Abstract: A shrouded impeller includes an impeller having a plurality of blades and configured to rotate about an axis, and a shroud disposed adjacent to the impeller and configured to corotate about the axis with the impeller and translate axially relative to the impeller. A method of varying a geometry of a flow area of the shrouded impeller includes rotating the shroud and the impeller about the axis and axially translating the shroud relative to the impeller to increase or decrease a rate of flow between the shroud and the impeller.

Abstract: A centrifugal compressor includes an impeller configured to drive fluid along a fluid flowpath via a plurality of discrete passages. Each of the discrete passages includes a discrete passage exit. A diffuser portion is disposed circumferentially about the impeller. The diffuser portion includes a plenum connected to each exit of the discrete passages via a plurality of diffuser inlets and an equalization plenum defined adjacent to the impeller. The equalization plenum is fluidly connected to each discrete passage exit via a corresponding slot.

Abstract: A nozzle assembly for a gas turbine engine includes a nozzle having a first material defining a first coefficient of thermal expansion, the nozzle having an airfoil defining a fluid passage therein, an inlet wall defining a fluid inlet that is fluidly connected to the fluid passage, and a passive valve assembly comprising an annular band, the annular band comprising a second material having a second coefficient of thermal expansion less than the first coefficient of thermal expansion such that the passive valve assembly is at least partially moveable relative to the fluid inlet.

Abstract: A rotor for a machine under this disclosure could be said to include a hub having a plurality of blades extending radially outwardly of the hub. At least one of the hub and the plurality of blades is formed of at least two metal materials. The two metal materials are selected to have different thermal expansion coefficients such that the overall rotor will be more resistant to forces it may experience as temperature or speed increases. There are layers of each of the two metal materials, with an intermediate gradient wherein the two materials are mixed. Alternatively, a shape memory alloy may be used. A method is also disclosed.

Abstract: A heart pump is disclosed herein. The heart pump can include a cannula having one or more outlets. An impeller can be positioned in the cannula. The impeller can be configured to pump blood through the outlets along a longitudinal axis when the impeller is rotated at an operational speed. The heart pump can be configured to adjust an effective area of the outlets while the impeller is rotating or to provide relative motion between the cannula and the impeller along the longitudinal axis while the impeller is rotating.

Abstract: An interlayered structure for joining of dissimilar materials, includes a first material substrate, a second material substrate having a composition dissimilar from a composition of the first material substrate, and a plurality of interlayers disposed between the first material substrate and the second material substrate, including a first interlayer nearest to the first material substrate and a last interlayer nearest to the second material substrate. The first interlayer has a composition selected to have a maximum solid solubility within the composition of the first material substrate that is greater than or equal to the other interlayers' solubility within the composition of the first material substrate. The last interlayer has a composition selected to have a maximum solid solubility within the composition of the second material substrate that is greater than or equal to the other interlayers' solubility within the composition of the second material substrate.

Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

Abstract: A pump for pumping a liquid, includes an impeller and an axially extending drive shaft assembly, wherein a distal end of the drive shaft assembly is received in a central recess of the impeller. The drive shaft assembly includes a drive shaft and a connector. The connector includes a sleeve that is in telescopic engagement with the drive shaft. During operation of the pump the impeller is displaceable in the axial direction in relation to the sleeve between a distal rest position and a proximal position. The impeller is biased towards the distal rest position by a spring member arranged between the sleeve and the impeller. The connector includes a hollow adjustment screw that is in threaded engagement with an interior side of the sleeve to limit the maximum degree of telescopic overlap between the sleeve and the drive shaft.

Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.

Abstract: The subject matter of the present invention is a variable-delivery pump device comprising a pump body (2), an impeller (5) and a shut-off element (8) capable of translational movement and adjustably covering at least part of the outer periphery of the impeller (5), as well as a cam element (9) which is rotationally driven and engages with said shut-off element (8) for effecting the translational movement thereof. The pump device (1) is characterized in that the shut-off element (8) and the cam element (9) have cylindrical walls (8?) and are arranged concentrically around the housing (7) that accepts the shaft (6) of the impeller (5), and in that the rotary cam element (9) is situated on the inside of the sliding shut-off element (8) and, on the external face of its wall, has at least one helical guideway (11) on which there runs at least one corresponding follower element (12) secured to the internal face of the wall (8?) of the shut-off element (8).

Abstract: A laundry appliance includes a rotating drum for processing laundry. A blower directs process air through an airflow path that includes the rotating drum. A heat exchanger is positioned within the airflow path that dehumidifies the process air. A fixedly-secured lint filter captures lint from the process air at a position upstream of the heat exchanger. A fluid spray system has spray nozzles that deliver fluid to a surface of the fixedly-secured lint filter. Each spray nozzle of the plurality of spray nozzles directs captured lint away from the fixedly-secured lint filter.

Abstract: A composite lay up tool comprising a metal faceplate (12) on a support member (13), wherein the faceplate has been formed by cold-gas dynamic spraying of particles of the metal onto a substrate and wherein the support member is compatible with the faceplate and comprises a casting of a ceramic composition. A process for forming the tool is disclosed. In one aspect, a castable ceramic composition comprises a binder and an aggregate component mixable with water to form a slurry ready for casting, wherein the aggregate component is one of, or a mixture of, fused silica and a particulate metal alloy, and the binder and aggregate component are present in the proportions 10-50 wt % and 90-50 wt % based on the dry weight of the composition.

Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.

Abstract: A variable vane assembly may comprise a first vane and a second vane. The first vane may comprise a first strut portion and a first flap portion. The first flap portion may be configured to pivot relative to the first strut portion. The second vane may comprise a second strut portion and a second flap portion. The second flap portion may be configured to pivot relative to the second strut portion. The first flap may be configured to pivot independently of the second flap.

Abstract: An electric water pump having a motor with an axially moveable rotor unit. A rotary pump member is fixed for axial movement with the rotor unit to vary its position within a pump chamber so as to vary the flow rate through the pump chamber.

Abstract: A valve and a heat exchanger apparatus for a gas turbine engine include a valve body having a valve seat and an actuation component including a plate formed from a set of metal layers and responsive to a change in at least one of a thermal condition and a pressure exerted thereon such that the plate moves and the valve moves between an opened and a closed position where a portion of the plate engages with the valve seat.

Abstract: A centrifugal pump with adaptive pump stages includes an impeller configured to provide kinetic energy to fluid flow through the pump. The impeller has multiple geometric dimensions. The pump includes a diffuser connected to the impeller that is configured to convert the kinetic energy provided by the impeller into static pressure energy to flow the fluid through the pump. The pump includes an adaptive material attached to the impeller that is configured to modify, during operation of the pump, a geometric dimension to modify fluid flow through the pump.

Abstract: An airfoil for a gas turbine having an outer shell with an inner volume and an inner shell arranged within the inner volume of the outer shell, wherein the inner shell has an aerodynamic profile having an inner nose section and an inner tail section. A first cooling channel and a second cooling channel merge into a common cooling channel at an inner tail section. A first tail fin is arranged between the first cooling channel and the common cooling channel such that a first mass flow rate of the cooling fluid flowing through the first cooling channel is controllable. A second tail fin is arranged between the second cooling channel and the common cooling channel such that a second mass flow rate of the cooling fluid flowing through the second cooling channel is controllable.

Abstract: In an aspect, there is provided a pump impeller assembly that includes a first impeller portion arranged to drive a fluid through a fluid conduit, a second impeller portion movable between a more-rotationally engaged position in which the second impeller portion has a first amount of rotational engagement with the first impeller portion, and a less-rotationally engaged position in which the second impeller portion has a second amount of rotational engagement with the first impeller portion that is less than the first amount of rotational engagement, and an actuator operatively connected to the second impeller portion and configured to drive movement of the second impeller portion between the more-rotationally engaged position and the less-rotationally engaged position based on a fluid property.

Abstract: A shroud for a J-tube of an air conditioning pack of an aircraft includes a first partial shroud piece and a second partial shroud piece that mate together to form a flow tube and a sleeve. The flow tube includes an inlet, an outlet fluidly connected to the inlet and disposed on an opposite end of the flow tube from the inlet, and a sidewall extending between the inlet and the outlet. The sleeve extends through a portion of the flow tube and out of the sidewall and is configured to contain a portion of the J-tube.

Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.

Abstract: A thermally driven spring valve for turbine gas path parts is disclosed herein. A thermally driven spring valve includes a bimetallic sheet comprising a base, a first finger portion extending from the base and a second finger portion extending from the base, the first finger portion having a first curvature vector and the second finger portion have a second curvature vector, wherein an exterior surface extends from the base through the first finger portion and the second finger portion and an interior surface extends from the base through the first finger portion and the second finger portion, wherein the exterior surface of the first finger portion is disposed proximate the interior surface of the base wherein the exterior surface of the second finger portion is disposed proximate the interior surface of the base. A thermally driven spring valve may include perforations through a finger portion.

Abstract: A regulating rod (1) has a rod part (2) which has an end region (3) provided with an external thread and an end piece (4) which has a receiving recess (5). A knurled nut (6) is arranged and guided in the receiving recess (5) and has an internal thread into which the external thread of the externally threaded end region (3) is screwed. The end piece (4) further has a weld window (8) adjacent the knurled nut. Once the length of the regulating rod is adjusted by rotation of the knurled nut, further rotation of the knurled nut is prevented by introducing and filling the weld window with a weld filler such that the knurled nut (6) is non-detachably fixed and thereby the set length of the regulating rod is fixed.

Abstract: An airfoil includes an airfoil body having a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.

Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

Abstract: An adjustable and lockable turnbuckle is disclosed herein. The turnbuckle may include an elongated body having internal threading within a first end thereof. The turnbuckle may include a first extension rod having external threading configured to mate with the internal threading at the first end of the elongated body. The turnbuckle may include a first jam nut having internal threading and a skirt. The internal threading of the first jam nut may be configured to mate with the external threading of the first extension rod to tighten the first jam nut against the first end of the elongated body so that the skirt of the first jam nut is positionable about the first end of the elongated body. A first aperture may extend through the elongated body, the first extension rod, and the skirt of the first jam nut. Moreover, a first pin may be positioned within the first aperture.

Abstract: A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base (12) made of a high temperature-resistant nickel alloy and a plurality of turbine blades (14) joined to the rotor base, whereby each turbine blade includes a rotor blade (16) made of a titanium alloy and a blade root. The blade root is configured as an adapter element (18) that is made of a material that can be welded to the titanium alloy as well as to the high temperature-resistant nickel alloy and that is integrally joined to the rotor base (12) and to the rotor blade (16) fusion. A method for the production of the component is also described.

Abstract: An improved seal assembly for use with a combustion liner assembly is employed with a gas turbine engine so as to control fluid flow. The seal assembly has a bi-metal sealing member that is affixed to a first surface that is proximal to a second perpendicular surface that is not in contact with the first surface, thus providing a potential fluid flow path. Upon heating, the bi-metal sealing member “uncoils” contacting the second perpendicular surface, thus blocking the flowpath between the two surfaces. Various metals may be provided to provide predetermined sealing characteristics.

Abstract: An airfoil includes an airfoil body having a first section and a second section that differ by coefficient of thermal expansion. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.

Abstract: A rotor blade comprising a core blade section; and a trailing edge section, the trailing edge section being attached to the core blade section along a join interface. The trailing edge section comprises a shape memory material which is actuable so as to cause selective deformation of the trailing edge section between a first condition in which a trailing edge of the trailing edge section follows a substantially smooth profile and a second condition in which the trailing edge is perturbed. The direction of the perturbation may be oblique or perpendicular to the direction of flow over the blade in use. The rotor blade may be a fan or propeller for a gas turbine engine.

Abstract: An exhaust-gas turbocharger (1) having a compressor (2); a turbine (3) which has a turbine housing (4); a bearing housing (5) which has a compressor-side flange and a turbine-side flange (6); a VTG cartridge (7) which has an adjusting ring (8); and an adjusting shaft (9) which is guided through the turbine-side flange (6) of the bearing housing (5), which has an inner lever (10) which engages into the adjusting ring (8) of the VTG cartridge (7), and which has an outer lever (11, 11?, 11?, 11??) which is connected to an actuating element (12) of an actuator (13), wherein the outer lever (11, 11?, 11?, 11??) has an open rounded fastening receptacle (14) into which an associated shaft portion (15) of the adjusting shaft (9) engages.

Abstract: A thermal expansion joint suited for metal sheet component assemblies and method of connection is described. The expansion joint connection is formed by overlapping edge portions of components which are subject to different temperatures. Slot apertures are formed in the edge portion of a first component at predetermined locations and hole apertures are formed in the edge portion of the second component and disposed for confronting alignment with the slot apertures. A connecting sleeve is disposed in each hole aperture and projects through the hole and associated slot and a retention washer is secured over an end of the connecting sleeve on the other side of the second component. A fastener extends through the retention washer and the connecting sleeve to clampingly interconnect the overlapped edge portions of the first and second components.

Abstract: A self-adjusting device (25) for controlling the clearance (C), especially in the radial direction, between rotating and stationary components (21, 23) of a thermally loaded turbo machine, changes clearance (C) in a linear and/or non-linear way during transition of the machine between standstill and steady-state operation. Simple and effective control can be achieved, even in the case of a nonlinear variation of the clearance during transitional operation, by the self-adjusting device (25) including at least two different driving elements (A, B) to move the rotating and fixed components (21, 23) relative to each other in order to change the clearance (C) between them, and by the different driving elements (A, B) being configured to be activated at different times during the transition of the machine.

Abstract: A hydropower generating turbine having an impeller housing disposed to receive water, at least one impeller disposed within the impeller housing, at least one adjustable duct pivotally connected to the impeller housing, and, where the duct has a plurality of duct leafs, wherein the duct leafs articulate and cause the duct to converge and diverge for selectively disposing a fluid about the impeller. The ducts may be inflow or outflow ducts, and the turbine may react to a change in the fluid and alter the shape of the impeller. Further, the turbine may have an automated controller where variable change in the flow is detected by a sensor and transmitted to the automated controller to cause a directional shift in the multidirectional turbine.

Abstract: A gas-turbine engine includes stator vanes (1) angularly variable about their longitudinal axes by actuating elements in order to control airflow supplied to downstream rotor blades (6). The actuating elements are arranged in the most confined downstream stages of the compressors and/or turbines, with these stages being exposed to high temperatures, so that stable and efficient operation is ensured. The actuating elements (8) fixed to the inner or the outer casing (4, 12) are made of a material expanding, contracting or deforming in dependence of the temperature and transmit the respective deformation to the swivellably borne stator vanes (1).

Abstract: The present invention provides a turbine blade that is exposed to a high temperature atmosphere at relatively high temperatures and to a low temperature atmosphere at relatively low temperatures, including: a concave-curve-like pressure surface that is concaved along a flow direction of fluid; a convex-curve-like suction surface that is convexed along the flow direction of the fluid; and a concave and convex formation device which causes a concave and convex portion along the flow of the fluid to appear on the suction surface when the turbine blade is exposed to the low temperature atmosphere, and which turns the suction surface into a smooth surface along a convex curve surface of the suction surface when the turbine blade is exposed to the high temperature atmosphere.

Abstract: A support for a bearing that guides a shaft in a turbomachine is disclosed. The support includes an annular part made of a shape memory material which retains an initial shape when the load applied to it remains below a threshold value and which deforms, absorbing energy when the applied load becomes at least equal to the threshold value. The annular part is capable of reverting at least approximately to its initial shape when the applied load drops back below the threshold value.

Abstract: A multidirectional hydrokinetic power generating turbine has an impeller housing with one or more impellers disposed within the impeller housing, one or more adjustable ducts pivotally connected to the impeller housing, and a plurality of duct leafs disposed about the one or more ducts. The plurality of duct leafs articulate and cause the one or more adjustable ducts to converge and diverge to selectively disposing a fluid about the one or more impellers.

Abstract: A method of repairing a turbine exhaust case strut heat shield vane includes removing a damaged portion of the vane, solution heat treating the vane, attaching a replacement section to the vane, and relieving local stresses in an attachment area between the replacement section and the vane.

Abstract: An apparatus for controlling a fluid flow is disclosed herein. The apparatus includes first and second spaced walls defining opposite sides of a first fluid passageway extending along a first axis. At least one of the first and second walls is cantilevered along the first axis and includes a distal end moveable relative to the first axis. The distal end of the at least one wall is moveable in response to changes in the flow temperature to passively vary a size of the first fluid passageway.

Abstract: A brazing assembly includes a tungsten/carbide/cobalt substrate (e.g., wear pad), a second substrate including titanium or titanium alloy (e.g., a midspan shroud of a fan or compressor blade) and a brazing material including gold, nickel, and copper present in respective amounts to improve the ductility of the braze joint. A brazed article includes a first substrate, a second substrate, and a braze joint having a post-braze hardness of between 450 and 600 KHN. A method to improve the impact resistance of a braze joint between a tungsten/carbide/cobalt substrate and a substrate including titanium or alloy thereof includes utilizing a brazing material including gold, nickel, and copper and brazing at temperatures less than about 1900° F. (1038° C.).

Abstract: An apparatus for sealing a turbine against leakage of a working fluid comprising at least one radially displaceable sealing ring, coaxially disposed about a rotating member of the turbine from a stationary member of the turbine, which sealing ring undergoes radial displacements that are coupled to radial displacements of the rotating member, such that a design radial clearance is substantially maintained without damage to the apparatus.

Abstract: A welded component includes at least one high temperature segment of a high alloy Cr steel with high creep strength and a low temperature segment of a low alloy steel with high toughness and/or a high yield strength which are connected materially to one another via a weld joint. In one such component a gradual transition of chemical, physical and mechanical properties in the joining area is achieved in that between the weld joint and the high temperature segment there are at least two successive clad layers of at least two lower alloy weld metals with a total content of elements which increase the creep strength, such as for example Cr, Mo, W and V, which total content decreases toward the weld joint, and/or an increasing total content of elements which increase the toughness and/or yield strength, such as for example Ni and Mn, which total content increases toward the weld joint.

Abstract: An axial flow compressor (16) comprises a plurality of variable stator vanes (32) circumferentially spaced apart and extending radially. Each variable stator vane (32) is rotatably mounted on a compressor casing (28). A control ring (38) surrounds the compressor casing (28). Each variable stator vane (32) is connected to the control ring (38) by a respective one of a plurality of operating levers (40) and the control ring (38) is spaced from the compressor casing (28) by a clearance. A plurality of bimetallic strips (50) are arranged circumferentially and are positioned radially between the control ring (38) and the compressor casing (28) and the bimetallic strips (50) control the clearance between the control ring (38) and the compressor casing (28) whereby any error of the variable stator vane (32) angular position is reduced. Each bimetallic strip (50) extends radially outwardly from the compressor casing (28) towards the control ring (38).

Abstract: A device for injecting cooling air into a turbo-machine turbine rotor includes a plurality of injectors distributed regularly around a longitudinal axis of the turbomachine and mounted between an inner shroud and an outer shroud. Each injector has a bimetallic structure with a first metal material forming a major portion of the structure of the injector and having a first coefficient of thermal expansion, and a second metal material forming a complementary portion of the structure in the vicinity of the suction side wall meeting the trailing edge of the injector, and having a second coefficient of thermal expansion that is smaller than the first.

Abstract: The invention relates to a hybrid blade (1) for thermal turbomachines, having an airfoil (2) made of a metallic material of a certain density, and having a blade root (3). It is characterized in that the blade root (3), compared with the airfoil (2), is made of a different metallic material having a lower density, and in that the airfoil (20) is connected to the blade root (3) in a positive-locking manner. The blade in this case is advantageously a compressor blade, in particular a high-pressure compressor blade, in which the airfoil (2) is made of a stainless CrNi steel and the blade root (3) is made of a high-temperature titanium alloy or an intermetallic gamma titanium aluminide alloy or an intermetallic orthorhombic titanium aluminide alloy.

Abstract: For material reduction, a fan blade made of solid material for a gas-turbine engine is provided in the area of the blade tip with at least one cavity (5) extending from the face of the blade tip. Thus, apart from the aspect of weight saving, the vibration amplitudes and the centrifugal forces can be reduced considerably and the natural vibration behavior improved in a simple manner, ultimately increasing mechanical strength.

Abstract: A wind turbine rotor blade (10) comprising one or more means (4) secured to the blade (10) for changing the profile thereof depending on the atmospheric temperature. The means comprises at least one laminate having at least two layers of materials with differing thermal expansion coefficients.

Abstract: A sealing system for reducing a gap between a tip of a shrouded turbine blade and a stationary shroud of a turbine engine. The sealing system includes one or more seal lands extending from a shrouded turbine blade toward a stationary shroud of a turbine engine. During operation of the turbine engine, the seal lands straighten and extend towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the shrouded turbine blades and increasing the efficiency of the turbine engine. The sealing system may also include one or more protrusions extending from the stationary shroud towards the tips of the shrouded turbine blades.

Abstract: A radial-flow pump (1), and especially a coolant pump for an internal combustion engine, comprising an impeller (2) provided with vanes (5) and a directing device (4) including at least one temperature- and/or speed-sensitive element for temperature-dependent control of the coolant flow, where at least one impeller vane (5) and/or the directing device (4) is configured as a speed-sensitive element. In order to increase efficiency, the proposal is put forward that the impeller vanes (5) should be elastically deformable by Coriolis forces of the coolant flow, the discharge angles (&agr;), which are preferably defined between impeller vanes (5) and impeller tangential planes (&egr;), decreasing with an increase in speed.