Abstract: A quiet compact radiator cooling fan having a hub portion, which extends radially outwardly and axially from its inlet to its outlet end, a shroud portion, which extends radially inwardly and axially adjacent the inlet end and radially outwardly and axially adjacent its outlet end forming a converging annular opening and a plurality of airfoil shaped, forward sweep blades disposed between the hub and shroud which cooperate with the hub and shroud to produce a mixed flow radiator fan which has improved blade loading and aeroacoustic performance producing a quiet and efficient cooling fan for off the road vehicles.

Abstract: A ring bracket-shroud mounting assembly for an car engine cooling system includes a bracket for enclosing and supporting fan blades and motor, and a shroud with a mounting seat for supporting the bracket. The bracket has at least one active lock coupler, and a shroud has at least one passive lock coupler. Each active lock coupler includes an overhanging means and each passive lock coupler includes a catch. The overhanging apparatus and catch are adapted to matingly engage and retain the ring bracket to the shroud when the overhanging apparatus and catch are placed adjacent to each other and the ring bracket is rotated relative to the shroud to a locking position to have the overhanging apparatus combined with the catch.

Abstract: A turbine 400 has a central duct 410 which accelerates fluid passing through it and a blade configuration which retards the flow of fluid near the tips of the turbine. This structure results in a vortex having a higher fluid pressure behind the tips of the turbine blades 408 and a lower fluid pressure behind the duct. In the present invention, this vortex is enhanced by (1) an increased acceleration of the fluid passing through the duct 410 and a deceleration of the fluid passing through the blades 408; and/or (2) by a fluid redirection device 850 for directing the fluid passing through the duct towards the outer diameter of the turbine.

Abstract: A centrifugal fan including a fan hub lying generally in a plane normal to the axis of fan rotation and having a central opening for receiving a motor housing, and a plurality of fan blades of substantially identical construction spaced circumferentially evenly around the fan hub and extending away from the fan hub in a direction parallel to the axis of fan rotation. Each fan blade includes a leading edge at its innermost radial periphery, and the leading edge, at least at the axially upper one-half section thereof, is convexly curved in the shape of a quarter ellipse having a major axis, Mg, substantially parallel to the axis of fan rotation and a minor axis, mh, normal to the major axis Mg. The fan also includes a continuous shroud joined to each fan blade at an axially upper section of the radially outer portion thereof and the shroud is concave in cross-section.

Abstract: A radial fan wheel comprising a number of fan blades symmetrically arranged with substantially equal spacing around the rotational shaft of the fan wheel. The blades are mounted between two end plates that are arranged perpendicularly to the shaft and are provided with blade surfaces which are substantially parallel to the shaft and each of which blade extends from one point at a distance from the shaft and substantially arched in the direction outwardly towards the periphery of the wheel. One first end plate is provided with a central air inlet and is shaped with a curve that, in a position radially outwardly from the innermost edges of the blades, substantially arches towards the second end plate and further radially outwardly towards the peripheral edges of the blades. Each blade is so designed in the peripheral segment that the blade extends radially longer outwardly adjacent the first end plate than the second end plate.

Abstract: The invention relates to an impeller of a rotary pump having an annular upper part defining a central inlet opening, a drive-adjacent disk-shaped lower part, and a plurality of blades secured between the upper and lower parts. The upper and lower parts are separate parts which secure together. Each blade is integrally formed with either the upper part or the lower part. Every other blade is formed with the upper part, and the remaining blades are formed with the lower part. Each blade has a free edge, remote from a base thereof, which has a projection which extends into a recess or opening formed in the part to which it is not integrally molded. After the upper and lower parts are assembled together, free spaces around the projections are filled with injected plastic, thereby securing the upper and lower parts together and securing the free ends of the blades.

Abstract: A fan includes a hub coupled to a driving shaft of a motor, a plurality of blades installed on the outer circumferential surface of the hub to be spaced from each other at a predetermined interval, and a band connecting free ends of the blades. An axial direction width (W1) between a leading edge and a trailing edge at the free end of each of the blades is greater than a width (W2) of the band.

Abstract: The object of the invention is to prevent the quantity of airflow by a fan from decreasing in dependence on the distance between the fan and obstacles such as an engine in a device for introducing and discharging cooling air having a shroud with a high covering rate. In the device for introducing and discharging cooling air having the shroud with the high covering rate, an airflow direction changing member is provided downstream of the fan, and each fixed blade of the member has a shift angle in the radial direction and an attack angle in a rotation direction of the fan, so that the air tends to be discharged outward in the radial direction.

Abstract: A fan module with an axial flow fan and a shroud member. The axial flow fan has a hub and a plurality of fan blades, each blade extending radially from the hub. At the tips of the blades are air guide members secured to respective fan blades and concentric with the hub. Each air guide member has an axially-extending arcuate portion, and a respective lip portion extending radially outwardly from each said arcuate portion. The axially-extending portion has an axial length substantially equal to or less than the axial length of said hub. The shroud member has a surface cooperating with the air guide members in an arrangement to reduce tip vortices.

Abstract: An axial flow fan has a hub with a longitudinal axis of rotation and an outer periphery for the hub. Several blades are secured at their root regions to the hub's outer periphery. Each of the blades has a medial line that is tangential to a respective hub radius at the hub's outer periphery.

Abstract: A turbine blade (18) for a gas turbine engine includes a machining datum (60) that extends radially from a pocket (54) in the outer shroud (36) of the blade. The datum is spaced from a sidewall (64) of the pocket so that the datum is peripherally continuous irrespective of whether the blade is in a prefinished state or in a completely finished state. Because the datum's peripheral continuity survives the original manufacturing process, the datum is available for use in post-manufacturing inspection and repair operations.

Abstract: A high efficiency axial flow fan includes a hub, fan blades and a circular band. The hub rotates about a rotational axis when torque is applied from a shaft rotatably driven by a power source. The circular band is concentric with the hub, connected to the tip of each blade, and is spaced radially outward from the hub. The blades are configured to produce an airflow when rotated about the rotational axis. Each blade has a chord length distribution, stagger angle and dihedral distribution which varies along the length of the blade. The dihedral distance of each blade varies as a function of blade radius from the rotational axis.

Abstract: A method for dynamically balancing a centrifugal blower fan wheel is disclosed. The method includes the steps of determining an amount and location of change in the fan inlet ring of the blower wheel which is required to balance the blower wheel. Once this determination is made, the radial thickness of the inlet ring is increased at a predetermined location to provide the proper amount of balance to the blower wheel. A mold is described for accomplishing this method.

Abstract: An inline fan wheel is disposed within a conduit for accelerating a flow in the conduit. The fan wheel has a backplate assembly. The backplate assembly has a backplate, presenting a substantially circular outer margin, and has a centrally disposed hub that is operably coupled to the backplate. The hub has a central bore defined therein. The bore is for sliding engagement with the axial shaft. A plurality of fan blades are radially equiangularly disposed with respect to the hub and are fixedly coupled to the backplate of the backplate assembly. Each of the plurality of fan blades has a generally rectangular planform and presents a leading edge, an opposed trailing edge and first and second side margins extending between the leading edge and the opposed trailing edge, the leading edge of each of the plurality of fan blades defining an acute included angle with the longitudinal axis of the conduit. A shroud defines a flow inlet that is operably coupled to and supported by the plurality of fan blades.

Abstract: A gas turbine rotor blade includes a shroud which is cooled effectively with cooling gas used for cooling the blade profile so that the temperature of the shroud is reduced and the life of the gas turbine rotor blade is extended. A two-step groove is engraved in the shroud along the tip of the blade profile and the upper portion of the two-step groove is plugged. Second cooling holes are bored along the direction of the plane of the shroud so as to be connected to and communicate with the first cooling holes which are bored in the blade profile in a direction along the longitudinal axis of the blade for passing cooling gas through the blade. Consequently, most of the cooling gas, after cooling the blade profile, can be used for cooling the shroud, so that the shroud is cooled effectively and the temperature thereof is prevented from rising. Preventing the temperature from rising can also prevent reduction of the creep resistance of the shroud and prevent the blade root on the shroud from being turned up.

Abstract: A cast and hot isostatically pressed gamma titanium aluminide turbine blade has an aerofoil portion including a concave pressure surface and a convex suction surface. The concave pressure surface has surface irregularities, produced by the action of the hot isostatic pressing process on voids located within the cast turbine blade, located in that region of the concave pressure surface where in operation aerodynamic separation occurs to minimise the aerodynamic effects of the surface irregularities upon the operation of the turbine blade. The remaining portion of the concave pressure surface and the whole of the convex suction surface are substantially free of surface irregularities.

Abstract: A shroud segment for a gas turbine engine includes a hook having an undercut surface. Various construction details are developed that provide a segment having a hook with minimized bending stress. In a particular embodiment, a shroud segment includes a plurality of hooks spaced along the leading and trailing edges of the shroud segment. Each of the plurality of hooks includes a positioning surface, a support surface and an undercut surface therebetween. The positioning surface defines the limits of axial movement of the shroud segment. The support surface reacts the radial loading on the shroud segment during operation of the gas turbine engine. The undercut surface is offset from the stator assembly to define the maximum length of the support surface.

Abstract: A cowl comprising, inter alia, a stationary part formed by a diffuser (10) which exhibits a fastening base (11), a nozzle-funnel (12), a connection zone (13), a cylindrical skirt (14), and a moving part (20) able to rotate about an axis (200), which moving part (21) exhibits a peripheral profiled annular hoop (20) which is intended to be rigidly connected to the blade (22) tips (221) of a helix and which is mounted coaxially in this skirt (14) so as to be able to rotate therein, is characterised in that, taking as references the direction of flow and the axis (200), this hoop (21) is delimited by an inner wall (2101), an outer wall (2102) and a rear section (2103), this connection zone (13) is delimited in particular by an inner surface (131) with an upstream limit (1310), and in that this rear section (2103) of the hoop (21) is situated in a plane (P) which is perpendicular to the axis (200) and which passes practically through the upstream limit (1310) of the inner surface (131) of the connection zone (13).

Abstract: A last-stage steam turbine bucket having a profile according to Charts I-XXXXI of Table I.The bucket is divided into a number of profile sections each of which is a predetermined radial distance from the root section. Each point on a profile section at the predetermined radial distance from the root is defined by an X-Y coordinate and a radius R along the arc of a circle connecting adjacent points.

Abstract: A low noise axial flow fan (10/110) having a plurality of identical blades (13/113) extending from a central hub (11/111). In a preferred embodiment, each blade is highly skewed, having a backward (with respect to fan rotation direction) skew in the root portion (15/115) of the blade nearest the hub, changing to a highly forward skew in the portion (16/116) of the blade near the tip. The fan may be shrouded or unshrouded. In the shrouded embodiment, the fan (110) is used in conjuncton with an inlet orifice structure (131). Each blade of the fan has a chord length (Ch) that increases from root (17/117) to tip (18/118), a pitch angle (.GAMMA.) that decreases from roto to tip and a camber angle (Ca) that decreases from root to tip. In the shrouded embodiment (110), both the contour of the inlet portion (126) of the shroud and the contour of the inlet portion (132) of the orifice structure are quarter sections of ellipses.

Abstract: A tip seal arrangement is provided for steam and gas turbines that allows the tip seals to be mounted on shrouds in such a way as to be easily replaceable while ensuring a minimum of contact between tenons and particles carried by leaking turbine fluid.The invention is practiced by multiple segments that clip to the shrouds so as to provide a full circle with a stand-up radial seal that projects outwardly from the shroud to provide a small clearance with the stationary diaphragm or casing that surrounds the rotating blades with the individual segments being relatively easy to remove and replace.

Abstract: A rotor includes a disc having a plurality of blades extending therefrom. The blades include tip shrouds, each having first and second axial ends, and first and second circumferential faces. The first and second faces of adjacent tip shrouds are spaced from each other to define gaps therebetween. The first and second ends each include U-shaped slots, each having an arcuate damper wire disposed therein. The slots are aligned generally parallel to an axial centerline axis of the rotor for allowing ease of manufacture and assembly while providing effective frictional damping by the damper wires urged by centrifugal force against the slots.

Abstract: The present rotating fan and shroud assembly reduces noise emitted therefrom and increases cooling system efficiency. The rotating fan and shroud assembly when combined with the labyrinth-type seal also improves serviceability and reduces maintenance time and cost. The positioning a the first end of an inlet bell-mouth portion of the shroud assembly between a pair of flexible members allows the assembly to be easily removed for servicing while preventing recirculation of the cooling air. A radially outward extension of the inlet bell-mouth portion, and the positioning of a second end of the inlet bell-mouth portion and its juncture with an intermediate portion in line with a leading edge of each of a plurality of blades provides a uniform contour for the flow of the cooling air as it enters into the plurality of blades.

Abstract: A turbine has a rotor which is a disc with blades projecting axially from its face working with stator blades on a disc like stator. Such discs and blades can be cast integrally and if necessary machined flat for good sealing. A plurality of interdigitated stator and rotor discs can be assembled. The rotor can be made of sintered or refractory material and bonded by a hoop of high tensile material to take centrifugal forces enabling low tensile strength material to be used for rotor parts.

Abstract: A blade for a fan or blower which has an abrupt transition region between an inner blade region which has a negative leading edge sweep angle, and an outer blade region which is highly forwardly swept. The outer blade region is further characterized by a blade chord that increases with increasing radius. The fan provides a low pitch width and superior noise and efficiency trade-offs.

Abstract: A compressor impeller has a ring-shaped shroud band which is mounted at blade tips, each blade tip being enclosed in an identical radially slidable manner by a guide block, and the guide blocks being fastened to the shroud band. As a result, a narrow sealing gap and thus lower aerodynamic losses can be implemented than in conventional compressors, and the different centrifugally and thermally induced expansions of the blade and of the shroud band can be compensated.

Abstract: An axial flow ring fan has improved efficiency and reduced noise by making the leading edge of each blade a generally sinusoidal shape and projecting this geometry throughout the blade by imparting fall off to each blade.

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: The shrouded turbine blade is provided with a wear resistant surface on the seals as well as along the abutment faces including the notched edges. The wear surfaces are characterized in being metallurgically bonded to the base material of the shroud without significant dilution by the base material. This is accomplished by using transparent plasma arc welding at a low amperage and a low temperature. The wear resistant surface can be of a material different from the base material of the shroud proper.

Abstract: An improvement in a pump including a shrouded inducer, the improvement comprising providing means for collecting recirculation flow about said inducer and directing it through a fluid permeable wall member to remove any tangential velocity components from the recirculation flow. The recirculation flow, free of tangential velocity components, is then reintroduced into the fluid to be pumped.

Abstract: Compact fan and shroud package for radiators with fan blades curved rearwardly to position rotating shroud at optimized distance from radiator for improved air flow through radiator.

Abstract: An annular beam 46 which is hollow and which extends circumferentially about an annular flow path 22, 24 for working medium gases is disclosed. The annular beam supports and positions both a shroud 42 and a fabric 44 for containing particles having axial and radial velocity. The annular beam has a first wall 48 and a second wall 50. The second wall is spaced radially from the first wall. A plurality of annular plates 52 extending circumferentially about the interior of the beam. The plates are attached to the first wall and to the second wall. In one detailed embodiment the annular plates have a C-shaped cross section formed of a circumferentially extending rib 58 and two axially oriented legs 60, 62. The radial height of the rib is many times greater than the radial height of the legs. A method of fabricating the annular beam is disclosed.

Abstract: A circumferentially banded fan that forces air through an adjacent heat exchanger and that has an air-guide housing positioned radially outside the band and extending downstream therefrom is disclosed. A plurality of elongated stationary members extend radially inwardly from the housing downstream from the fan blades, and the stationary members have a flow-control surface which removes the rotational component imparted to the airflow by the rotating fan blades. A tangent to the flow control surfaces at their radial center line forms an angle with the airflow exiting the blades which is substantially equal to the tangent-to-axis angle.

Abstract: A cooling fan to be located between an internal combustion engine and a radiator and rotatingly driven from a rotational shaft of the engine. The fan includes a plurality of blade elements radially projecting from a boss portion and a cylindrical ring formed at the outer ends of the blade elements coaxially with the boss portion. In each blade element, a base line, which is drawn through a base point located on a chord of blade between leading and trailing edges of the blade element at a distance of 40% from the leading edge in percentage to the length of the chord, describes a straight or moderately curved line from the inner to the outer end of the blade element, which is inclined rotationally forward of a radial line passing through the base point at the inner end of the blade element.

Abstract: A circumferentially extending structure 30 for containing particles having an axial component of velocity and a radial component of velocity is disclosed. The structure includes an inner casing 48 and an outer casing 50. The outer casing is formed of a plurality of layers of flexible fabric and includes layers having differing masses per unit length in the fabric. The layers of fabric extend about the inner casing. A means for applying a load to the fabric engages the fabric to place the fabric in tension. One such means is a plurality of bars 80, 82 and turnbuckles 74. In one embodiment, the fabric has a greater mass per unit length in the leading edge region and a greater tension is applied to the leading edge region than other regions of the fabric. A method of forming the structures is disclosed.

Abstract: A rotor for operation without the influence of flow-guiding stationary housings or channels in a flow medium contained in a space of unlimited dimensions, particularly for a wind power plant or a helicopter or an autogiro, comprising one set of rotor blades and a shroud arranged in the region of the periphery of the rotor and formed as an axially symmetrical outer annular shroud rotating in unison with the rotor. The outer annular shroud in cross-section lying in an imaginary plane extending through the rotor axis has a profile the angle of which is greater than its critical (stalling) angle of attack with respect to a flow direction extending parallel to the rotor axis. The profile is adapted to generate a lift force under the effective flow conditions given at rotation of the rotor within the operational rotational speed range, and is oriented such that its suction side forms the inner side of the annular shroud.

Abstract: A cooled rotor blade for a gas turbine has an aerofoil in which there are longitudinally extending cooling fluid passages. At the tip of the aerofoil is located a separate, chordwise extending tube. The tube has apertures in its wall which correspond with at least some of the cooling fluid passages, whereby the spent cooling fluid from these passages may pass through the tube to rejoin the gas flow of the engine.

Abstract: A vibration, damper, or snubber device is disposed on the radially outward surface of a shroud member mounted on a turbine rotor. The rotor has an annular array of twisted blades connected together to form blade groups by a first and a second shroud member. The vibration damper, or snubber, is mounted on the first shroud member and extends therefrom across a gap between the shroud members to circumferentially overlap a portion of the second shroud member. A predetermined axial gap is defined between a portion of the second shroud and the snubber. When an untwist motion is imposed upon the blades due to rotation of the rotor, the axial gap closes and an abutment between the snubber and the second shroud occurs to inhibit further untwist motion and to simultaneously provide a friction interface to inhibit circumferential motion between the second shroud and the vibration damper.