Abstract: In a variable nozzle structure for a turbine, moveable vanes for controlling variable cross section nozzles which lead to a turbine wheel are actuated by a drive unit which comprises an actuator for causing a linear motion to a rod member, a lever arm member which is pivotally supported by a part of the turbine casing and is connected to the rod member at its one end so as to be able to rotate about its pivot point with respect to a turbine casing when the rod member is driven linearly, a crank arm member which is integrally connected to a pin shaft which is securely attached to each of the moveable vanes and pivotally supports the corresponding moveable vane, and an engagement member which is fixedly attached to the lever arm member and is engaged with the crank arm member so as to cause the rotational motion of the crank arm member when the lever arm member is rotatively driven by the rod member. Thereby, accurate control of the variable nozzles can be accomplished with a simple structure.

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: An inlet guide vane assembly for a pump or a compressor having rotary blades. The guide vanes are pivotably disposed so that a portion of the vanes can be inserted into or withdrawn from the inlet passageway of the pump or the compressor by pivoting the guide vanes about a pivot axes. A control is provided for controlling the degree of pivot.

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 supercharger for an internal combustion engine has a turbine driven compressor. The turbine is driven by the exhaust gases and is mounted in a volute casing. The volute casing has an internal flow passage which has an inlet and the passage is arranged to receive and discharge a flow of motive gases. The passage is partly defined by one or more movable wall members. The or each wall member is movable to vary the passage area whilst allowing the whole of the flow of motive gas to flow through the passage. Two movable wall members can be provided operated by a common linkage and the volute casing can have two inlets to receive the exhaust gases from separate manifolds of an internal combustion engine.

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 blower and valve apparatus for a pneumatic tube system is enclosed in a divided housing (10). A conventional blower fan (36) operates to create pressure in a pressure area P and suction in a suction area S of the housing. Area P has two air passage outlets; a first pressure outlet (38) to atmosphere and a second pressure outlet (40) to a neutral area C. Area S likewise has two air passage outlets; a first suction outlet (44) to atmosphere and a second suction outlet 42 to neutral area C. Area C is connected through a coupling (23) to the end of a pneumatic tube. A first rotatable flapper vane (50) is mounted in area P. At one extreme of its arcuate movement, the rotatable flapper vane closes the first pressure outlet to atmosphere and at the other extreme closes the second pressure outlet to area C. A second rotatable flapper vane (54) is mounted in area S.

Abstract: A fluid container associated with the wicket gate operating ring to receive fluid from a source so as to add an emergency counterweight to the gate operating ring upon failure of the gate operating ring servomotors.

Abstract: The present invention discloses a device for varying the fluid passage area between adjacent turbine stator vanes. Upstream and downstream baffles are pivotally attached to the turbine casing, such that their distal ends may be extended into and retracted from the fluid passage area, so as to vary the cross section of the throat between adjacent vanes. A control system interconnects all of the baffles so as to synchronize and positively control their movements. The invention finds particular use in an aircraft turbojet engine.

Abstract: A centrifugal gas compressor includes a centrifugal impeller and a diffuser with control vanes which pivot about their leading edges. The radially inward-facing surfaces of the control vanes are curves with a radius of curvature substantially equal to the radial spacing of the leading edges from the impeller rotation axis. In the closed vane position, each leading edge is overlaid by a trailing edge of an adjacent vane so that a closed annular wall blocks all outflow. One or more diffuser vanes may be fixedly positioned with respect to each control vane so as to pivot with the control vanes. The diffuser vanes are positioned radially outward from the control vanes and define respective gradually widening paths to diffuse the outflowing gas. As an alternative to diffuser vanes, the control vanes may be extended in length to define the widening paths between adjacent control vanes.

Abstract: This invention relates to a device for controlling the extraction pressure of an extraction condensing turbine with pivotable vanes or vane parts of guide vane lattices arranged downstream of the steam extraction point(s) where the pivoting motion of the vanes is effected by means of adjusting levers or arms by axial displacement of adjusting rings forming the bearings said adjusting levers or arms.

Abstract: A device for changing and attaching or mounting an angle of stationary vanes of an axial-flow fluid machine by rotating the stationary vanes through a circumferential movement of an intermediate cylinder. The device includes at least one arm secured to one end of the intermediate cylinder and engaging at a second end in a groove formed in a block member which is attached to an end of an actuator and is movable in a tangential direction of the intermediate cylinder. A guide arrangement is provided for guiding a movement of the block member and at least a portion of the actuator so as to ensure a smooth operation of the actuator by freeing the same from any influence of undesireable forces such as lateral pressure caused by a thermal expansion of the intermediate cylinder.

Abstract: The disclosure illustrates a turbocharger comprising a radially inward flow turbine and a vaned inlet turbine nozzle. A variable inlet area is provided by an annular control ring continuous at its inner diametrical face and having slots extending inward from its radially inner portion of the vanes. The control ring may be attached to a steel stamping which, in turn, is attached to shafts of a pair of actuators for axially displacing the control ring and thus varying flow area through said turbine nozzle. By only partially embracing the inlet canes, the possibility of sticking due to carbon build-up is minimized if not eliminated.

Abstract: A combustion turbine engine having an improved variable-area turbine stator assembly.

Abstract: A guide vane operating mechanism for a hydraulic machine including a main shaft carrying a runner and guide vanes for varying the angle of attack of water to the runner. A guide ring is rotatably arranged around the main shaft, with a guide vane driving mechanism being provided for a linkage between the main shaft and the guide vanes so as to drive the guide vanes between fully-open and fully-closed positions. At least one servomotor has a reciprocating actuating rod, with a guide ring actuating mechanism for transmitting the driving power to the guide ring to cause a rotation of the latter. The guide ring actuating mechanism includes means connects the actuating rod to the guide ring in such a manner so as to permit the actuating rod and the guide ring to make a cranking motion relative to each other.

Abstract: A control sleeve is provided in an axial turbine device, an axial translation of which controls the stator vanes of the turbine device. In order to obtain as precise as possible a motion of the control sleeve in the axial direction without high friction forces and without the danger of jamming, a parallelogram linkage guide arrangement is provided. The parallelogram linkage guide arrangement is formed by a control yoke and control links arranged parallel thereto having pivot axes in the machine housing and further pivot axes in the control sleeve.

Abstract: A variable geometry device for use with the turbine nozzle of a turbine engine of the type having a support housing and a combustion chamber contained within the support housing. A pair of spaced walls in the support housing define an annular and radially extending nozzle passageway. The outer end of the nozzle passageway is open to the combustion chamber while the inner end of the nozzle passageway is open to one or more turbine stages. A plurality of circumferentially spaced nozzle vanes are mounted to one of the spaced walls and protrude across the nozzle passageway. An annular opening is formed around the opposite spaced wall and an annular ring is axially slidably mounted within the opening. A motor is operatively connected to this ring and, upon actuation, axially displaces the ring within the nozzle passageway.

Abstract: A variable geometry device is provided for use with the compressor outlet of a turbine engine. The turbine engine includes a support housing, a compressor contained within the support housing and having a compressed air outlet and in which a pair of spaced walls define an annular and radially extending diffuser passageway. The inner end of the diffuser passageway is open to the compressed outlet while the outer end of the diffuser passageway is open to the combustion chamber for the turbine engine. A plurality of circumferentially spaced diffuser vanes are mounted to one of the diffuser walls and protrude across the diffuser passageway. An annular recessed channel is formed around the opposite diffuser wall and an annular ring is mounted within the channel. A motor is operatively connected to this ring and, upon actuation, displaces the ring transversely across the diffuser passageway to variably restrict the diffuser passageway.

Abstract: A centrifugal machine having a variable diffuser that includes a radially disposed fixed wall and an opposed movable wall defining the diffuser passage. Guideways are formed in the movable wall in which a series of diffuser vanes are slidably mounted. A spring biased retainer loosely holds each of the vanes in an associated guideway and urges the vanes into seating contact with the fixed wall so that each vane can adjust its position in assembly to accommodate for changes in diffuser alignment due to thermal growth or the like.

Abstract: Herein disclosed is a blower which comprises a fan, means for driving said fan, a body housing or guard mounting said fan therein, a wind deflector mounted in the front opening of said body so that it can rotate in said front opening, and a rear guard mounted in the rear opening of said body. Said wind deflector is formed with changing vanes which are made receptive of the air wind generated by said fan for imparting a rotational force to said wind deflector. Moreover, the changing vanes are made at least partially so movable that they can be adjusted to have an arbitrary vane angle for changing a rotating speed on a rotating direction of said wind deflector.

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: A turbine having a radial inlet to the turbine wheel is provided with a multi-stage stator wherein the vanes of its separate stages are fixed at different angles of incidence. The stator is mounted for movement so that each of its stages may be positioned in alignment with said opening. The vanes of one stage of the stator are inclined relative to the inlet to produce forward rotation of the turbine wheel while those of another stage are inclined oppositely to produce reverse rotation thereof. The system includes means for positioning the stator so that the vanes of two adjacent stages thereof are located in partial alignment with the inlet opening so as to regulate the power output of the turbine to a neutral state.

Abstract: An aircraft propulsion means 20 comprises a multibladed, unshrouded, propeller fan 27 adapted in a cruise condition to operate at such high disc loadings that a substantial component of swirl is imparted to the slipstream in a given sense, and swirl reducing means (for example a multi-bladed stator 35) arranged with respect to the propeller fan to impart a considerable component of swirl in the opposite sense, whereby the total swirl imparted to the slipstream is nil or relatively low.

Abstract: A fluid compressor including a rotating impeller and apparatus inhibiting fluid surging. The surge inhibiting apparatus includes a multitude of guide vanes circumscribing an inlet of the compressor. Movement of the guide vanes with respect to fluid flowing to the compressor is effective to inhibit fluid surging. A combustion turbine including such a fluid compressor, and a vehicle powered by such an engine are also disclosed.

Abstract: The invention relates to a method of operation of a pump-turbine between part-load and reverse pumping operation in which the various operating conditions are produced by changing the position of the wicket gates in that some of the wicket gates are removed from the synchronous operation as provided by the mechanical gate ring operator and inserting a servo-motor between the wicket gate and the gate ring which functions to alter the connection between the selected wicket gates and the gate ring operator.

Abstract: This invention relates to a fully modulatable centrifugal pump capable of handling a fluid containing solid contaminant particles and minimizing the temperature rise of the pumped fluid. The pump is of the type that includes an impeller to propel the fluid through a radial outlet to a diffuser which includes a plurality of diffuser passages. The improvement is comprised of the following cooperative combination which includes rotatably mounted valve elements passing, in part, through the diffuser and across the diffuser passages. Each of the valve elements have a port therethrough to variably selectively allow fluid passage therethrough upon rotation of the valve element. A driving arrangement is coupled to each of the valve elements to thereby affect a yieldable rotation of the valve elements in one direction to progressively reduce the opening of the valve element port to the diffuser passage.

Abstract: A variable geometry device is provided for use in a turbine engine having a support housing, a rotor contained within the support housing and a pair of spaced walls forming an annular and radially extending passageway open at one end to the rotor. An annular recessed channel is formed in one of the support housing walls while a ring is mounted within the channel and movable between a retracted position in which the ring is nested within the channel and an extended position in which the ring protrudes transversely into and variably restricts the passageway so that the restriction of the fluid passageway is substantially proportional to the transverse position of the ring. A plurality of circumferentially spaced vanes are secured to the ring and these vanes extend transversely across the fluid passageway and are slidably received within slots formed in the other support housing wall.

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 guide blade arrangement for devices for flowing medium and comprising an annular passage (20) wherein a ring of angularly adjustable guide blades (22) are arranged. Said passage is provided with an inner wall (26) separating it from a control chamber (28). Each guide blade (22) is provided with a supporting pin (36) rotatably mounted in said inner wall extending through the same and provided within said control chamber with an arm (40), the free end of which is by means of a stud (42) pivotably connected to a control member (45) common to all said arms. All said arms (40) being parallel and having the same length and said control member being constituted by a control ring (45) carried by said studs (42), whereby special supporting means for the said ring within the control chamber are avoided.

Abstract: The pump isolation valve provides a means by which the pump may be selectively isolated from the remainder of the coolant system while being compatible with the internal hydraulic arrangement of the pump during normal operation of the pump. The valve comprises a valve cylinder disposed around the pump and adjacent to the last pump diffuser with a turning vane attached to the lower end of the valve cylinder in a manner so as to hydraulically match with the discharge diffuser. The valve cylinder is connected to a drive means for sliding the valve cylinder relative to the diffuser support cylinder so as to block flow in either direction through the discharge diffuser when the valve is in the closed position and to aid in the flow of the coolant from the discharge diffuser by means of the turning vane when the valve is in the open position.

Abstract: A counterweight link rod incorporates a counterweight lifting lug to provide a safe and easily usable means to lift a counterweight during erection or maintenance for positioning it with respect to a connection point with the wicket gate operating ring. The arrangement also provides a readily available permanent means for attaching an overhead crane hook to the wicket gate operating ring for stroking the gates during erection or maintenance. The arrangement also provides a means for operating the wicket gate operating ring when the operating ring servo-motors fail.

Abstract: A common mounting base plate is secured to a turbine gallery floor and anchor a pair of servomotors which are connected to operate a wicket gate operator ring; the arrangement permits the servomotors to be angularly positioned to clear the gate ring counterweight and to allow the servomotors to operate in identical modes simultaneously--both push together or both pull together.

Abstract: The present application discloses an electric fan apparatus comprising a fan, a wind direction shifting plate disposed in front of said fan and adapted to be rotated by the pressure of a wind generated by said fan, a rotary shaft disposed at the center of said wind direction shifting plate and adapted to be rotated integrally with said wind direction shifting plate, a speed governor mechanism interlocked with said rotary shaft and a housing box for housing said speed governor mechanism.With said wind direction shifting plate rotated, a wind may be provided in a wide range. Provision is made to improve the durability of said speed governor mechanism, which is formed with a gear mechanism and a blade. Said housing box contains a liquid into which at least a portion of said gear mechanism is immersed, so that said wind direction shifting plate is rotated at a substantially constant low speed.

Abstract: A diffuser control for controlling vapor flow through a diffuser passage comprising an annular recess defined by a housing of the diffuser passage and in communication therewith, and an annular control ring supported for movement within the recess and the diffuser passage between a throttling position, wherein the restriction means throttles vapor flow through the diffuser passage, and an open position for permitting a substantially free flow of vapor through the diffuser passage. The diffuser control further comprises a plurality of springs supported by the housing for urging the control ring toward the throttling position, a stop for limiting movement of the control ring at the throttling position, a low pressure conduit for connecting the annular recess to a low pressure source, and a seal for retarding vapor flow from a higher pressure side of the control ring to a lower pressure side thereof when the control ring is in the open position.

Abstract: A turbine assembly is provided for use on an internal combustion engine such as a diesel engine having conventional intake and exhaust manifolds. The assembly includes a hollow section which has an inlet communicating with the exhaust manifold, and an outlet communicating with an exhaust gas entry into a chamber in which a turbine wheel is mounted. Rotatably mounted within the hollow section is a rotor which is adjustable to various selected positions. When in a first selected position, the rotor permits substantially unrestricted exhaust gas flow through the assembly. When in a second selected position, a predetermined amount of exhaust gas is diverted from the turbine wheel chamber through a bypass passageway formed in the hollow section. The end of the bypass passageway terminates downstream of the turbine wheel chamber. When in a third selected position of adjustment, the rotor effects substantial blockage of the exhaust gas flow through the assembly.

Abstract: An exhaust brake modulating control system is provided for an internal combustion engine having a turbo-charger and source of pressurized fluid. The system includes a double-acting piston-cylinder assembly having one cylinder end communicating with the engine exhaust manifold and an opposite end separated from the one end by a piston head. An adjustable control valve is provided having an outlet connected to the cylinder second end, and a plurality of inlets selectively connected to the outlet. One inlet communicates with the pressurized fluid source and a second inlet is vented to the atmosphere. Communicating with the exhaust manifold is an inlet of a hollow section in which a rotor is rotatably mounted. The hollow section has an outlet separated from the inlet by the rotor. The outlet communicates with the turbine wheel chamber of the turbo-charger. When the rotor assumes a first selected position, substantially unrestricted exhaust gas flow past the rotor occurs.

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 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 centrifugal type impeller pump has a restricting valve to control the inlet area of the collector for reducing recirculating flow from the collector to the impeller. The restricting valve includes a ring mounted upon the pump housing for rotary and axial motion. Rotary motion is imparted to the ring by an actuator. Cam slots in the ring and pins secured to the housing produce axial motion of the ring as the ring rotates. Precise positioning of the ring is possible because large motions of the actuator can be utilized to provide small changes in ring position. The axial position of the ring is determinative of the inlet area of the collector.