Abstract: Nozzle control apparatus for an axial flow air turbine having an inlet nozzle for air entering the turbine and an associated turbine inlet housing for channeling air flowing to the inlet nozzle for at least partially blocking air flow from the turbine inlet housing to the turbine inlet nozzle. The nozzle control apparatus uses an axially movable annular slider member that is biased to its open position by an annular spring and is moved axially by bleed air pressure exerted on a portion of the annular slider member.

Abstract: A marine propeller with increased performance in reverse has a hub and a multiplicity of blades extending radially outward. A portion of the trailing edges of some or all of the blades are modified to lessen interference between blades and increase the bite of those blades when operated in reverse.

Abstract: The invention relates to a fan wheel for a turbo charger. The fan wheel (1) is comprised of a base body with a central axis of rotation (5) wherein the base body is assembled of two cover discs (2, 3) positioned approximately congruently opposite one another, between whose end faces (12, 13) facing one another fan blades (6) are arranged. The fan blades (6) are formed as monolithic parts on at least one of the cover discs (2, 3) and have an axial contact surface (30) against which an oppositely positioned axial contact surface (31) of the other cover disc (2,3) rests. Fastening means are provided in the area of the contact surfaces (8, 9) for non-detachably connecting the cover discs (2, 3) to one another.

Abstract: The invention refers to a component defining a blade or a vane for a rotary machine having a rotor rotatable about an axis. The component includes an inner space forming a passage for a cooling fluid between first and second walls. First ribs project from the fist wall and extend essentially in parallel to each other to form fist channels for the fluid from a leading part of the inner space to a trailing part of the space. The first ribs extend in a first direction forming a first angle of inclination to the axis in the leading part and in a second direction forming a second angle of inclination to the axis in the trailing part. The first angle is greater than the second angle.

Abstract: A wind power unit, that uses the power of wind, is made as a support installed power-generating unit comprising at least one turbine with a nozzle apparatus mechanically connected to a generator, a central shell, an annular front shell having at least one input channel of the turbine that forms with the central shell an output channel of the turbine, and annular outside shell that forms with the central shell diffuser output channel. The power-generating unit is equipped with an additional annular shell forming with external surfaces of the front and central shells narrowing-expanding first intermediate channel connected in its intermediate part to turbine output channel, while, with the internal surface of the outside shell, a second intermediate channel connected long with the first intermediate channel is used to diffuse the output channel.

Abstract: Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle of which directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, or a duct, the fluid particles in the resonant chamber of the passive acoustic jet being replenished with low momentum flux particles drawn from the fluid flow in a direction normal to the surface, thereby to provide a net time averaged flow of increased momentum flux particles to defer, even eliminate, the onset of boundary layer separation in the diffuser or duct. The passive acoustic jet is used in the vicinity of fan blade tips to alleviate undesirable flow effects in the tip region, such as leakage.

Abstract: A pump (1) for pumping a slurry comprises a pump housing (2) defining a pumping chamber (5) with an impeller (6) located therein for pumping the slurry from an axial inlet port (7) to a radial outlet port (8). The impeller (6) is carried on a pump shaft (10) which is in turn rotatably carried in a shaft carrier sleeve (18) in a carrier housing (12) which also carries the pump housing (2). The shaft carrier sleeve (18) and the pump shaft (10) are axially adjustable in the direction of the arrows A and B for adjusting an axial clearance gap (25) between the impeller (6) and the pump housing (2). A shaft seal (9) for sealing the pumping chamber (5) comprises a packed gland seal (42) and a rotating sealing ring (38) and a stationary sealing ring (39). A lubricating fluid cavity (40) is located between the packed gland seal (42) and the rotating and stationary sealing rings (38,39) for lubricating axially facing rotating and stationary sealing surfaces (52,58).

Abstract: A turbine and method which employ kinetic and potential energy of a fluid to obtain mechanical and/or electric energy, is founded on the use of bulb shaped rotating blades that interact with a fluid, such as water or air, Each rotating blade rotates around its own axis and in the radial direction of the fluid itself.

Abstract: A gas turbine engine (10) has a compressor (14) which includes a rotary stage (16) supported for rotation by a plurality of wire wound stators (34). When the stators (34) are electrically energised, they exert Maxwell type magnetic forces on a magnetically permeable ring (18) joining the tips of compressor blades (21) in the stage (16), and lift it into a position in space where it can rotate on a common axis with the turbine of the engine (10).

Abstract: A tip clearance control device for a gas turbine engine having a shroud surrounding a stage of rotor blades. The tip clearance control device comprises a one-piece split ring having opposed overlapping end portions. The split ring is directly supported onto the inner surface of the shroud and is adapted to automatically adjust for thermal growth of the shroud during engine operation.

Abstract: Turbine nozzles and turbine moving blades of an axial-flow turbine are provided which are capable of reducing a secondary flow loss with a simple structure. A nozzle blade passage formed by nozzle blades, an outer diaphragm ring and an inner diaphragm ring is structured in such a manner that the shapes of inner and outer walls of the nozzle blades are made to be irregular so that stepped portions (h1 at the root and h2 at the tip) each having curvature R are formed. The nozzle blades are formed in such a manner that ends (Zr, Zp and Zt) of an trailing edge of the nozzle blades are positioned at the most downstream position at the central portion of the nozzle blades. Moreover, relationships Zt<Zr<Zp are satisfied. Similarly to the nozzle blade passage, the moving blades are formed in such a manner that stepped portions h3 and h4 each having curvature R are formed in the moving blade passage.

Abstract: A fan blade includes a metal airfoil having a pocket disposed in a first side thereof, with the pocket including a filler bonded thereto. The pocket includes a plurality of cells separated by corresponding ribs which are submerged in the filler.

Abstract: A transfer function between the inlet air-flow consumed by a Gas Turbine engine, and the engine parameters of speed, pressure ratio, and Inlet Guide Vane (IGV) angle is described. An active compressor Operating Limit Line (OLL) management strategy that leverages this improved flow measurement transfer function is also described. The improved flow measurement capability afforded by the transfer function permits a deterioration in flow rate caused by compressor fouling to be detected. Using the deterioration in flow rate as a proxy for compressor fouling, a degraded surge boundary associated with fouling can be predicted, using a transfer function between degradation of air-flow along operating line and degradation of surge line. In combination, the inventive improvements in flow measurement and operating line management afford added compressor surge protection across the operating range, while permitting the attainment of elevated pressure ratios associated with high thermodynamic efficiency and output.

Abstract: A fan case for a turbofan engine having a fan including plurality of fan blades mounted to a rotor disk and a decoupler that fails in response to a predetermined load includes a substantially annular shell. The shell has a forward section, an intermediate section, and an aft section. The fan case further includes an aft facing step formed at the forward end of the intermediate section to prevent blade fragments from being ejected forward. The intermediate section is axially aligned with the fan and has a large inside diameter. The intermediate section thus defines an annular space around the fan blades that is sufficiently large to allow the fan to orbit when the decoupler fails. The intermediate section and the aft section are aligned radially to allow blade fragments to be ejected aft, avoiding additional secondary blade damage.

Abstract: An air circulating fan wherein the fan components are shipped disassembled. All of the fasteners used to assemble the fan components may be operated without tools, utilizing thumb screws and the like wherein the fan is capable of a “toolless” assembly. A hand operated fan mounting clamp includes a safety device to prevent loosening due to vibration.

Abstract: The invention concerns a blade profile for aircraft rotor, comprising, between a leading edge (1A) and a trailing edge (1B), a suction face (2) and a blade face (3) whereof the geometric locus of the equidistant points of the latter defines the curvature. The invention is characterised in that the value of the ratio of the maximum curvature to the maximum thickness develops linearly with the profile (1) relative thickness and ranges between 0.13 and 0.19 for a relative thickness of 7% of the chord (C) and ranges between 0.18 and 0.24 for a relative thickness of 15% of the chord (C).

Abstract: Composite rotor blades are constructed from a honeycombed polymer interior core structure having a bonded glass skin covering associated with the top and bottom surfaces thereof. Over time, environmental conditions lead to cracks or fissures in the glass skin coverings allowing moisture to accumulate in the interior honeycomb core of the blade. The present apparatus and method removes this accumulated moisture from composite rotor blades as well as from other objects constructed of polymer composite materials in general and includes an atmospherically sealed container of sufficient size to house the rotor blades or other objects within the container. The apparatus includes support fixturing for holding the rotor blades or other objects suspended within the container, a dehumidifier to reduce the moisture level of the air cycled through the container, a heater to control the temperature within the container, and a vacuum mechanism for controlling the pressure inside the container.

Abstract: A wiring system for an electrothermal propeller deicer for both left and right hand rotating propellers, where the deicer has leads extending therefrom and terminating in a connector which mates with a connector connecting leads from the power supply. The mated connectors are secured in a support bracket attached to the propeller blade hub using an adjustable, flexible, self connecting strap which can be removed without removing the support bracket during deicer replacement.

Abstract: Increased impact resistance capability is achieved in a cost and weight efficient manner by providing a spinner made of a 3-D orthogonal woven composite material. The spinner defines a generally conical shell having a plurality of axial rib stiffeners and at least one circumferential rib stiffener integrally formed thereon. The combination of the integral rib stiffeners with the 3-D orthogonal woven composite material results in a substantially greater torsional stiffness. The use of the 3-D orthogonal woven composite material also eliminates delamination found in laminated composite spinners.

Abstract: Efficiency of a boat propeller is increased by curved flanges extending along the tips of the propeller blades. The flanges form projections at the blade tips which deflect water that flows radially towards the tips outward into the thrust producing water flow through the propeller. The flanges have arcuate outer surfaces that face away from the propeller hub and which have a center of curvature at the axis of rotation of the propeller. Arcuate inner surfaces of the flanges have centers of curvature which are offset from the axis of rotation. This flange configuration inhibits cavitation in the region of the flanges and also at the hub region of the propeller.