a housing that is on a second side of the perforated plate in the plate thickness direction and partitions a space between the housing and the perforated plate, wherein a part of each of the plurality of holes on the first side in the thickness direction is inclined to at least one of the first side and a second side of a flow direction of the main flow.

Abstract: A combustor liner panel attachment assembly includes a liner extending from a first end to a second end, and circumferentially to partially define a combustion zone. The assembly also includes a spring element located adjacent to a portion of the liner and operatively coupled to a stationary structure, the spring element having a recessed segment. The assembly further includes a protrusion feature extending radially outwardly from the liner, the protrusion feature disposed within the recessed segment of the spring element to axially retain the liner.

Abstract: A combustor liner panel attachment assembly includes a liner extending from a first end to a second end, and circumferentially to partially define a combustion zone. The assembly also includes a spring element located adjacent to a portion of the liner and operatively coupled to a stationary structure, the spring element having a recessed segment. The assembly further includes a protrusion feature extending radially outwardly from the liner, the protrusion feature disposed within the recessed segment of the spring element to axially retain the liner.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.

Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.

Abstract: A monolithic heater body may include a combustor body, a hot-side heat exchanger body, and an eductor body. The combustor body may define a combustion chamber and a conditioning conduit circumferentially surrounding the combustion chamber. The conditioning conduit may fluidly communicate with the combustion chamber at a distal portion of the combustion chamber. The hot-side heat exchanger body may define a hot-side heat exchanger that includes a heating fluid pathway fluidly communicating with a proximal portion of the combustion chamber. The eductor body may define an eduction pathway fluidly communicating with a downstream portion of the heating fluid pathway and a proximal portion of the conditioning conduit.

Abstract: A combustor for a turbine engine includes a first liner and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner is a first double wall liner with a first wall forming a portion of the combustion chamber and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The combustor further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall, through the first wall, and into the combustion chamber.

Abstract: A gas turbine engine component assembly is provided. The gas turbine engine comprises: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate mitigation device extending from the first surface of the second component a selected distance wherein the particulate mitigation device has an opening therethrough in fluid connection with the cooling channel, and wherein the selected distance is selected to reduce the amount of particulate entering the cooling channel.

Abstract: A combustor (3) includes: a fuel nozzle configured to inject fuel; a tubular body (24) having a tubular shape in which a combustion region through which combustion gas flows is formed inside, and in which a plurality of slits (50) are formed extending in the circumferential direction at intervals in the circumferential direction; and throttle pieces (60) which are fitted into the slits (50), project radially inward from the inner circumferential side of the tubular body (24), and have a throttle face that extends along the flow direction of the combustion gas as it extends from the radially outer side inward.

Abstract: In a combustion cylinder, an outer-side region of a cooling part on an outer side with regard to a reference line orthogonal to a radial direction and an axial direction of a gas turbine and passing through a center of a combustor basket, and an inner-side region of the cooling part on an inner side with regard to the reference line are set. A connection angle at an intersection between an extension line of an outer surface of the combustor basket along the axial direction and an inner surface of a combustor transition piece is set. First regions are set at positions near the reference line, and second regions, with a larger connection angle than the first regions, are set at positions farther from the reference line than the first regions. The second regions are set to have a higher flow rate of a cooling medium than the first regions.

Abstract: An assembly for a turbomachine combustion chamber, including a boss for turbomachine combustion chamber, including a tubular body configured to be inserted in a receiving orifice formed in an annular wall of a flame tube and to accommodate a shank of a connecting pin for connecting the flame tube to an external casing, a first end of the boss including an annular flange configured to prevent radial translational movement of the boss in a first direction, and a second end of the boss being configured to be crimped to the wall of the flame tube so as to prevent radial translational movement of the boss in a second direction, and an annular element configured to fit coaxially with the receiving orifice and in radial contact with the annular wall of the flame tube on the one hand and with the annular flange of the boss on the other.

Abstract: A combustion chamber shingle arrangement of a gas turbine, including a combustion chamber shingle, at least one threaded bolt configured for attaching the combustion chamber shingle, and a base body connecting the threaded bolt to the combustion chamber shingle, wherein the base body comprises a platform and a connection area that connects the platform to the combustion chamber shingle, wherein the threaded bolt is arranged at the platform, and wherein a hollow space is embodied between the platform and the combustion chamber shingle.

Abstract: A gas turbine engine component assembly including: a first component having a first surface and second surface opposite the first surface, the first component includes a cooling hole extending from second surface to first surface; a second component having a first surface and second surface, the first surface of first component and second surface of second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling second surface of second component; and an aperture extension feature in the second component and extending into cooling channel, the aperture extension feature includes a passageway fluidly connecting cooling channel to an area located proximate to the first surface of second component, the aperture extension feature includes a face and inlet located in the first face to fluidly connect passageway to cooling channel, the first face being oriented between 0° and 120° relative to second surface of second component.

Abstract: An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.

Abstract: A combustor shell is provided. The combustor shell may include a first aperture at least partially defined by an inner wall of the combustor shell and passing from a diffuser-facing side of the combustor shell to a combustor-facing side of the combustor shell. The combustor shell may include a spacer comprising a first segment coupled to a first flange, wherein the first flange is disposed on the diffuser-facing side of the combustor shell, wherein an outer wall of the spacer is coupled with at least a portion of an inner wall of the combustor shell.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.

Abstract: A combustion duct assembly for a gas turbine includes a liner, an annular spring seal and a transition piece. The annular spring seal is outwardly convex and coupled to an outer face of the downstream side of the liner. The transition piece has includes an inner wall and an outer wall that surrounds the inner wall. The convex part of annular spring seal is operable to elastically engage the inner wall of the transition piece. An end portion of the downstream side of the annular spring seal is fixed to the line. The annular spring seal includes a plurality of through holes formed in an upstream side of a point where the annular spring seal comes into contact with the inner wall. The liner includes a plurality of vent holes formed in an inner area surrounded by the spring seal.

Abstract: Components for gas turbine engines and methods of making the same, the components including a component body having an external side wall and an internal side wall and defining at least a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall, at least one segmented rib extending within the component body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities, the at least one segmented rib comprising at least two rib segments separated by a segment gap, and a discharge hole formed in the external side wall fluidly connected the segment gap to an exterior surface of the component body.

Abstract: A gas turbine combustion chamber with an inner combustion chamber wall and an outer combustion chamber wall, which form an annular combustor, is provided. Mixing air holes are formed in the inner combustion chamber wall and the outer combustion chamber wall in a circumferentially distributed manner. The respective combustion chamber wall is bulged in the area of the mixing air holes towards the interior space of the combustion chamber wall and the mixing air hole is arranged inside the bulge. The mixing air hole is formed at an inflow surface of the bulge with respect to the through-flow direction of the combustion chamber.

Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.

Abstract: A combustion chamber includes a duct wall for guiding a hot gas flow in a hot gas flow path during operation. The duct wall is a double-walled construction including an inner face, an outer face, and a wall cavity. A sleeve at least partly encloses the duct wall for guiding a cooling gas in a cooling channel between the sleeve and the duct wall along the outer surface of the duct wall to an exit end, and the cavity opens to the cooling channel. A gas turbine is disclosing as having such a combustion chamber.

Abstract: A combustor including a transition piece that defines a flow channel therein; a combustor basket inserted in the transition piece from an upstream side of the flow channel that sends a combustion gas through the flow channel and defines a gap through which a compressed air is sent with an inner peripheral surface of the transition piece; wherein the combustor basket includes a notch portion recessed from an end of the combustor basket on a downstream side toward the upstream side, and a purge air introduction hole through which the compressed air in the gap is introduced into the notch portion.

Abstract: An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.

Abstract: An engine component for a gas turbine engine which generates a hot combustion gas flow adjacent a hot surface and provides a cooling fluid flow adjacent a cooling surface comprises a wall separating the hot combustion gas flow and the cooling fluid flow. At least one concavity is provided in the cooling surface and at least one film hole is provided in the cooling surface providing the cooling fluid flow to the hot surface. An inlet for the film hole is spaced from the at least one concavity, located upstream of the at least one concavity and in alignment with the at least one concavity relative to the cooling fluid flow.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

Abstract: A gas turbine engine combustion chamber arrangement includes an annular outer wall and annular inner wall including an upstream and a downstream row of tiles. The downstream end of each tile in the upstream row of tiles has a rail extending towards and sealing with the outer wall and a lip extending in a downstream direction towards the tiles in the downstream row of tiles. The outer wall has a row of apertures to direct coolant onto the lips of the tiles in the upstream row of tiles. The downstream end of each tile in the upstream row of tiles has a plurality of fences extending in a downstream direction from the rail and each fence extends from the outer surface of the lip towards the outer wall. The row of apertures in the annular outer wall is arranged to direct coolant onto the lip between two circumferentially adjacent fences.

Abstract: An engine component assembly includes at least one cavity that is in communication with a source of cooling air. An insert disposed within the cavity includes a plurality of scoops protruding into a flow of cooling air for directing cooling air through the insert and against an inner surface of the cavity.

Abstract: A method of fabricating a combustor thermal shield comprising a combustor panel, a cooling feature, and an attachment feature, the combustor thermal shield to be used in a gas turbine engine combustor, includes shaping a sheet of material used to form the combustor panel. The method also includes additively manufacturing the cooling feature onto the sheet of material forming the combustor panel. The method also includes attaching the attachment feature to the sheet of material forming the combustor panel. The method also includes curving the sheet of material forming the combustor panel to achieve a curve profile according to a design of the gas turbine engine combustor.

Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.

Abstract: A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner surface facing away from the outer shell and an outer surface facing toward the outer shell, and the outer surface has one or more false flanges. At least one of the one or more false flanges includes a first surface protruding from the outer surface and facing the outer shell, and a flow diverting portion extending between the first surface and the outer surface of the inner shell. The flow diverting portion includes a first portion that diverges in a first circumferential direction between the first surface and the outer surface.

Abstract: A grommet may define a dilution hole in a combustor panel. The grommet may comprise a set of upstream features such as, for example, a first inlet leading into a first plurality of passages with the first plurality of passages each having a first outlet directed towards an inner diameter of the grommet. A set of perimeter features may include a second inlet leading into a convective cooling passage having a plurality of internal cooling features. The convective cooling passage may further lead into a second plurality of passages each having a second outlet extending about the inner diameter of the grommet in a circumferential direction A set of downstream features may include a third inlet leading to a third plurality of passages each having a third outlet directed towards an outer diameter of the grommet.

Abstract: In an embodiment of the invention, a dual-wall casing for a combustor comprises an outer wall and an inner wall defining a channel therebetween. The walls are fastened together by a bolt which extends from the inner wall and across the channel. In use, the inner wall is exposed to combustion products. Cooling is provided by a primary inlet hole extending through the outer wall and arranged upstream (with respect to the direction of flow of coolant in the channel) of the bolt and an array of effusion holes extending through the inner wall and positioned with their inlet in line of sight of the primary inlet hole. The primary inlet hole is sized with respect to the array of effusion holes such that it has a flow area which causes locally negligible flow restriction.