Abstract: Gas turbine engine combustor designs are tending to higher operating temperatures and, therefore, utilisation of high temperature materials such as, for example, ceramics, composite material and high temperature nickel alloys. However use of these materials for combustor components leads, in turn, to problems of how to join together those components. A high temperature material combustor barrel and a similar combustor head heatshield are joined to a metal or metal alloy combustor head by means of a lip around the circumference of the head swaged or rolled onto a lip on the barrel trapping the heatshield between them.

Abstract: A wall structure for a wall bounding a combustion chamber of a gas turbine engine is disclosed having a first wall with an inner surface facing towards the interior of the combustion chamber and an outer surface facing away from the interior of the combustion chamber such that the inner surface forms a boundary of the combustion chamber and the outer surface has a surface roughness to prevent the formation of a fluid flow cooling layer which would cool the outer surface. The invention also has a second wall spaced from the outer surface of the first wall in a direction away from the interior of the combustion chamber so as to define a cooling fluid circulatory space between the first and second walls. A plurality of first perforations extend through the first wall in communication with the cooling fluid circulatory space to enable passage of cooling fluid from the space through the first perforations to form a cooling fluid film on the inner surface of the first wall.

Abstract: Two composite parts, such as sheet and a hollow gas turbine liner tile, are fastened together using a fastening system that includes a journal bearing that fits in a bore in the sheet and springs to support a bolt fastener that is tightened to hold the parts together. Resilient spacers are placed between the sheet and the liner. The springs may comprise a stack of rings, each ring being a tightly wound helical spring, giving the ring a hollow cross section and resilient qualities.

Abstract: A hybrid ceramic article for high temperature applications is disclosed. The thermal barrier comprises an array of refractory ceramic tiles embedded in a fiber reinforced glass-ceramic matrix composite structure. The hybrid ceramic article exhibits high thermal stability and elevated temperature load bearing ability. A combustor liner and a combustor liner panel for a gas turbine engine and also disclosed.

Abstract: In a gas turbine liner, air metering passages are placed in dimples in a first liner sheet to provide an air chamber. A second liner sheet contains an air outlet for each dimple. The second sheet masks the metering passage and a portion of the dimple. A coating is applied to the second sheet and extends into the dimple but does not cover the metering passage.

Abstract: Carbon monoxide and unburned hydrocarbon burnout in gas turbine combustors is promoted by a combustor liner having a plurality of vortex generating members or ridges formed therein. The liner includes a substrate having an inner surface and a thermal barrier coating disposed on the inner surface. The vortex generating ridges are formed in the thermal barrier coating and extend transverse to the mean direction of flow through the liner. The thermal barrier coating is capped with a catalytic material which enhances carbon monoxide and unburned hydrocarbon oxidation. The ridges are defined by raised portions of the catalytic material and are of sufficient height to cause mixing between the hot flame products and the cool incompletely-burned flow along the liner wall. Alternatively, the ridges can be defined by forming corrugations in the substrate and disposing a uniform catalytically-active thermal barrier coating over the corrugated substrate.

Abstract: A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes a pair of legs extending radially outwardly from an outer shroud and a pair of mounting legs extending radially inwardly from an inner shroud. Each of the pair of legs and mounting legs have a pair of holes therein. A plurality of members attached to the gas turbine engine have a plurality of bores therein which axially align with corresponding ones of the pair of holes in the legs. A plurality of pins are positioned within the corresponding holes and bores radially positioning the nozzle guide vane assembly about a central axis of the gas turbine engine.

Abstract: A combustor assembly having a preestablished rate of thermal expansion is mounted within a gas turbine engine housing having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the combustor assembly. The combustor assembly is constructed of a inlet end portion, a outlet end portion and a plurality of combustor ring segments positioned between the end portions. A mounting assembly is positioned between the combustor assembly and the gas turbine engine housing to allow for the difference in the rate of thermal expansion while maintaining axially compressive force on the combustor assembly to maintain contact between the separate components.

Abstract: The gas generator comprises an annular main porous piece, at least one calibration lining for defining a flow rate of a first liquid propellant component that is injected through the porous piece towards a combustion chamber that is delimited by one of the faces of the porous piece, and means for radially injecting a flow of a second propellant component into the immediate proximity of the face of the porous piece that delimits the combustion chamber in such a manner as to cause the first and second propellant components to be mixed in the immediate proximity of the face of the porous piece that delimits the combustion chamber.

Abstract: In a heat shield on a load-bearing structure, the heat shield has a multiplicity of tiles which are in contact with the load-bearing structure, are adjacent one another for substantially covering an area and are fastened by means of approximately L-shaped metallic restraints that are anchored in grooves of the load-bearing structure. The restraints may be completely screened by hot sides of the tiles facing towards a hot fluid. It is also possible to avoid the use of expensive fastening devices for the restraints. The configuration of the heat shield on the load-bearing structure is very highly thermally load-resistant, simple to manufacture and does not expose the tiles to any stresses which could be critical with respect to the brittleness of the ceramic.

Abstract: A combustor assembly having a preestablished rate of thermal expansion is mounted within a gas turbine engine having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the combustor assembly. The combustor assembly is constructed of a inlet end portion, a outlet end portion and a plurality of combustor ring segments positioned between the end portions. A retaining ring is positioned radially adjacent the combustor ring segments to allow for thermal radial expansion of the combustor ring segments while maintaining radially compressive force on the combustor ring segments and distributing force evenly along the combustor ring.

Abstract: An afterburner assembly is disclosed in which the flameholder ring is for by plurality of flameholder ring segments, each segment being integrally formed with a generally radially extending arm. The flameholder ring segments extend beyond each opposite sides of the arm. The arm and flameholder ring segments are attached to the casing of the afterburner by a support element which is pivotally attached to the arm and fixedly attached to the afterburner casing. The distal end of the arm slidably contacts the casing defining the opposite side of the afterburner duct to enable the arm to slide relative to the casing to allow for differential thermal expansion of the respective elements. When each of the arm/flameholder ring segments are attached to the afterburner casing, the flameholder ring segments form a generally annular flameholder ring.

Abstract: A tube assembly, such as a flame tube for a gas turbine plant, includes a tube segment having an inner region for guiding a hot gas in one flow direction. A heat shield faces toward the inner region and includes a plurality of bricks being disposed side by side. At least one metal support frame supports the heat shield. The support frame has a plurality of conduits for supplying a cooling gas and a lip encompassing the tube segment and substantially covering the conduits toward the inner region leaving a slit for conducting the cooling gas from the conduits past the lip to the inner region.

Abstract: A gas turbine engine combustor liner with improved high temperature capability is achieved by embedding ceramic tiles into a fiber reinforced glass ceramic matrix composite substrate, so as to incorporate a space between the tiles and the substrate, the space serving to eliminate a direct heat conductive path between the tile and the substrate. The space is created by inserting a fugitive layer between the tiles and the substrate prior to compaction of the substrate, followed by removal of the fugitive layer. A fugitive material sprayed on the supportive region of the tiles prior to liner fabrication prevents the substrate material from bonding to the tiles, and prevents cracking of the tiles during temperature cycling.

Abstract: A mounting assembly includes an annular supporting flange disposed coaxially about a centerline axis which has a plurality of circumferentially spaced apart supporting holes therethrough. An annular liner is disposed coaxially with the supporting flange and includes a plurality of circumferentially spaced apart mounting holes aligned with respective ones of the supporting holes. Each of a plurality of mounting pins includes a proximal end fixedly joined to the supporting flange through a respective one of the supporting holes, and a distal end disposed through a respective one of the liner mounting holes for supporting the liner to the supporting flange while unrestrained differential thermal movement of the liner relative to the supporting flange.

Abstract: A support assembly for a gas turbine engine combustor includes an annular frame having a plurality of circumferentially spaced apart tenons, and an annular combustor liner disposed coaxially with the frame and including a plurality of circumferentially spaced apart tenons circumferentially adjoining respective ones of the frame tenons for radially and tangentially supporting the liner to the frame while allowing unrestrained differential thermal radial movement therebetween.

Abstract: A combustor includes a dome assembly having radially outer and inner liners joined thereto and defining therebetween a combustion zone. The dome assembly includes at least one annular dome having a pair of axially extending first flanges between which are disposed a plurality of circumferentially spaced apart carburetors for discharging a fuel/air mixture into the combustion zone for generating combustion gases. An annular heat shield includes a pair of axially extending legs integrally joined to a radially extending face in a generally U-shaped configuration, with the face including a plurality of circumferentially spaced apart ports disposed concentrically with perspective ones of the carburetors for allowing the fuel/air mixture to be discharged therefrom through the heat shield.

Abstract: A centerbody cup construction for use in a dry low NOx gas turbine combustor includes a pair of inner and outer generally cylindrical members, the inner member having a diverging cup portion attached to its forward end extending toward the outer cylindrical member, and a coolant manifold arranged between the inner and outer cylindrical members radially adjacent the centerbody cup portion.

Abstract: A fuel manifold is disclosed for providing fuel to a combustor disposed radially inside an annular casing. The manifold is disposed inside the casing and includes an arcuate manifold tube, a thermal insulation layer surrounding the tube, and a cover layer surrounding the insulation layer which is substantially rigid for protecting the insulation layer from physical damage.

Abstract: A high temperature ceramic/metallic turbine engine includes a metallic housing which journals a rotor member of the turbine engine. A ceramic disk-like shroud portion of the engine is supported on the metallic housing portion and maintains a close running clearance with the rotor member. A ceramic spacer assembly maintains the close running clearance of the shroud portion and rotor member despite differential thermal movements between the shroud portion and metallic housing portion.

Abstract: A cooling system including a cooling duct adjacent to the hot air duct of an air heater. The cooling duct includes a first wall and a second wall spaced from the first wall such that a passageway is formed therebetween. A wire mesh sheet is arranged in the duct passageway. The wire mesh sheet comprises a plurality of layers of wire mesh and has an undulate configuration which together with its density prevents substantial heat radiation from the first wall of the cooling duct to the second wall without significantly impeding airflow through the cooling duct. Cooling air introduced into the cooling duct flows through the duct, removes heat, radiated by the first wall and absorbed by the wire mesh sheet, and carries that heat away from the duct as it exits through the outlet opening. In this way, the system cools the first wall and prevents any significant heat transfer to the second wall of the cooling duct and elements in the vicinity thereof.

Abstract: In accordance with one aspect of the invention, a venturi having a heat shield along its inner diameter and a thermal barrier coating along its outer diameter is provided, whereby the temperature gradient of the venturi is lowered and metal distress and erosion caused by water injected therethrough is reduced. In an alternate embodiment, a floating insert is placed within an area along the venturi's inner diameter, where it is held in position by a heat shield.

Abstract: A mounting for a ceramic scroll on a metal engine block of a gas turbine engine includes a first ceramic ring and a pair of cross key connections between the first ceramic ring, the ceramic scroll, and the engine block. The cross key connections support the scroll on the engine block independent of relative radial thermal growth and for bodily movement toward an annular mounting shoulder on the engine. The scroll has an uninterrupted annular shoulder facing the mounting shoulder on the engine block. A second ceramic ring is captured between mounting shoulder and the uninterrupted shoulder on the scroll when the latter is bodily shifted toward the mouting shoulder to define a gas seal between the scroll and the engine block.

Abstract: An aircraft augmentor cooling blanket is provided, which is woven from flexible refractory ceramic fibers, which blanket is bonded to a cooling air supply support structure by a metal wire woven through a lower blanket portion and brazed to the support structure. The resulting liner is lightweight, readily accommodates thermal expansion and contraction and absorbs sonic screech energy.

Abstract: A gas turbine engine combustor is provided, having a single wall sheet metal liner which is generally annular in shape which may be corrugated and a multi-hole film cooling means which includes at least one pattern of a great many small closely spaced sharply downstream angled film cooling holes disposed essentially along portion of the liner to be cooled. Another embodiment provided a corrugated aircraft engine afterburner sheet metal liner having at least one pattern of great many small closely spaced sharply downstream angled film cooling holes disposed essentially along the entire surface of the liner.

Abstract: The structure consists of a composite material having a reinforcement texture and a matrix. The composition of the matrix varies practically without discontinuity, in the structure's thickness direction, from an essentially refractory material (13) in the region of the front face intended to be exposed to very high temperatures, up to a material that is essentially heat conductive (16). Cooling fluid circulation conduits (15) can be arranged within the structure at a portion where the matrix is essentially heat conductive.

Abstract: A combustor shield assembly is provided wherein a plurality of ceramic tiles are mounted on a ceramic support panel, which panel has a plurality of keyhole-shaped apertures therethrough to receive a plurality of ceramic tiles, each of which has a knob upstanding on a neck from the base or shield of such tile, each of the knobs being sized to fit through the larger end of the apertures, but not the smaller end thereof to provide a bearing and support surface for such knob and thus for the tiles. An apertured retaining panel is provided, having apertures slightly larger than the knobs, which panel is positioned over the top of the support panel with the apertures thereof around the respective knobs to secure the tiles in place in the support panel. A plurality of the so-assembled tiles on their respective support panel are mounted in spaced overlapping layers to a combustor liner so as to mount the tiles before the liner as a heat shield therefor.

Abstract: In a gas turbine engine, an annular flange of a ceramic scroll is clamped to an annular shoulder of a gas turbine engine housing by a plurality of nuts on thread rods extending perpendicular to the annular shoulder. A metal sleeve around each rod cooperates therewith in defining a coolant passage which is connected at one end to a source of compressed air and which discharges at the other end into a cooling chamber around the nuts through grooves in a surface of each nut. Air circulating in the coolant passages and through the cooling chamber cools and thermally shields the rods and the nuts.

Abstract: A heat protective lining for a passage in a turbojet engine is formed of tiles arranged side by side to form rings which are themselves arranged end to end. Each tile comprises a panel provided at its upstream and downstream edges with radially outwardly directed flanges forming circumferential stiffeners, the upstream flange having on its upstream radial face male securing and sealing means cooperating with complementary female means on the downstream radial face of the downstream flange of the adjacent upstream tile.

Abstract: The burner comprises a combustion chamber equipped with a flame retention cone. The flame retention cone comprises a diverging jacket with orifices for the passage of oxygen-carrier gas. A fuel lance provided with radially arranged exit openings has its outlet in an upstream inlet section of the flame retention cone. An igniter is arranged in an oxygen-carrier gas duct outside an ignition opening provided in the area of the fuel lance exit openings. The combustion chamber is accommodated inside an outer tube. The downstream ends of the combustion chamber and the outer tube enclose openings spaced, relative to each other, in the circumferential direction to allow the exit of oxygen-carrier gas. The burner provides for flame stability and low-polluting combustion.

Abstract: A hot gas overheat protection device is provided for gas turbine engines and the like. An outer metal wall having cooling air supplied through cooling holes therethrough from the outside is shielded from hot gas flow by the provision of highly temperature resistant lining wall elements spaced from the metal wall. A thin metal skin is provided between the metal wall and the wall elements defining intermediate spaces communicating with cooling air ports in the metal wall. The thin metal skin has a melting point equal to or lower than that of the metal wall so as to provide for fusion or rupture of the thin metal skin in the event the insulating wall elements are locally ruptured, whereby the cooling air is provided through the cooling air ports in a direction against the flow of hot gases to thereby mitigate the effects of the rupture and protect the metal wall.

Abstract: A surface, of an inner sleeve of a combustion apparatus for a gas turbine, which is subjected to a flame radiation heat is coated with a ceramic coating. A coating which is superior in high temperature corrosion resistant characteristics to a metal material forming the inner sleeve is provided on the opposite surface of the inner sleeve. Thus, heat transferred to the inner sleeve by the radiation from the flame is shielded by the ceramic coating. A formation of oxides on the coating of the corrosion resistant metal material formed on the opposite surface of the sleeve is prevented. A heat release through the surface from the metal material forming the inner sleeve is enhanced, whereby a thermal stress generated in the inner sleeve is suppressed to thereby prevent a generation of a cracks.

Abstract: Improved performance in a hot gas generator 10 is achieved by providing a pair of hemispherical liners 22 and 24 loosely positioned within an interior wall 14 of a vessel 12 so as to be disposed above a combustion chamber 20 therein. The hemispherical liners 22 and 24 normally have a groove 26 at an interface therebetween and are formed of a material adapted to thermally expand under heat. Specifically, the hemispherical liners 22 and 24 expand to close the groove 26 at the interface in a manner producing relatively little stress thereon.

Abstract: In a staged low NOx lean premix hot wall gas turbine combustor, the interior wall of the combustor is maintained at or near the flame temperature to provide stable operation over a wide range of heat release values. One or more stages of the staged combustor includes a Stirred Reactor region followed by a Plug Flow Reactor region. In one embodiment, a lean premixture of fuel and air is inducted tangentially into an annular intake manifold for inducting a cyclonic flow of the premixture into the combustion chamber. In another embodiment, the Stirred Reactor region is developed by colliding, preferably head-on, a plurality of jets of lean premixture within the combustion chamber.

Abstract: A staged low NO.sub.x gas turbine combustor includes a refractory fibrous thermally insulatively lined primary combustion chamber, operating fuel-rich, and exhausting through a throat into a metallic secondary combustion chamber containing a fuel-lean secondary combustion zone in which combustion is completed. A radiation cooling zone is provided intermediate the throat and secondary combustion zone for cooling of the primary combustion products before quick quench in the secondary combustion zone. The fibrous lining of the primary combustion chamber is densified at its interior surface with a refractory such as zirconia or silicon carbide to inhibit flame erosion. The liner is wrapped with a supportive compliant blanket of fibrous refractory insulation. Air cooling of the metallic wall of the secondary chamber surrounding the radiation cooling zone is intensified relative to the remainder of the secondary combustion chamber.

Abstract: A combustion chamber arrangement for gas turbine propulsion units with a flame tube of ceramic material which is surrounded by a metallic wall while leaving free an intermediate space; the flame tube is composed of ring-shaped parts whereby sheet metal mounting members are so arranged between the outer walls of which and the metallic walls, especially of a housing without heat contact to the parts of the flame tube that a first and a second intermediate space for peripheral partial flows of cooling air is formed.

Abstract: Carbon build-up in a hot gas generator is avoided in a construction including a vessel 24 having a narrow inlet end 26, a narrow outlet end 28 and an intermediate, relatively wide, combustion chamber 30 by either disposing a heat shield 50 on the interior surface 48 of the combustion chamber 30 or locating a flow path 54 for coolant about the exterior surface 52 of the vessel 24, or both.

Abstract: An aircraft emergency power unit having a high pressure air storage tank, an aviation fuel storage tank, and a combustor which combusts pressurized air and aviation fuel in a stoichiometrically fuel rich ratio to produce a motive combustion gas.

Abstract: A combustion chamber liner having a layer of refractory material, a layer of metallic material, means to adaptably fix the layer of refractory material to the layer of metallic material and a means for internally cooling the liner. The means to adaptably fix the layer of refractory material to the layer of metallic material allows both layers to expand and contract separately without risk of damaging the liner because of different thermal expansion rates. The means for internally cooling the liner allows the liner to operate at higher temperatures and increases the useful life of the liner.

Abstract: A combustion chamber liner has three layers; a first ceramic layer, a second filamentary steel wool type layer and a third metallic layer. The interior of the liner is cooled by passages in the third layer and emergency or failure activated cooling occurs in a damaged area in the first layer. Sensor means can be placed in the liner or externally of the liner to detect changes in the coolant flow or pressure and thereby detect a failure in the liner.

Abstract: A low-NO.sub.x combustor is provided with a rich, primary burn zone and a lean, secondary burn zone. NO.sub.x formation is inhibited in the rich burn zone by an oxygen deficiency and in the lean burn zone by a low combustion reaction temperature.

Abstract: Each panel of the louver liner of the combustor of a gas turbine engine is coated with a ceramic composition on the surface adjacent the combustion zone with a tapered end at the lip of the cooling air film generating mechanism. A second taper may be incorporated at the back side of the lip of the next adjacent cooling air film generating mechanism.

Abstract: A carbon film is formed on a ceramic element, or a metal film is formed on the carbon film, and subsequently the ceramic element is bonded to another ceramic or metal element, thereby forming a composite article. The composite article has a high bonding strength and is hardly fractured at joint. Ceramic articles having a surface coating of a hard carbon film or a hard carbon film containing metal grains can also be formed by this process.

Abstract: A burner for the operation of premixing burners, with gaseous fuels or vaporized fuels for the production in a mixer pipe of a homogeneous mixture comprising the fuel, the quantity of combustion air required for the complete combustion of the fuel and additional cooling gas as needed for combustion between 1,100.degree. and 1,700.degree. C. This mixture flows to a burner head with a widening cross-section and a burner plate at the wide end where it is burnt at a central main flame bore arranged at the burner plate and several surrounding support flame bores. The flames then pass through a converging burner mouth and a downstream flame guard which protects the flames against the entrance of air or flue gas from the environment, against cooling and against heating until the completion of combustion. The burner mouth and the flame guard are coated by a non-catalytic material.

Abstract: A radial lip of a high temperature combustor liner is mechanically locked in a radially directed capture slot in a supporting shell of a combustor. In one embodiment, the capture slot is formed at abutting edges of shell sections which are joined by a weld bead. The weld bead is accessible for grinding off to provide access to the liner for replacement. In embodiments in which a plurality of liner sections are employed, a downstream end of a liner section overlaps and shields an upstream end of an adjacent liner section including the radial lip thereof to protect the radial lip and capture slot from temperatures in the combustion zone and to channel a sheet flow of film cooling air along an inner surface of the adjacent liner. Positioning bosses may be included between adjacent liner sections for centering.

Abstract: A burner for the operation of premixing burners, with gaseous fuels or vaporized fuels for the production in a mixer pipe of a homogeneous mixture comprising the fuel, the quantity of combustion air required for the complete combustion of the fuel and additional cooling gas as needed for combustion between 1,100.degree. and 1,700.degree. C. This mixture flows to a burner head with a widening cross-section and a burner plate at the wide end where it is burnt at a central main flame bore arranged at the burner plate and several surrounding support flame bores. The flames then pass through a converging burner mouth and a downstream flame guard which protects the flames against the entrance of air or flue gas from the environment, against cooling and against heating until the completion of combustion. The burner mouth and the flame guard are coated by a non-catalytic material.

Abstract: The invention is concerned with the problem of joining ceramic components to metal components.A composite ceramic-metal component is proposed, e.g. a rotor disc for a gas turbine engine (see FIG. 2), in which the main body of the component is made from a ceramic, e.g. Silicon Nitride, but the areas at which attachment is to be made to a metal component is formed from metal compacted onto the ceramic by a hot isostatic pressing process.The method of manufacture described is to form a ceramic core with holes appropriately positioned in it where a connection is to be made to another component, surround the core with a powdered metal, e.g. a Nickel-based superalloy, ensuring that the holes also fill with powder, compacting the powder by hot isostatic pressing, and then machining away unwanted metal.

Abstract: A combustion chamber for gas turbines, especially for motor vehicles, which includes a first reaction chamber, an outlet opening of which terminates in a second coaxially disposed reaction chamber. Each reaction chamber is associated with a premixing chamber provided with an air inlet and a fuel injection nozzle. An insert surrounds the first reaction chamber and its premixing chamber and projects into a flame tube. The flame tube encompasses the second reaction chamber and an outer wall of the insert forms with an inner wall of the flame tube an annular premixing chamber for the second reaction chamber. Several fuel injection nozzles are arranged in a zone of the air inlet of the second reaction chamber.

Abstract: A thermal shield structure with ceramic blocks for protecting high-temperature-exposed wall surface in which wedge-shaped supporting members and wedge-shaped members to be supported, respectively provided on the wall surface and ceramics blocks as a plurality of pairs of wedge-groove couplings, are engaged with each other to cover the wall surface with the ceramic blocks. In accordance with the invention, a gap small enough to prevent mutual disengagement of each pair of the wedge-shaped supporting member and the wedge-shaped supported member is provided therebetween to permit movement of the ceramic blocks towards the wall surface. A passage for an air supply into each wedge-shaped supporting member is provided so that each wedge-shaped supported member is urged by the pressure of supplied air to be retained in the wedge-shaped supporting member, whereby the ceramic blocks are held on the wall surface.

Abstract: A heat shield assembly 10 for attachment to an afterburner liner 18. The heat shield assembly 10 comprises a clamp 14 and an optional support bracket 16 which hold a carbon-carbon panel 12 adjacent to the liner 18. The carbon-carbon panel shields a damaged area 20 of the liner in order to extend the liner's service life.