Abstract: An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.

Abstract: A rotor for use in a gas turbine engine includes a wheel and a plurality of blades. The wheel is arrange about an axis of the gas turbine engine for rotation. The plurality of blades are arranged around the wheel and extend radially outward from the wheel to interact with gases flowing through the engine. One or more of the plurlaty of blades is formed to include a hole that extends into an external surface of the blade and a plug located in the first hole. The blade and the plug are made of different materials or have different densities to vary the frequency response of the blade.

Abstract: Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications.

Abstract: A variable pitch fan assembly includes variable pitch fan blades circumscribed about engine centerline axis coupled to a drive shaft centered about the engine centerline axis. Each blade pivotable about pitch axis perpendicular to centerline axis and having blade turning lever connected thereto. One or more linear actuators non-rotatably mounted parallel to engine centerline axis and operably linked to fan blades for pivoting fan blades and connected to spider ring through thrust bearings for transmission of axial displacement of non-rotatable actuator rods of actuators while the fan blades are rotating. Spider arms extending away from spider ring towards blade roots and each spider arm connected to one of the turning levers. Turning levers may be connected and caromed to spider arms by pin and slot joint. Each spider arm may include joint pin disposed through joint slot of turning lever. Joint slot may be angled or curved.

Abstract: In order to simplify the design of an aircraft turbo engine propeller while enhancing the safety function thereof related to control of the blade angle of attack, a propeller is provided comprising a secondary rotational coupling to couple in rotation, along the radial axis of the blade, the inner radial end of the blade root with a mechanical joining member of a blade angle of attack control device, the secondary coupling being designed and configured to be active in the event of failure of the main pin.

Abstract: A turbine engine compressor includes a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring capable of pivoting axially in relation to the casing, where the linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole in the control ring, where at least one of the holes in the control ring serves for insertion of the pins of the linking members, is oblong in shape and extends in the circumferential direction in order to allow movement of the pin in the oblong hole, during rotation of the control ring.

Abstract: A method and device for retrofitting a gas turbine engine for improved hot day performance are disclosed. The method can include removing a first selected stator bladerow from the plurality of compressor stages, the first selected stator bladerow having a first inlet swirl angle and including a first plurality of fixed stator vanes. Each stator vane of the first plurality of fixed stator vanes can have a first stator vane angle. The method can also include providing a first improved stator bladerow to replace the first selected stator bladerow. The first improved stator bladerow can have a second plurality of fixed stator vanes, each having a second stator vane angle smaller than the first stator vane angle. The method can also include replacing the first selected stator bladerow with the first improved stator bladerow to produce an increased pressure ratio and flow rate compared to the first selected stator bladerow.

Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of vortex generators, each of the vortex generators positioned on the leading edge of a respective fan blade proximate the upstream splitter and the core stream restricting the migration of the core stream into the bypass stream through the fluid passage.

Abstract: An aircraft assembly includes at least one first wing portion providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion, at least one vertical thruster positioned inside the at least one wing opening to provide vertical thrust during a vertical flight, and a mounting system including an open frame portion in a frame of the aircraft and at least one attachment member disposed in the open frame portion to attach at least one pod to the open frame portion in the aircraft frame. The aircraft assembly can further include at least one pod including a mounting frame to attach to the mounting system and a cabin to contain at least one of cargo and passengers.

Abstract: A device for supplying oil under pressure to a linear actuator of a turbine engine, in which the actuator includes an internal fixed portion and an external movable portion and a regulating device for regulating and supplying oil to chambers of the actuator, is provided. The regulating device is mounted radially outside the movable portion of the actuator, and the fixed portion of the actuator includes on its upstream end portion oil passage channels of which the outlets open radially outwards. The device further includes an oil distribution ring which is mounted on the upstream end portion of the fixed portion and which includes internal conduits of which the inlets communicate with the outlets of the channels of the fixed portion and the outlets open axially downstream and are connected to the regulating device.

Abstract: A shut-off valve for a turbine of an oscillating water column may include a plurality of guide vanes configured to control a fluid flow into a flow passage defined by the turbine. The plurality of guide vanes may be at least partially disposed within the flow passage and may include a plurality of fixed guide vanes and a plurality of movable guide vanes. The plurality of fixed guide vanes and the plurality of movable guide vanes may be sequentially disposed in an alternating pattern in the flow passage.

Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Abstract: A present invention's object is to maintain a discharge performance by making a discharge flow rate constant in a low rotation region of an engine rotation speed and to reduce the discharge flow rate in a high rotation region. The present invention consists of a housing case, an impeller base provided with plural holes and plural elliptical elongated holes, a vane body provided with a rotary shaft on an inner peripheral side and a rocking shaft on an outer peripheral side, a plate cam in which an elongated groove is formed on an outer peripheral side of a disc portion and a single torsion spring. The spring and the plate cam are housed in the housing case and the impeller base. The rotary shaft is inserted rotatably into the holes, and the rocking shaft is movably inserted into the elliptical elongated holes and the elongated groove.

Abstract: An assembly includes a torque box and a first bell crank. The torque box has a housing with an interior cavity. The first bell crank is pivotally supported from the housing and extends through the interior cavity. The first bell crank has three arms for transferring an actuating force to a plurality of variable guide vanes for positioning the guide vanes within a gas turbine engine.

Abstract: A turbomachine having clearance control capability is provided and includes a turbine stage including a blade configured to rotate around a centerline, a movable portion of a casing circumferentially surrounding the turbine stage and a rotatable cam operably coupled to the movable portion and thereby configured to control an axial position of the movable portion. A radially outermost tip of the blade and an interior surface of the movable portion are sloped with respect to the centerline such that the controlled axial position of the movable portion is determinative of a clearance between the blade and the movable portion.

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: A sealing device for passing a connecting rod of a system for controlling a pitch of fan blades of a turboprop through a partition. The device includes a tube for fastening to the partition that is to be sealed, and a frustoconical sheath through which the connecting rod is to pass, the sheath configured to slide axially inside the tube and including, at its wider end, a sealing mechanism co-operating with the tube, and, at its narrower end, a leaktight fastener fastening to a corresponding end of the connecting rod.

Abstract: The present application provides a compressor for a gas turbine. The compressor may include a number of rotor wheels positioned about a compressor aft section having a low alloy material, a number of inlet guide vanes positioned about a compressor inlet section, and a wet compression system positioned about the compressor inlet section.

Abstract: A device and method for axially displacing at least one turbine rotor relative to at least one corresponding turbine stator in a multistage axial turbine is disclosed. The turbine shaft is provided with a split design and has a first axially displaceable shaft half, which is connected via a turbine disc to the turbine rotor and via a torque coupling to the second shaft half. By axially displacing the turbine rotor relative to the turbine stator and by controlling this axial displacement, the operation of the turbine is held in its possible optimum of efficiency.

Abstract: A method of decreasing the operational stresses acting on a target airfoil row in a turbine engine; wherein the target airfoil row is bordered on each side by a first upstream airfoil row and a first downstream airfoil row; the first upstream airfoil row and the first downstream airfoil row having substantially the same number of similar airfoils and both comprising one of a row of rotor blades and a row of stator blades, and the target airfoil row comprising the other; the method comprising the step of: configuring the circumferential position of the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that at least a portion of the airfoils of the first upstream airfoil row and at least a portion of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25% and 75% pitch.

Abstract: A turbomachine includes a compressor having a compressor intake, and an intake system mounted upstream of the compressor intake. The intake system includes a housing and a plurality of selectively positionable vanes arranged within the housing. The plurality of selectively positionable vanes are moveable between a first position to remove a first amount of foreign particles, and a second position, to remove a second amount of foreign particles.

Abstract: A turbine that will produce useful mechanical force from the dynamic force of the sea wave. This is done by rectifying the bidirectional force obtained from such wave. This turbine will produce a unidirectional rotation from the bidirectional force of the wave. The turbine will adjust the pitch of its blades automatically as the air flow inside the pipe changes direction, The air flow will change the pitch of the blade, because the blade is mounted on a shaft through ball bearings. Because the blade is acting like a flag on a pole that has a long tail and also the blade has a long tail and will always change its direction in accord to the direction of the air flow.

Abstract: The vertical windmill includes a rotatable wind wheel column mounted to a base. The column includes a plurality of hollow wheel hubs stacked vertically atop each other. Each wheel hub includes a plurality of radiating mounting arms equidistantly spaced around the axis of the wheel hub such that the arms of an adjacent hub are angularly offset with respect to the other. A plurality of mounting assemblies is disposed on each of the mounting arms for mounting an array of wing blades. Each alternate stacked wheel hub and mounting arms together forms a wind wheel with vertically oriented wing blades mounted between upper and lower spaced arms such that the top wheel is interconnected with the lower wheel at a height less than the height of the blades. Each array of blades may freely rotate or be positively rotated to orient the blades for optimum usage of wind power in rotating the column.

Abstract: A wind turbine for generating electricity is configured as a drum with a housing that has adjustable shutters to control the amount of wind reaching the turbine blades. Alternatively, the turbine blades can be pivotably mounted and opened and closed using a cam follower, cam track system to minimize wind exposure to downstream turbine blades.

Abstract: A supercharger system is disclosed herein having a front end, a rear end, an inlet and an outlet, the system contained within a housing, wherein the supercharger system includes a rotor assembly, and a plurality of intake runners that comprise an interlaced cross-runner pattern, wherein the supercharger system comprises a front drive, front inlet configuration and an inverted orientation.

Abstract: A novel technique for partially improving wear resistance of an input portion of a drive ring, where power of a shifting drive is input from an external actuator, in an adjustment mechanism incorporated in a VGS type turbocharger for concurrently rotating adjustable blades, without specifically attaching a separate member afterwards is provided.

Abstract: An engine provides torque by transmitting power in a fluid using optimally positioned lift-to-drag ratio blades with air-foil shape sections. The fluid may be liquid or gas. Various considerations of engine configuration, fluid density, fluid pressure and fluid temperature are design parameters that can be tuned to achieve high performance. The fluid flow created can be used to drive rotary motion of an output axle, for example.

Abstract: Attachment apparatus and method for interlocking attachment of a scraper blade with a drive shaft of a scraped surface heat exchanger includes a blade having dual attachment beams and a central locking member, and at least one pin having dual fingers each for interlocking with a respective attachment beam.

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.

Abstract: Attachment apparatus and method for interlocking attachment of a scraper blade with a drive shaft of a scraped surface heat exchanger includes a blade having dual attachment beams and a central locking member, and at least one pin having dual fingers each for interlocking with a respective attachment beam.

Abstract: The present invention discloses a wind driven power generator.

Abstract: An attachment apparatus and method for interlocking attachment of a scraper blade with a drive shaft of a scraped surface heat exchanger includes a blade having dual attachment beams and a central locking member, and at least one pin having dual fingers each for interlocking with a respective attachment beam.

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

Abstract: A fluid impeller, such as a fan for moving air or gases, includes one or more rotatable fluid impelling blades; a flow guiding member adjacent to an edge of the blades, and at least one blade facing surface of the flow guiding member being formed substantially as a segment of a sphere of radius r1 about a center of curvature. Each blade has a flow guiding member abutting edge curved substantially to fit against a sphere of radius r1.

Abstract: A protection device for protecting a control mechanism of inlet guide-vanes of a turbojet engine includes a narrowed section on a connecting rod. The connecting rod is for transmitting the movement of a spindle of a piston of the control mechanism or actuator to a control ring that directs all of the inlet guide-vanes. The narrowed section of the connecting rod is a frangible part.

Abstract: A vertical-shaft multi-stage pump has adjustable vanes on its lower stage. A vane angle operating mechanism has an operating shaft extending through a hollow portion of the drive shaft of the upper stage and a link mechanism connected to the operating shaft and the adjustable vane impeller for converting axial motion of the operating shaft into vane angle rotational motion. The pump is particularly suited for use in an underground drainage system.

Abstract: A hydroelectric power generator equipment includes a hydraulic turbine which has a runner with blades adjustable of opening thereof and a hollow turbine shaft mounting thereon the runner, a power generator having a hollow shaft connected to the turbine shaft, a hydraulic cylinder mounted on the runner to drive the blades, and first and second liquid passages each passing through the turbine and generator shafts and feeding oil to the hydraulic cylinder to adjust the opening of the runner blades. One of members defining the first and second liquid passages is screwed in the inner wall of the shafts around an axially middle portion of the first and second liquid passages to suppress radial movement of the passage defining member. Some of the members are slidably or firmly inserted in other members so that disassembly is easy.

Abstract: A lightweight counterrotatable propeller system driven by a rotatable shaft is disclosed. The system includes first and second counterrotatable propellers, each propeller including a plurality of blades mounted on first and second hubs, respectively. Each blade is attached to the hub by means of a ball screw which converts centrifugal force on each of the rotating propeller blades into a pitch changing force. Gearing means for operatively connecting the shaft with each propeller are located between the propellers with a carrying member for one of the propellers forming an outer wall which radially bounds the gearing means. Additionally, non-rotating actuating means for changing propeller pitch are operatively connected to the blades of each of said first and second propellers through first and second thrust bearings, respectively.

Abstract: Blade pitch varying means for use in a gas turbine engine are disclosed. The blade pitch varying means may be used on an engine with a single row or two counterrotating rows of variable pitch blades which are disposed outwardly from an annular gas flowpath and which are connected with a rotating airfoil within the flowpath. The blade pitch varying means comprise actuation means, bearing means, and gearing means. The actuation means are in a nonrotating reference frame disposed inwardly from the flowpath and deliver an axial force. The bearing means transmit the axial force from the nonrotating into a rotating reference frame which contains both the propulsor blade and the airfoil in the gas flowpath. The gearing means are located in the rotating reference frame and convert the axial force into a force for varying the blade pitch.

Abstract: An apparatus for controlling a hydraulic turbine is disclosed comprising a hydraulic circuit to control the positioning of turbine runner blades and a hydraulic circuit to control the positioning of turbine wicket gates. The runner blade hydraulic circuit comprises a solenoid valve for normal operation of the blades and a slow rate servovalve for moving the blades when the actual blade position differs from a desired position by less than a predetermined tolerance. The wicket gate circuit comprises a solenoid valve for normal control of the gates. A diverter directs flow from the solenoid valve to a flow rate control valve when the difference between the actual and desired position of the gates is less than a second predetermined tolerance.

Abstract: Multiple flat-plate blade rows of pitch adjustable blades are offset mounted in a manner such that when flat-plate blades in adjacent rows are aligned at a specific pitch setting, respective flat-plate blades of the adjacent rows nearly mate. The offset between the flat-plate blade rows functions to produce unequal pitch angle settings of the blades of adjacent rows which, in turn, function to produce the result that the respective flat-plate blades which nearly mate, in combination, produce a blade configuration which has an effective camber.

Abstract: The disclosure concerns a hydroelectric machine set in which the electrical machine is in the form of a rim which surrounds a service water duct containing the bladed wheel of a hydraulic machine, and wherein the blades of said wheel are joined to the rotor of the electrical machine by torque-transmitting connections which allow free radial movement of the blades relatively to the rotor. Preferably, those connections also permit pivoting movement of the blades relatively to the rotor.

Abstract: A seal is provided between the turbine runner and the stationary structure which permits expansion of the runner without danger of contacting the stationary structure and thereby causing the seal to seize. The portion of the runner which defines the sealing passage faces radially inwardly. Therefore, if the runner expands, the sealing clearance will enlarge rather than decrease thereby overcoming the possibility of seizure.

Abstract: Variable geometry guide vanes are provided in a variable pitch turbofan assembly. A method is disclosed for reducing aerodynamically induced stresses in the variable pitch fan blades as the blades are changed between the forward and reverse pitch modes. The guide vane geometry is scheduled to change in a manner to control the flow into and out of the fan blades in order to establish a favorable aerodynamic environment during the transition between the forward and the reverse pitch modes.

Abstract: This invention cures the problem attendant the ingestion of oil in the engine of a fan-turbine engine combustion propulsor should oil leak from the fan blade seal by capturing and judiciously venting the leakage.

Abstract: An axial fan operative to control the developed air volume and pressure by varying the pitch of the fan blades. The fan housing is adapted to be connected to the main air conduit as an axial continuation thereof and centrally mounts a fan motor which directly drives the fan. The blade pitch control mechanism adjacent the fan utilizes an axially reciprocable actuator coupled through linkages to each of the fan blades whereby the pitch of all of the blades is simultaneously changed upon movement of the actuator. The control mechanism is contained within the fan hub and within a cylindrical central fairing located adjacent the fan and radially inwardly of the blades. This protects the control mechanism and reduces drag. The actuator is moved axially by means located externally of the main air conduit and connected to the actuator by a single lever arm extending through the central fairing and main air conduit.