Abstract: A turbocharger (1) is provided with one or more movement control members (300) that are connected to the housing (2, 3, 3a) and limit axial movement of the adjustment ring (5). The members (300) can be inserted into one or more holes (400) formed in the housing (2, 3, 3a) and can extend from the holes (400) in a direction towards the adjustment ring (5). The holes (400) can be through-holes, blind-holes or combinations thereof. Various connection structures and methods can be used to affix the members (300) to the housing (2, 3, 3a) including self-locking members, casting, heat welding, friction welding, vibration hammering and staking.

Abstract: A variable stator vane assembly for a gas turbine engine has a projection protruding from the upper stem of the vane and which engages an aperture in the vane lever to provide a visual indication of correct alignment between the lever and the vane.

Abstract: A system for controlling angular position of stator blades including: a mechanism for calculating a set angular position of the blades according to one of speeds; and a module for correcting the set position including: a mechanism for determining the angular position of the blades; a mechanism for measuring fuel flow rate of the turbine engine; a memory unit in which consecutive angular positions of the blades are combined with the fuel flow rates of the turbine engine measured at the angular positions; and a mechanism for determining a correcting angle according to the difference between the fuel flow rates measured between two consecutive angular position of the blades. A method for optimizing the common angular position can utilize the system.

Abstract: The invention relates to a charging device (1), more preferably an exhaust gas turbocharger for a motor vehicle, which turbine geometry comprises guide blades (5) rotatably mounted in a blade bearing ring (4), wherein the blade bearing ring (4) with a side is directly exposed to a hot gas flow (12) while the side of the blade bearing ring (4) facing away from this is only indirectly exposed to the hot gas flow (12). It is substantial to the invention that the blade bearing ring (4) on its side directly exposed to the hot gas flow (12) is produced of a different material than on its side only indirectly exposed to the hot gas flow (12) wherein the two materials with regard to their heat expansion coefficients are selected in such a manner that the blade bearing ring (4) at preferentially all occurring operating temperatures expands evenly without warping.

Abstract: One or more variable pitch airfoils in fluid communication with a rotor of a fluid turbine can control the amount of energy directed to the rotor, and further control the amount of energy generated by the turbine. Varying the pitch of the airfoils may provide a means of controlling the power output of a fluid turbine without the need to control the pitch of the rotor blades, and may further provide a means of mitigating the effects of wind shear on the rotor. Variable pitch airfoils may also include a means of controlling the active power, reactive power and SCADA, of a group of fluid turbines.

Abstract: A method and a device to counteract wear about a guide vane (16) from a particle bearing drive water, the guide vane (16) being arranged in a guide vane housing (14) in a water turbine (1), and where the method comprises: —routing a supply channel (36) for water cleaner than the drive water to the attachment point area between the guide vane (16) and the guide vane housing (14); and—leading water cleaner than the drive water to flow through a slit (28) where the slit (28) at least partly encircles the guide vane (16).

Abstract: The present invention provides a variable pressure ratio gas turbine. In an embodiment, the engine is configured to selectively bypass all or a portion of a high pressure compressor and a high pressure turbine. In an embodiment, during bypass operation, all or a portion of the flow that would otherwise pass through the high pressure compressor and the high pressure turbine may be routed through a respective compressor bypass duct and turbine bypass duct.

Abstract: An aircraft propulsion system has a propulsive rotor assembly rotatable about an axis of rotation and comprising a plurality of blades and a rotationally fixed vane assembly located adjacent to the propulsive rotor assembly and arranged circumferentially around the axis of rotation. As airflow enters the propulsive rotor assembly, a portion of the airflow passes over the vane assembly which is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blades. This results in a reduced tendency of the airflow through the propulsive rotor assembly to become choked.

Abstract: An exemplary assembly includes a component of a turbocharger that includes a bore that extends between an inner, exhaust gas side of the component and an outer, ambient side of the component; a shaft that includes a pin portion and a head portion; a sleeve positioned on the pin portion of the shaft; and a bushing positioned over at least part of the sleeve and over at least part of the head portion of the shaft where the bushing seats the shaft and the sleeve in the bore. During operation of a turbocharger that includes such an assembly, the shaft, the sleeve and the bushing restrict flow of exhaust gas from the inner, exhaust gas side of the component to the outer, ambient side of the component. Various other exemplary devices, assemblies, methods, etc., are also disclosed.

Abstract: A compressor for a gas turbine engine with variable inlet guide vanes each defining an airfoil portion twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall to a maximum value near the shroud side wall. A method of reducing vortex whistle in a radial inlet of a compressor is also provided.

Abstract: A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.

Abstract: A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions.

Abstract: A vane assembly for a gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible features, a first platform, a second platform spaced from the first platform, and a first variable airfoil that extends radially across an annulus between the first platform and the second platform. One of a radial outer portion and a radial inner portion of the variable airfoil includes a rotational shaft and the other of the radial outer portion and the radial inner portion includes a ball and socket joint that rotationally connect the first variable airfoil relative to the first platform and the second platform.

Abstract: A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a movable actuation rod and a first linkage arrangement which includes a first bell crank connecting the actuation rod to a first component. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank connecting the actuation rod to a second component. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first and the second linkage arrangements are configure so that over a predetermined range of movement of the actuation rod the first component is moved which the second component is not moved.

Abstract: An axial turbine (1) has a plurality of expansion stages (2) each defined by stator blades (13) and rotor blades. The expansion stages (2) are followed by an exhaust diffuser (4) for collecting the flow passing through the expansion stages (2) and discharging it to the outside. The expansion stages (2) and/or the diffuser (4) have at least a non-axial symmetric portion. The stator blades (13) define different openings (17) along the circumference of the turbine.

Abstract: An inner diameter shroud for receiving an inner diameter base portion of a rotatable vane in a gas turbine engine has a single piece channel and a core. The channel has a leading edge wall, an inner diameter wall, a trailing edge wall, a radial outer surface, and at least two axial projections. The axial projections prevent radial movement of the core. The core has an outer radial surface that generally aligns with the radial outer surface of the channel. The core is movable in the channel in a circumferential direction and is configured to rotatably retain the inner diameter base portion of the rotatable vane.

Abstract: A variable stator blade assembly of a compressor, in particular of a gas turbine, including a compressor casing with a counterbore and a receptacle, a stator blade with a spindle, a spindle bush and a seal is provided. The spindle bush is placed inside the receptacle and spindle is placed inside the spindle bush wherein the seal is placed radially between the spindle and the spindle bush. The spindle is the dynamic seal face and a face within the spindle bush is the static seal face.

Abstract: A pitch drive device of a wind turbine generator and a wind turbine generator that have simple and inexpensive structures and that are capable of preventing a decrease in the reliability of the pitch drive device are provided. There is provided a cylinder (12) configured to change a pitch angle by driving a wind-turbine rotary blade (6) to turn around an axis with respect to a rotor head (4); and a cylinder bearing (14) configured to support, in a turnable manner, a trunnion (16) extending from the cylinder (12) substantially parallel the axis of the wind-turbine rotary blade (6), wherein anti-vibration rubber (21) configured to elastically support the trunnion (16) is provided on a support section configured to support the trunnion (16) of the cylinder bearing (14).

Abstract: A turbomachine compressor including variable-pitch vanes, each including an airfoil connected via a plate of circular outline to a pivot guided to pivot in an orifice in a casing, the plate including an air feed duct including one end for communication with a passage formed in the casing when the vane is in a first position, so as to inject air into the annulus of the compressor upstream from the vane, and to be closed by the casing when the vane is in a second position.

Abstract: A variable geometry turbocharger assembly comprises a unison ring which rotates about a longitudinal axis defined by a shaft on which a turbine wheel and compressor wheel are attached in order to pivot a plurality of vanes and thereby control a flow of exhaust gas to the turbine wheel. The unison ring rotates on at least one guide pin which is secured to the turbocharger. The guide pins may be press-fit into apertures in a center housing at an outer pilot surface. In other embodiments the guide pins may be press-fit into a different part of the turbocharger such as a nozzle ring. The guide pins may each have a wear surface which defines a circumferential radius of curvature which is substantially equal to a circumferential radius of curvature of a radially inner surface of the unison ring.

Abstract: An airflow shielding device is configured for being secured to fan and includes a first member, a second member, and a plurality of shielding pieces. The first member defines a first through opening. The second member defines a second through opening corresponding to the first through opening. The shielding pieces are rotatably secured between the first member and the second member and rotate between a closed position, where the shielding pieces cover the first through opening, and an open position, where the shielding pieces are located so that air can flow through the first and second through openings.

Abstract: A variable vane actuation system is disclosed herein. The variable vane actuation system includes a ring member disposed for pivoting movement about a centerline axis. The ring member is engaged with a plurality of vanes in a turbine engine such that the plurality of vanes pivot in response to the pivoting movement of the ring member. The variable vane actuation system also includes a ring moving device engaged with the ring member at first and second positions spaced from one another about the centerline axis. The ring moving device is operable to apply first and second forces, respectively, at the first and second positions to pivot the ring member.

Abstract: In one embodiment a system is disclosed that includes an actuation device coupled with a turbomachinery mechanism. The actuation device can include multiple fluid pathways and a valve to alternatively place each of these pathways in fluid communication with a supply port while another of the pathways is in fluid communication with a return port to selectively move an actuation member along a range of travel. A brake valve may also be included to provide pressurized fluid to the actuation member when the actuation device is in an on condition and divert at least a portion of the pressurized fluid away from the actuation member through another pathway when the actuation device is in an off condition. A fluid-powered brake is coupled to this further pathway to selectively apply braking force to the actuation member in response to the diverted pressurized fluid.

Abstract: The present invention includes a pivotable vane having an airfoil with a vane spindle or stem extending toward a distal end thereof. The vane stem has a head with a pair of tapered flats having an outwardly extending angle as defined from the distal end of the head towards the airfoil. A vane arm having a substantially C-shaped connector with a pair of contact ends is constructed to maintain a gap with the tapered flats at an initial assembly step and positively engage the tapered flats at a final assembly step.

Abstract: In one aspect of the present invention, a downhole drill string assembly comprises a bore there through to receive drilling fluid. A turbine may be disposed within the bore and exposed to the drilling fluid. At least one flow guide may be disposed within the bore and exposed to the drilling fluid wherein the flow guide acts to redirect the flow of the drilling fluid across the turbine. The flow guide may be adjusted by an actuator. Adjustments to the flow guide may be controlled by a downhole telemetry system, a processing unit, a control loop, or any combination thereof. In various embodiments the turbine may comprise rotatable turbine blades.

Abstract: A variable vane actuation system is disclosed herein. The variable vane actuation system includes a first vane having a first vane axis. The variable vane actuation system also includes an actuator operably engaged with the first vane to selectively pivot the first vane about the first vane axis. The variable vane actuation system also includes a ring member operably connected with the first vane. The ring member is disposed for pivoting movement about a centerline axis transverse to the first vane axis. The variable vane actuation system also includes a second vane having a second vane axis spaced from the first vane axis about the centerline axis. The second vane is operably connected with the ring member. Forces moving the second vane are generated by the actuator and transmitted first through the first vane and then through the ring member before being applied to the second vane.

Abstract: Systems and methods for maneuvering an underwater vehicle by generating vehicle maneuvering forces from a propulsor of the vehicle are provided. A ducted, pre-swirl propulsor is configured such that the pitch angles of the stator blades of the upstream stator row can be varied. By varying the pitch angles of the stator blades about the circumference, a mean stator side force is generated. Subsequently, the axial velocity and swirl that is ingested into the inflow is varied. The rotor of the propulsor then generates a side force in response to the inflow.

Abstract: A turbo compressor in an axial type of construction is disclosed. The turbo compressor has a bladed stator and a bladed rotor, and has a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside.

Abstract: A variable vane assembly, for example of stator vanes in a gas turbine engine, comprises vanes which can be turned together about their longitudinal axes by means of a unison ring which is turned by an actuator about the engine axis. The unison ring is coupled to the vanes by levers. The unison ring has varying stiffness along its circumference, increasing in the direction away from the drive point at which the actuator acts. The varying stiffness may be achieved by varying the radial thickness of the unison ring. The unison ring is thus able to resist ovalization so that the vanes move together.

Abstract: When changing a nozzle blade angle by rotating a drive ring, a contact load generated between an inner circumferential surface of the drive ring and an outer circumferential surface of a mount can be reduced, allowing the drive ring to rotate smoothly and reducing the amount of wear and a driving force. It is also possible to reduce an impact force, such as engine vibrations, generated at the drive ring when an external force acts, reducing the risk of damage. A plurality of notches (19) are provided at an inner rim of the drive ring (14), and, among inner circumferential surfaces (14a, 14b, 14c, 14d, 14e, 14f, 14g, and 14h) located between the notches (19), when a driving force for rotating the drive ring (14) is applied, the inner diameters of the inner circumferential surfaces (14e, 14f, 14g, and 14h) where the contact load with the outer circumferential surface of a mount becomes large are made larger than the outer diameter of the outer circumferential surface.

Abstract: An inlet guide vane assembly includes an active control feedback system and a plurality of inlet guide vanes. The inlet guide vanes are variable between a plurality of positions. Each of the plurality of inlet guide vanes is positioned in response to an output of the activate control feedback system.

Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.

Abstract: Charging equipment is disclosed, comprising a variable turbine geometry, and a plurality of guide vanes rotatably mounted between at least one of a guide vane carrier, a cover disc and a turbine housing. The guide vane carrier is positioned on at least one of the cover disc and on the turbine housing by at least one spacer. The geometry has at least two different types of flow channels, a first flow channel wherein flow is influenced by the spacer, and a second flow channel wherein flow is not influenced by the spacer. The first flow channel guide vanes have a radial distance (R1) to a turbine wheel axis, and to a distance from an adjacent guide vane are configured and adjusted such that a gas flow from the first flow channel meeting the turbine wheel corresponds to a gas flow from the second flow channel meeting the turbine wheel.

Abstract: Disclosed herein is a turbine variable position guide vane actuation system. The system includes, a plurality of variable position guide vanes, a plurality of actuators with each actuator in operable communication with one of the plurality of variable position guide vanes, and each of the plurality of actuators having a pin. The system further having at least one structure, movable parallel to an axis of the turbine, having a plurality of slots and each of the plurality of slots is in operable communication with one of the pins.

Abstract: A turbomachine includes a variably positioned vane, an outer spindle integral with a vane outer button, where the vane is coupled to the vane outer button, an annular sleeve defining the spindle, where the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent. The annular sleeve includes a wall portion having an aperture and the spindle extends through the aperture. A nut engages spindle threads, where the nut applies force to the wall portion toward the radially inward extent. An end of the spindle extends through the turbine casing, and a cantilever rotation actuator is coupled to the end of the spindle. A first bearing and second bearing engage the annular sleeve. A vane inner button is coupled to the vane, and a third bearing engages the vane inner button.

Abstract: A multistage vacuum pump has a pair of rotors disposed in each of pump chambers connected in stages. As the rotors rotate while intermeshing, a suctioned gas is compressed and discharged, angles of the rotors are adjusted so that a phase angle ?? of the rotors of adjacent pump chambers relative to a rotation angle C of the rotors during a single cycle of the pump chambers from intake to discharge and the number of stages S of the rotors satisfies ???C/S. When a rotor angle is ?1, an mth stage rotor angle is ?m, and an nth stage rotor angle is ?n in order from an upstream side of a gas flow direction, relationships of ?1??m??n and ?1<?n, where n and m are natural numbers and n>m, are satisfied.

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 fastening for an attachment of a guide device to a gas outlet housing is positioned in a region radially outside guide blades. In this way, a circumferential position of the guide blades may be freely selected within predefined angles. Collisions are avoided between the guide blades and fasteners.

Abstract: An axial-flow compressor has at least one stator vane row. At least one blade of the stator vane row is provided as a rotating unit (6), with the rotating unit being completely rotatable about a drive axis to act as a rotary compressor and with the drive axis being essentially vertical to a rotary axis of the axial-flow compressor.

Abstract: Gas turbine engine systems involving gear-driven variable vanes are provided. In this regard, a representative gas turbine engine system includes: a ring gear assembly operative to be mounted within an engine casing; and a vane module having a first vane airfoil and a first gear, the first gear being operative to engage the ring gear assembly such that movement of the ring gear alters a position of the first vane airfoil.

Abstract: A gas-turbine axial compressor has a casing 3 and a rotatable shaft 6, which form an annular duct, in which at least one stator 2 and one rotor 4 are arranged. A shroud 21 is arranged at a free end of the stator 2 vanes, which extends over part of the axial length of the stator 2. A rotor platform 23 of at least one rotor 4 extends axially beneath a further part of the axial length of the stator 2, at which no shroud 21 is arranged.

Abstract: A variable inlet guide vane assembly for a gas turbine engine, where the guide vanes are pivotably connected to a sync ring that is contained within an annular groove within the casing so that leakage through holes in the casing is minimized. The guide vanes include a slider mechanism on one of the ends that will allow for both an axial and a rotational movement of the guide vane pin when the guide vanes pivot about a fixed pin on an opposite end of the guide vanes. A round rotary vane actuator with a height much less than a diameter is mounted outside of the casing and connects to the sync ring through a driving linkage.

Abstract: Expansion turbine having a variable nozzle mechanism comprises an adiabatic expansion device located in a vacuum container having a turbine impeller therein which rotates and drives the turbine impeller during adiabatic expansion of very low temperature gas, and varies the throat area of very low temperature gas introduced in the turbine impeller by driving a nozzle member disposed near the outside end of the adiabatic expansion device by a drive force from a driving member located outside the vacuum container; wherein the driving member comprises a cylindrical member disposed coaxially with the turbine impeller, and the nozzle member is provided on the extension of the body of the cylindrical member in the axial direction.

Abstract: A variable guide vane actuator for positioning the guide vanes of a turbine engine in a hypersonic missile uses compressor exhaust to drive a linked, floating piston assembly that is coupled to the guide vanes. The relatively low pressure compressor exhaust is metered by a valve to drive the piston arrangement to accurately position the guide vanes in proportion to the input control signal. Reliability and accuracy gains are achieved by inhibiting the effects of vibration and thermal distortion through the elimination of piston/bore contact, the use of a rigid, cantilevered mounting arrangement and cooling with the pre-combusted liquid fuel.

Abstract: Disclosed is an air intake for a turbocharger for an internal combustion engine, said air intake including a series of variable position guide vanes for directing the air such that it is swirling in a rotational sense on reaching the impeller of the compressor of the turbocharger. The variable position guide vanes are made comprised of sound absorbent material such as to achieve a substantial reduction in turbocharger noise at the air intake.

Abstract: A turbomachine including a variable-pitch stator vane stage is disclosed. A control ring that is coaxial around the casing includes two segments that are assembled together by side connection straps fastened on either side of the segments with mutual insetting and in the vicinity of the ends of the segments.

Abstract: A variable geometry turbine comprises a turbine wheel (5) supported in a housing (1) for rotation about a turbine axis. An annular inlet passage (9) is defined between first and second radial inlet surfaces, one of said first and second inlet surfaces being defined by a moveable wall member (40). A substantially annular array of vanes (41) is provided which extend across the inlet passageway (9); each vane (41) being fixed to said first inlet surface. Each vane (41) has first and second major vane surfaces (45, 46) having a chordal length extending between a radially outer leading vane edge (47) and a radially inner trailing vane edge (48), the first major vane surface (45) facing generally away from the axis and the second major vane surface (46) facing generally towards the axis. A rib (43) extends across at least a substantial portion of the chordal length of at least one of the first and second major vane surfaces (45, 46) of one or more vanes (41) of the array.

Abstract: In a turbocharger equipped with a nozzle vane for changing the speed of exhaust gas running through a turbine in accordance with the speed of engine revolution, the member to constitute the nozzle vane and to constitute an exhaust guide for guiding exhaust gas to the turbine is characterized in that the exhaust guide member of a nozzle vane-type turbocharge is formed of an austenite stainless steel containing, in terms of % by mass, at most 0.08% of C, from 2.0 to 4.0% of Si, at most 2.0% of Mn, from 8.0 to 16.0% of Ni, from 18.0 to 20.0% of Cr and at most 0.04% of N and containing these ingredients in such a manner that they satisfy a DE value of the specified formula to be from 5.0 to 12.0, with a balance of Fe and inevitable impurities.

Abstract: A stator stage of a compressor of a turbomachine including an annular row of variable-pitch vanes is disclosed. Each vane includes an external cylindrical pivot defining the axis of rotation of the vane, and an internal cylindrical pivot mounted in a housing of an internal ring. The internal pivot of each vane extends along an axis substantially parallel to the axis of rotation of the vane and at a distance from this axis, and is mounted in the housing of the ring by a swiveling or a tilting system.

Abstract: Gas turbine engines and related systems involving variable vanes are provided. In this regard, a representative vane assembly for a gas turbine engine includes: a first inner diameter platform; a first outer diameter platform spaced from the first inner diameter platform; and a variable vane airfoil rotatably attached to and extending between the first inner diameter platform and the first outer diameter platform such that at least a portion of the vane airfoil extends beyond a periphery of at least one of the first inner diameter platform and the first outer diameter platform.