Abstract: A method for producing an additively manufactured object includes melting and solidifying a filler metal to form weld beads and depositing the weld beads adjoining each other, thereby forming a weld-bead layer, and repeatedly depositing a next weld-bead layer on the formed weld-bead layer to conduct additive manufacturing. The method includes a bead formation step of forming a new weld bead so as to fill a recess formed by at least three of the already formed weld beads, in a cross-section perpendicular to a longitudinal direction of the weld beads.

Abstract: Power generation systems comprising modular blades and a secondary power source, and methods of manufacturing the same employing additive manufacturing. Various features of the system are described, including a rotor, spoke and support base. A slip gear assembly is described to coordinate the wiring of the secondary power sources.

Abstract: A rotor shaft for a turbine rotor of a turbine, in particular a steam turbine, having a shaft main body made of a first material and at least one ring which is made of a second material and is attached to the shaft main body, wherein the second material has equal or greater strength and/or greater corrosion resistance than the first material, wherein at least one blade slot is formed on the ring, and wherein the ring is materially bonded to the shaft main body by narrow-gap welding.

Abstract: The invention relates to a method for preparing a fiber-reinforced article, having attached to at least part of its surface a layer of a material that is not fiber-reinforced, comprising the steps of 1) preparing a shell via an additive manufacturing technique, the shell—being of a material that is not fiber-reinforced; and—having a surface that corresponds in negative relief to a surface of the article formed in step 3); thereafter 10 2) applying—long and/or continuous reinforcement fibers; and—a curable resin to the surface of the shell that is in negative relief, to form a mixture of curable resin and long and/or continuous reinforcement fibers on the 1 surface of the shell, so that the surface of the mixture contacting the shell adopts the shape of the surface of the shell that is in negative relief; thereafter 3) curing the curable resin to form the fiber-reinforced article having attached to at least part of its surface a layer of a material that is not 20 fiber-reinforced.

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side, a cold side and at least one attachment mechanism having a stud and a central axis extending through the stud and a plurality of standoff pins positioned circumferentially around the stud, the standoff pins having a radial extent, a circumferential extent that is greater than the radial extent, a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape.

Abstract: A system includes a laser-line imaging subsystem to measure a feature. The laser-line imaging subsystem includes a laser to project a laser-line, and a digital video camera mounted at an angle with respect to an axis of said laser to obtain an optical image of the laser-line. A control subsystem is operable to compute three-dimensional coordinate points via triangulation of an intersection between the laser-line and the optical image of the laser-line, the three-dimensional coordinate points data used by the control subsystem to calculate predictive airflow through the workpiece with respect to the volume of the machined holes.

Abstract: A repair system includes a 3D-object repair apparatus and a repair-data providing apparatus. The repair-data providing apparatus includes: a damaged-part determining part to determine a location of the damaged part of the object to be repaired by comparing 3D-object data of the object to be repaired obtained by the scanner and 3D-object data of an original of the object to be repaired; a mode selecting part to select a repair mode from among a first repair mode of repairing only the damaged part of the object to be repaired and a second repair mode of repairing a range broader than the damaged part of the object to be repaired, the range including the damaged part, in accordance with a condition of a damaged surface of the object to be repaired; and a repair-data generating part to generate the 3D-object repair data corresponding to the selected repair mode.

Abstract: An apparatus and method for servicing a combustion liner in a combustion case of a turbine is provided. The apparatus includes an elongated bar having a handle at one end and a force applying member at an opposing end of the elongated bar. An attachment member is configured for attachment to a flange of the combustion case. The attachment member is also configured for pivotal attachment to the elongated bar. The apparatus is configured to apply a radially outward force on a downstream portion of the combustion liner when a radially inward force is applied to the handle.

Abstract: Engine blocks and methods of forming engine blocks are disclosed. The engine block may include a cast aluminum body and a plurality of cast-in liners. Each cast-in liner may include (a) an outer layer of 2xxx-series aluminum molecularly bonded to the cast aluminum body and (b) an inner layer directly contacting the outer layer and forming at least a portion of an engine bore. The inner layer may be a wear-resistant coating, such as a steel coating. The method may include extruding an elongated 2xxx-series aluminum extrusion having an inner cavity bounded by an inner surface and applying a wear-resistant coating to the inner surface. The extrusion may be sectioned into a plurality of cylinder liners and the cylinder liners may be into an aluminum engine block such that each cast-in liner forms at least a portion of an inner surface of an engine bore in the engine block.

Abstract: The invention relates to a repair method for a component and includes the steps of removal of a damaged region of the component with the formation of at least one separating surface; arrangement of the component in a processing chamber of a device for the additive restoration of at least the region of the component that has been removed; determining first structural data of the component disposed in the processing chamber; providing second structural data of the component; determining third structural data based on the first and the second structural data; and additive restoration of the component region that has been removed on the at least one separating surface of the component. In addition, the invention relates to a device for the additive repair of a component.

Abstract: A device for circulation of air for a turbomachine, the device including an inlet provided to receive incident airflow, air circulation ducts connected to the inlet, a central part including side walls, peripheral walls arranged at a distance from the central part, so as to form the air circulation ducts, each duct being arranged between one of the side walls of the central part and one of the peripheral walls, each peripheral wall including an upstream end portion delimiting with one of the side walls an inlet orifice of one of the ducts and a downstream end portion delimiting with one of the side walls an outlet orifice of one of the ducts, at least one member mobile in translation relative to the peripheral walls, the at least one mobile member being formed in the central part and arranged so that its displacement varies a section of each of the inlet orifices and a section of at least one of the outlet orifices.

Abstract: A vehicle exhaust system includes a mixer having an inlet that receives engine exhaust gases and an outlet to direct swirling engine exhaust gas to a downstream exhaust component. The mixer has a plurality of internal surfaces that come into contact with the engine exhaust gases. At least one of the internal surfaces has a coating comprised of a low-coefficient of friction material.

Abstract: A fluid pulse valve and a method of using the fluid pulse valve are disclosed. The fluid pulse valve comprises an outer housing, a rotor contained within the outer housing, a stator tube surrounding the rotor and adjacent to the outer housing, the stator tube comprising a plurality of slots, and a closer coaxially and rotationally coupled to the rotor and at least a portion of the closer in line with the plurality of slots. As the closer rotates, the closer covers and uncovers the plurality of slots to create a pulse.

Abstract: A fastening system and method to removably attach change part components to a capping or filling machine in order to adapt a general purpose machine for use with a specific size or shape container. The fastening system and method uses magnetic forces to pull component parts into alignment and to interlock portions of interchangeable components. In addition, a blocking component is interposed between two other interchangeable component parts or within mushroom slots, securing the components in place, aided by biasing magnets. This system and method relies on a combination of mechanical and magnetic forces by using mechanical forces to reinforce or supplement biasing magnetic forces, and vice versa, creating a durable connection that will withstand the rigors of the filling and capping process, yet which is simple to assemble and disassemble without tools. The less intricate component parts are less prone to damage during assembly, use, or disassembly.

Abstract: A driveshaft vessel assembly for a gas turbine engine is disclosed. The driveshaft vessel assembly comprises a driveshaft vessel and an outlet guide vane. The driveshaft vessel includes a forward face, an aft face, and opposing side faces and is configured to house at least a portion of a radial driveshaft. The outlet guide vane includes a leading edge and a trailing edge. The length of the trailing edge is substantially equal to a length of the forward face of the driveshaft vessel such that the trailing edge of the outlet guide vane is faired into the forward face of the driveshaft vessel.

Abstract: A system and method of fabricating a percussion tool that includes a choke valve that is replaceable and/or maintainable without disassembly of the percussion tool. The flow tube includes inner and outer walls and at least one opening formed in the outer wall. The inner wall extends from a top end of the flow tube to a bottom end of the flow tube and defines a central channel therein. The outer wall extends from the top end towards the bottom end, surrounds a portion of the inner wall, and defines an outer channel with the inner wall. The choke is positioned at the top end over the central channel and regulate a fluid flow therethrough. A check valve is positioned in fluid communication with the choke.

Abstract: An apparatus, system, and method of fabricating a percussion tool that includes a flow tube. The flow tube includes upper and lower portions, inner and outer walls, and at least one opening formed in the outer wall. The upper portion extends from a top end towards a bottom end. The lower portion extends from the upper portion to the bottom end. The inner wall extends from the top end to the bottom end and defines a central channel therein. The outer wall extends from the top end towards the bottom end, surrounds a portion of the inner wall and defines an outer channel with the inner wall. The opening is fluidly communicable with a first conduit formed within a piston, which surrounds a portion of the flow tube, when in an up position and is fluidly communicable with a second conduit formed within the piston when in a down position.

Abstract: One embodiment includes a pivot thrust reverser comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator.

Abstract: An engine strut for providing fan hub frame structural support and monitoring an air flow within an aircraft engine includes an airfoil coupled to the aircraft engine and has a first portion and a second portion. The first portion is positioned upstream of the second portion with respect to the air flow. A shield is coupled to the engine and positioned between the first portion and the second portion. The shield includes a first side spaced from the first portion and defining a first flow path with the first portion. The shield further includes a second side spaced from the second portion and defining a second flow path with the second portion. At least one sensor is coupled to the aircraft engine and positioned in flow communication with the second flow path.

Abstract: A method of assembling an enclosure of a gas turbine is provided. The method includes disposing gas turbine equipment in an interior of a frame at a first site, connecting wall panels to the frame to form a pre-assembled module at the first site, shipping the pre-assembled module from the first site to a second site and disposing the pre-assembled module proximate to the gas turbine such that the gas turbine equipment is exposed for connection to the gas turbine and a portion of the wall panels form a portion of an outer enclosure of the gas turbine and the gas turbine equipment.

Abstract: A gas turbine combustion chamber with an inner housing and an outer housing the inner housing having an inner wall element with a first hole arrangement and a second hole arrangement is provided. The inner wall element envelopes a burner volume. The first hole arrangement has first holes arranged in a first areal density, the second hole arrangement has second holes arranged in a second areal density. The outer housing has an outer wall element with a further first hole arrangement and a further second hole arrangement. The outer wall element of the outer housing envelops the inner wall element of the inner housing so that a gap in between is formed. The further first hole arrangement has further first holes arranged in a further first areal density, the further second hole arrangement has further second holes arranged in a further second areal density.

Abstract: A method for assembling an actuating ram of air bleed valves, which ram is placed between low pressure and high pressure compressors of a turbomachine, the ram including a piston rod surrounded by a spacer extending from the piston cylinder and configured to be connected to an end of the transmission mechanism linked to the bleed valves, the method including: deploying the piston rod such that it projects from the spacer; connecting the projecting piston rod to the end of the transmission mechanism; retracting the piston rod to bring the cylinder closer to the case wall; and attaching the spacer to the case wall.

Abstract: A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions.

Abstract: A turbine housing includes a turbine inlet plenum and a turbine housing body. The turbine housing body includes a turbine outlet mounting face, a seal plate mounting face, and a center bore formed between the turbine outlet mounting face and the seal plate mounting face. A first support is formed about the turbine inlet plenum and in contact with the turbine housing body. A relief pocket is formed in the first support proximate the seal plate mounting face. The relief pocket is formed at a first distance from a turbine housing center axis of the center bore and at a first depth relative to the seal plate mounting face. A ratio of the first distance to the first depth is between 2.66 and 2.90.

Abstract: A damper bearing assembly for a gas turbine engine is disclosed. The damper bearing assembly is designed to define forward and aft axial gaps which allow for normal deflection under standard operating thrust loads, but then close during a fan blade out event to allow the increased load to transfer to the damper housing. Frictional forces between contacting parts limit torsional windup and increase torsional resistance with increasing load. The damper bearing assembly includes a damper housing configured substantially within a U-shaped spring finger housing and a spanner nut with a radial hook portion coupled to the spring finger housing. The damper housing is coupled to the spring finger housing such that it is substantially confined within the U-shaped void. The spanner nut is coupled to the spring finger housing such that the radial hook portion is configured to limit the deflection of the spring finger housing and damper housing during a fan blade out event.

Abstract: A flexible coupling for a gas turbine engine includes a fan hub frame having a first flange and a core engine having a second flange. The first flange includes a first plurality of fingers extending from a face of the flange and the second flange includes a second plurality of fingers extending from a face of the second flange. The second plurality of fingers of the second flange is complementary to the first plurality of fingers extending from the first flange. The first flange and the second flange are coupled together in form-fitting engagement such that the first plurality of fingers and the second plurality of fingers form an interdigitated configuration.

Abstract: Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided.

Abstract: A method of fabricating a near-net shape erosion shield, a method of forming a shielded article, and a near-net shape erosion shield are provided. The method of fabricating a near-net shape erosion shield includes providing a base, positioning an energy source relative to the base, and depositing at least one wear resistant material over the base with an energy beam from the energy source. The at least one wear resistant material deposited on the base forms the near-net shape erosion shield configured to be positioned on a turbine component. The method of forming a shielded article includes removing the base from the near-net shape erosion shield, and securing the near-net shape erosion shield to a turbine component. The near-net shape erosion shield includes a near-net shape erosion-resistant portion configured to be positioned on a turbine component.

Abstract: A retaining clip for use in limiting radial movement between a first section and a second section of a split fairing is provided. The first section includes a first clip tab and the second section includes a second clip tab extending therefrom, wherein the first and second clip tabs form a slot when the first section and the second section are substantially aligned. The retaining clip includes a first portion sized for insertion into the slot, a third portion coupled to the first and second clip tabs such that the first and second clip tabs are positioned between the first portion and the third portion, and a second portion extending between the first portion and the third portion.

Abstract: A method and a device for orienting an actuator of an exhaust-gas turbocharger which has an actuator that is equipped with an actuator housing and is connected to a control rod. First, an actuator holder is fastened to the compressor housing of the exhaust-gas turbocharger. Then the actuator is inserted into the actuator holder. Then the actuator is positioned within the actuator holder. Then a compensating material is introduced through an injection opening into a compensating-material receiving space which is provided in the actuator holder. Finally, the compensating material is hardened.

Abstract: A seismic land vibrator, comprising a baseplate comprising a substantially flat, rigid member; at least one driven member that is connected with the baseplate and extends in a direction that is substantially perpendicular to baseplate; a rotation sensor that is coupled to the baseplate and adapted to provide a signal that is indicative of rotational movement of at least a portion of the baseplate.

Abstract: The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure. A drive member may be accessible near a second end of the elongated body, and the drive member may be configured to rotate within the elongated body and to drive the movable arm along a longitudinal axis of the elongated body toward the second end to separate the tubular structure from the second combustor.

Abstract: A stage of a space launcher including an engine core, a tank secured above the engine core, and a nozzle including a first deployable nozzle section secured below the engine core, the nozzle further including a second and a third section configured to be situated extending from each other when the nozzle is in a deployed propulsion configuration. The stage further includes a structure for temporarily supporting nozzle sections mounted on the tank, configured to change the nozzle to a configuration for accessing the engine core wherein the nozzle sections are inserted into each other, with the third section bearing against a lower support of the temporary structure.

Abstract: A method for casting a collar (44, 46) for a heat shield (36) of a strut (32) in a gas turbine exhaust section (20). A casting geometry (60, 70) is defined with extra wall thickness (56, 68) in an area of wall curvature (53, 54), which provides a flow path beyond a final geometry of the collar to facilitate a flow of molten metal in the mold (63, 64). The extra thickness is removed after casting, leaving the collar in its final geometry, which may have uniform wall thickness (T, T2). The extra thickness in the casting geometry may be provided by increased radius (R3) in the wall curvature and/or by casting feed portals (66, 68) that span the wall curvature between a tubular portion (50) and a flange (52) of the collar.

Abstract: A long-duct mixed-flow nozzle system for a turbofan engine, the nozzle system may include an inner housing configured to enclose a core and form a core flow duct, the inner housing terminating in a core nozzle having a core exit aperture, an outer housing forming a fan flow duct and terminating in a fan exit aperture at a location downstream of the core exit aperture, the fan exit aperture having a plurality of chevrons, and the core exit aperture having a plurality of chutes separated by radially extending lobes configured to mix exhaust gas from the core flow duct with bypass gas flow in the fan flow duct, the radially extending lobes varying in profile from each other.

Abstract: A method for retrofitting an already existing gas turbine power plant is provided. The method features at least the following steps: fluidically connecting a gas turbine to a flue gas duct which is suitable for conducting flue gas which is produced by the gas turbine; connecting the flue gas duct to a steam generating unit which is fluidically connected to a water-steam cycle, and via which water-steam cycle a power generating facility can be operated; fluidically connecting a CO2 separation apparatus to the flue gas duct for separating the CO2 from the flue gas in the flue gas duct; and electrically connecting the power generating facility to the CO2 separation apparatus, preferably for the essentially energy-autonomous operation of the CO2 separation apparatus.

Abstract: A torque converter is provided. The torque converter includes a plurality of arc springs and a turbine shell defining a pocket receiving the plurality of arc springs. The turbine shell may further include a rounded portion supporting turbine blades, an outer radial portion extending radially from the rounded portion and an axial extension extending axially from the outer radial portion. The rounded portion, the outer radial portion and the axial extension may define the pocket. A method for forming a drive assembly for a torque converter is also provided.

Abstract: A dual flow check valve includes a valve body having an inner valve cavity, a first valve opening, and a second valve opening. The dual flow check valve further includes a seal disposed within the valve body. The seal is operatively coupled within the valve body such that the seal is configured to move relative to the valve body between an open position, in which the seal allows the gas to flow between the first and second valve openings through the inner valve cavity, and a closed position, in which the seal inhibits the gas and the liquid from flowing through the inner valve cavity from the first valve opening to the second valve opening.

Abstract: A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.

Abstract: The invention relates to a process for producing an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine. The insulation element (12) is produced from a solid body (24) provided with a metallic shell (26), the solid body (24) consisting at least partially of a ceramic material. The invention also relates to an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine, and to an aero engine having a housing (10), in which at least one insulation element (12) is arranged radially above at least one guide vane (14).

Abstract: A method is provided for solid-propellant engines to be dismantled safely and in accordance with environmental standards having been scrapped. For each engine to be dismantled, it is mounted on a static test rig, immersed in a tank filled with water and started such that propellant is used up under the water. The soluble part of the combustion products (gases or condensates) thus remains trapped in the water in the tank while the non-soluble solid products drop to the bottom of the tank. The body of the engine emptied of its fuel in this way and rendered pyrotechnically inert is then taken apart or disassembled. Periodically, the water in the tank is withdrawn and the tank stripped of its deposits such that subsequent dismantling operations can be carried out under proper conditions. All of the combustion products recovered are sent to appropriate reprocessing plants. The method allows high dismantling rates.

Abstract: A method for mounting and setting an actuator of an exhaust gas turbocharger and a suitable electric actuating device are provided. The actuating device has an axially movable actuating rod which is connected to a coupling element which for its part is connected via a pivot pin to an actuation section of a bypass valve, the actuation section being configured as a lever arm. In order to set the desired closed position of the bypass valve during a predefined actuation of the actuating device, the coupling element is first connected to the actuating rod while still being displaceable. Before the fixing, the position of the actuating device which corresponds to the closed position is set by application of the corresponding voltage to the electric actuating device. Subsequently, a prestressing force is applied to the coupling element coaxially with respect to the actuating rod via a pneumatic actuator.

Abstract: A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure. The nosecone includes at least a first tool hole extending through the nosecone. The first tool hole is structurally reinforced.

Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.

Abstract: The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26).

Abstract: A gas turbine engine combustor includes an exit duct having annular first and second exit duct walls radially spaced apart to define therebetween the combustor exit opening. The first and/or second exit duct walls has a double-skin wall section which includes an inner hot wall facing the combustor exit opening and an outer cold wall fastened to the inner hot wall and radially spaced away therefrom to define a radial gap therebetween. The outer cold wall has a coefficient of thermal expansion greater than that of the inner hot wall. This helps reduce thermal growth mismatch between the outer cold wall and the inner hot wall during operation of the combustor, and reduces thermal stress at the joint between the hot and cold walls.

Abstract: An aircraft propulsion power plant for use in an aircraft includes one or more core engines housed in an airframe of the aircraft, one or more secondary propulsion units, each of the one or more secondary propulsion units being removably attached to the airframe, and one or more power transmission means, each of the one or more power transmission means being configured to transmit mechanical power from the or each core engine to a corresponding one of the or each secondary propulsion unit when the or each secondary propulsion unit is attached to the airframe.

Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.

Abstract: A turbomachine fuel-air mixer component includes a first component portion formed from a non-additive manufacturing process. The first component portion includes a plurality of tube elements each having an end portion. A second, additively manufactured component portion is additively joined to the first component portion. The second, additively manufactured component portion includes a plurality of additively manufactured tube sections constructed at, and fluidically connected with, respective ones of each end portion of the plurality of tube elements. The first and second component portions collectively defining at least a portion of the turbomachine fuel-air mixer component.

Abstract: A cooling system for use in a turbine assembly is provided. The cooling system includes a first filter configured to remove particles entrained in a flow of intake air, an array of nozzles downstream from the first filter, and a second filter downstream from the array. The array of nozzles is configured to facilitate reducing a temperature of the intake air, and the second filter is configured to repel cooling liquid discharged from the array of nozzles while allowing cooled intake air to flow therethrough.