Abstract: A cam mechanism enabling the pilot to automatically advance the propeller low pitch stop with the engine power lever on airplanes with multibladed propeller systems having a beta control mechanism for adjusting the blade angle. The cam provides an inexpensive and reliable alternative to costly and complex automatic feathering systems.

Abstract: A multi-blade, variable pitch wind driven propeller in which a shock absorber is connected with each blade to dampen movement in both the radially inward and radially outward movements of the blade. Tension springs are connected with the blades to move them inwardly against centrifugal force, and in a preferred form of the invention, the tension spring has a variable rate so that it exerts greater resistance near its limit of outward travel. A coil compression spring may also be connected with each blade to absorb loads at the inner limit of travel of the blade and to impart an initial impetus to outward movement of the blade. In addition, retrofit lock nut means is provided for attachment to the ball stud connected to the butt end of each blade to extend along substantially the entire length of the stud and achieve a ratio of ball stud diameter, in inches, to rotor radius, in feet, of least as much as 0.100, thereby minimizing the risk of failure of the stud.

Abstract: The drawings and description describe a hand-portable fire fighting, positive pressure blower 10 for providing positive pressure within a smoke filled space to remove the smoke, heat and carbon dioxide from a smoke filled space to facilitate the extinguishment of the fire and the overhauling of the space subsequent to the extinguishment. It further greatly enhances the safety of the fire fighters. The blower 10 includes a portable support frame 12 having an internal combustion engine 13 mounted thereon with a two blade wooden prop 18 mounted on the drive shaft for generating a cylindrical stream of fast moving air to be directed into the smoke filled space. The blower 10 includes a tilting mechanism 22 that has a lead screw with a crank that extends between a front leg frame section 58 and a central frame section 24. The front leg section 28 has a vibrational dampening cross frame element 60 that extends between the forward extending left front leg 62 and the right front leg 64.

Abstract: An annular fairing forming a bolt guard associated with the heads of screws of an attachment carries, inside thereof and in line with each screw, first cylindrical sockets each comprising two slightly inwardly bent tongues which cooperate with apertures provided in a respective second socket disposed within the first socket and comprising an inturned downstream edge which is impressed over and thereby engaged with peripheral teeth on the head of the respective screw.

Abstract: A method and apparatus for work expanding a cryogenic liquid wherein the liquid is expanded in a manner to avoid a transient pressure drop below the flash point thus reducing the potential for cavitation and consequent operating inefficiencies.

Abstract: An aircraft propeller has adjustable pitch blades which are reset from a low pitch in-flight idle position to a lower pitch ground idle position by a beta feedback and reset mechanism. The reset mechanism includes a set of cam elements supported for movement in response to rotation of the blades and positioned to engage a follower plate adjustably mounted on the beta feedback control rods.

Abstract: Method and apparatus for assembling integral platform blade groups to a rotor of a steam turbine in which the platform roots are skewed with respect to the axis of the turbine. The platform roots are formed to define a set of spaced grooves and steeples are formed on the rotor to mate with the platform roots. Grooves on the platform and in the rotor are alignable to accept a connecting member when the steeples are aligned in abutting relationship with platform roots. The connecting member joins the blade group to the rotor. In one form, the bearing surfaces of the steeples, roots and connecting member are formed to lie on one or more circles circumscribing the rotor axis.

Abstract: A pump impeller especially useful for moving heavy sediment and debris includes a drive plate having a series of blades mounted on one side thereof and radially extending from the center of the drive plate. Each of the blades is provided with a material retainer secured to the leading edge of the blade in the form of a winglet. The winglet forces the sediment and debris outwardly to be driven by the leading edge and across the tip of the blade. Each of the top or inlet edges of the blades is sharpened to cut weeds or debris which may then be pumped with the sediment.

Abstract: Control system for synchrophasing the propellers of an aircraft, each propeller provided with a blade pitch controller for controlling the blade angle of the propeller, the systen containing for each propeller a control loop, comprising: a revolution rate controller, means for determining the blade passing frequency, an adjustable propeller revolution rate reference source supplying a revolution rate setpoint control signal, comparator means for comparing the blade passing frequency with said setpoint to generate an error signal for the revolution rate controller.

Abstract: Replacement low pressure end blading for a utility power steam turbine having an extended length compared to original equipment end blading providing higher efficiency. The blading incorporates extended flat areas on the blade trailing edge for improved flow characteristics and reduced losses. Mass distribution is used to tune the blade to avoid natural harmonic frequencies coincidental with turbine rotational frequencies or harmonics thereof. Blade root modifications are included to facilitate installation.

Abstract: An axial flow ring fan has improved efficiency and reduced noise by making the leading edge of each blade a generally sinusoidal shape.

Abstract: A wind power or hydraulic power machine with axial feed, radial outflow and variable geometry vanes is disclosed. This machine has a support that channels the flow, in limiting the escape flows to the maximum, and provides protection in giving to this wind power or hydraulic power machine excellent resistance to axial stresses, and plays the role of an inertia wheel.

Abstract: A gas turbine rotor includes a disk (50) with axial dovetail slots (64) and air cooled blades (52) having mating, but shortened dovetails (66). The axial flow path (68) so formed is blocked at the far end and is in fluid communication with the blade cooling passages. Balance weights (70) fit within the openings in a manner which does not interfere with the cooling airflow.

Abstract: The invention comprises an internal blade retention system for rotary engines and particularly for gas turbine engines. The system comprises a rotary disk 12 positioned for rotation within the turbine engine, the disk having a multitude of dovetail blade slots 16 and a groove 12E centrally positioned on its circumferential edge and cutting across the blade slots. A preloaded circular snap ring 10 is positioned in the centrally located groove 12E on the disk edge and in its relaxed position the snap ring extends radially outward from the groove. Multiple blades 14 are installed onto the blade seats in the disk, each of the blades having a base with a centrally located goove 14E that engages the snap ring 10 in order to axially lock the blade in its seat.

Abstract: A helicopter rotor blade supported by a flexbeam to be rotatable about an axis of rotation, in which a pitching motion thereof is allowable, is provided with a device for changing the pitch and damping the lead-lag motion thereof. The device comprises a bushing in a through hole formed at the inboard end of the flexbeam, an elastomeric pivot loosely fitted in the bushing, elastomeric dampers of cylindrical shape mounted on the upper and lower surfaces of the flexbeam and coupled with the upper and lower ends of the elastomeric pivot by means of nuts, and torque arms extending through the bushing and the elastomeric dampers and having the central portion thereof connected to central shafts of the elastomeric pivots. Each of the torque arms has both ends outwardly projecting beyond the elastomeric dampers and secured to a pitch sleeve which encloses the flexbeam.

Abstract: Hydraulic fluid is input to a transfer tube of a variable pitch propeller system forward of a rotatable portion of a controller. A transfer bearing is provided about the drive shaft to transfer hydraulic fluid therethrough and between the drive shaft and the transfer tube to transfer hydraulic fluid from the drive shaft into the transfer tube, such transfer bearing allowing relative rotation between the housing and the drive shaft and between the drive shaft and the transfer tube. The transfer tube is slideably connected to the rotatable portion of the controller.

Abstract: An improved turbine blade tip with diffusion cooling holes in the tip is disclosed. One particular embodiment of the invention provides an improved squealer blade tip with diffusion cooling holes in the tip. Yet another embodiment of the invention provides blade tip diffusion cooling holes comprising a first cylindrical portion coupled to a second conical portion.

Abstract: Aerodynamically designed and improved auxiliary blade attachment that wedge firmly onto the trailing edges of the main blades of conventional ceiling fans. The highly functional shape and super lightweight one-piece construction of these easy-to-use auxiliary blades and their strategic placement on the main fan blades serve to heighten the angle of incidence and thus create an intensified dual air current laterally and downwardly in relation to the fan's central core. The result is a dynamic increase of cubic feet of propeller-cooled air per minute without electrically increasing the velocity of ceiling fan rotation.

Abstract: A flexbeam for rotor blades of a helicopter comprises a flapping flexible structure forming a mast mounting and flapping part, a flexible structure forming a feathering and lead-lag motion part coupled with the flapping flexible structure, and a rotor blade mounting part located at the free end of the flexible structure and adapted to be coupled with a rotor blade. The feathering and lead-lag motion part comprises an elongated central member made of a composite fiber material, and a pair of elongated frame members disposed along the longitudinal sides of the central member. The frame members are each made of loops of unidirectional composite fiber material and has a Y-shaped cross section. The feathering and lead-lag motion part is fabricated by integrally joining the central member and the frame members along the longitudinal sides of the latter. The Y-shaped cross section has a pair of parallel ribs extending away from the central member.

Abstract: A boltless blade retainer for preventing forward axial movement of the rotor blades in a turbo machine relative to the rotor disk comprises an annular extension or hook formed on each dovetail post on the web of the rotor disk, an impeller or blade retainer formed with a flange which is carried against the web and dovetail posts and a retaining ring interposed between the hooks of the dovetail posts and the flange of the impeller. The retaining ring secures the impeller in a fixed axial position relative to the dovetail posts and rotor disk, and is positioned to engage the rotor blades carried in the axial slots between adjacent dovetail posts to prevent their movement in a forward axial direction.