Abstract: A gas turbine engine has an oil tube for delivering oil through a high temperature zone of the engine to an engine component for cooling and lubrication. An insulation tube surrounds the oil tube and extends in a substantial length of the oil tube. The opposed ends of the insulation tube are integrally and sealingly connected to respective end portions of the oil tube to form a dead air annulus between the oil tube and the insulation tube.

Abstract: A ring segment for a blade outer air seal which includes an array of separated floating wall surfaces each extending from a pedestal and having an inner side with a fibrous metal pad secured and a TBC secured over the pads. The pedestals are formed by diffusion chambers formed between an outer side and an inner side of the ring segment. Purge air holes connect the diffusion chambers to the impingement cavity formed above the ring segment. Thin slots form the separated floating wall surfaces and connect the diffusion chambers to discharge cooling air through the sides of the floating wall surfaces. Cooling air holes also pass through the pedestals to discharge cooling air onto the TBC surfaces.

Abstract: A turbocharger has a turbine housing formed with a coolant inlet channel and a coolant outlet channel. The turbine housing contains a coolant separating region in which delivered coolant is separated and a coolant combining region in which coolant is combined again. Each of the coolant separating region and the coolant combining region is equipped with a conical conducting body.

Abstract: An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.

Abstract: This disclosure describes embodiments of a vane conditioning apparatus for use in power generating systems. These embodiments generate one or more fluid streams, which impinge on vane separators in the power generating system to change the temperature of the vane separators. In one embodiment, the vane conditioning apparatus comprises a vortex tube to convert pressurized supply air to a hot fluid stream and a cold fluid stream. A flow control device couples with the vortex tube to regulates flow of the hot fluid stream and the cold fluid stream to the vane separators.

Abstract: A fluid flow machine has a main flow path in which at least one row of blades (2) is arranged, with at least one blade end of a blade row (2) being firmly connected to the main flow path confinement and, in an area of this fixed blade end at a sidewall (9), at least one longish, obstacle-type boundary layer barrier (11) is provided which in at least part of its course is oriented obliquely to the main flow direction, thereby deflecting fluid flowing near the sidewall towards the blade pressure side.

Abstract: The present invention relates to a cooling device for a jet engine having an axial compressor with several compressor stages including a rotor with rotor blades, a stator with stator vanes and an annulus. In order to reduce the temperature of the components at the outlet of the high-pressure compressor by simple measures and hence to increase the efficiency of a jet engine, a slot-like branch opening surrounding the rotor for a cooling airflow diverted from the main airflow into a first cavity upstream of the rotor is provided upstream of the last compressor stage of the axial compressor, with passage openings being arranged in the rotor for passing on the diverted cooling airflow from the first cavity into a second cavity downstream of the rotor.

Abstract: A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine and a counter-flow cooling system arranged within the casing. The counter-flow cooling system is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction.

Abstract: An automotive cabin cooling system uses a bladeless turbocompressor driven by automobile engine exhaust to compress incoming ambient air. The compressed air is directed to an intercooler where it is cooled and then to another bladeless turbine used as an expander where the air cools as it expands and is directed to the cabin interior. Excess energy may be captured by an alternator couple to the expander turbine. The system employs no chemical refrigerant and may be further modified to include another intercooler on the output of the expander turbine to isolate the cooled cabin environment.

Abstract: This bearing comprises a fixed outer ring and a rotatable inner ring, and at least one lubrication ring having at least one lubrication duct extending between an outer surface and an inner surface of the lubrication ring. The at least one lubrication duct is placed so that the scalar product of a vector collinear to the longitudinal axis of the lubrication duct, and a vector (VL1) collinear to the tangent line (L1) to an outer cylindrical surface of the inner ring, at the point where the longitudinal axis of the lubrication duct (270) intersects the outer cylindrical surface of the inner ring, and oriented in the same direction as the rotation direction (F) of the inner ring, is strictly superior to zero, said vectors being projected in a plane (P2) perpendicular to the rotation axis of the bearing.

Abstract: A compressor rotor compresses air and delivers the compressed air to a downstream inlet and across a turbine rotor. A shaft rotates with the turbine rotor and the compressor rotor. The shaft is hollow with an inner bore and an outer periphery. At least one journal bearing supports a portion of the shaft, and has an inner bore spaced from the outer periphery of the shaft. A cooling air path is provided between the shaft outer periphery and the bearing inner periphery, and along a length of the bearing to at least one connection hole. The connection hole provides cooling air from an outer periphery of the shaft to the inner bore of the shaft. In a separate feature, a shaft for use in an air supply machine includes a hollow interior, with such a connection hole.

Abstract: An oil pump including an upstream pump unit including an upstream inner rotor and an upstream outer rotor; a downstream pump unit including a downstream inner rotor and a downstream outer rotor as being arranged adjacently to the upstream pump unit in a predetermined axis line direction; a rotary shaft concurrently rotating the upstream inner rotor and the downstream inner rotor; and a housing which contains the upstream pump unit and the downstream pump unit as supporting the rotary shaft and which includes an inlet port for sucking oil from the outside into the upstream pump unit, an ejection port for ejecting a part thereof to the outside in a pressurization process of the upstream pump unit, a communication port for providing communication between the upstream pump unit and the downstream pump unit, and a discharge port for discharging oil from the downstream pump unit to the outside.

Abstract: A component includes a substrate having outer and inner surfaces, where the inner surface defines at least one hollow, interior space. The outer surface defines pressure side and suction side walls, which are joined together at leading and trailing edges of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface. The coating comprises at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge. A method of forming cooling channels in the vicinity of the trailing edge is also provided.

Abstract: A blade outer air seal for a gas turbine engine is provided. The blade outer air seal includes a body having an outer radial surface, an inner radial surface, and a plurality of cooling air apertures. The body extends between a forward edge and an aft edge. The inner radial surface includes at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section. Each of the plurality of cooling air apertures extends between the outer radial surface and the riser, and each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface.

Abstract: A system adapted for clearance control for a gas turbine including an outer turbine casing, an inner turbine casing and a plenum defined between the inner and outer turbine casings is disclosed. The clearance control system may include an impingement box disposed within the plenum. The impingement box may define a plurality of impingement holes. In addition, the clearance control system may include a first conduit in flow communication with the interior of the impingement box and a second conduit in flow communication with the plenum at a location exterior to the impingement box.

Abstract: A system for modulating the amount of air supplied through a pressure boundary in a gas turbine is disclosed that includes a passageway located on the pressure boundary. Additionally, a temperature activated valve is mounted within the passageway and is configured to activate at a predetermined temperature threshold. Specifically, the temperature activated valve activates from a closed position to an open position when the local temperature at the temperature activated valve reaches or exceeds the predetermined temperature threshold to allow air to flow through the passageway.

Abstract: A turbine arrangement with a rotor and a stator surrounding the rotor forming a flow path for hot and pressurized combustion gases between the rotor and the stator is provided. The rotor defines a radial direction and a circumferential direction and includes turbine blades extending in the radial direction through the flow path towards the stator. The turbine blades have shrouds located at their tips and the stator includes a wall section along which the shrouds move when the rotor is turning. A supersonic nozzle is located in the wall section and is connected to a cooling fluid provider. The supersonic nozzle provides a supersonic cooling fluid flow towards the shroud. The supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow has a flow component parallel to the moving direction of the shroud.

Abstract: A steam turbine having an exhaust-steam casing for directing an exhaust-steam mass flow, a shaft bearing for mounting a turbine shaft, and at least two bearing struts, by means of which the shaft bearing is fastened to the exhaust-steam casing, is characterized according to the invention in that each of the at least two bearing struts has a cooling cavity arranged in the respective bearing strut for directing a coolant, and the cooling cavities of the at least two bearing struts are connected in a fluidically conductive manner via a closed-off connecting cavity in the region of the shaft bearing.

Abstract: A turbine casing assembly, comprising an annular seal segment assembly for surrounding the turbine adjacent to the turbine blades. An abradable coating is provided on the inboard surface of the seal segments of the assembly and one or more coolant ducts extend from the outboard surface of the seal segment assembly through respective seal segments and the abradable coating, for carrying a coolant towards the blade tips. One or more annular grooves are formed in the inboard surface of the abradable coating, the or each coolant duct opening into one of the one or more annular grooves.

Abstract: A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.

Abstract: A turbine bypass system comprises a bypass path which is selectively operable to deliver hot gases to a gas cooler and a pebble bed positioned in the bypass path upstream of the gas cooler. The pebble bed absorbs heat from the bypass gases and thereby reduces the temperature of the bypass gases prior to delivery of the bypass gases to the gas cooler.

Abstract: A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge.

Abstract: A turbine engine has a fan comprising a duct and supporting struts, a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. A cooling circuit is located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor, and includes at least intercooler configured to transfer heat from inlet air to a secondary fluid heat sink.

Abstract: A turbine engine component includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.

Abstract: A gas turbine includes a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft, and a channel provided in the blade ring 1 and through which a cooling medium is flowed. The channel includes an inner channel formed in the blade ring 1, and a tubular outer channel which is connected to the inner channel, is disposed in an outer portion of the blade ring 1, and extends in a circumferential direction of the blade ring 1. The outer channel includes a plurality of fixing portions fixed to the blade ring 1 and a thermal stress absorbing portion disposed between the fixing portions adjacent in the circumferential direction and expandable and contractible in the circumferential direction.

Abstract: A method of manufacturing a component is provided. The method includes forming one or more grooves in an outer surface of a substrate. Each groove extends at least partially along the surface of the substrate and has a base, a top and at least one discharge point. The method further includes forming a run-out region adjacent to the discharge point for each groove and disposing a coating over at least a portion of the surface of the substrate. The groove(s) and the coating define one or more channels for cooling the component. Components with cooling channels are also provided.

Abstract: A turbine airfoil (20B) with a thermal expansion control mechanism that increases the airfoil camber (60, 61) under operational heating. The airfoil has four-wall geometry, including pressure side outer and inner walls (26, 28B), and suction side outer and inner walls (32, 34B). It has near-wall cooling channels (31F, 31A, 33F, 33A) between the outer and inner walls. A cooling fluid flow pattern (50C, 50W, 50H) in the airfoil causes the pressure side inner wall (28B) to increase in curvature under operational heating. The pressure side inner wall (28B) is thicker than walls (26, 34B) that oppose it in camber deformation, so it dominates them in collaboration with the suction side outer wall (32), and the airfoil camber increases. This reduces and relocates a maximum stress area (47) from the suction side outer wall (32) to the suction side inner wall (34B, 72) and the pressure side outer wall (26).

Abstract: An inducer for a casing of a gas turbine system is disclosed. The inducer includes a plurality of orifices defined in the casing, the plurality of orifices disposed in an annular array about the casing, and a plurality of cartridges, each of the plurality of cartridges configured to mate with one of the plurality of orifices. Each of the plurality of cartridges includes an inlet and an outlet for flowing a cooling medium therethrough. The inducer further includes at least one flow modifier disposed in each of the plurality of cartridges for modifying the flow of the cooling medium through each of the plurality of cartridges. Each of the plurality of cartridges is independently removable from each of the plurality of orifices.

Abstract: A device and method for drawing off and recirculating cooling streams, specifically for drawing off and recirculating a cooling stream of fuel for cooling at least one aircraft engine accessory, is disclosed. The device having a tubular jacket part defining a flow cross-section through which a primary stream, specifically a fuel stream, flows by way of an extraction pipe which is positioned approximately in the center of the flow cross-section, or jacket part, in order to draw off a cooling stream from the primary stream, by way of a hollow strut extending in the radial direction to divert this cooling stream from the device with the aid of the extraction pipe and to supply it to at least one accessory to be cooled, and by way of a return opening to recirculate the cooling stream directed through the accessory for cooling purposes to the primary stream.

Abstract: A turbine stator vane with a low volume cooling circuit, the vane includes inner and outer endwall impingement cavities that feed cooling air to upward and downward flowing near wall cooling passages formed within the walls of the airfoil. The cooling passages then discharge into a collection cavity where the cooling air then flows out through trailing edge exit holes to cool the trailing edge region. The cooling passages are staggered from upward flowing to downward flowing.

Abstract: A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing system restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing system restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing system and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.

Abstract: A cooling system for a turbine engine, as well as a methodology for controlling the cooling system, is described. A valve member is disposed between a cooling fluid passage and a wheel space of the turbine engine and operates to admit cooling fluid to the wheel space for cooling thereof. The valve assembly is responsive to a condition in the wheel space and varies the flow of additional cooling fluid to the wheel space based on that condition.

Abstract: An apparatus for extracting energy from a fluid flow including a secondary fluid channel, a fluid driveable generator unit and a primary fluid channel. The primary fluid channel comprises a fluid intake in fluid communication with a throat. The throat is configured to increase the flow velocity and reduce the pressure of the primary fluid flowing through the primary fluid channel and includes at least one plenum in the interior of the throat configured to further reduce the pressure of the primary fluid flowing through the primary fluid channel. The plenum includes at least one perforation through its exterior surface in fluid communication with the secondary fluid channel. As such, the flow of primary fluid through the primary fluid channel draws the secondary fluid into the primary fluid channel through the secondary fluid channel and the perforation and thereby into driving engagement with the generator.

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 turbine rotor blade with a platform includes platform cooling channels on the pressure side and the suction side of the platform. The cooling channels are formed from straight section that generally follows a contour of the airfoil in order to provide cooling to as much of the platform surfaces as possible. Pressure side cooling channels have a V-shape from inlet to outlet. Suction side channels branch off from a common channel located along a suction side edge of the platform.

Abstract: A component for a gas turbine engine including a gas path wall having a first surface and a second surface. A cooling hole extends through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface. Cusps are formed on the transition.

Abstract: In an oil supply apparatus, a valve body includes first and second radially protruding lands, and a small-diameter portion continuously connecting the first and second lands and having a diameter smaller than at least the outer diameter of the first and second lands. Rotational speeds of a rotor are set as first, second and third rotational ranges in the ascending order. In the first rotational range, work oil from a second discharge port is fed to a first oil passage via the small diameter portion. In the second rotational range, work oil from the second discharge port is fed to a return oil passage via the small diameter portion. In the third rotational range after the second oil passage is blocked relative to the return oil passage by the second land, work oil from the second discharge port is fed to the first oil passage.

Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet, a first diffusing section extending downstream from the metering section, and a second diffusing section extending downstream from the first diffusing section to the outlet. The second diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally relative to the metering section, and a trailing edge.

Abstract: A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed.

Abstract: A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream disk.

Abstract: A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includes a metering section extending from an inlet in the first surface of the wall to a transition, a diffusing section extending from the transition to an outlet in the second surface of the wall, a cusp on the transition, and a first longitudinal ridge extending along the diffusing section between the transition and the outlet. The first longitudinal ridge divides the diffusing section into first and second lobes.

Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.

Abstract: A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface. The component also includes a diffusing section extending from the metering section to the outlet. A gas turbine engine wall includes first and second surfaces and a cooling hole extending between an inlet at the first surface and an outlet at the second surface. The cooling hole includes a metering section commencing at the inlet and a diffusing section in communication with the metering section and terminating at the outlet. The metering section includes a top portion having a first arcuate surface and a bottom portion having a second arcuate surface. The first and second arcuate surfaces have arcs extending in substantially similar directions.

Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet at the first wall surface, an outlet at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally from the metering section, a third lobe adjacent the second lobe and diverging longitudinally and laterally from the metering section, and a transition region having an end adjacent the outlet and a portion that extends between the lobes and the outlet. The first and third lobes each include a curved outer portion.

Abstract: A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.

Abstract: A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet.

Abstract: A gas turbine is provided. The gas turbine includes at least one rotor, having rotor blades arranged on the periphery of rotor disks in a plurality of radial planes, and a tie-bolt extending along slots in the rotor disks and holding the rotor disks together as a unit. At least one annular spacer for fixing the position of the tie-bolt in relation to the center line of the rotor disks is also provided. The spacer includes through-openings that are arranged radially in relation to the tie-bolt or to its center line and that extend coaxially.

Abstract: A heat exchanger component is made by forming a wafer having a pair of opposed outer major faces with interstices between them from a stack of wire mesh screens. The outer major surfaces of the wafer are sealed by depositing a metal coating on them. The deposited metal coatings define between them a flow path for a heat exchange fluid extending through the interstices of the wafer.

Abstract: A steam turbine flow adjustment system. In one embodiment, the system includes a steam turbine having a first inlet port and a second inlet port for receiving inlet steam; a first conduit and a second conduit operably connected to a first valve and a second valve, respectively, the first conduit and the second conduit for providing the inlet steam to the first inlet port and the second inlet port, respectively; and a control system operably connected to the first valve and the second valve for controlling an amount of inlet steam flow admitted and pressure to each of the first inlet port and the second inlet port based upon a load demand on the steam turbine and an admission pressure of the inlet steam.

Abstract: A turbine rotor blade with counter flowing near wall cooling channels that includes an outer spanwise flowing near wall cooling channel and an inner chordwise flowing near wall cooling channel connected in series and with an arrangement of pedestals to produce turbulent flow. Cooling air form the spanwise flow channels flows through a blade tip floor cooling channel and then into a collection cavity, and then through impingement cooling holes in the leading edge region and into the chordwise channels before discharging out exit holes on both sides of the blade. An arrangement of pedestals forms 90 degree flow paths through the near wall cooling channels.