Abstract: The invention concerns a radial fan (1), especially as a fan for the cooling unit (2) of a vehicle. The fan includes an impeller (3) with radial blades (4), a cover disc (5) designed nozzle-like, and an air guide ring (6), as well as a stationary inflow nozzle (8). An axial air gap (10) is provided between the cover disc (5) and the co-rotating air guide ring (6).

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 blade assembly, which may have blisk for a gas turbine engine, includes an annular rim disposed about a rotor axis and a blade assembly disposed around the rim. The blade assembly has circumferentially disposed and radially extending inner and outer rows of inner and outer airfoils, respectively and each airfoil has axially spaced apart leading and trailing airfoil edges. An annular shroud is disposed between and connecting the inner and outer rows of inner and outer airfoils and has axially spaced apart annular leading and trailing shroud edges corresponding to the leading and trailing airfoil edges, respectively. An axially extending cavity is provided in each of the leading and trailing shroud edges for reducing stresses in leading and trailing airfoil edges, respectively and the corresponding airfoil edges are located near the cavities. The cavities preferably extend axially under the corresponding airfoil edges.

Abstract: A fan assembly includes a circular first array of first fan blades; a first primary ring member supportively connecting inner extremities of the first blades about a fan axis, respective end extremities of at least a majority of the first blades defining inside and outside diameters of the array, the first blades being oriented for producing a primary axial fluid flow between the inside and outside diameters in response to rotation of the first ring member, the first ring member extending between the inside and outside diameters. A second primary ring member connects outer extremities of the first blades, the first blades in combination with the first ring member defining a generally circular opening about the fan axis.

Abstract: An apparatus for tensioning a subsurface float line and the like during doyment of the line and thereafter includes a capstan rotatably mounted and located in a liquid medium, the capstan having a bore extending from one end of the capstan to the other end, the bore including a plurality of pump blades for moving the liquid through the bore when the capstan is rotated, the capstan also including turbine blades located around the circumference of the capstan and adjacent both ends of the capstan, the capstan also including a circular surface interposed between the turbine blades for communicating with the line to be tensioned. The pump and turbine blades do work when the capstan is rotated thereby creating a counter rotational (drag) force that tensions the line during and after deployment.

Abstract: An axially compact axial flow fan with improved air-moving properties has a first array of fan blades that extend radially from a fan hub to a circumferential blade support member, a second array of fan blades extend from the first support member to a radially outward second circumferential blade support member. The fan blades in the second array each enjoy pitch angles that decrease from the second circumferential blade support radially along only a portion of each blade length. Thereafter, the pitch angles for the blades in the second array remains constant to the second circumferentially extending blade support member.

Abstract: An aerodynamically optimized mid-span snubber for combustion turbine blades provides sufficient stiffness to ameliorate vibratory stress but does so with minimal degradation of aerodynamic performance. The snubber has an optimized aerodynamic cross-sectional shape that forms when two snubber portions attached to adjacent rotor blades come into contact upon rotation of the rotor at an operational velocity.

Abstract: An array (32) of flow directing elements such as fan blades (20) for a turbine engine (10) is disclosed. Each blade in the array has a set of circumferentially shrouds (42, 44) whose contact edges (46, 48) abut each other during engine operation. A shroud angle .sigma. establishes the running chord angle .alpha. of the airfoil (30) portion of the array. Slight differences in the shroud angles of adjacent blades cause corresponding differences in the running chord angles so that the array is detuned and airfoil flutter is precluded.

Abstract: A blisk includes a disk and a plurality of inner airfoils extending radially outwardly therefrom, with each of the inner airfoils having an integral shroud support at a radially outer end thereof. A plurality of outer airfoils extend radially outwardly from respective ones of the shroud supports, and a plurality of discrete shroud segments are disposed respectively between adjacent ones of the shroud supports to collectively form an annular shroud for radially separating flow between the inner and outer airfoils. Each of the shroud segments is removably joined to only one of the adjacent shroud supports to improve manufacturing access, to allow replacability, and to allow differential movement and friction damping during operation.

Abstract: The total number (M) of plural blades of a blade apparatus is selected so as not to be a prime number and not to be a power multiplier of a prime number. Plural blades are divided into at least a first blade group in which one blade group has the blades of a first integer number (N.sub.1) and a second blade group in which one blade group has blades of a second integer number (N.sub.2). Each of the first integer number (N.sub.1) and the second integer number (N.sub.2) have no common divisor except 1. The total number (M) of plural blades is the product of the first integer number (N.sub.1) and the second integer number (N.sub.2). The blades of the first integer number (N.sub.1) blade group are connected by a first stage connecting member and the blades of the second integer number (N.sub.2) blade group are connected by a second stage connecting member.

Abstract: A compressor or fan blade (112) for a gas turbine engine includes a suction surface midspan shroud (122) which is cambered so that the shroud trailing edge (132) is substantially aligned with the direction of the air flow in the vicinity of the shroud trailing edge (132). The cambered portion originates at the chordwise location where a shock wave (60) attached to the leading edge of the neighboring blade crosses the shroud (136). The cambered portion gradually transitions to an uncambered profile at a circumferential location intermediate the suction surface (110) of the blade (112) and the pressure surface shroud of the neighboring blade.

Abstract: A next-to-the-last stage steam turbine bucket has a profile according to the table set forth in the specification. The buckets also include continuous couplings at the bucket mid-point including nubs on each bucket projecting from opposite sides thereof in generally circumferentially extending directions. A sleeve is disposed between each pair of adjacent buckets and has open opposite ends for receiving the nubs of the adjacent buckets. The cross-sections of the nubs and open ends of the sleeve are generally complementary and non-circular to prevent sleeve rotation during turbine operation. The buckets have a continuous cover including cover elements having tenons projecting from opposite sides for reception in corresponding openings in the tips of adjacent buckets.

Abstract: A circular foil connectable to a source of power for producing thrust in an axial direction when rotated, includes a flat circular plate and a plurality of closely spaced-apart fins fixed to an upper face of the circular plate, which occupy substantially the entire peripheral portion of the plate. A cylindrical hoop is fixed to the plate adjacent to radially inwardly extending edges of the fins to prevent fluid disposed adjacent to the circular plate and radially inwardly of the fins, from flowing radially outwardly and into the space between the fins as the circular foil is rotated. The foil is rotated at a sufficient speed to discharge fluid molecules from spaces between the fins at a rate faster than they can be replenished. This creates an imbalance of fluid pressure on the first side of the foil relative to an opposite second side thereof. As a result, the circular foil moves in the direction of the deficit.

Abstract: An improved method of adaptive machining is disclosed which affords automatic blending between a machined surface and a complex variable contour forged surface. An adaptive postprocessor generates an adaptive NC part program from a conventional APT file which has the capability to modify the cutter tool path in real time during the machining cycle based on limited surface measurement data. Variable measurement data taken from each workpiece generates a unique toolpath adapted specifically to the contour of that workpiece being processed, obviating the subsequent need for time consuming manual grinding and smoothing operations between machined and forged surfaces.

Abstract: A new lightweight bladed rotor for gas turbine or turbojet engines combines an inner support ring with blade straps made of fiber reinforced material. The blade straps wrap halfway around the inner support ring so that their ends extend radially outwardly to form blade pairs. A rim connects the blade straps near their ends to provide rigidity and to define a flowpath.

Abstract: A last-stage steam turbine bucket having a profile according to Charts II-XIII, XV-XXVII and XXIX of Table I.

Abstract: Turbine blades are held in groups formed by a series of spaced lugs constituting a lashing structure. Selected lugs have gaps which are "Z"-shaped, the gaps tending to close during untwisting of the blades when the blades are subjected to high centrifugal forces.

Abstract: A component is provided with a relative undersize in an area to be subjected to increased stress, for instance, through temperature. The component is made of a hardenable steel. The undersize is overlaid with a non-hardenable steel thereby to provide the full size. A second layer on top of the first layer can be provided. When the second layer is metallurgically bonded in a manner that generates heat, it does not cause a heat affected zone in the base hardenable steel. Blades for steam turbines benefit from this procedure.

Abstract: A hydraulic/pneumatic turbine transmission (10) for converting a pressurized fluid source (26) to rotary motion of variable torque and rpm is disclosed. Turbine transmission (10) generally has housing (12) including main body housing (12a) and front housing cover plate (12b). An output shaft (11) is rotatably secured within housing (12) and has a main turbine runner (16) radially attached thereto. Main turbine runner (16) includes a plurality of concentrically disposed subrunners of progressively smaller diameter. A pair of diametrically disposed variable position nozzles are provided and disposed within housing (12) to selectively supply pressurized fluid to any one of the plurality of subrunners. A plurality of arcuate scavenge ports (33) are provided within housing (12) to allow a pressurized fluid to exit subsequent to impact on main turbine runner (16). Variable position nozzles (23) can be independently controlled to produce 2x-1 output speeds, where x is equal to the number or subrunners.

Abstract: Disclosed is a vibration damped gas turbine engine airfoil row. The airfoil row, comprising first and second coaxial, circular spools and airfoils extending radially therebetween, is cast in at least one piece and then the second or inner spool is cut between adjacent airfoils. Damping inserts are held in place adjacent the inner surface of the second spool by a retaining means.

Abstract: An axial flow compressor for a bypass type jet engine has a low pressure stage which includes a one-piece, annular hoop shroud mounted to the airfoil of each of the rotor blades in the low pressure stage to divide the airflow entering the compressor into an outer, bypass airflow path and an inner airflow path directed to the higher pressure stages of the compressor. The hoop shroud is formed of circumferentially wound, parallel fibers such as silicone carbide fibers embedded in a metal matrix material such as titanium, wherein the volume ratio of the hoop shroud is approximately one-third fibers and two-thirds metal matrix material.

Abstract: A jet propulsion engine submergible in water for driving a water craft wherein a drive shaft is connected to an internal combustion engine for rotation thereof. A first turbine is mounted on the drive shaft for rotation therewith for providing a first high velocity stream of water axially through the propulsion engine. A propeller is journalled on the drive shaft adjacent to and downstream of the first turbine for rotation independently of the drive shaft. A second turbine is mounted on the drive shaft adjacent to and downstream of the propeller for rotation therewith for generating a second high velocity stream of water axially through the propulsion engine. The speed of the propulsion engine increases through the effects of the first and second high velocity streams of water for driving the water craft while the propeller becomes less effective until it is rendered free wheeling at cruising speeds of the water craft.

Abstract: An air turbine including a plurality of elongated rotor blades extending from a hub, first and second airfoils interconnecting the blades, and a vane element positioned between the airfoils, said airfoils and vane element being concentrically disposed about the hub.

Abstract: The present invention relates to a heat exchange machine for removing the excess of the heat during the summer period and the excess of humidity during the cold period. The machine comprises two tubes, one inside the other, an intermediate frame with two sets of blades attached to the frame from inside and outside thereof and driven by a common reversible motor in the same direction. One of these sets is the set of blades rigidly fixed to and the other one is swingingly mounted in the frame, so that the change of the direction of the fixed set of blades induces the change of the direction of the air flow in one of the tubes, meanwhile the direction of the air flow along the other tube induced by the other set of swingable blades remains the same regardless of the direction of rotation of this set.

Abstract: A power turbine (12) comprises alternate annular arrays of contra-rotatable turbine blades. Two arrays of turbine blades (30) and (47) have annular arrays of aerofoil propulsion blades (17,18) respectively attached thereto. Alternate arrays of turbine blades are attached to a primary drum member (55) in such a manner that below normal operating temperatures, limited relative radial movement is permitted between them. However when the normal operating temperature is reached, the relative radial movement is inhibited in such a manner that the rigidity of the power turbine (12) enhanced.

Abstract: A power turbine suitable for a gas turbine engine which a blade of one array of turbine blades has a fan propulsion blade attached to its radially outer extent. A drum member is further provided which carries at least one further annular array of turbine blades and is coaxially interposed between the arrays of turbine blades and fan propulsion blades to rotate with the same in operation. Aperatures are defined through the drum member to accommodate the attachment structure provided between the turbine blade and the fan propulsion blades such that relative radial movement is permitted between the turbine blade and the drum.

Abstract: An open-vane regenerative impeller for a fuel pump. The impeller has a ring-like body portion from which a plurality of open-vane impeller vanes extend radially out and a plurality of fan blades extend radially in. The impeller is disposed in a closed cavity between two pump bodies with the vanes in an annular pumping chamber and the fan blades in a cylindrical vapor collection chamber radially inboard of the pumping chamber. The fan blades operate to blow vapor out of the vapor collection chamber through a vapor discharge slot in one of the pump bodies when rotation of the impeller commences thereby to enhance the initial vacuum at the inlet port to the pumping chamber.

Abstract: A heat exchanger is disclosed having a coil positioned between an outer casing member with a bottom having a sump formed therein and an inner casing member containing a rotatable shaft to which a fan is mounted. The fan has a first stage or set of blades which pushes air from the outside down over the coils and a second stage or set of blades having a pitch opposite the first set for pulling the air up through the inner casing member to exhaust. A distributor having a pump which operates on centrifugal force is also provided which draws a liquid heat transfer medium preferably water from the sump and rotates with the fan blades to effectively "sling" the medium over the coils as the fan rotates.

Abstract: Hub flexures affording beamwise flapping (i.e. flapping perpendicular to the original tip-path plane), mount aircraft propellers through a hub assembly to a drive shaft of a fixed wing aircraft for increasing propulsive efficiency. The hub flexures permit the propeller blades of the fixed wing aircraft to exhibit advantageous beamwise flapping and reach equilibrium positions in response to loading conditions which would otherwise result in efficiency loss. The flexures permit only flapping perpendicular to the original tip-path plane and provide blade rigidity in radial, in-plane and torsional loading. The propeller blades may also be of the variable pitch variety wherein the flexures are advantageously inboard of the blade pitch change bearings. The flexures further facilitate both passive, or responsive flapping in response to actively induced cylic pitch to achieve maximum propulsive efficiency under any given loading conditions.

Abstract: A propeller for controlling the discharge of gases and cooling water exhausting from the central hub of an outboard motor unit comprising a cylindrical shroud surrounding the propeller hub to confine the exhaust to the inner most part of the blades and discharge it downstream of the propeller when operating the unit in the forward or reverse mode. Several attachments to this shroud which enhance the discharge performance of the propeller are disclosed. An alternate embodiment comprises a shroud which may be attached to a conventional through-hub marine propulsion device to channel the exhaust away from the propeller area.

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: Windmill apparatus comprises an open framework defining a wheel having means defining a pivot axis and embodying a plurality of radially and closely spaced concentric rows of air foils. The foils in each row are connected for their conjoint movement to and from a pre-set operating position, within defined limits. The movement of each foil is about an axis which is substantially radial to the wheel and it is arranged to automatically feather when subject to impact of winds the speed of which is at a dangerous level. As oriented in the wheel the radial extremities of each foil are substantially flat and bridged by a continuous peripheral surface portion. One portion of said peripheral surface portion is flatted to define the operating face of the foil. The flatted portion is preferably comprised of two planar surface portions one of which leads the other, having regard for the facing of the foil operating surface into the prevailing wind.

Abstract: In a turbine for a compressible fluid in which the fluid flow leaving the tepenultimate stage is separated into two coaxial flows, the inner flow passes through both the penultimate and the final stages of the turbine while the outer flow passes through the final stage only. This high efficiency arrangement for the last stages of a high power turbine exploits the advantages made available by using titanium as the blade material.

Abstract: An improved fluid driven turbine blade system is provided, which is self-governing at relatively high fluid velocities. This is achieved by a combination of two sets of turbine blades, one having a positive efficiency, and the other having a negative efficiency at the fluid velocity at which the self-governing effect occurs. Also provided is a variable friction drive apparatus for powering an energy conversion device. The combination of the improved turbine blade system and the variable friction drive comprises a windmill for driving an electric generator, the windmill having a low required start-up torque at low wind speeds and being self-governing so as not to overspeed the generator at high speeds.

Abstract: A turbine rotor comprising radially extending blades having inner and outer ends and an axially symmetrical annular shroud having upstream and downstream ends affixed to the blades adjacent the outer ends thereof and rotating with the blades. The annular shroud increases in diameter from its upstream end to its downstream end such that a passage formed thereby widens from its upstream intake opening towards it downstream outlet opening, with the annular shroud in radial section having a profile adapted to produce a lift force under onflow conditions and being oriented such that its suction side forms the interior surface of the annular shroud facing the passage and that its angle of attack relative to a direction extending parallel to the central axis of the annular passage is smaller than the critical (stalling) angle of the profile. A further annular shroud may be fixed to the inner ends of the blades.

Abstract: In an axial flow compressor including a rotor wheel having a plurality of rotating blades mounted thereon, said rotor being arranged to rotate about a central axis of the compressor, there is provided an aerodynamically profiled ring arranged concentrically to the compressor axis in front or upstream of the plurality of rotating blades in order to define between an outer surface of the profiled ring and an inner wall of the compressor casing an annular flow channel which converges in the direction of flow through the compressor. A plurality of stationary blades are located upstream of the profiled ring.

Abstract: An elongated cylindrical body is provided of a greater length than its diameter and including a cylindrical side wall. The body is open at its opposite ends and journaled for rotation about an axis generally coinciding with the center axis of the body. The body includes a plurality of circumferentially spaced longitudinally extending slots similarly slightly inclined relative to radial planes of the body passing through the slots. One set of corresponding edge portions of the cylindrical side wall defining corresponding longitudinal edges of the slots include integral outwardly projecting substantially rectangular vanes extending along the slots and the vanes comprise outwardly deflected integral positions of the cylindrical side wall of the body. Further, in a modified form of the invention, the other set of corresponding longitudinal edges of the slots include inwardly projecting substantially rectangular vanes extending along the slots.

Abstract: A wind turbine rotor in which the hub supports several bases spaced from each other around the hub, with all said bases mounted for turning movement about axes radial to the axis of the rotor, and with each base supporting a plurality of thin elongated vanes, each being airfoil shape in section with the several vanes on each base having the chords of their airfoils substantially parallel to one another. The vanes are mounted on the base in spaced relation to one another and substantially radial to the axis of the rotor and are interconnected at or near their outer ends.

Abstract: A quick response gasifier spool for an automotive gas turbine engine has a shaft with a turbine wheel connected on one end thereof with a row of turbine blades driven by motive fluid from an engine combustor and further has a low inertia centrifugal compressor impeller with a low mass hub secured to the opposite end of the shaft. The impeller has a plurality of separate, free formed blades each having a root segment integrally formed with the hub; the blades including spaced apart radial tip portions joined by a continuous ring of span splitter elements located on the radial extent of each of the blades to prevent flutter between adjacent free blade radial tips and wherein each element of the continuous ring includes a leading edge and a trailing edge joined by a curved segment located along a flow streamline path between each of the individual blades.

Abstract: A turbomachine rotor wheel comprising a disk mounting a lower row of blades, and dividing platforms mounting an upper row of blades. Each blade in the lower row comprises at least two members, whereby the section of the blade normal to the blade axis includes at least two parts spaced a distance equal to the width of the blade passage. Therewith, at least two parts of the blade section are attached to the dividing platform thereof.

Abstract: A self-supporting, self-locating seal having a central portion and a pair of end segments so designed as to fit within the mid span joint formed between adjacent turbine engine blades. Because of the design of the seal, the seal is held securely in position simply by its geometry and the centrifugal forces applied thereto during turbine engine operation.

Abstract: A gas turbine disk design having a sideplate construction which prevents the leakage of hot gas across the turbine disk is disclosed. The sideplates are segmented and facilitate cooling of the turbine blades. Slidably mounted studs hold the sideplates in surface contact with the disk and prevent the buildup of stress concentrations in either the plates or the attaching members.