Abstract: A ram air turbine (RAT) prevents release of its turbine blades due an over-speed condition by detecting an over-speed condition with a turbine hub-mounted centrifugally operated trigger mechanism and rotating the blades to a fixed coarse pitch position with a release mechanism that responds to the trigger mechanism.

Abstract: The present invention provides a device enabling the collective pitch of the blades of the main rotor of a single-engined rotorcraft to be reduced automatically in the event of an engine failure. The device comprises an actuator which increases the collective pitch of the blades above a predefined threshold, and which decreases the collective pitch below the predefined threshold. The actuator is arranged on a bell crank of the mixing unit of the rotorcraft.

Abstract: A rotor for a wind power installation having at least one rotor blade. The smaller the surface area on which the wind acts, that is to say in particular the rotor blade area, the correspondingly lower is the load level for which installation has to be designed and the correspondingly more easily can the rotor blade be transported. On the other hand the size of the wind power installation entails minimum dimensions which are unavoidable for operation and below which the installation dimensions may not fall. In order to provide a rotor blade which on the one hand has the aerodynamically required surface area but which on the other hand is so designed that the surface area of the rotor blade and therewith the depth thereof can be reduced in predetermined situations a part of the surface of the rotor blade is deformmable or movable.

Abstract: A wind turbine with at least one blade having a pitch axis that is offset laterally so that the blade does not intersect with an axis of rotation of the wind turbine, and a center of mass and an aerodynamic center are offset from the pitch axis in the direction parallel to the axis of rotation of the wind turbine. The blade is arranged so that the blade can pitch towards stall against the action of a resilient device and also so that the centrifugal loading on at least one of the blade and one or more components optionally attached to the blade, acts against the spring in a direction to shed power by pitching the blade towards stall and also so that the torque loading provided by a power conversion device acts to pitch the blade in the opposite direction, so as to reduce the amount of load shedding whenever the power is being extracted from the wind turbine.

Abstract: A system and method for providing pressurised oil during non-feathered in-flight shutdown conditions in a variable-pitch aircraft propeller engine. A secondary pump provides pressurised oil substantially independent of an engine main oil circuit.

Abstract: A method is provided for controlling a wind turbine, and a wind turbine is provided with a control device for controlling a wind turbine. A method and a wind turbine are developed so that losses of yield, particularly as a result of variations in the conversion of the kinetic energy of the wind into electrical energy, e.g., in the rotor, drive train and generator, are minimized as far as possible. A method is provided for controlling a wind turbine, wherein at least one operational setting is varied within predefined limits.

Abstract: A vertical shaft driving device wherein a plurality of rotary blades (8a, 8b, 8c and 8d) each including a blade (10) supported on a planetary shaft are equally arranged circumferentially of a central shaft (12) and capable of orbital motion integrally with the central shaft (12), and wherein the rotary blades are arranged in a multipoint intersection form, in which blade faces of the blades (10) are obliquely disposed with respect to radial directions with a center at the central shaft (12). By arranging the blades (10) in the multipoint intersection form, it is possible to provide the vertical shaft driving device, in which air flows or water flows can be efficiently utilized to obtain a great output power.

Abstract: A method for operating a rotary machine is provided. The rotary machine includes a stationary member and a rotatable member wherein the rotatable member is configured to rotate at least partially within the stationary member. The method includes determining an off-normal operating condition of the rotary machine facilitating undesirable contact between the rotatable member and the stationary member, monitoring a parameter associated with the off-normal operating condition, and preventing operation of the rotary machine while the monitored parameter is within a predetermined range.

Abstract: A power turbine speed control system for a helicopter is disclosed which includes components for generating a power turbine speed signal based upon a demanded rotor speed, a high-order filter for filtering the power turbine speed signal by effectuating a rapid attenuation of main and tail rotor torsional frequencies in the power turbine speed signal without compromising phase at low frequencies, and a governor for providing isochronous power turbine speed and rotor speed control based upon the filtered power turbine speed signal.

Abstract: Disclosed is a wind power generating apparatus in which windmill blades are mounted in a multi-stage fashion to a rotating shaft while being spaced apart from one another to efficiently generate wind power. Each windmill blade includes blade bodies mounted to the rotating shaft, and provided with wind pressure adjusting holes, wind pressure adjusting plates coupled to each blade body, and connected together to a wire, each wind pressure adjusting plate being slidable along guides respectively arranged at opposite sides of the associated wind pressure adjusting hole to adjust an opening degree of the wind pressure adjusting hole, elastic members each adapted to connect one end of the associated wire to the associated blade body, and winches each adapted to connect the other end of the associated blade body, the winches being mounted to a single shaft to simultaneously wind or unwind all wire.

Abstract: System for controlling the torsional stability of the drivetrain of a machine, in particular of a helicopter. The system (1) comprises a means (7) for acting on the speed of an engine (5) of the power train of the machine, a means (8) for measuring a speed NTL of rotation of the free turbine of the engine (5), a correction device (9) for correcting the measured speed NTL into a corrected value NTLcorr, a means (11) for determining a preset value NTLpres of the speed of rotation of the free turbine of the engine (5), and a a computation unit (12) for automatically computing, on the basis of the preset value NTLpres and of the corrected value NTLcorr, operating commands which are applied automatically to the first means (7). The correction device (9) corrects the measured speed NTL so as to obtain a corrected value NTLcorr exhibiting, at least around the first torsional mode of the drivetrain, the same modulus and an opposite phase with respect to the preset value NTLpres.

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 wind turbine with an array of rotors arranged at various heights. Each rotor is optimized for the height at which it is located. Optimization of each rotor could include selection of rated power, solidity, tip speed, blade twist, blade taper, or rotor diameter. Each rotor can also be operated in a manner that is optimized for the wind speed it experiences. Optimized operation parameters could include blade pitch angle or rotor speed.

Abstract: A protective device is provided for protecting a turbo molecular pump having a rotor mounted for undergoing rotation, an intake port for sucking gas by rotation of the rotor, and an exhaust port for exhausting the gas sucked from the intake port. The protective device has a detecting device for detecting the occurrence of an abnormal phenomenon in the turbo molecular pump. An abnormal phenomenon inference device infers a type of the abnormal phenomenon detected by the detecting device. A value obtaining device infers a magnitude of damage given to the turbo molecular pump by the abnormal phenomenon inferred by the abnormal phenomenon inference device and obtains a value weighted based on the inferred magnitude of the damage. A value accumulation device accumulates the value obtained by the value obtaining device. A sum obtaining device obtains a sum of the values accumulated in the value accumulation device.

Abstract: A variable pitch fan in which the pitch of the fan blades is varied under control of a controller according to the speed of the fan. The controller is programmed to respond to increased fan speed by decreasing pitch of the fan blades. The variable pitch fan has a piston extending axially from a main shaft, about which main shaft a fan blade hub rotates. A pitch shifter is mounted on a cylinder, which itself is mounted on the piston. The pitch shifter is actuated by hydraulic fluid supplied through the main shaft to the cylinder. The piston is preferably axially stationary in relation to the main shaft. The cylinder is secured against rotational movement by cooperating out of round surfaces. Grease for the pitch shifter is supplied through the guide pin. One guide pin may be used for grease supply, while another may be used for excess grease return.

Abstract: A variable speed helicopter tilt rotor system and method for operating such a system are provided which allow the helicopter rotor to be operated at an optimal angular velocity in revolutions per minute (RPM) minimizing the power required to turn the rotor thereby resulting in helicopter performance efficiency improvements, reduction in noise, and improvements in rotor, helicopter transmission and engine life. The system and method provide for an increase in helicopter endurance and range. The system and method also provide a substantial improvement in helicopter performance during take-off, hover and maneuver. All such improvements are valid in helicopter mode when the helicopter is supported by rotor vertical lift, in airplane mode when the helicopter is supported by wing lift and the rotor is tilted forward to provide propulsive thrust and in conversion from helicopter mode to airplane mode.

Abstract: A wind turbine with an array of rotors arranged at various heights. Each rotor is optimized for the height at which it is located. Optimization of each rotor could include selection of rated power, solidity, tip speed, blade twist, blade taper, or rotor diameter. Each rotor can also be operated in a manner that is optimized for the wind speed it experiences. Optimized operation parameters could include blade pitch angle or rotor speed.

Abstract: The invention concerns a device for adjusting the power of a power pack driving a helicopter rotor, comprising means for dosing the fuel feed rate. The invention is characterised in that it further comprises: an electronic control device (1) including means (8) acquiring an input signal corresponding to the rotational speed of the rotor NP, means for processing said input signal comprising a differentiating element (11) and a summing element (13) and a threshold comparator (15) receiving the output signal of said processing means and an actuating device (2) receiving the output signal of the electronic control device (1) and actuating the means (3) dosing the fuel feed rate.

Abstract: A system and method of automatically setting a flat rate engine power setting of an aircraft determines the weight of loaded cargo containers to determine the total gross weight of the aircraft prior to take-off, determines, from the total gross weight, the required flat rate engine power for the aircraft, such as by inputting the stored value into a look-up table, and automatically sets the flat rate setting of the aircraft's engines to correspond to the determined required engine power, prior to take-off, by sending the obtained required flat rate engine power as a command signal to an engine control system.

Abstract: A variable speed helicopter rotor system and method for operating such a system are provided which allow the helicopter rotor to be operated at an optimal angular velocity in revolutions per minute (RPM) minimizing the power required to turn the rotor and thereby resulting in helicopter performance efficiency improvements, reduction in noise, and improvements in rotor, helicopter transmission and engine life. The system and method provide for an increase in helicopter endurance and. The system and method also provide a substantial improvement in helicopter performance during take-off, hover and maneuver.

Abstract: An apparatus for generating electric power using wind force which is capable of generating good quality electric power by combining the apparatus with the inventor's water wave force-based electric power generating apparatus and installing this combined apparatus in the sea.

Abstract: A hydraulically reversible, adjustable propeller unit for aircraft, land vehicles and watercraft, with a propeller with at least two blades, the pitch of which is controllable by means of a control unit (controller), whereby a hydraulic connection exists between the rotating propeller and the stationary control unit for controlling the blade pitch, with a spring-preloaded piston actuated by means of a hydraulic fluid, and with adjustable mechanical stop means for the start position, the brake position and the cruising or sailing position, whereby the piston is designed as a spring-preloaded double piston consisting of an inner piston and a ring piston arranged around the inner piston, said two pistons being lockable with each other by means of a centrifugal-force locking mechanism; the stop means for the start position is designed for limiting the setting range of the locked double piston in order to prevent unintentional reversing at speeds above about 1500 rpm; and the brake position can be reached only whe

Abstract: The present invention comprises a feedback-controlled braking apparatus that applies a modulated braking force that smoothly decelerates a rotating shaft such that it comes to rest at a precise location. According to a preferred embodiment of the present invention the rotor hub of a rotor/wing aircraft is coupled to a hydraulically actuated friction brake, such as a conventional disk brake. The disk brake caliper is supplied with fluid pressure from an electrically actuated servo valve which, in turn, is controlled by an electronic controller. A sensor monitors the angular position and velocity of the rotor main shaft. The velocity and position information is provided to the controller, which modulates the brake pressure as required to bring the rotor to a stop at exactly the right orientation relative to the aircraft.

Abstract: A propeller with pivoting blades is provided as a cleaning tool (1) for the work area of metal cutting machines, where the angle of adjustment for the pivoting blades is such that an air jet is generated supporting the propeller blades (15) in folding open. The propeller blade (15) is arranged in a tool changer stacker instead of a common tool or on a tool spindle and serves to automatically clean the work area by a blowing process.

Abstract: A cooling control apparatus controls a plurality of cooling members. The apparatus has a monitor which monitors states of predetermined combinations of the cooling members and a controller which controls the cooling members based on the states monitored by the monitor.

Abstract: An improved electronic hydraulic propeller control designed as a retro-fit kit for existing Hamilton Standard Division 54460 and 54H60 propeller controllers includes an apparatus for controlling the pitch angle of a propeller blade. The retro-fit kit includes an electro-hydraulic servo valve, an electronic controller, a protection valve, and a propeller maintenance interface panel. These components functionally replace the existing hydromechanical propeller control system without reconfiguration of the existing interface. The apparatus converts mechanical inputs of the propeller and airframe systems to electronic signals, which can be measured by the electronic control. The apparatus also receives and converts the electronic control's commands into hydraulic pressure and flow changes through an electro-hydraulic servo valve. The electronic controller performs the required calculations to interpret and then react to changes in the propeller/airframe systems.

Abstract: A variable speed helicopter rotor system and method for operating such a system are provided which allow the helicopter rotor to be operated at an optimal angular velocity in revolutions per minute (RPM) minimizing the power required to turn the rotor and thereby resulting in helicopter performance efficiency improvements, reduction in noise, and improvements in rotor, helicopter transmission and engine life. The system and method provide for an increase in helicopter endurance and. The system and method also provide a substantial improvement in helicopter performance during take-off, hover and maneuver.

Abstract: A fluid-activatable vane is defined by a thin vane body having opposed narrow leading and trailing side edges and opposed substantially smooth large top and bottom surfaces. The body has a central longitudinal axis and is substantially symmetrical on opposed sides of the axis. An attachment shaft is aligned with the central axis at a near end edge of the vane to secure two diametrically opposed vanes through a coupling wherein the vane will tilt along a 90.degree. arc from a horizontal plane to a vertical plane when exposed to a fluid flow. The two vanes form a propeller and are fixed to a respective end of the attachment shaft in a respective plane and offset 90.degree. from one another. A fluid actuatable torquing curved outer end edge portion is formed integral with the vane body in an outer end edge portion thereof and on a respective side of a central longitudinal axis.

Abstract: A propeller pitch control apparatus for an aircraft in which the vector sum of the aircraft forward speed and the propeller rotational tip speed is a selected fraction of the speed of sound, the fraction based on percent power and altitude, to maximize efficiency and minimize noise.

Abstract: An impeller having flexible impeller blades with a stiffness which allows the blades to flex into a backward-curved impeller configuration at the maximum intended rotational speed of operation, and to return to a more radial blade configuration at lower rotational speeds, thereby enabling efficient operation at a broad range of rotational speeds.

Abstract: A fluid energy turbine has a radial flow rotor in which fluid driven blades are peripherally distributed about a horizontal axis and in which auxiliary-biased outlet gates are provided for release of high fluid pressures to govern turbine speed such as in high windstorms.

Abstract: A system for controlling functions of a propeller having a plurality of blades is disclosed. The system comprises an electronic control for controlling the functions of the propeller. A plurality of backup devices are provided for backing up the electronic control upon the occurrence of conditions. These conditions include at least one of testing, manual override, and a malfunction in the electronic control causing at least one of the functions to endanger safety. The system further includes a bypass device for bypassing the electronic control and for invoking at least one of the plurality of backup devices to acquire control over at least one of the functions. The bypass devices include a mechanism for determining the occurrence of at least one of the conditions and for actuating electronic control override.

Abstract: A rotary fan includes a rotatable base plate, a plurality of fan blades mounted rotatably on the base plate at a peripheral portion thereof by means of supporting studs, and a blade angle adjusting mechanism mounted in association with each of the fan blades for allowing the fan blade to rotate pivotally about the supporting stud under a centrifugal force acting on the fan blade such that the rate of increase of the air quantity produced by the fan blade decreases as a rotation number of the rotatable base plate increases within a predetermined high-speed rotation range of the rotatable base plate, while in other rotation speed range outside of the high-speed rotation range, the blade angle adjusting mechanism acts to suppress the rotation of the fan blade around the supporting stud. Noise generated by the rotary fan can significantly be reduced while ensuring a sufficient quantity of air flow.

Abstract: In a propeller for a boat, a plurality of stationary blades and a plurality of variable blades are alternately disposed around an outer periphery of a propeller boss. Exhaust passages are formed in the propeller boss to axially pass through the propeller boss at location corresponding to the stationary blades. Despite the provision of the variable blade which is variable in diameter or pitch, the exhaust passage can be formed into a large sectional area in the blade boss without being obstructed by a blade shaft for the variable blade.

Abstract: A fluid energy turbine has a radial flow rotor in which fluid driven blades are peripherally distributed about a horizontal axis and in which auxiliary biased outlet gates are provided for release of high fluid pressures to govern turbine speed such as in high storm winds. The blades additionally may be made featherable to govern the turbine speed by feathering the blades either preceding or after the gate openings or simultaneously as preset by the degree of biasing of both determined by matching to weather conditions in the area of use. In other embodiments, the gates are interconnected to the featherable blades for coordinated operation by means such as cables or rods.

Abstract: A rotor hub is provided for coupling a wind turbine rotor blade and a shaft. The hub has a yoke with a body which is connected to the shaft, and extension portions which are connected to teeter bearing blocks, each of which has an aperture. The blocks are connected to a saddle which envelops the rotor blade by one or two shafts which pass through the apertures in the bearing blocks. The saddle and blade are separated by a rubber interface which provides for distribution of stress over a larger portion of the blade. Two teeter control mechanisms, which may include hydraulic pistons and springs, are connected to the rotor blade and to the yoke at extension portions. These control mechanisms provide end-of-stroke damping, braking, and stiffness based on the teeter angle and speed of the blade.

Abstract: A propeller control system comprises a phase controller (11) having a phase control gain to control a propeller phase relationship, free air turbulence detection means (7, 9) and a gain controller (8) for varying the phase control gain in response to detected free air turbulence such that in the presence of turbulence a low gain is selected and in the absence of turbulence a high gain is selected. By varying the gain in this way the sensitivity of the phase controller (11) is reduced during turbulent conditions preventing excessive phase changes by the controller (11) striving to follow a turbulent master propeller. Similarly a speed controller (14) has its gain set by a gain controller (17) according to the degree of turbulence detected.

Abstract: A wind turbine has a rotor with at least one blade which has an aileron which is adjusted by an actuator. A hinge has two portions, one for mounting a stationary hinge arm to the blade, the other for coupling to the aileron actuator. Several types of hinges can be used, along with different actuators. The aileron is designed so that it has a constant chord with a number of identical sub-assemblies. The leading edge of the aileron has at least one curved portion so that the aileron does not vent over a certain range of angles, but vents if the position is outside the range. A cyclic actuator can be mounted to the aileron to adjust the position periodically. Generally, the aileron will be adjusted over a range related to the rotational position of the blade. A method for operating the cyclic assembly is also described.

Abstract: An electric pitch control apparatus for a variable-pitch propeller equipped with a pitch control mechanism having an electrically controlled actuator for controlling a pitch angle of the propeller blade in accordance with a control current applied thereto. The electric pitch control apparatus is designed to compensate a difference between target and actual pitch control amounts caused by a secular change of the pitch control mechanism thereby to effect an accurate control of the propeller pitch.

Abstract: A marine propeller includes a hub rotatable about a longitudinal axis and having a plurality of blades extending radially outwardly therefrom and pivotable about respective radial pivot axes between a low pitch position and a high pitch position. A disc has a plurality of guide slots each receiving and retaining a respective lever arm extending rearwardly within the hub from a respective blade. A biasing spring coaxial with the longitudinal axis of rotation of the hub biases the disc to in turn bias the lever arms and blades to the low pitch position. The disc is a generally flat planar plate-like member extending radially outwardly from the longitudinal axis at the rear of the hub and includes a preload mechanism accessible at the rear of the hub for adjusting the bias. The disc restricts movement of the lever arms along the guide slots such that the lever arms can move only in unison, which prevents blade flutter.

Abstract: An electric pitch control apparatus for a variable-pitch propeller capable of properly controlling the pitch angle of the propeller blade in accordance with instantaneous operational conditions of the propeller and of effecting adjustment of the pitch angle of the propeller blade without any delay of a time in response to operation of the engine output lever for promptly coinciding an actual rotational number of the prime engine with a target rotational number.

Abstract: The invention concerns a system for controlling an aircraft propeller. A hydraulic motor controls pitch of the propeller blades. The propeller blades are characterized by the absence of feather-inducing counterweights. An overspeed governor senses when propeller speed exceeds a limit, and, in response, assumes control of the hydraulic motor and drives the blades toward a coarsened pitch position, which reduces the propeller speed. In another form of the invention, a mechanical brake can override the hydraulic motor and mechanically retard a rotating gear, which causes the propeller blades to move toward a coarsened pitch.

Abstract: A pitch control apparatus for a variable pitch propeller for drive connection to an aircraft engine, wherein an optimum rotation number of the engine is calculated in relation to a flight speed of the aircraft, an opening degree of the engine throttle and the density of atmospheric air in flight of the aircraft to maximize a thurst force acting on the aircraft, and wherein a pitch angle of the propeller blade is controlled in such a manner that the rotation number of the engine becomes substantially equal to the optimum rotation number.

Abstract: A speed and phase sensor counterrotates aircraft propellers. A toothed wheel is attached to each propeller, and the teeth trigger a sensor as they pass, producing a sequence of signals. From the sequence of signals, rotational speed of each propeller is computer based on time intervals between successive signals. The speed can be computed several times during one revolution, thus giving speed information which is highly up-to-date. Given that spacing between teeth may not be uniform, the signals produced may be nonuniform in time. Error coefficients are derived to correct for nonuniformities in the resulting signals, thus allowing accurate speed to be computed despite the spacing nonuniformities. Phase can be viewed as the relative rotational position of one propeller with respect to the other, but measured at a fixed time. Phase is computed from the signals.

Abstract: A self-actuating variable pitch marine propeller which incorporates two or more blades having cylindrical shafts which are rotatably connected to a central hub via cylindrical joints; the blades rotate about and translate radially, relative to the hub center, along the blade shaft, or shank, axis. In operation, the blades move radially outwardly from the hub center as they rotate from lower to higher pitch. The blades are biased towards the lower pitch. As the propeller rotational speed increases, centrifugal forces act on the blade mass creating a radially directed outward force. This radially outward force, upon reaching a sufficient magnitude, causes the blades to move radially outward. A blade positioning mechanism connected between each blade and the hub directs the blades to rotate to a higher pitch angle as the blades move radially outward.

Abstract: A wind turbine generator blade includes a movable front portion, extending from the faster-moving blade tip in a span-wise direction along the blade, and mounted on a pivot axis permitting the front portion to be displaced to a "high drag" position in which it has a high negative angle of incidence which will in turn give rise to a high negative angle of attack to the relative airflow and hence an increased drag tending to slow down an overspeeding blade, but will also give rise to an increased lift which assists in slowing down the overspeeding blade. It has been found that a truncated aerofoil section such as that used for the front blade portion has a relatively high stalling angle, allowing its use in conditions such that the angle of attack may approach 30.degree. without stalling of the front blade portion, but in the presence of a considerably increased total drag on the blade.

Abstract: A ground mode pitch position logic and control is shown and described in this invention. A method for scheduling and limiting the pitch actuator reference signal in accordance with the actuator commanded schedule, propeller overspeed and propeller underspeed.

Abstract: An aircraft engine propeller autofeather system (4) has a feather solenoid (8) which is actuated by either a signal provided by an engine power loss detector (10) or a signal provided by an engine overspeed detector (12). The overspeed detector (12) detects excessive propeller speed by comparing the speed to a first predetermined value (21) or by comparing the speed rate of change to a second predetermined value (23) combined with comparing the speed to a third predetermined value (25).

Abstract: A power conversion turbine for actuation by fluid in motion such as, for example the wind, with a body supported to rotate about a central axis and carrying a plurality of vanes spaced from said axis and being movable about respective vane axes parallel to said central axis and which vanes are circumferentially spaced from each other and dimensioned such that, when said vanes are in a FIRST closed position they collectively form a substantially unbroken cylindrical surface and are selectively movable from said FIRST position to a fully open SECOND position and said vanes including interconnecting means causing selected ones of said vanes to close as one or more opposing vanes are caused to move from the first to the second position by reason of passage of fluid and means integrally connected with said interconnecting means for infinitely varying the degree of opening of the vanes between fully closed and fully open positions.

Abstract: A blade pitch control mechanism for a ram air driven turbine blade mounted for rotation on a hub assembly having a central axis. A governor control member, including a seat, is mounted on a portion of the hub assembly for reciprocation along the central axis. A first spring acts on the governor control member in a first axial direction. A governor slide member is mounted for reciprocation along the central axis. The blade is in mating engagement with the governor slide member. A second spring acts between the governor slide member and the seat of the governor control member for biasing the slide member opposite the first axial direction. This causes the blade to assume a course pitch when the blade and hub assembly are in storage and to allow the blade to move to fine pitch during start-up. A flyweight is mounted on the hub assembly and engages the governor control member for acting against the first spring to control blade pitch and govern turbine speed after start-up.