Abstract: A turbine engine stator has a metal casing surrounding an envelope carrying bearings for the pivots of pivoting blades. A control mechanism for setting the position of the blades includes a radial spindle to which are transmitted the thrust forces of the gases, the envelope being advantageously formed from angular sectors of axially juxtaposed flanges or rings and which are not loaded. Therefore, the bearings are not subject to wear giving rise to gas leaks and efficiency losses. Advantageously, the envelope is made from a composite material.

Abstract: Variable phase vane provided with a composite pivot having a joining piece for receiving the control pieces. The joining piece is made of a material less dense than the actual pivot. These two elements are force-fitted without using any weld or mechanical linking device.

Abstract: A guide vane for an axial guide baffle of an axial flow engine, such as a jet engine, is adjustable in its position about a guide vane adjustment axis extending radially to a rotational engine axis. The guide vane has a vane body and an adjustment lever extending at an angle of about 90.degree. away from the adjustment axis. The vane body, the adjustment lever, and at least one bearing journal form an integral one piece construction either of molded fiber composite material or of forged, e.g. drop forged, metal.

Abstract: A hydroelectric installation includes a hydraulic machine connected vertically below an electric machine by a shaft, in a concrete installation pit. A guide vane assembly of the hydraulic machine is operated by a motor-driven operating unit which projects below the hydraulic machine in a lower working space of the pit. The shaft has a thrust bearing which bears down against the upper cover of the hydraulic machine and thereby substantially cancels upward hydraulic force exerted on that upper cover. In the installation procedure, the outer casing, speed ring and upper cover of the hydraulic machine are installed first, so that the hydraulic machine can be assembled downwardly in the lower working space concurrently with upward assembly of the electric machine in an upper working space of the pit. This shortens installation time.

Abstract: The invention relates to a method to calculate optimum wicket gate positions based on only the initial face-to-face readings comprising the steps of measuring the initial gate openings, determining an optimum unit opening, and rotating each gate to the optimum opening. The method results in a one time adjustment that is more accurate and faster than conventional methods.

Abstract: In an axial flow turbine with a row of individually adjustable guide vanes (8) and a row of rotor blades (5), the guide vanes can be rotated by an adjusting shaft (9) supported in a casing (4) and passing through a vane carrier (3). The tips of the rotor blades seal against a cover (7). In order to match the duct contour to different heights of blading (5, 8), only the vane carrier (3) and the cover (7) are designed to be exchangeable, with otherwise unaltered machine geometry.

Abstract: In an annular array of stator aerofoil vanes (25 ) each of the vanes (25 ) has a flank portion (35 ) which is pivotally attached to the remainder of its associated vane (25). Actuation means (60) are provided to pivot each flank portion (35) relative to the remainder of its associated vane (25 ). Such movement of the flank portions (35 ) provides variation in the cross-sectional areas of the throat (61) defined between adjacent stator vanes (25).

Abstract: A stator for a turbo-engine and a method for mounting the stator serve to improve fixing of the vanes of the stator and resistance of these vanes to impact in the event foreign bodies enter the turbo-engine. The stator includes several vanes radially maintained by their external and internal pivots between an internal ferrule and an external casing. The internal ferrule includes at least one bore intended to receive one of the internal pivots and the external casing includes a mechanism for the radial positioning and locking of the vane so as to make it possible to keep the internal pivot of the vane in the bore.

Abstract: A device for ensuring the sealing in a rotary machine between a rotor and fixed blade stages.Blade edges are joined by rings carrying circular seals in slots. Springs force the seals in the longitudinal direction towards transverse faces of reinforcements of the rotor.A turbulence-free gas flow is obtained as a result of the total seal obtained by the seals (19). Moreover, the rotor can be constructed with a substantially rectilinear ferrule which only induces limited stress concentrations.

Abstract: A sealing structure for a gas turbine blade which pivots about a pivot shaft. A split ring is located in a groove on the shaft, in which the ring can be embedded and held by a bush. When the blade is fitted, the bush abuts against a wall of the stator, slides on the pivot shaft and frees the ring, which expands and forms the seal. The invention relates to gas turbines where the stator blades have a variable setting.

Abstract: A multiple vane, variable pitch, fluid active or reactive device to move or be moved by a fluid including first and second wheels each rotatable about its axis and the axes disposed in selected parallel offset relation. Aperatures provided in the first wheel receive rotatable vane shafts. A vane is provided on each shaft and a distal end of each shaft extends through the aperture. Follower members are connected to the distal ends of the shaft and extend generally parallel to the chord line of the vanes to control the pitch angle of the vanes. The second wheel is inset a selected distance from the first wheel and provides cams that extend outwardly from the second wheel to engage the follower members of the first wheel. A drive member is provided so that a rotational force applied to either wheel is transferred by a gear drive to the other wheel.

Abstract: An aerofoil vane actuation mechanism suitable for a gas turbine engine (10) comprises an annular array of pivotable aerofoil vanes (21) which are linked to an annular actuation member (30) by a plurality of levers (27). Each aerofoil vane (21) additionally has an indication lever (31) attached to it. Each indication lever (31) cooperates with the actuation member (30) so that under normal conditions, during pivoting of the vanes (21), no load transfer takes place between them. However in the event of one or more of the vanes (21) failing to pivot properly, such load transfer does take place. Means (37) are provided to detect such load transfer to provide an indication of such failure of a vane (21) to pivot properly.

Abstract: Conventionally gas turbine engine compressors have fixed inlet guide vanes to give a predetermined swirl to incoming air at an engine design speed, so that air enters the compressor at an optimum angle. At speeds much lower, for example, than the design speed the guide vane is less efficient. The guide vanes are thereby made variable in camber. Each vane comprises a number of spanwise hinged members which can be moved relative one to another to vary the vane camber.

Abstract: A variable angle stator vane assembly for an axial flow gas turbine engine compressor. The compressor casing has a bore surrounded by a boss at the position of each assembly. A housing having a central bore and a bushing assembly is located in the casing bore and is bolted to the boss. The stator vane spindle extends through the housing bore and busing assembly. The housing and bushing assembly can be removed from the casing bore, to be rotated 180.degree. or replaced, without removing the casing from the compressor or the stator vane spindle from the casing bore.

Abstract: An industrial gas turbine engine includes in serial flow relationship a booster compressor, a core engine, a power turbine having a first shaft joined to the booster and an output shaft, and means for independently varying the radially outer and radially inner booster flow areas. The means for independently varying the radially inner and outer booster flow areas can include a dual panel variable booster inlet guide vane assembly having first and second variable vane portions. The vane assembly can include a first variable vane portion rotatably supported with a first vane panel extending in a cantilevered manner adjacent a second vane panel to provide a closely spaced radial clearance therebetween. Varying means can be positioned outward of a casing for independently varying the first and second vane portions. The variable vane assembly can be operable with compressor bleed means or power turbine outlet area varying means.

Abstract: A blade control rod system for controlling blades of a gas turbine stator is provided with at least one rod for controlling an associated blade. The blade includes a shaft about which the blade pivots with one end of the rod being engaged on the blade. The control rod system includes a projection which extends beneath a portion of at least one adjacent rod, so that the accidental loosening of a nut which secures the rod on the shaft of the blade is not sufficient to allow the rod to become detached.

Abstract: Pre-rotational swirl controller for rotary pumps having a flow duct enclosed by a casing and a plurality of guide vanes located substantially radially within it. Each of these has two bearings, i.e. one on a hub located centrally and one on a trunnion which passes through the casing and which is also acted upon by an adjusting device. The guide vanes can be radially assembled through the casing because, for each guide vane, there is a removal slot which is closed by a cap which carries the seal and the bearing for the guide-vane trunnion, these being designed so as to be tolerant of alignment errors. A self-locking setting gear with a large transmission ratio and a through drive shaft is provided for the adjustment.

Abstract: Apparatus for the support and adjustment of stator blades of a gas turbine, in which an adjusting ring is connected to the stator blades by adjustment levers disposed outside the turbine housing. The adjusting ring is supported for rotation in the circumferential direction on a support ring, which has elastic resilience in the radial direction, the support ring being suspended on and centered in a movable manner on radial pins fixed in an outer housing of the turbine. The connection of the adjusting ring and the support ring is achieved by a ball-bearing which is pre-stressed. When the adjusting ring is displaced circumferentially, the stator blades are pivoted around suspension shafts by levers fixed to the shafts and connected to the adjusting ring for universal pivotal movement.

Abstract: Thermally actuated flow diverters for gas turbine engines are provided which include an arrangement of vanes in spaced overlapping array, which direct, e.g. coolant air flow to rotating engine components, each vane having 3 foil components joined at 3 hinge points. That is, a leading foil positioned on the suction side of the vane, a trailing foil pivotably mounted to a rearward portion of such leading foil at a first pivot axis and a third foil positioned on the pressure side of the vane connecting a forward portion of such leading foil and such trailing foil at second and third pivot axes respectively. Either the third foil or the leading foil is fixedly mounted to engine walls of the same material, the other of these two foils defining an actuation link that is expandable and contractable relative to such walls; the third foil having a coefficient of thermal expansion greater than that of the leading foil.

Abstract: A method and apparatus for adjusting the angle of variable angle inlet guide vanes provides a non-linear adjustment schedule for a selected vane row as compared to the adjustment schedule for the IGV vane row. The non-linear schedule is conveniently achieved by providing a modified adjustment linkage utilizing a bell crank. The non-linear schedule provides improved engine stall margin at low engine speeds.

Abstract: An axial drag regulator for large-volume radial compressors includes a flow channel which transitions from a first cylinder section via a spherical nozzle-like section into a second cylinder section, which in turn has a barrel face which has an inclination of slightly above 0.degree. and up to 10.degree. with reference to a barrel face which is parallel to the axis of the cylinder sections. The guide vanes supported in the transition plane from the first cylinder section to the spherical section have an axis of rotation which divides the guide vane face at a ratio of 1/3:2/3. The ratio of the diameter of the first cylinder section to the diameter at the intake of the second cylinder section is between 1.1 and 1.4. The rotation of the guide vanes is carried out by an adjusting ring placed upon the outside of the casing, which actuates the rotatable axle shafts of the guide vanes by the intermediation of an articulated lever.

Abstract: A variable vane assembly for a gas turbine engine is disclosed having a disk member bearing against a recess formed in the inner surface of the gas turbine engine casing is formed separately from the vane. The disk member has a diametrical notch that accommodates a strip member formed integrally with the vane and which extends generally parallel to the chord of the vane. The control rod, which is also formed integrallly with the vane, passes through an opening defined by the disk member and is pivotally supported by the engine casing. A low friction sleeve may be interposed between the control rod and the opening defined by the engine casing to reduce the pivoting friction of the vane. This sleeve may be formed as a separate element, or may be formed integrally with the disk member, which may also be formed of low-friction material.

Abstract: An arrangement for adjusting guide blades by thermal expansion has an expansion rod which has a significantly different coefficient of linear expansion with respect to the supporting housing and is aligned in the circumferential direction of the turbo-engine and is connected with an adjusting ring by way of a step-up lever. As a result, a guide blade adjustment can be achieved easily as a function of the working gas temperature.

Abstract: A turbocharger for an internal combustion engine can provide a two-stage compressor with movable stator blades to shift the compressor performance and match the air output of the turbocharger to varying air requirements of an internal combustion engine. The turbocharger can also be provided with a generally optimum boost pressure ratio of about 4.5:1 to 4.6:1. Such a compressor comprises a first axial-compressor stage, typically providing a 1.3:1 pressure boost ratio, and a second radial-compressor stage, typically providing a pressure ratio of 3.5:1. The turbine of such a turbocharger can be a combination flow turbine and can be provided with closure means to vary the turbine geometry and provide more efficient turbine operation at low-engine speeds. The turbocharger includes a roller bearing system adapted to accommodate imbalance. A control system operating in response to engine-operating conditions can operate the compressor-stator vanes and, if present, the turbine closure means.

Abstract: In a turbomachine, such as a turboshaft aero-engine, having a compressor casing composed of upstream and downstream casing rings, and a variably settable stage of stator blades which is mounted in one of said casing rings near the junction therebetween so that, in normal operation, the blades have their leading (or trailing) edges projecting into the other casing ring, the setting of the blades being adjusted by a control ring surrounding the casing, there is provided a locking system for temporarily locking the blades in an angular setting in which the leading (or trailing) edges are retracted clear of said other casing when the casing is to be dismantled or assembled.

Abstract: A stator vane stage in a split-case, variable geometry axial flow compressor includes two 180-degree spoke-like arrays of stator vanes on upper and lower case halves of the compressor case and a pair of unitary, 180-degree arc shroud ring segments. Each stator vane has a pivot shaft at one end rotatably supported in a radial bore in the corresponding case half by a bushing and a cylindrical vane button at the other end. Each shroud ring segment has a corresponding plurality of cylindrical vane button sockets in an outer surface thereof which rotatably receives a corresponding vane button. The spoke-like array of the stator vanes rigidly positions the shroud ring segments relative to the compressor case.

Abstract: Improvements to a mechanism for positioning variable vanes of a gas turbine are disclosed. Various construction details for introducing flexibility into the mechanism and for holding components in a snugly fitting relationship are discussed.

Abstract: An improvement in the inner tip support of variable inlet guide vanes in an axial flow compressor. Each of the guide vanes is rotatably mounted on a spindle at its radially outer end so that it can pivot between an open and a closed position. The improvement comprises a bushing disposed in the casing radially inward of each of said guide vanes, and a button on the end of each of said guide vanes contained within and forming clearances with the bushing walls, the button being eccentrically offset with respect to the guide vane spindle by a preselected amount and in a preselected direction to cause the button to provide restraining force on the vane inner ends when the vanes are in an open position.

Abstract: A guide vane assembly for controllably varying fluid mass flow rates past compressor blades in an auxiliary power unit. The auxiliary power unit comprises a rotary apparatus for compressing fluid in a compressor housing wherein a plurality of compressor blades are mounted on a rotating hub. A fluid flow path extends through the housing which has a duct portion extending upstream of the compressor blades to an inlet plenum to define at least a portion of the fluid flow path. The guide vane assembly includes a central gear box adjacent the compressor housing which has a ring gear mounted for limited rotational movement. A plurality of guide vanes are disposed in the duct portion of the housing and are mounted for pivotal movement responsive to rotational movement of the ring gear. The guide vane assembly is adapted to convert rotation of the ring gear to pivotal movement of the guide vanes.

Abstract: This invention relates to vanes for gas turbines and methods for making them. Embodiments include vanes that have internal fluid travel paths and cavities to permit the passage of fluids therethrough. Such embodiments have an internal structure member supporting an outer shell which has been formed so as to have outer surfaces in the configuration desired for a vane, and has been retentively positioned on said structural member. The outer surfaces of the support member are so configured that together with the inner surfaces of the cover, they form desired internal travel paths and cavities. Embodiments include such structures and methods for making same wherein the internal support structure is made in accordance with the teachings of U.S. Pat. No. 4,483,168.

Abstract: This invention relates to a device for controlling and synchronizing the guide vanes of a distributor of hydraulic machines, particulalry of turbines, which comprises ramps borne by spaced apart radial tabs secured with the synchronization ring. Each lever fitted angularly on the journal of each guide vane presents a free end which cooperates with the corresponding ramp by a roller. The profile of the guide vanes is such that the hydrodynamic force tend to close them.

Abstract: A variable stator vane assembly suitable for a power turbine in which each stator vane is provided at its radially inner and outer extents with disc-shaped platforms which locate on bushes provided on associated support structure. The bushes are cooled by a flow of cooling air which is of higher pressure than that of the hot gases operationally flowing over the vanes so as to prevent the leakage of such hot gases past the bushes.

Abstract: The shafts of guide vanes of an axial-flow engine, in particular, a combustion turbine, are supported angle-adjustably in an annular guide vane carrier and are spring-loaded and vibration-damped in their axis directions. An adjustment ring concentric to the flow channel is supported play-free and with low-friction engagement in a groove of a carrier ring by radial and axial rolls. Levers wedged on the guide vane shafts are pivoted by pins in a cylinder bolt, which, in turn, are supported rotatably and displaceably in laterally open bores of the adjustment ring and axis-parallel to it. This permits a largely play-free transfer of the adjustment motion onto the guide vane shafts without point or line contact. The guide vane carrier closes off the groove of the carrier ring so, that the entire mechanism is protected against dust.

Abstract: An adjusting device of a compressor includes guide vanes (2) arranged in the form of a ring around a longitudinal axis (4), which vanes are in each case connected fixedly in terms of rotation to pivot pins (8) and are pivotally mounted in the housing (46). Two-armed cranks (10) are connected fixedly in terms of rotation to the pivot pins (8), cranks (10) neighboring each other in circumferential direction being linked to each other by means of coupling links (24, 26). With a lower overall volume and low use of materials, a jamming, in particular in view of thermal expansions and production tolerances, is to be avoided. For use with a radial-flow compressor, it is proposed to arrange the cranks (10) and the coupling links (24, 26) in an annular space (52) which neighbors the discharge port, into which space the pivot pins (8) parallel to the longitudinal axis (4) protrude with their free ends.

Abstract: An inner shroud for a gas turbine engine is described comprising six approximately equiangular segments each segment adapted to securely contain a plurality of vane stems. The segments comprise interlocking first and second sections forming a channel having an aperture suitably sized to securely contain the vane stem. The sections when fit together form an outer recess area suitably sized to substantially accommodate the button portion of the vane stem and an inner cavity suitably sized to accommodate the inner portion of the vane stem. This results in reduced shroud curling when used in a split case compressor.

Abstract: Thermal degradation of variable nozzle components in a gas turbine power plant is minimized by a construction including a radial outflow compressor 16 on a shaft 10 with a radial inflow turbine 18, combustion gas delivery path 78 which is generally concentric about the shaft 10, a compressed gas delivery path 40 from the compressor 16 to the turbine 18 which is parallel to the axial combustion gas path 78 and rotatably mounted guide vanes 80 located in the axial combustion path 78 which are provided with control elements 82 that extend through the compressed gas path 40 so as to be cooled by compressed gas flowing in such path 40.

Abstract: Variable stator vane arrangements for compressors of gas turbine engines suffer from errors in the angular position of the variable stator vanes because of relative movement between the stator casing and control ring which is allowed by a clearance between the stator casing and control ring. A plurality of pieces of material which have a relatively high coefficient of expansion are arranged circumferentially and are positioned radially between the control ring and the stator casing. The pieces of material control the effective clearance between the control ring and the stator casing so that the error of the variable stator vane angular position is minimized. The pieces of material may be formed from a polyimide resin or high coefficient of expansion steel, and may be positioned in housings which are secured to the control ring.

Abstract: A variable guide vane 12 bushing assembly 10 which features means that prevents bushing rotation. A bushing 16 comprises flats 16b on its outer sleeve, the flats interlock with race track shaped holes 20a on a tab-lock washer 20. The tab-lock washer spans two or more adjacent vane stems (12,14) and thus is not susceptible to rotation. A retainer 24 and the vane arm 26 assemble on top of the tab-lock washer to complete the assembly.

Abstract: The cooling insert for a movable vane in a jet engine is divided into plural overlapping forward and aft segregated members, each member being coolant fed through separate vane trunnion areas and each insert is of successively decreasing cross-sectional area. Problems of locally inadequate vane cooling, coolant match point movement, and unequal coolant supply pressures are addressed by the disclosed apparatus. Reuse of the trunnion supplied impingement cooling air for additional cooling functions is also disclosed.

Abstract: A compressor for a gas turbine engine has a split case and a split stator vane inner shroud. Selected rotatable stator vanes longitudinally restrain the shroud and seal carried thereon to retain the desired roundness.

Abstract: An axial torque governor for a turbo-supercharger for internal combustion engines has a flow channel which is composed of a cylindrical section and of a spherical section following thereupon, the spherical section merging into a second cylindrical section by way of a nozzle section. The radius of the spherical section is equal to the radius of the first cylindrical section. A plurality of guide vanes are each composed of essentially circular segments which cover the cross-section of the first cylindrical section given complete closure of the inlet passage, whereby the pivoting axes of the guide vanes respectively lie in the entry edge of the vanes.

Abstract: The adjustment of clearances at the time of assembly and subsequently during operation of a labyrinth seal lying between the rotor and stator of a turbomachine is effected by radial displacements of a bush radially rigid with an outer pivot pin of each blade of the stator and co-operates with a boss of the casing by means of screw-threads. Such displacements are controlled as a function of a signal provided by a computer which integrates various operational parameters of the turbomachine and acts on a control ring connected by a lever to the said bush. The internal pivot of the blade is rigid with an annular member which carries a layer of abradable material constituting a fixed part of the labyrinth seal. The rotary part of the labyrinth seal is mounted on an opposed part of the rotor. A method for effecting the adjustment of the clearances is also described.

Abstract: The connection between the actuating link of each variably settable vane of a compressor flow straightener in a turbine plant and the control ring for the vanes comprises a cylindrical roller rotatably mounted in a bore in the ring parallel to the axis of the compressor, the roller having a radial bore registering with a radial opening in the ring and housing the shaft of the link as a rotary and sliding fit. This arrangement prevents any torsional strain on the link during operation, and is found to be substantially simpler and more reliable than the known arrangements.

Abstract: A variable stator assembly is provided for a gas turbine engine. The assembly comprises at least one winglet disposed on the radially inner end of each variable stator blade and/or on the radially outer end of each variable stator blade. The assembly further comprises at least one shroud disposed substantially adjacent and parallel to the associated winglet and within the flow path relative to the winglet. In a preferred embodiment, the assembly comprises both inner and outer winglets and inner and outer shrouds, with the shrouds being disposed intermediate the pair of winglets. The downstream edge of the shroud is configured to be substantially adjacent to the upstream edge of each variable stator blade through the full range of movement of each variable stator blade. Additionally, the shroud extends into the flow path between adjacent variable stator blades.

Abstract: A linkage (36) is provided for manipulating an internal component (32) of a turbofan gas turbine engine (10) in response to an externally mounted actuator (50). The linkage includes a radial torque shaft (38) supported between two spherical bearings (40, 42). The shaft (38) is slidable within the radially outer bearing (42) for accommodating relative radial movement in addition to relative axial and circumferential movement between the inner compressor case (26) and the outer fan duct (28).

Abstract: A guide vane for turbo-engines has a stationary vane section and a movable vane section with a gap between the two sections. The gap is covered on one side by a flexible band connected along its tape edges to the vane sections. The other side of the gap is covered by an elastic connected to the stationary vane section along one band edge while the other band edge overlaps part of the movable vane section to permit free relative movement between the elastic band (7) and the movable vane section. A plurality of such guide vanes are mounted at the radially outer end of their position adjustment member to an outer housing ring while the radially inner vane end or at least the radially inner end of the movable vane is free. A common position adjustment ring is connected to all adjustment members.

Abstract: A turbo-machine compressor which includes variable incidence stator vanes the angular adjustment of which is controlled by a control ring coupled to individual vanes by individual links. Each link has at least one contact surface on each of its longitudinal edges, such surfaces being either plane or convex. In the event of failure of any link, the change in orientation is controlled within narrow limits by contact with the contact surfaces of adjacent links which have not failed.

Abstract: An actuator assembly for imparting non-proportional tangential displacement (22b) to a plurality of unison rings (16b, 16c) disposed about the exterior of a compressor case (10b) is provided. The assembly includes a linear drive component (26b) mounted on trunnions (74, 76) and supported by a frame 48. The drive component (26b) imparts a rotating motion to a crankshaft 70 which in turn drives the unison rings (16b, 16c) via the respective crank arms (42b, 42c) and pushrod (30b, 30c) linkages. Radial loading of the compressor case (10b) is avoided by aligning both the pushrod (30b) and the elongated frame first end (50) tangential to the compressor case (10b).

Abstract: A method of manufacturing a variable incidence stator blade assembly comprising forming a blade with a root which forms an extension of the aerodynamic profile of the blade, forming a bush with a recess accommodating the root by ultrasonic, electro-chemical or electro-erosion machining and assembling the blade and bush in a turbo-machine outer casing and in an inner ring of channel section.A variable incidence stator blade assembled in a compressor of a gas turbine is also described, the blade assembly being as manufactured by the method. The channel section inner ring carried an abradable layer which co-operates to form a seal with annular lips carried by the compressor rotor drum.

Abstract: Disclosed is an actuator for rotating a plurality of circumferentially spaced variable vanes each having a spindle extending through a casing about which the vane is rotatable. The actuator includes an arcuate unison member and a plurality of levers each having first and second ends, respective ones of the levers being fixedly attached to a vane spindle at the lever first end and rotatably attached to the unison member at the lever second end. Frangible means are provided for allowing at least one of the vanes to be rotated to an angular position different from the position of adjacent ones of the vanes upon impact of the one vane by a foreign object, and limit means are provided for maintaining the angular position of the one vane within predetermined limits with respect to the angular position of adjacent vanes to prevent 1/REV excitation.