Abstract: A piping assembly and a method for connecting an inner shell and an outer shell in a turbine system are disclosed. The piping assembly includes an inner fitting for connection to the inner shell and an outer fitting for connection to the outer shell. The piping assembly further includes an attenuation member extending between the inner fitting and the outer fitting and comprising an attenuation curve. The attenuation curve permits movement of the attenuation member in at least one of a longitudinal direction, a radial direction, or a tangential direction.

Abstract: A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.

Abstract: A turbocharger assembly includes a compressor assembly, a turbine wheel, a shaft, a bearing assembly, and a cooling gas conduit. The compressor assembly includes a compressor impeller. The compressor impeller includes an outermost impeller edge and has a maximum cross-sectional dimension at the outermost impeller edge. The shaft interconnects the compressor impeller and the turbine wheel. The bearing assembly surrounds at least a portion of the shaft. The cooling gas conduit is disposed in fluid communication with the compressor assembly and the bearing assembly. At least a portion of the cooling gas conduit is disposed adjacent the outermost impeller edge such that the cooling gas conduit is configured to receive a portion of intake gases flowing along the outermost impeller edge and guide the portion of the intake gases toward the bearing assembly to cool the bearing assembly.

Abstract: A power generating bearing assembly providing a bearing retained by a bearing housing. The bearing housing includes a bearing cooling passage system having at least one integrated liquid cooling passage integrated within the bearing housing. A turbine receiving bore is formed through the bearing housing, penetrating the integrated liquid cooling segment. A turbine assembly is inserted into the turbine receiving bore, positioning a turbine blade subassembly of the turbine assembly within the integrated liquid cooling passage, wherein fluid flowing within the integrated liquid cooling passage causes the blade subassembly to rotate. The rotation of the blade subassembly rotates an electric power generator to create electric power. The turbine assembly can include an electro-magnetic subassembly mounting plate, wherein the turbine subassembly is located on an interior surface of the mounting plate and at least a portion of the power generating portion located on an exterior portion of the mounting plate.

Abstract: The main purpose of the invention is an interface device (1) between first (2) and second (3) turbomachine elements, characterised in that it comprises an annular air inlet structure (4) comprising opposite first (5) and second (6) parts, designed to come into contact with first (2) and second (3) turbomachine elements respectively, the first part (5) being configured to be in swivel contact with the first element (2), and an elastic return device (7) that can be placed around the air inlet structure (4) and designed to come into contact with at least the first turbomachine element (2).

Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.

Abstract: A heat exchange arrangement for a gas turbine engine. The arrangement includes a first conduit for an engine component cooling fluid and a second conduit for a second fluid. The arrangement further includes a heat exchange portion in which fluids flowing through the first and second conduits are in a heat exchange relationship. A valve is provided, which is configured to moderate the mass flow rate of one of the fluids through the heat exchange portion. The arrangement includes divert valve in the first conduit which diverts flow to the second conduit as the flow in the second conduit is moderated to reduce thermal shock in the heat exchange portion.

Abstract: A seal segment for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits, wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous path between an inlet on the outboard side of the plate and an exhaust.

Abstract: The present application relates to a bladed stator of a turbomachine compressor, configured to straighten an annular stream of the turbomachine. The stator includes at least one annular wall configured to define the annular stream, a row of blades extending radially from the annular wall and means of pressurizing in communication with the annular stream. The means of pressurizing are configured to pressurize a chamber which is separated from a lubrication housing by a labyrinth seal. The means of pressurizing comprise at least one passage extending through the thickness of the annular wall and connecting with the annular stream. The means of pressurizing further includes at least one scoop in communication with the passage and the annular stream. The scoop is open upstream so as to capture the dynamic pressure of the annular stream.

Abstract: A method for designing an air cooled turbine airfoil includes selecting a number of different internal cooling air circuits, forming a ceramic core for each of the different cooling air circuits, forming a metal airfoil over each of the ceramic cores, leaching away the ceramic cores, mounting the airfoils in a stage of a turbine, passing a hot gas stream through the turbine, passing cooling air through each of the airfoils, and measuring a pressure and temperature differential across each of the airfoils to determine which cooling air circuit has the best performance.

Abstract: A heat exchanger arrangement for a gas turbine engine. The arrangement including a flow path within an outer cowl, which flow path locates a heat exchanger part way therealong. A valve is provided at an inlet end of the flow path to selectively receive fluid into the flow path from outside of the cowl and/or from a pressurized fluid flow. An exit from the flow path includes a plenum chamber to receive exhausted coolant flows from the heat exchanger and possibly other exhaust flows. The heat exchanger exhaust flow is then utilized to provide cooling to engine structures.

Abstract: A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.

Abstract: A seal is provided between first and second relatively movable members. The seal comprises a liner attached to the first relatively movable member which liner is abraded by the second relatively movable member. The abradable liner comprises a metallic, open porous structure formed by fusing a metallic feedstock with an energy beam to build up sequential deposits of the fused feedstock.

Abstract: A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more air amplifiers positioned in a turbine case. An exhaust outlet of the air amplifier may extend into a cavity created by a turbine case and may be configured to exhaust air in a generally circumferential direction to entrain air within the cavity to flow circumferentially to establish a consistent air temperature within the cavity thereby preventing uneven cooling of turbine engine components after shutdown and prevent damage to turbine components during a warm restart.

Abstract: An industrial engine turbine stator vane with a three-pass aft flowing serpentine cooling circuit and turn channels formed outside of the endwalls that connect adjacent legs of the serpentine flow circuit. A ceramic core used to cast the vane includes dual print-outs extending from the turn channel forming pieces that provide a more rigid core structure to prevent core shift or movement during casting. The dual core print-outs form purge air holes for the rim cavity that is then covered with cover plates if purge air holes are not required.

Abstract: A stator blade carrier for a gas turbine is provided. The stator blade carrier includes a plurality of axial segments. At least one axial segment is designed as a tubular lattice structure. This allows a simpler design technically and a more flexible adaptation to the temperature profile present on the stator blade carrier to maintain operational safety.

Abstract: An arrangement for connecting at least one duct with an air-distribution casing, the at least one duct including two sidewalls opposite one another and including a peripheral wall connecting edges of the two sidewalls. The arrangement includes a connecting tube that extends through the casing, passes through an orifice associated with each of the two sidewalls, and is connected to the at least one duct. A system controlling clearance of a turbo engine and a turbo engine can include air-injection ducts connected to the distribution casing by such an arrangement.

Abstract: The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method may include the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover about an opening of the cavity, positioning an impingement plenum within a platform cavity, inserting an unfixed spoolie through an assembly port of the impingement plenum and into an airflow cavity of the insert, and closing the assembly port.

Abstract: A cooling apparatus bifurcates and regulates cooling airflow provided to a mid-turbine frame. The cooling apparatus includes a flow metering tube and a metering plate. The flow metering tube includes a top portion and a tube portion, wherein the top portion includes a first central aperture that directs a first cooling airflow into the tube portion and a first plurality of apertures located circumferentially around the central aperture that directs a second cooling airflow to a portion outside the tube portion. The metering plate is located on the top portion of the flow metering tube, wherein the metering plate includes a second central aperture aligned with the central aperture of the flow metering tube and a second plurality of apertures located circumferentially around the central aperture, wherein a size of the second central aperture meters the first cooling airflow and a size and number of the second plurality of apertures meters the second cooling airflow.

Abstract: An turbine stator vane for an industrial engine, the vane having a serpentine flow cooling circuit with a first leg located along a leading edge of the vane airfoil and a partition rib separating the first leg from a second leg. A root turn channel connects the first leg to the second leg. A lower end of the partition rib includes a guide vane that directs cooling air from an aft section of the first leg toward a bleed hole for purging an ISSH. A plurality of turning guide ribs located in the aft section of the first leg also directs the cooling air toward the bleed hole.

Abstract: A labyrinth seal is provided for forming a seal between a first and a second component which rotate relative to each other. The seal has an abradable lining mounted to the first component, and a plurality of fins projecting from the second component. The fins are arranged in abutment with the abradable lining to form a labyrinthal path for a flow of air through the seal. The seal further has a bypass passage which extends through the abradable lining. The bypass passage allows air to flow through the seal and bypass the labyrinthal path.

Abstract: A gas turbine engine component comprises a plurality of walls, a cooling channel, a plurality of ribs and a plurality of pedestals. The plurality of walls has a pair of major surfaces opposed to define an interior chamber. The cooling channel extends through the interior chamber of the plurality of walls between the major surfaces. The plurality of ribs extends through the cooling channel to form a plurality of wavy passages having bowed-out sections. The plurality of pedestals is positioned between adjacent ribs, each pedestal being positioned in a bowed-out section.

Abstract: A ventilation inlet comprising a ventilation pipe to receive flow from a first flow zone and to deliver the flow to a second flow zone; a divider arranged to divide a portion of the ventilation pipe into a static pressure zone and a total pressure zone; and a deflector arranged to direct flow from the total pressure zone at least partially across the static pressure zone to restrict delivery of the flow from the static pressure zone to the second flow zone dependent on the pressure of the flow in the first flow zone.

Abstract: A dirt separator assembly for a gas turbine engine comprises a cyclonic accelerator in flow communication with compressor discharge air, the accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in the passage, a plurality of turning vanes disposed along each of the passages, the passage turning tangentially between the inlet and the outlet, the accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air, and, at least one vent located in the accelerator passages for expelling dust separated from the swirling compressed cooling air.

Abstract: A fluid transfer arrangement comprising a duct having a first end and a second end, a pulse generation mechanism located at the first end of the duct to direct fluid pulses towards the second end of the duct in use, and a baffle located at the second end of the duct that defines an aperture having sharp edges. The sharp edges generate ring vortex fluid flow from the aperture in use. Applications include impingement heating and cooling.

Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes an elongated intermediate plenum extending parallel to leading and trailing edges of the ring segment, and is located radially between an inner side of the panel and a hook structure extending from an outer side of the panel. A plurality of cooling fluid feed passages supply cooling fluid to the intermediate plenum, and a plurality of convective cooling passages extend through the panel from the intermediate plenum to one of the leading and trailing edges for cooling the inner side of the panel. The intermediate plenum is located in axial alignment with and defines an area of reduced thermal mass receiving impingement cooling adjacent to the hook structure.

Abstract: An airflow fan accessory comprising an accessory having a scented fabric and a fastening mechanism located along the outer edge of the scented fabric. In a preferred embodiment, the accessory may be easily attached to and detached from the fan blade enclosure of any typical airflow fan. Upon air flow through the fan and airflow fan accessory, a pleasant scent may be imparted to the room via release of scent from the scented fabric component.

Abstract: A gas turbine engine has a fairing and an air intake that includes an air inlet embedded within the fairing for supplying free stream atmospheric air to a gas generator.

Abstract: Disclosed is a steam turbine that utilizes heat pipes to remove heat from the surfaces of the disks of the steam turbine to provide greater efficiency and longer operational service of the steam turbine.

Abstract: A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.

Abstract: A compressor for a gas turbine engine having a bleed air recirculation system includes a plurality of bleed holes extending through the shroud at a first axial location thereon substantially adjacent the blade tips. The bleed holes have a closed outer perimeter along their complete length. An annular bleed cavity surrounds the shroud and is in communication with outlet openings of the bleed holes. The bleed holes provide communication between said main gas flow passage and the bleed cavity. The bleed cavity includes exit passages having outlets disposed in said shroud at a second axial location which is upstream of both the first axial location and the leading edge of the blades of the rotor. Bleed air is passively bled from the main gas flow passage via the bleed holes, recirculated through the bleed cavity and re-injected back into the main gas flow passage at the second axial location.

Abstract: One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.

Abstract: In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms (45) with a plurality of outer teeth (46a-c) running parallel to each other in the circumferential direction and being arranged one after the other in the direction of the hot gas flow. The teeth (46a-c) are divided into first and second teeth (46a; 46b-c), the second teeth (46b-c) being located downstream of the first teeth (46a), the first teeth (46a) are opposite to a downstream projection (33) of the adjacent vanes (21) of the turbine stage (TS), and the second teeth (46b-c) are opposite to the respective stator heat shields (27).

Abstract: A pump for providing a flow of fluid from a fluid source to a fluid destination. The pump includes a rotatable turbine, a first inlet port in fluid communication with the turbine, a first outlet port in fluid communication with the first inlet port, a second inlet port in fluid communication with the turbine, and a second outlet port in fluid communication with the second inlet port. The turbine pumps fluid from the fluid source into the first inlet port and out of the first inlet port into a reservoir. The turbine pumps fluid in the reservoir into the second inlet port and out of the second outlet port to the fluid destination.

Abstract: A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.

Abstract: An external supply pipe is disclosed, for supplying steam to a mid-span packing disposed about a shaft coupling a high pressure (HP) and an intermediate pressure (IP) section of an opposed flow steam turbine. The external supply pipe is disposed on an exterior of the steam turbine casing, which allows for direct measurement of steam flow to the mid-span packing.

Abstract: An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment.

Abstract: An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side (12) of the rotor disk (20) through openings (24) on the rotor disk (20) to a low-pressure side (14) of the rotor disk (20).

Abstract: A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel.

Abstract: A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.

Abstract: Provided are a turbo fan and an air conditioner using the same. The turbo fan includes a main plate rotating by power provided from a fan motor, a blade having one end connected to the main plate to rotate, a shroud connected to the other end of the blade, and an orifice guiding a flow of indoor air in a direction of the shroud. The shroud includes a guide surface defining one surface of the shroud, the guide surface having a predetermined curvature and an air guide connected to a side of the shroud, the air guide being disposed in a direction of the orifice from the shroud.

Abstract: The invention relates to a method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in said discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, characterised in that it consists of disposing at least one divergent radial deflection means in primary duct, spaced apart from the walls of said primary duct.

Abstract: A turbine includes an inner casing to which at least a stator vane of a turbine section is mountable, and an outer casing arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing. The outer cooling channel includes a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel. The cooling channel includes a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine. The fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel includes a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine.

Abstract: A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.

Abstract: The present disclosure introduces a rotor assembly having a concentric arrangement comprising a rotating turbine portion, a cooling channel and an annular reinforcement wall. The concentric arrangement is configured to rotate around a common axis. Also introduced is a rotary engine comprising the rotor assembly, in which the cooling channel further functions as a rotating compressor portion.

Abstract: Systems and methods Embodiments for facilitating onboarding of a cooling fluid are disclosed herein. According to one embodiment, a system may include a rotor assembly, a wheel space cavity adjacent to the rotor assembly, and a bucket shank cavity in fluid communication with the wheel space cavity. The system may also include at least one protrusion disposed on the rotor assembly in the wheel space cavity. The at least one protrusion may be configured to direct the cooling fluid radially from the wheel space cavity to the bucket shank cavity to minimize pressure loss in the cooling fluid.

Abstract: A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.

Abstract: A turbo compressor to suction and compress gas includes a housing including a flow passageway through which gas flows, an impeller disposed inside the flow passageway, the impeller providing suction for the gas by being rotationally driven, a liquid discharge port provided in the flow passageway on the upstream side of the impeller, the liquid discharge port discharging, from the flow passageway, any liquid produced as the gas liquefies when the turbo compressor is stopped, a liquid discharge pipe connected to the liquid discharge port, an electromagnetic valve connected to the liquid discharge pipe, and a controller configured to open the electromagnetic valve before the impeller is rotationally driven. A refrigerator includes the turbo compressor, wherein the turbo compressor compresses refrigerant gas.

Abstract: An inlet portion (31) of a compressor housing (30) forms part of an intake passage, and a drawing passage (35), which extends through the inlet portion (31), draws blow-by gas from outside the inlet portion (31) to inside the inlet portion (31). A throttling portion (47) is formed inside the inlet portion (31) and arranged at a joined portion of the intake passage and the drawing passage (35) so that a cross-sectional passage area at the joined portion is smaller than a cross-sectional passage area of a portion located at an intake air upstream side of the joined portion and a cross-sectional passage area of a portion located at an intake air downstream side of the joined portion.

Abstract: A cooling structure for a turbomachine. In one embodiment, the cooling structure is for a seal slot of the turbomachine. The cooling structure includes a body coupled to a surface of the seal slot. The body includes a passageway on a first surface of the body for providing a cooling fluid to the seal slot. In an other embodiment, a apparatus includes a first component and a second component adjacent the first component. The apparatus also includes a seal slot extending between the first component and the second component, and a cooling structure positioned within the seal slot. The cooling structure includes a body coupled to a surface of the seal slot. The body has a passageway on a first surface of the body for providing a cooling fluid to the seal slot.