Abstract: A multistage hydraulic machine includes a water chamber in a bottom ring of the highest-pressure stage. The water chamber supplies cooling water to seal gaps between rotary and stationary elements through a communication passage connected to the water chamber.

Abstract: The invention relates to a turbo-machine incorporating a compressor with stator vanes of which the angle of incidence is adjustable. In order to enable adjustment in the position of the internal ring of a stator of the compressor, each of the sectors of the ring is provided with adjustment locations constituted by the bushes of pivot bearings for the roots of the vanes which roots comprise an external screw thread cooperating with a complementary internal screw thread of their seating and these come into abutment against a shoulder of the pivot of each vane so that the radial position of each of the sectors can be adjusted by rotation of the bushes in their respective seating.

Abstract: Stator vane retaining means such as may be used in a compressor of a gas turbine engine is disclosed. The compressor is the type including a casing with first and second annular members and a plurality of vanes, each vane having a vane axis and a root end for mounting to the casing. The stator vane retaining means comprise a first flange extending radially outwardly from the first member and a second flange extending radially outwardly from the second member. The second flange includes a plurality of radially extending recesses. The flanges are adapted to mate so that the first flange encloses the recesses thereby forming a plurality of radially extending holes. Each of the holes is adapted to receive one of the root ends. The stator vane retaining means may also include a plurality of bolts extending through the flanges and intersecting a cut-out portion of each of the root ends of the vanes. In this manner, radial retention of each of the vanes is provided.

Abstract: There is provided a propulsion installation of an air-cushion transport vcle wherein an axial fan having working blades is installed in an annular duct; a ring slat is positioned before said annular duct so that said annular duct and said ring slat form therebetween an annular passage the exit of which is disposed ahead of said working blades installed in said annular passage is a vane cascade made up of curved plates, with a concave portion of each being directed toward a pressure side of said working blades.

Abstract: A low-temperature pump having a throttling valve formed by tilting radially disposed vanes in side-by-side relation, capable of fully opening a pump port to a process chamber. Motion from one vane can be coupled to the next through shims which support the vanes and form a seal when the vanes are flat in a common plane. One of the vanes may be controlled independently of the others so that coarse and fine modes of operation may be achieved by separately controlling (N-1) vanes and the Nth vane. The vanes are maintained in thermal contact with a chilled outer wall surface of a first pumping stage of a two-stage pump, the second stage coaxially surrounding a first stage maintained at a very low temperature. A central hub, at the convergence region for the vanes, supports a shield, protecting the second stage from radiation through a port in the upper regions of the pump.

Abstract: The device consists of an arm having structure for attachment to the bottom pivot of a stator blade. Stopping elements are provided in the inner stator ring against which the arm can come to rest. The stopping elements consist of the sides of a circumferential notch formed in the inner surface of the inner ring. A C-shaped molding fastened onto the inner ring makes the notch leak-proof.

Abstract: A system for pressurizing cavities arranged laterally of pivotal vanes of a variable primary nozzle system in a radial turbine. The cavities are supplied with fluid of increased or reduced pressure to resist the clamping forces of the mounting rings. The fluid may conveniently be influent pressure or nozzle discharge pressure as may be appropriate. Pressure to the cavities is controlled as responsive to the pressure in the actuator system for adjusting the nozzles.

Abstract: Adjacent cylindrical bearings disposed within a wall are prevented from rotating and moving axially by a sheet metal tablock which simultaneously engages a slot in the external surfaces of each bearing. A cap fits around each bearing, and a flange on each cap overlies the tablock. Tab ends of the tablock are folded over the flange and trap the tablock in position.

Abstract: In a device for regulating the air supply of an internal combustion engine supercharged by a turbo-compressor unit driven in rotation by the engine's exhaust, the intake of the rotating compressor is controlled by an intake regulation (or gating) system capable of reducing the compressive effect of the rotor of the compressor. Control elements of said regulation (or gating) system are connected with the accelerator linkage so as to close the regulation (or gating) system and reduce the compressive effect to the maximum degree when the accelerator moves toward the idling position of the engine.

Abstract: A linkage system for actuating the variable vanes and the air bleed valve of a gas turbine engine compressor in an intermittent sequence includes a single actuator and a linkage mechanism. The latter is formed of a first actuating linkage extending to the bleed control valve, a second actuation linkage extending to the variable guide vanes, and an intermediate crank mechanism connected to the first and second actuating linkages and also to the single actuator. The linkage system is operative to convert the linear motion from the single actuator to multiplane intermittent rotational motion of the actuating linkages extending to the variable vanes and the bleed valve of the compressor. When embodied in a military aircraft, the single actuator is preferably disposed above the compressor casing so as to make it less vulnerable to enemy ground fire.

Abstract: A gas flow control valve wherein radially disposed vanes are mounted within an annular flange with rotationally mounted shims connecting the radial vanes to the inner peripheral surface of a flange. The shims are disposed in a rim-to-rim configuration with a groove defined in rims of the shims and a cable laid in the grooves in a serpentine pattern. By causing one of the shims to rotate by means of a sealed shaft extending through the flange, the remaining shims may be driven by the cable causing corresponding motion of the vanes. The shims are mounted to the flange by means of pins. The shims are relatively thin such that they may be hidden beneath overhanging regions on opposite side walls of the flange, exposing only the radially disposed vanes to a gas flow path.

Abstract: This wide range compressor has a casing forming a passage with an inlet and an axial portion, and a rotor with blades extending into the passage and functioning, when the rotor operates, to draw air into the inlet and force it through the passage. One of the problems with wide range compressors is a variation of the pressure as the volume changes rather than maintaining a desired constant or substantially constant discharge pressure. To solve this problem, the present compressor is provided, first, with a ring in the inlet to divide the flow into inner and outer annuluses and, second, with vane or other elements positioned and operative to vary one of the flow annuluses to maintain the output pressure of the compressor substantially uniform over the complete range. The concept embodied in the additional structure disclosed herein is applicable to fans, blowers, compressors, and pumps of axial, centrifugal, or mixed flow configurations which often have difficult wide range requirements.

Abstract: A turbine vane adjustment assembly for calibrating the nozzle/throat width dimension between adjacent adjustable vanes in a nozzle vane ring assembly and for producing conjoint rotation of the individual vane following their calibration includes a vane stem that extends outwardly of a turbine case and further includes a motion converting sleeve in surrounding relationship thereto and coacting means between the sleeve and the vane stem that concurrently rotates both the sleeve and the stem and also provides relative axial movement of the sleeve with respect to the vane stem; the adjustment assembly further includes an actuator arm for rotating each of the vanes and means for connecting the actuator arm to the sleeve to cause angular positioning of the actuator arm to be directly transmitted to each of the vanes following calibration thereof.

Abstract: A variable geometry gas turbine has an array of ceramic composition vanes positioned by an actuating ring coupled through a plurality of circumferentially spaced turbine vane levers to the outer end of a metallic vane drive shaft at each of the ceramic vanes. Each of the ceramic vanes has an end slot of bow tie configuration including flared end segments and a center slot therebetween. Each of the vane drive shafts has a cross head with ends thereof spaced with respect to the sides of the end slot to define clearance for free expansion of the cross head with respect to the vane and the cross head being configured to uniformly distribute drive loads across bearing surfaces of the vane slot.

Abstract: Disclosed are apparatus for controlling fluid flow including a circumferential plurality of blades mounted between a parallel pair of axially spaced annular elements. The interstitial passages between the blades may be varied by the relative rotation of one annular element functioning as a ring actuator with respect to the stationary second annular element. The orientation of the circumferential blades is adjusted in unison by cam type engagements between one of the annular elements and the blades. An appropriate axial clamping force is applied to the assembly to frictionally secure the blades between the annular rings and to prevent end leakage of the fluid between the annular rings and the blade faces adjacent to the rings. Variation in the clamping forces acting on the blades as the blades are pivotally rotated to vary the passage cross sections therebetween may be controlled by providing pressurizable pockets in the blade faces adjacent to one or both of the annular elements.

Abstract: An inlet guide vane assembly for controlling air flow through a fan. A plurality of shafts are mounted extending radially inward of an inlet cone, and are affixed to a hub positioned at the center of the cone and concentric thereto. Rotatably mounted on each shaft is an adjustable inlet vane, having a crank arm extending from its root end. Cam follower bearings are used to rotatably mount a ring on the hub. The ring is connected to each of the crank arms by a link having a ball and socket joint at each end. Rotation of the ring thereby causes the inlet vanes to rotate about their supporting shafts without binding.

Abstract: Apparatus is provided for maintaining minimum clearance between variable position airfoils and the wall forming the gas flow path in a gas turbine engine. A constant clearance is maintained between a radially facing contoured wall surface and a radially facing contoured end face on the airfoil. The contour of the wall surface and the end face may each be spherical.

Abstract: Hydraulic turbo machines including pumps and pump turbines having pivotally adjustable wicket gates are vulnerable to damage caused by the ingress of dirty water containing abrasive particles into the bushings in which the stems of the wicket gates are pivotally supported in the headcover and bottom ring. This problem is overcome by the provision of individual seals between the end of each wicket gate and an adjoining surface portion of the headcover or bottom ring in which the bushings are located. In addition, seal water at a pressure in excess of machine operating pressure forces the seal ring into contact with the end of the wicket gate and also causes a slight flow of clean water outwardly between the seal and the respective end of the wicket gate, so as to keep the seal entry zone flushed clear of particulate material.

Abstract: An arrangement for operating shut-off members in gas turbine engines, particularly turbojet engines. Circumferential rotation of an actuating ring is converted into axial opening or closing movement by transmission element. These transmission elements are in the form of bellcranks which are pivotally supported in their elbow area on a fixed casing of the engine. A free arm end of each bellcrank is hinged to the actuating ring. Another free end of each bellcrank is hinged to a pull rod engaging at least one axially moveable shut-off member, or an axially adjustable shut-off element thereon. Two pull rods associated with respective shut-off members, are each pivotally connected on a side opposite the associated shut-off members at various points of an arm of the bellcrank. The arrangement is such that co-directional movement of the shut-off members produces different travels or strokes of the shut-off members.

Abstract: A variable inlet vane adjusting construction including a plurality of vanes pivotally mounted about a hub, an adjusting ring circumferentially slidable on the hub, a plurality of circumferentially spaced axial slots on the adjusting ring, a bearing of substantially solid rectangular configuration in each of the slots and in engagement with the sides of the slots, a plurality of pin members each having first and second ends with the first ends being mounted for universal movement on each of said bearings and the second ends fixedly mounted on levers which are in turn fixedly secured to the vanes.

Abstract: Disclosed is a variable guide vane arrangement for use in a high-load compressor having at least one axial-flow stage in turbomachines including gas turbine engines, comprising a plurality of guide vanes positioned radially adjacent one another about a circumference in the axial flow stage of the compressor, each vane having a low-pressure and a high-pressure side during operation; a plurality of generally disk shaped turntable members, each of the vanes being secured at its outer end to one of the turntable members and each of the turntable members being rotatably mounted about the circumference, the diameter of each of the turntable members being greater than the spacing between adjacent guide vanes; and each of the turntable members being generally round and having a cut-out portion on the side adjacent to the low-pressure side of the guide vane secured thereto.

Abstract: A hydraulic turbine wicket gate operating assembly including an eccentric pin having a separate hexagonal spacer attached provides a novel means for turning the eccentric pin and fixing it from rotation beyond a desired point. With the arrangement, a single gate operating ring can be utilized to permit all of the gates to move in unison and to provide for the simultaneous closing of each gate against each adjacent gate.

Abstract: A hydraulic turbo-machine incorporating wicket gates for purposes of controlling and closing down the flow of working fluid through the machine is provided with an annular ring gate selectively operable to take up any operating clearance between the casing and the adjacent axial edge of the wicket gates. This arrangement makes it practical to incorporate relatively large initial clearances between the wicket gates and the fixed machine structure, so as to leave provision for natural contraction of such clearances during the life of the machine, due to shrinkage of the concrete or other expected or unexpected causes. The operation of the annular ring as a piston within a cylinder is facilitated utilizing penstock water or oil under pressure as the motivating fluid.

Abstract: An arrangement for reducing the gap formed by the adjustable axial-flow guide vanes of fluid flow engines, such as gas turbine engines, between the root-sided lower edges of the vane airfoil and the thereto contiguous outer wall of an annular flow passageway. Grooves are formed in the outer wall of the flow passageway above a leading and/or trailing lower edge of the vane airfoil; a soft vane base-covering coating filling said grooves; and recesses formed in the coating-filled grooves slightly above the pivot plane of the respective lower vane edges.

Abstract: An improved floating seal is provided to minimize leakage around the ends of a variable area turbine stator nozzle for use in cooperation with a circumscribing shroud. The seal is contoured to float within a pocket formed in the end of the nozzle vane which extends to the vane trailing edge. The forward end of the seal is forced into engagement with the shroud by the pressure of cooling air from within the vane. A seal surface attached to the trailing edge of the seal and projecting laterally of the vane utilizes the differential pressure across the vane airfoil surfaces to hold the trailing edge of the seal into engagement with the shroud. The improved floating seal reduces vane end leakage experienced by prior art floating seals.

Abstract: An annular inner vane cover is axially spaced from a rotatably mounted runner and has first and second flanges. An annular water guide is disposed between said runner and said inner vane cover and has a third flange, which is jointed to said first flange. An inner tubular housing has a fourth flange, which is joined to said second flange. An annular runner cover surrounds said runner and has a fifth flange. An annular outer vane cover surrounds said inner vane cover and is radially spaced therefrom and has a sixth flange joined to said fifth flange, and a seventh flange. An outer tubular housing surrounds the inner tubular housing and is radially spaced therefrom and defines a welded interface with said outer vane cover. Outer and inner vane mounts are carried by said outer and inner vane covers, respectively. A plurality of vanes are provided, each of which is mounted for rotation on its own axis in one of said outer vane mounts and one of said inner vane mounts. Said flanges lie in parallel planes.

Abstract: A flow regulator for regulating a gas flow passing through a tubular casing containing a plurality of radial shafts, each carrying a pivotably adjustable blade and being fixedly secured at one end to said casing and at the other end to a concentric interior hub. A protruding crank on each adjusting blade is connected to an adjusting ring so that each blade is pivoted on its shaft axis when the ring is displaced.

Abstract: A centrifugal blower for air conditioning applications is shown having an adjustable inlet guide vane control for a blower wheel having forwardly curved blades. The pivot axis of each inlet guide vane is substantially offset or displaced from the plane of the inlet guide vane.

Abstract: A gas turbine unit comprising an expansion turbine, a compressor and a turbine engine arranged in sequence on a common shaft. The rotor element of the expansion turbine comprises fan blades having a straight non-curved profile. Guide vanes are provided upstream of the expansion turbine to form a throttling device for controlling the flow of air to the expansion turbine. The guide vanes are adjustable relative to the blades of the expansion turbine to deflect the air to vary the throttling effect to cause the expansion turbine to operate alternately as a compressor and a turbine in response to the adjustment of the guide vanes.

Abstract: A cantilevered turbine vane of the variable area variety is provided with unique retaining means to prevent relative movement between the vane and a fixed turbine housing through which the vane trunnion passes. Vernier adjusting means are provided to maintain a predetermined radial clearance between the vane and the fixed turbine housing, thereby eliminating binding between the two structures.

Abstract: In a method for recovering energy of an exhaust gas from a blast furnace as electric energy by introducing the total flow rate of the exhaust gas into a turbine, the efficiency of recovery of the power energy is enhanced by controlling the attachment angle of stationary blades of the turbine so that the furnace top pressure might be maintained at a predetermined level.

Abstract: The invention is concerned with an improvement in a movable vane assembly of the type used in a gas turbine engine or compressor for interaction with a gas stream comprising a plurality of radially aligned vanes, generally of an air foil configuration, circumferentially arranged within an annular passage formed by a housing, said vanes being supported for rotation about their radial axis to vary the effective cross-sectional area of said annular passage, a plurality of rotatable gear means connected for rotation with said aligned vanes and a ring gear having teeth means adapted for simultaneous engagement with the teeth means of said rotatable gear means such that rotation of said ring gear causes rotation of said vanes. In one sense the improvement comprises a support for the ring gear supportingly connected to the first housing inwardly radially and coaxial with the ring gear, the support comprising an annular ring having longitudinally extending slot means therein.

Abstract: A variable area turbine nozzle vane is supported from stationary housing structure and disposed in a confined fluid flow path between the gas generator and the power turbine of a split shaft gas turbine engine. The radially innermost structure defining the flow path for the working fluid is supported by a strut passing through, and also supporting, a hollow variable vane so that no external support struts are present in the flow path of the working fluid.

Abstract: A method of controlling the operation of a water turbine, in particular a bulb type turbine, wherein the mobile guide vane assembly serves only to reflect the water during operation, the starting and stopping of the turbine being controlled and water-tight sealing when the turbine is stopped being provided by a gate sluice.

Abstract: The invention is concerned with an improvement in a movable vane assembly of the type used in a gas turbine engine or compressor for interaction with a gas stream.

Abstract: A diffuser for a centrifugal compressor or a nozzle assembly for a centripetal turbine comprising a pair of axially-spaced walls defining an annular housing open at its inner and outer peripheries and a plurality of vanes extending between the walls and defining therewith, between adjacent vanes, working fluid passages open to the inner and outer peripheries of the housing, each vane being defined by a pair of partitions having a common edge extending between the housing walls adjacent the inner periphery of the housing and spaced apart circumferentially at positions remote from the inner periphery of the housing.

Abstract: Apparatus for controlling the direction of flow of the working medium gases in the compression section of a gas turbine engine is disclosed. Vanes are disposed across the flow path for the medium gases to direct the flow to a preferred downstream angle. In one embodiment vanes are disposed across the compressor exit passage. The camber of the vanes at the compressor exit is variable in response to engine operating conditions to conform the flow to a fixed optimum angle of entry into the combustion section.

Abstract: In the connection between the unison ring and the actuating arms carried by the several vanes of a variable stator ring in an axial flow compressor and providing for turning the vanes as the unison ring is moved, the pivot that must permit angular misalignment, relative rotation and axial movement is an elliptical-shaped bushing mounted on either the ring or arm and engaging a cylindrical surface on the other of the ring or arm. The bushing is normally mounted on a pin and the cylindrical surface is provided by a sleeve, the elliptical element having slidable engagement with the sleeve. The bushing may be a metallic spring or may be made of an elastomer.

Abstract: A unison ring for adjusting the nozzle vanes in a split shaft gas turbine is mounted via a secondary ring attached to and encircling the casing. The secondary ring is mounted so as to accommodate dimensional variations in the housing due to temperature changes without altering the freely movable mounting engagement of the unison ring. The unison ring can thus be easily adjusted regardless of the variations in radial dimension between the housing and the unison ring.

Abstract: Apparatus for varying the nozzle area in the turbine section of a gas turbine engine is disclosed. Nozzle guide vanes extend across the flow path for the working medium gases and are rotatable to alter the area of the nozzle. In one embodiment the rotatable vanes are cantilevered from the outer engine case and are opposed at their radially inner ends by a shroud which is affixed to the inner engine case.

Abstract: An inlet guide vane for a turbofan engine comprises a principal airfoil portion fabricated of metal and a radially outward and rearward corner portion fabricated of a frangible material which is attached to the metal portion and completes the airfoil structure. When foreign objects are ingested into the airstream to cause the closely spaced fan blades to deform forwardly to impact against the inlet guide vane, the frangible rearward corner of the inlet guide vane is caused to break off into small pieces and pass through the system without causing any significant secondary damage, thereby leaving the principal portion of the inlet guide vane to function as a relatively efficient airfoil.

Abstract: A mechanism for varying the position of a plurality of nozzle vanes in a gas turbine engine. The mechanism includes a single double-acting hydraulic actuating jack disposed between two bell cranks for simultaneously applying force to a ring gear at two diametrically opposed connection points. The single actuating jack applies equal and opposite forces to the diametrically opposed connection points on the ring gear and reduces distortion producing stresses therein. The ring gear simultaneously engages a plurality of individual gear segments rotatable with each individual nozzle vane in the engine. Movement of the single actuator jack causes balanced rotation of the ring gear and simultaneous rotation of the nozzle vanes.

Abstract: A turbine nozzle has a row of vanes each rotatable about an axis extending spanwise of the vane. Each vane is rotated by a shaft which extends through one shroud of the stator vane stage. The free end of each vane is sealed by a flexible seal ring structure made up of overlapping flexible leaves. These leaves are fixed to the nozzle inner shroud at the downstream side of the vanes and motive fluid under pressure is admitted upstream of the vanes to the space between the leaves and the shroud so that the pressure difference across the leaves biases them into engagement with the ends of the vanes. The purpose is to seal against leakage past the vane ends without causing undue frictional resistance to varying the vane setting angle.

Abstract: Means for preventing the wasteful leakage of cooling air within the turbine section of a gas turbine engine is disclosed. A segmented shroud radially separates the flow path for the working medium gases from cooling air supply chambers which are disposed radially outward of the flow path. Rotatable vanes penetrate the shroud and extend into the medium flow path to control the flow of medium gases through the turbine. A ring, which is split, is urged against the vane and the adjacent shroud segments in operative response to a spring member to prevent the excess leakage of cooling air therebetween.

Abstract: In adjusting turbine vanes to control the nozzle area, the unison ring actuates a lever that has one end fixed to the vane casing ring and the vane actuating arm is connected to the lever at a point between the ends to reduce actuating forces required by the unison ring and to permit close tolerance control on the vane angle position.

Abstract: A hydrodynamic torque converter for vehicles, particularly for passenger motor vehicles, with at least one pump wheel, one turbine wheel and one guide wheel supported on a free-wheeling device, in which the guide blades are automatically adjustable, when the guide wheel rotates, in dependence on the centrifugal force in the sense of a cascade opening with an increasing rotational speed.

Abstract: A hydraulic turbine is disclosed having wicket gate vanes which are rotatable between extreme positions to interrupt and permit the flow of water through a substantially cylindrical water passageway. In order to effectively block the flow of water through the passageway, the outer peripheral surface of the vanes must have a spherical configuration to match the circular cross-section of the cylindrical passageway. However, with this configuration, when the vanes are in an open position, a vee-shaped space is defined between the ends of the vanes and the water passageway. Baffles are provided to fill this space so that debris cannot collect therein.

Abstract: Apparatus for varying the nozzle area in the turbine section of a gas turbine engine is disclosed. Nozzle guide vanes extend across the flow path for the working medium gases and are rotatable to alter the area of the nozzle. In one embodiment the rotatable vanes are cantilevered from the outer engine case and are opposed at their radially inner ends by a shroud which is affixed to the inner engine case. The outer engine case has a double wall type construction including a plurality of bearing cartridges disposed between the walls.

Abstract: A mechanical joint for connecting each of the actuating levers on a row of variable position engine vanes to a common synchronizing ring including a flattened cylindrical slider fitting in a cylindrical recess in the actuating lever and having a stepped hole to receive a substantially radially extending pin in the synchronizing ring.

Abstract: In order to raise the degree of compression without unduly increasing the dimensions a compressor having at least two stages includes a first centripetal stage and a last centrifugal stage mounted upon the same shaft. The diameter at the centripetal stage inlet does not exceed the diameter at the outlet of the centrifugal stage and the air flows radially inwards in the first stage, and radially outwards in the last stage.