Abstract: A helicopter composite swashplate ring that has a triaxial braided tubular ring that withstands both forces in-plane and normal to the plane of the swashplate. The triaxial braided tubular ring comprises substantially circumferential fibers interwoven with angled fibers oriented at a predetermined angle to the circumferential fibers. The tubular ring contains a composite circumferential spacer ring that comprises an upper ring plate connected to a lower ring plate by a plurality of first tubular support members. The upper ring plate and lower ring plate are adjacent the inside upper and insider lower surfaces of the tubular ring, respectively. The upper and lower plates have openings in alignment with the first tubular support members. The ring plates have a plurality of sections extending radially outward. The sections have lug openings that are in alignment with a plurality of second vertical support members to form channels therethrough for accepting servo or control rod lugs.

Abstract: A turbine rotor has composite ceramic blades each having a bulb-shaped root with planar flanks which define an angle of convergence between them not exceeding ten degrees, and by which the root is held in a dovetail section socket in the periphery of the rotor disc by means of wedge-shaped members also disposed in the socket on opposite sides of the root. Each wedge-shaped member is part of an element including a platform which is disposed adjacent the curved portion of the blade radially outwards of the socket and which is joined to the wedge-shaped member by an integral strut. The platforms of all of the elements extend in a circumferential direction and combine to define a continuous ring forming part of the inner boundary of the gas flow path through the turbine.

Abstract: An improved design for a structure such as a turbine vane or blade subjected to extreme temperature levels and/or gradients resulting in extreme deformation stresses within the structure. The present structures comprise an interior skeletal support having a plurality of spaced, flexible support legs which extend out and are attached to spaced areas of a flexible outer surface skin which is subjected to extreme temperature levels or temperature gradients during use. The extreme stresses normally developed by the expansion of the surface skin are avoided by the ability of the skin to move minutely and flex the spaced support legs to variable extents and in predetermined directions.

Abstract: An adjustable diameter screw propeller includes a hub having a plurality of spindles, each mounted in the hub for rotation about an axis disposed radially of the hub axis and a mechanism for synchronously turning the spindles in a common direction. A plurality of propeller blades having a fixed pitch contour and a skew in the range of 60.degree. to 90.degree. are attached to respective ones of the spindles, such that as the spindles are turned, the blades rotate between a first disposition in which the diameter of the propeller is maximum and a second disposition in which the diameter of the propeller is reduced. In addition, the pitch of the propeller increases as the propeller diameter decreases to compensate for the loss of power that would otherwise occur as the propeller diameter is decreased.

Abstract: A supplementary fin for attachment to the blades of dispersion fans in microwave ovens is disclosed. Supplementary fins 7 and 7a are removably attached to the underside of respective blades 2 and 2a of standard dispersing fan 1. To maintain balance of the fan assembly, supplementary fins 7b and 7c are attached to the top side of respective dispersing fan blades 2b and 2c. The removable attachment capability of the supplementary fins is accomplished by sliding of tongue 5 through a rectangular hole 4 so as to align a fixing hole 6 with a circular hole 3. An expandable clip 9 is inserted through holes 3 and 6 and is expanded by insertion of a pin 8 so as to removably attach the supplementary fin 7 to dispersing fan blade 2. This removable attachment capability allows optimum dispersion characteristics to be achieved for a variety of dispersing fans, fan motors, and oven air venting configurations, by simple replacement of supplementary fins with supplementary fins of different design.

Abstract: A wind energy converter with a rotor having a vertical swivelling axis has n each rotor arm a vertical vane that is supported so as to be able to pivot about an approximately vertical pivotting axis on the leading edge of the vane. A balance weight is installed in a vane nose section that is located ahead of the leading edge of the vane. The overall center of gravity of the mass of the body consisting of the vane and the balance weight is located ahead of the swivelling axis of the vane. The vane is made with an assymetrical airfoil section. The vane adjusts to the particular optimal angle of attack in the course of each rotation of the rotor. The wind energy converter has a high degree of efficiency at low and medium relative velocity values, and is self-starting.

Abstract: The present invention relates to a circulation flow control rotor system for an aircraft which includes rotor blades provided with slit shaped blower nozzles further comprising control devices for obtaining a cyclic or multicyclic or collective rotor blade angle control under utilization of individual pressure gas flow from a pressure chamber to the nozzle slits; further including deformable control members which are going to be deformed in accordance with certain rules underlying the requisite control.

Abstract: Pump having an impeller with accurately formed radial passages and the method for making it.

Abstract: A compressor blade assembly for a compressor operating at transonic or supersonic blade speeds has a part span shroud. The shroud is twisted having a first angle in the direction of airflow on one side of the shock wave and a second angle in the direction of airflow on the other side of the shock wave.

Abstract: Two-part turbine-blade retainer structures are disclosed for axial retention of each of a plurality of turbine blades to a rotor wheel, wherein radial retention is via fir-tree engagement of individual blade roots to the wheel. In a preferred embodiment, a male or bolt element of the retainer has a shank which is characterized by a smoothly cylindrical portion adjacent at one end to one of the heads; this cylindrical portion terminates at a shoulder, beyond which the shank is reduced and externally threaded. A sleeve or nut element of the retainer has an elongate threaded bore and is characterized by an outer cylindrical surface which extends to the second head. The two elements are proportioned to be inserted through opposite ends of a passageway and to be screwed together into firm engagement at the shoulder (i.e., at a location intermediate the two heads), with the sleeve covering the threads of the male element and the heads preventing the turbine blade from axial motion with respect to the wheel.

Abstract: A fiber reinforced braided composite main helicopter rotor hub retention plate whose fiber orientation withstands forces both in the plane of the retention plate and normal to the plane. The retention plate comprises a fiber reinforced resin braided tubular ring having substantially circumferential fibers interwoven with angled fibers disposed about a central core. Arms extend inward from the braided ring for attachment to a driveshaft.

Abstract: An impeller, comprising a main disc (1), blades (2) and a covering disc (3) which consists of interconnected web (4) and ring (5). The joint of the web (4) and ring (5) is detachable to form mated surface (6 and 7) in the place of the joint and has on the surface (7) of the ring (5) an annular shoulder (8) and on the surface (6) of the web (4) an annular groove (9) accomodating the shoulder (8). The internal diameter Do of the web (4) is less than the diameter (D) of the ring (5) along their mated surfaces (6 and 7) by 1 to 1.5.times.10.sup.-3 Do.

Abstract: A rotor hub system for a helicopter in which the rotor hub and pitch housing are fabricated predominately of composite material, the flap hinge, pitch hinge and lead-lag hinge contain elastomeric bearings and one step blade folding in either the forward or aft direction using the same drive system. The rotor hub includes closed loop straps which define generally opposed lugs of the flap hinge, and the pitch housing includes a pair of closed loop straps which define the lugs of the lead-lag hinge and a lug of the flap hinge. The use of composite materials as the predominant material of the rotor hub and the pitch housing results in a highly load redundant structure permitting a reduction in size and number of parts, a reduction in drag, and an increase in reliability and safety.

Abstract: This disclosure relates to a marine propulsion system including a double propeller. To obtain a forward thrust, the two propellers are driven in opposite directions while producing forward propulsion forces. To obtain a rearward thrust, only one propeller is driven in the direction to produce a rearward force. The two propellers are attached to coaxial inner and outer horizontal shafts. A single vertical shaft is coupled by bevel gears to the shafts, and movable clutches couple the driving force to the horizontal shafts.

Abstract: The conical section of the hollow shaft of a high pressure compressor behind the last rotor disc is surrounded by an annular protective shield. The shield serves to protect the hollow shaft and the last rotor disc from the main stream of hot compressed air leaving the compressor. Between the hollow shaft and the heat shield a stream of cooling air is furthermore conducted from the vicinity of the axis to the outer region of the last rotor disc. The stream of air then passes through corresponding circumferentially distributed axial holes in the last rotor disc.

Abstract: In a variable pitch wind turbine system, pitch angle is determined by a pneumatically pressurized hydraulic actuator connected between crank arms on the blade pitch axles. The hydraulic line extends coaxially through the rotor drive shaft via a rotary union to a gas charged accumulator on the yaw carriage. The pitch axes are positively coupled for 1:1 counter-rotation by a gear train, preferably lying on the opposite side of the rotor axis from the hydraulic actuator.

Abstract: An improved helicopter rotor flexbeam (20) comprises a pair of generally parallel outwardly open, cross-sectionally C-shaped beams (25) of a geometry which defines therein a first inboard region (A) of enhanced out-of-plane flexibility and a second outboard region (B) of enhanced in-plane and torsional flexibility.

Abstract: A process provides a method for attaching a turbine blade to a blade support such as a rotor or rotor disc of a turbine. The root portion of the blade is formed to a shape approximately that of a groove in the surface of the rotor or rotor disc and the root portion of the blade is inserted within the groove. A composition comprising a particulate compound selected from the group consisting of a ceramic, graphite metal, metal alloy and mixtures thereof is positioned between the root portion of the blade and steeples, located one on either side of the groove.

Abstract: A multi-blade rotor for a windmill-type apparatus, including a hub supported on a shaft or a fixed angle, and rotor blades that are connected to the hub, via bearing arrangement, in such a way that the rotor blades are rotatable about their longitudinal axes. The inventive easy-to-manufacture, and relatively lightweight, hub has rotationally symmetrical hollow bodies, the number of which correspond to the number of rotor blades. The hollow bodies are mounted on rod-like or tubular pressure members, the number of which correspond to the number of hollow bodies. The pressure members are mounted on the shaft or fixed axle via bearing plates in such a way that their longitudinal central axes are respectively disposed at or nearly at the point of concentration of the bending moment surface of the pertaining hollow body.

Abstract: An airfoil-shaped blade assembly having a metallic core, thin coolant liner and ceramic blade jacket includes variable-size cooling passages and a circumferential stagnant air gap to provide a substantially cooler core temperature during high temperature operations.