Abstract: An airfoil for a gas turbine engine includes pressure and suction surfaces that are provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extending to the trailing edge. The cooling passage terminates in a trailing edge exit that is arranged in the trailing edge. Multiple rows of pedestals include a first row of pedestals that join the pressure and suction walls. The first row of pedestals is arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.

Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.

Abstract: An airfoil having one-sided pedestals is disclosed. The airfoil may define various cavities, such as an inflow feed cavity, an impingement cavity, and an outflow cavity. The various cavities may be connected by crossover sections such as an inflow crossover section and an outflow crossover section. Cooling air may be conducted into the inflow feed cavity, out of the inflow feed cavity through an inflow crossover section into an impingement cavity, and through an impingement cavity. The cooling air may be conducted out of the impingement cavity and into an outflow cavity through an outflow crossover section. Various cavities may include one-wall pedestals. One-wall pedestals may be structures extending from a wall of a cavity into the void of the cavity, whereupon cooling air may impinge, effectuating convective cooling.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a pedestal that traverses a flow channel disposed between a first wall and a second wall. The pedestal includes at least one interior bore configured to communicate a cooling fluid inside of the pedestal.

Abstract: A shroud segment assembly for use within a turbine shroud of a gas turbine engine may generally include a forward shroud portion having a forward outer arm and a forward inner arm extending from a forward wall and an aft shroud portion having an aft outer arm and an aft inner arm extending from an aft wall. Additionally, the shroud segment assembly may include a first expansion joint positioned between the forward and aft shroud portions such that the first expansion joint extends circumferentially between the forward outer arm of the forward shroud portion and the aft outer arm of the aft shroud portion and a second expansion joint positioned between the forward and aft shroud portions such that the second expansion joint extends circumferentially between the forward inner arm of the forward shroud portion and the aft outer arm of the aft shroud portion.

Abstract: A damper system for a turbine having adjacent turbine bucket platforms including opposing slash faces having opposing grooves is provided. The system includes a pin having a substantially cylindrical-shaped body configured for positioning in the opposing grooves. A set of slots are provided in an outer surface of the pin and at spaced axial locations therealong. The set of slots face in a radially outward direction relative to the turbine bucket platforms.

Abstract: A method for producing a blade for a turbomachine, the blade having a blade tip cladding on its blade tip and an erosion-resistant layer at least on its blade airfoil, wherein firstly a blade tip cladding is applied on the blade tip, subsequently a poorly adhering sublayer is deposited on the blade tip cladding, and then the erosion-resistant layer is produced on the poorly adhering sublayer and the blade airfoil, the poorly adhering sublayer being removed again together with the erosion-resistant layer following completion of the erosion-resistant layer. The invention also relates to a blade for a turbomachine, the blade having a blade tip cladding on its blade tip and an erosion-resistant layer at least on its blade airfoil. The blade tip cladding comprises a metal matrix with incorporated hard material particles and an oxide layer arranged on the metal matrix.

Abstract: A method for manufacturing a blade (1) for a turbomachine, the blade having a hardfacing on its tip (4) and an erosion-protection coating (13) at least on its airfoil (3) is provided. Initially, a blade tip hardfacing is applied to the blade tip and, subsequently, a mask (10) is positioned in the region of the blade tip hardfacing, the mask covering the blade tip hardfacing, and, subsequently, the erosion-protection coating is deposited. The mask is removed after the erosion-protection coating is completed. A blade for a turbomachine, the blade having a hardfacing on its tip (4) and an erosion-protection coating (13) at least on its airfoil (3) is also provided. The erosion-protection coating at least partially covers the blade tip hardfacing, and the thickness of the erosion-protection coating decreases continuously in and/or toward the region of the blade tip hardfacing.

Abstract: In a turbo engine, the rotor includes a shaft, blades, and a shaft-blade connection. The shaft blade connection can be provided as a fir tree connection, having a fir tree blade root and fir tree shaft grooves receiving the blade roots. The blade roots can include lobes, while the grooves can include undercut recesses receiving the lobes. The inclined mating bearing surfaces provided on a shaft post or on a lobe, respectively, are offset with respect to each other in the circumferential direction while partially overlapping. Each bearing surface is tangentially adjoined by a convexly curved end of bedding surface.

Abstract: A bladed rotor includes rotor disc having a peripheral region, and a plurality of rotor blades attached to and extending radially outwardly from peripheral region. Each rotor blade has a root portion which is located in a correspondingly shaped axially-extending slot provided in the peripheral region of rotor disc, and the root portion of each blade is axially retained in its respective slot by a plate located axially adjacent the root portion and rotor disc, and which extends circumferentially across respective slot. Retention plate is held in position by seal member having a first surface which engages radially-inwardly directed surface of rotor disc, and second surface which is located radially-outwardly of first surface and engages the retention plate. Seal member has a curved profile in radial cross-section so as to define a concavity located radially between first and second engaging surfaces and which is directed axially towards the rotor disc.

Abstract: The invention relates to a radial control shaft (48) for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, the shaft comprising an external portion (52) that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade (26) in order to adjust its pitch, and an internal portion (50), independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing (40) in order to pivot the shaft about a radial axis (Z-Z), and to close an oil enclosure in which said bearing is housed, the external and internal portions of the shaft being coupled to each other. The invention also relates to a method of mounting such a shaft and to a control device including such a shaft.

Abstract: A stationary guide vane includes a top platform, a bottom platform, and a vane body located between the top platform and the bottom platform. The vane body includes one or more cavities formed on a side wall of the vane body. One or more of the cavities are filled with vibration damping material and a vane cover is bonded to the vane body over the one or more containers.

Abstract: A spring guide for use in a seal housing including a first body portion, a second body portion, and a flange portion, including a flange width, extending circumferentially between the first body portion and the second body portion. The flange width being less than or equal to approximately 2.1 millimeters.

Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.

Abstract: In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud.

Abstract: A sealing structure that seals a clearance between an outer peripheral surface of a rotor and an inner peripheral surface of a stator. The sealing structure includes: a plurality of step portions that are provided on a first surface which is one of the outer peripheral surface of the rotor and the inner peripheral surface of the stator so as to be arranged in the axial direction, and that protrude from the first surface toward a second surface which is the other of the outer peripheral surface of the rotor and the inner peripheral surface of the stator; and a seal fin that is provided on the second surface, and that forms a small clearance between a corresponding peripheral surface of the step portions. A portion in the vicinity of a tip of the seal fin in the radial direction is inclined toward the upstream side.

Abstract: One exemplary embodiment of this disclosure relates to a system having a static segment with a circumferentially extending slot. The system further includes a retention clip partially received in the slot, and partially contacting a circumferential end of the static segment.

Abstract: The present disclosure relates generally to blade outer air seal section mount including a resilient spring element that acts to provide re-centering forces to the blade outer air seal section when non-uniform forces applied to the blade outer air seal section causing it to move away from its nominal position.

Abstract: A method of manufacturing a net shaped seal comprises depositing a first layer of fine powder comprising an abradable feed stock material on a substrate. The method includes guiding a heat source over the fine powder material layer; fusing together the fine powder material; depositing a second layer of fine powder material over the first layer; fusing the second layer of fine powder material with a second pass of the heat source at predetermined locations; and repeating the depositing step and fusing step to form subsequent layers to form an abradable seal on the substrate.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A method of making a shroud assembly by: forming a shroud frame consisting of a one-piece hook and rail assembly which includes a first rail and a second rail disposed at lateral edges and a first support and a second support connected to the first rail and the second rail, the first and second rails and the first and second supports being integrally joined to one another and defining a central aperture therebetween; joining a metallic backsheet to the shroud frame covering the central aperture; and attaching a honeycomb rubs strip to the metallic backsheet via an upper edge of the honeycomb seal structure.

Abstract: A seal assembly, comprising a first segment, a second segment, and a seal incorporated between the first segment and the second segment, the seal comprising a mesh. The first segment may comprise a blade outer air seal and the second segment may comprise a vane. In various embodiments, the first segment and the second segment may define a gap, and the seal may seal the gap. The seal may have a first member and a second member that enmeshes the first member. The seal may comprise a member that enmeshes a non-metallic member. The seal may comprise a ceramic fiber enmeshed by a member. The seal may comprise a non-metallic member enmeshed by a metallic member. The seal may comprise a plurality of annular connecting members, each annular connecting member extending about the seal. The seal may comprise a single annular member.

Abstract: A blade outer air seal (BOAS) assembly is provided. The BOAS assembly may comprise an outer case, a first support arm, a second support arm, a control rod, a blade outer air seal (BOAS), and a unison ring. The unison ring may be located radially inward of the outer case and in mechanical communication with the control rod. The BOAS may be configured to expand or contract in response to a rotation of the control rod. The first support arm may be fixed to the outer case. The second support arm may be fixed to the outer case. The control rod may be coupled to the first support arm and the second support arm, wherein the control rod may be configured to rotate about a control rod axis. The BOAS may comprise a first segment and a second segment.

Abstract: An intershaft integrated seal and lock-nut assembly includes spaced apart forward and aft shafts, forward lock-nut threaded onto aft end of forward shaft, aft lock-nut threaded onto a forward end of aft shaft, and seal ring sealingly engaging and disposed between forward and aft lock-nuts operable to seal annular gap between forward and aft shafts. Seal ring may be disposed in annular ring groove extending radially inwardly into one of forward and aft lock-nuts and annular cylindrical inner surface on other one of lock-nuts operable to seal against seal ring. Seal ring may be carbon seal ring and split. Aft lock-nut may include forwardly extending annular arm having annular cylindrical inner surface. Retention tabbed rings may engage lock-nuts and shafts and snap rings may engage retention tabbed rings and lock-nuts. Seal ring may be in ring groove in aft lock-nut.

Abstract: The invention provides a drain to allow water to flow out of a pressure sensing line. The drain comprises a tube including a plurality of restrictors in flow series, each restrictor comprising a constriction whose internal diameter is less than the internal diameter of the tube.

Abstract: A drain includes a vortex throttle, to remove water from a pressure sensing line. The vortex throttle resists the flow of air through it. Therefore, for a given diameter of inlet and outlet ports the mass flow rate through the vortex throttle is much smaller than through a plain hole of the same diameter. The inlet and outlet ports may therefore be made larger than in known arrangements (so reducing the risk of blockage), but the operation of the vortex throttle restricts the mass flow of air through the drain pipe (so minimising the detrimental effects on the engine's operation). Collected water effectively drains from the pressure sensing line, without the disadvantages of known arrangements.

Abstract: A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.

Abstract: A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.

Abstract: A vane strut positioning and securement system includes a housing including a washer aperture defined in an inner diameter thereof and a lock washer disposed within the washer aperture of the housing, the lock washer configured to lock a vane strut orientation under compression against a vane strut washer. The washer aperture is defined partially through a thickness of the housing, and the housing includes a strut post opening defined through the housing from the inner diameter to an outer diameter of the housing.

Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

Abstract: A gas turbine engine including a core engine and a fan configured in mechanical communication with the core engine is provided. The gas turbine engine also includes a plurality of outlet guide vanes positioned downstream from the fan along an axial direction defined by the gas turbine engine. The plurality of outlet guide vanes extend outwardly from an outer casing the core engine generally along the radial direction defined by the gas turbine engine. Each outlet guide vane defines a center of pressure and a pitch axis. The pitch axis of each outlet guide vane is positioned forward the center of pressure of each outlet guide vane such that in the event of a mechanical failure, the outlet guide vane defaults to a neutral position.

Abstract: There is described herein the automation of propeller feather testing functions, whereby the test is automatically performed and a pass/fail signal is issued upon completion.

Abstract: The invention refers to a method for controlling part load operation of a gas turbine comprising a controller wherein a load set point of the controller is greater or equal a minimum load set point. The minimum load set point depends on a hot gas temperature that is calculated based on a hot gas temperature model.

Abstract: The object of the invention is a device for cleaning the core engine of a jet engine, having a supply unit, which provides the cleaning medium, a nozzle unit, which is configured for feeding the cleaning medium into the core engine, and a line connection between the supply unit and the nozzle unit. The invention provides that the nozzle unit has a means for the rotationally fixed connection to the fan shaft of the jet engine, and that a rotary coupling is provided between the nozzle unit and the line connection. The object of the invention is further an arrangement of such a device and a turbo fan jet engine, and a method for cleaning the core engine of a jet engine using the device.

Abstract: A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.

Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.

Abstract: An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.

Abstract: A bearing damping system includes a pump configured to pump a fluid. The system further includes a variable position valve having a plurality of open positions each configured to generate different pressures in the fluid downstream from the variable position valve. The system also includes a bearing assembly. The bearing assembly includes a bearing housing. The bearing assembly also includes a stationary bearing race positioned within the bearing housing. The bearing assembly also includes a rotating bearing race spaced apart from the stationary bearing race and configured to be attached to a rotating component. A bearing element is disposed between the stationary bearing race and the bearing housing. A fluid compartment is defined by the space between the bearing housing and the stationary race and is configured to receive the fluid from the second conduit.

Abstract: A turbocharger for an internal combustion engine, the turbocharger being supported by hydrostatic bearings in both a radial and an axial direction by a compressed air supplied from a compressor of the turbocharger and boosted in pressure by a separate boost pump to a high enough pressure to support the rotor of the turbocharger.

Abstract: A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell.

Abstract: A mid-turbine frame for use in a gas turbine engine comprises at least one vane extending between a vane inner platform and a vane outer platform, and an inner case radially inward of the inner platform. A plurality of tie rods extend from a platform radially inward of the inner case to a radially outer location which is secured by a mount member. The tie rods are secured in the inner case by a forward bolt, and at least one rear bolt, with the forward bolt extending along an axis which is non-parallel to a center axis of the inner case. A gas turbine engine and a method for assembling a mid-turbine frame are also disclosed.

Abstract: A shroud retention system may include a shroud hanger having an outer hanger wall that defines a clip groove including a narrow groove portion and an enlarged groove portion, with the enlarged groove portion defining a radial height that is greater than a radial height of the narrow groove portion. The system may also include a shroud segment having a shroud wall and a retention clip configured to couple the shroud segment to the shroud hanger. The retention clip may include an inner rail, an outer rail and a clip wall extending radially between the inner and outer rails. The inner rail may be configured to extend along an inner surface of the shroud wall. The outer rail may include a narrow rail portion configured to be received within the narrow groove portion and an enlarged rail portion configured to be received within the enlarged groove portion.

Abstract: According to some embodiments, a ceramic matrix composite (CMC) hanger sleeve is provided for retaining a ceramic matrix composite shroud panel. The sleeve may be connected to an upper hanger by a retainer or a casing. The hanger sleeve includes a radially inward opening with a flowpath panel disposed therein. When the CMC flowpath panel is worn due to time, rubs or both, the panel may be replaced without need to replace the entire assembly.

Abstract: A mounting frame for a ram air turbine includes a front support block having a top side opposite a bottom side. A rear support block is disposed opposite the front support block, the rear support block also having a top side, and a bottom side. A top plate extends between the front support block and the rear support block, the top plate having a forward end connected to the front support block proximate the top side of the front support block, an aft end connected to the rear support block proximate the top side of the rear support block. A bottom plate extends between the front support and the rear support opposite the top plate.

Abstract: To remove water accumulated in a cooling air system while preventing performance loss of a gas turbine, the gas turbine is provided with a cooling air system that connects an intermediate stage or the exit of a compressor to a turbine to supply compressed air bled from the compressor to the turbine, a TCA cooler, i.e., a heat exchanger, that cools the compressed air on the route of the cooling air system, and a drain water discharge valve, i.e., a first drain water discharge valve and a second drain water discharge valve disposed downstream of the compressed air of the TCA cooler, wherein at least for a predetermined period of time after a rated speed of the gas turbine at start up has been reached, the drain water discharge valve is set to an open state, and thereafter, the drain water discharge valve is set to a closed state.

Abstract: A method for generating electricity by means of a thermal power plant and a liquid vaporization apparatus involves producing heat energy by means of the power plant and using the heat energy to vaporize water or to heat water vapor, expanding the water vapor formed in a first turbine and using the first turbine to drive an electricity generator in order to produce electricity, vaporizing liquefied gas coming from a cryogenic storage in order to produce pressurized gas, reheating the pressurized gas with a part of the water vapor intended for the first turbine of the power plant and expanding the pressurized fluid in a second turbine to produce electricity.

Abstract: A method for generating electricity by means of a nuclear power plant and a liquid vaporization apparatus involves producing heat energy by means of the nuclear power plant and using the heat energy to vaporize water or to heat water vapor, expanding the water vapor formed in a first turbine and using the first turbine to drive an electricity generator in order to produce electricity, vaporizing liquefied gas coming from a cryogenic storage in order to produce a pressurized gas, reheating the pressurized gas with a part of the water vapor intended for the first turbine of the power plant and expanding the pressurized fluid in a second turbine to produce electricity.

Abstract: A system and method can comprise a heat source, a plasma assisted vitrifier comprising a syphon valve; and a self-cleaning heat exchanger comprising a fired tube side and a water tube side. The self-cleaning heat exchanger can be configured to receive a heat source comprising an oxidized fossil fuel to one of the fire tube side or the water tube side and the self-cleaning heat exchanger can be further configured to receive a dirty water input on the other of the fire tube side and the water tube side to generate a steam. The plasma assisted vitrifier can be configured to process an organic or inorganic solid waste. The syphon valve is configured to assist in generating a reclaimed product, and the plasma assisted vitrifier is further configured to supply a portion of the process heat to the self-cleaning heat exchanger.

Abstract: A system for using recovered energy to increase the source to sink temperature differential for heating and cooling the working fluid of a prime mover, and in particular to a heat of compression braking source and liquefied or solidified air sink.

Abstract: In the method for driving a turbine according to the invention, at the moment of switching the direction of flow from the first tank (1) to the second tank (2) and at the moment of switching the direction of flow from the second tank (2) to the first tank (1), the liquid from the third tank (3) is displaced through the turbine (4). The controller (33) operating in conjunction with liquid level sensors (34, 35, 36, 37, 38, 39) is used by means of which steam valves (8, 9, 12, 13, 16, 17) and hydraulic valves (21, 22, 26, 27) are opened and closed, making possible the liquid flow direction to be switched from the first tank (1) to the second tank (2) and vice versa and making possible the liquid to be displaced from the third tank (3) through the turbine (4) to the selected first tank (2) or second tank (2).