The deflection of the control surfaces originating from the relative motion between linkage 11, rotating with said blade assembly, versus the inclination of bearing 15, whose inner ring is fixed with respect to said tilt axis and rotated with hub 4 in fixed relation to the mainshaft 1. The inclination of said bearing causes the control surfaces connected by said linkage to reciprocate. This invention relates to cycloidal fluid flow engines, which have their mainshaft transverse to the external flow, their blades move on a quasi cylindrical orbit around the mainshaft, but with respect to the external flow, the blades follow a path which closely approximates a cycloid or a trochoid. The blade assemblies, being symmetric at zero deflection of all control surfaces, follow the cyclic change of the relative flow 18 in FIG. 13 at gear 97, will control the angle of attack of all stationary wings 61. This would also serve as rudder control for a ship after the propeller has been stopped.
- Nos relajamos y nos ponemos a descansar
- Colabora en el crecimiento de los huesos
- Per la liason d’una proteïna especifica amb un sucre situada a la superfícia d’un bactèri
- Dicen estar a gusto con el personal del hospital porque son cercanos y cariñosos
FIGS. 11 and 12 illustrate an example for a crossflow starting device on a marine propeller, having wing 61 and elevator 62 extending downward into the water, keeping all other components above the waterline 63 and protected from water spray by a suitable shield. DETAILED DESCRIPTION OF THE DRAWINGS The mainshaft of the cycloidal fluid flow engine is indicated generally at 1, is mounted in suitable bearings represented at 2 and carries permanently connected radially extending structure, for example arms, generally indicated at 3, which support blade assemblies by means of hubs indicated at 4. Said bearings of the mainshaft are seated in a housing indicated at 5, which links said engine to the power plant or propulsion unit, depending on the mode of operation as a turbine or a propeller. 13, a rotational motion of the inclined bearing 82 relative to radial structure 3 is provided by a mechanical, electrical or hydraulic gear train, like bevelgearing or remote indexing systems, represented by a chain drive consisting of sprocket wheels 83 and 84, having equal pitch circles, and connected by a chain as indicated at 85. Sprocket wheel 84 is mounted to bushing 86 which can be rotated about the housing 5 through gearing indicated at 87 and 88. Sprocket wheel 83 is mounted to bushing 89, which is rotably mounted into hollow hub shaft 64 of the blade assembly, and which carries the tiltable bearing assembly 82. Said chaindrive keeps bearing 82 rotationally fixed with respect to bushing 86, being mounted on engine housing 5 and controlable by means of gears 87 and 88. Gear 88 is manually or automatically by sensors of the external flow direction controlled for directing the thrust during propeller operation, or in case of turbine operation for aligning the blade assemblies with the external flow.
11, having a cross flow starting device, but each inclined bearing is mounted with a fixed axis of inclination tangential to the radial structure, as illustrated in FIGS. In FIGS. 3 and 4, bearing assembly 20 is pivotly supported over axis 21–21 by means of bearing 22 located on the inner ring of bearing 20 and bushing 23. Dolor en la parte anterior de la rodilla . For manual control of the inclination, crank 24, attached to the inner ring of bearing 20, is controlled through linkage indicated at 25 and 26, employing a bearing 27 for separation of the rotation of radial structure 3 from the stationary linkage 28, which passes through the center of hollow mainshaft 30 to lever 29. Control of the mainshaft speed is accomplished by a centrifugal governor shown in FIG. The control systems for instance, providing the proper reciprocating actuation of the control surfaces, can be mechanically modified, but also routinely replaced by electro mechanical systems employing sliprings or switches, reversing polarity depending on the relative rotation between the engine housing, the radial structure and the blade systems.
Dolores Musculares Piernas
This makes control modes, which can provide only a fixed relation between the blade rotation and orbital position unsuitable for higher rotational speeds, where the overall performance rating is best. A further object of the invention is to provide a cycloidal propeller, which accomplishes the transition from the reciprocating motion of the blades centered about their orbit at low advance ratios, to the fish tailing motion at high advance ratio, centered about the line of travel; thus capable of extending the speed range of an air- or waterborn vehicle above the orbital speed of the blades, allowing reduction of absolute blade speed and wave drag or cavitation connected with excessive fluid flow velocities. SUMMARY OF THE INVENTION The broad objective of my invention is to provide a new, more efficient and versatile cycloidal fluid flow engine having the blades flow dynamically pitch controllable through the full range of external flow conditions and orbital speeds of the blades, applicable for fully controllable turbine and propeller operation including the limit case of no rotation, where the blades aquire the roll of stationary lift producing wings of an aircraft, or rudders of a vessel.
Indirect pitch control of freely rotating blades by means of trim tabs, controlled by cam devices, has been proposed, but is insuficient for achieving accurate pitch control throughout the range of advance ratios because a trimtab alone can not provide for the longitudinal stability and control needed for accomplishing the fast pitch changes by a cycloidal turbine even at very low speeds. A important factor in achieving the proper pitch angles lies in optimizing the blade assembly toward high control stability in the sense that a specific angle of attack position without over-travel. Each blade assembly comprises a wing with or without camber-changing devices and a tail, imparting airplane type pitch stability and control characteristics to the freely rotable blade assembly, optimizing the lift production. 7 to 10. These devices change the zero lift angle of the symmetric airfoil of wing 7, thus requiring no, or very little rotation of the wing assembly, which reduces the inertia interaction considerably.