Abstract: A device for the reduction of secondary losses in the bladed flow duct of a turbomachine, wherein the device is arranged in the region of at least one of the two duct walls and, presently, intermediate two circumferentially adjacent blades, and is of the type in that the duct wall has a boundary layer step so that the face of the boundary layer step faces towards the pressure side of the blade.

Abstract: A high speed turbo disc mounting assembly for the reduction of turbo disc failure and the provision for disc migration radially at high speeds comprising a shaft, a bushing mounted on said shaft having an annular flange through which torque pin apertures are provided, and a turbo disc mounted on said bushing such that torque pins aligned in channels at the interface of the disc and bushing provide for rotational engagement of the disc to the bushing without restricting outward migration of the disc or imparting undue stress concentrations to the high dynamic stress level area of said disc.

Abstract: A rotor for turbo engines, for example for small gas turbines or turbo-superchargers (exhaust-driven superchargers). The rotor has at least two vane wheels, and a shaft with structural elements rigidly secured thereto. The rotor, with the vane wheels and the shaft, comprises a one-piece high-quality cast part. The rotor may be mechanically or otherwise suitably machined exclusively at sealing surfaces, bearing seats, threads, follower or synchronization toothing or gearing, and other structural elements of the shaft.

Abstract: The method produces an article which has a first zone comprising a nonoxide ceramic material (which materials cannot be soldered or welded) and a second zone comprising a different, softer material such as one which can be soldered or welded to other parts. A transition layer between the zones of the article comprises both materials for bonding the zones together. The method forms the article from powders with heat and pressure.

Abstract: A retainer for securing the compressor rotor (172) to the compressor-turbine shaft (160) of a turbocharger includes a retaining sleeve (180) having an aperture therethrough for mounting the sleeve onto the shaft adjacent the compressor rotor to prevent movement of the rotor on the shaft in the direction of the sleeve. The sleeve has an inner bore (180a) having a diameter forming an interference fit on the shaft such that the sleeve prevents movement of the compressor rotor on the shaft. In one embodiment, a lug (300) extends from the sleeve (180) and engages the compressor rotor to transmit a rotational force from the shaft to the rotor through the sleeve and lug.

Abstract: A wheel of a turbomachine is secured to a shaft of the machine by initially securing the wheel between one end of the shaft and a piston-like member. A space is formed between opposed sides of the member and wheel by moving the member relative to the wheel. A spacing member is placed in the space for placing a compressive force on the wheel for positively securing the wheel to the shaft.

Abstract: A wind power generating system is provided to generate power for the farm or ranch, state or county service buildings, and light industrial uses. The concept utilizes wind energy efficiently to convert power and can be rendered inoperative to avoid destruction by excessive wind flows.

Abstract: In the first embodiment, the invention comprises an imperforate turbine wheel having a hub of polygonal cross-section engageable with a hollow shaft of polygonal conformation, and a thrust collar and bolt for fastening the shaft and wheel together.

Abstract: A hybrid dual property radial turbine rotor for a gas turbine engine includes an airfoil shell having a plurality of radially outwardly directed airfoils thereon joined to a continuously circumferentially formed inner periphery including a constant diameter axially extending portion and a radially outwardly flared skirt portion thereon into which is fitted a preformed hub plug of dense stress resistant material having an axially extending nose portion thereon with a controlled constant circumference surface throughout its length of a precision dimensioned diameter and further including a conical end thereon with a surface thereon of a slope that is congruent with the slope of the flared skirt portion of the cast metal rotor shell and wherein the slope of the flared skirt portion is configured to optimize the location of the high strength hub material and to achieve optimum blade and hub stress levels.

Abstract: A face disc keyed to the shaft and keyed to a peripheral flange on a turbine blade disc eliminates stress concentration at the highly stressed juncture of the blade disc and shaft on fabricated turbine rotors.

Abstract: A lightweight, rotor assembly for a gas turbine engine having a critical speed characteristic well above the operating speed is disclosed. Various construction details which enhance the axial stiffness of the rotor assembly and which shield a portion of the disk from working medium gases are developed. The rotor assembly employs a frustoconical member to connect a shaft to the disk.

Abstract: A rotating speed detecting device of a turbocharger comprising the compressor wheel and the turbine wheel which are fixed onto the opposed ends of the rotary shaft. A hole is formed on the central portion of the shaft. An electromagnetic detector is arranged in the vicinity of the central portion of the shaft so that the detecting head of the detector can face the hole of the shaft.

Abstract: A machined-to-size superalloy turbine rotor disc for a gas turbine engine has its fatigue life increased by coating its fatigue-prone machined surfaces with an air-impervious protective layer of material which retains its integrity and adherence to the machined surfaces for a large number of mechanical and heat stress cycles.

Abstract: A compressor rotor wheel construction and a method of making same is provided which includes a blade portion of heat-resistant metallic material, a rotor disk portion made of a high-strength metallic material, and a steel spacer ring arrangement connecting the blade and rotor disk portions. The steel spacer rings are connected by explosion welding to the blade portion, are then finish machined, as is the rotor portion, and then the spacer rings are connected respectively to the rotor disk portion by brazing or welding.

Abstract: In a gas turbine rotor of disc-type construction with a tie rod braced at least at one location along the length thereof against compressor or turbine discs by ring-shaped intermediate members, the intermediate members includes substantially conically expansible turning rings having a wider diameter end engageable in a circular groove formed in a lateral surface of one of the discs, the turning rings having at the smaller diameter end thereof an inner peripheral surface with which they are braced on the tie rod.

Abstract: A rigid coupling between two rotating machines wherein one half of the coupling is provided with a boss which is inserted into a recess provided in the other coupling half. In order to center the boss in the recess, a centering ring is applied to the boss, the external surface of the ring which engages the wall of the recess having a conical configuration with a gradient of from 1:100 to 1:1000 which corresponds to a slope of from 1:200 to 1:2000 respectively. As an alternative, the centering ring can be applied to the wall of the recess, in which case the inner surface of the ring which engages the surface of the boss would be given a conical configuration.

Abstract: A cast metal turbine wheel is made comprising a cylindrical disc with equiaxed grains and integral blades with columnar grains oriented substantially parallel to the leading and trailing blade edges. The blades are solidified unidirectionally by withdrawing heat through chill means located adjacent the mold at the blade tips. Cooling is inhibited from other blade surfaces by retaining cast metal in mold portions located above and below the blades. The disc portion of the mold is insulated so that it cools slowly to promote grain nucleation throughout the metal therein and equiaxed grain growth.

Abstract: A coolable disk structure which is capable of extended use in the turbine section of a gas turbine engine is disclosed. Various construction details which improve the service life of the disk are developed. Techniques which provide positive control of the heating and cooling rates in turbine disks are incorporated in the structure to increase the low cycle fatigue life of the disk by optimizing the disk thermal profile.

Abstract: A wheel of a turbo-machine is secured to the shaft of the machine by forming a side of the wheel with an end cap affixed thereto. Compressive force generating means connected to the end cap generate a force for compressing the wheel between the end cap and shaft.

Abstract: A rotor driven for an axial flow gas turbine engine compressor is formed as a composite structure of inner and outer skins with a core therebetween and a set of tensile reinforcing rings each located in a respective groove of a corrugated outer surface of the drum. In the completed drum the drum body is preferably under compressive prestress while the reinforcing rings are under tensile prestress.

Abstract: An improved windage shield is provided for use with turbomachinery members partially defining an internal flow path wherein the members are connected by a fastener which protrudes beyond one of the members. The windage shield comprises a portion which is captured between the fastener and one of the members and a cylindrical section which extends downstream of the members to form a smooth cover for isolating the members from the internal fluid flow. The protruding fastener end is recessed into, and generally flush with, the captured portion of the windage shield.

Abstract: The rear radially extending component of a radial flow turbine or compressor rotor is centered on a cylindrical surface spaced from the common shaft, on which the rotor is wedged by a tapered sleeve, by an extension of one component fitting into a recess in the other, but this cylindrical surface is not required to transfer any torque, because that is transferred from the forwardly extending component to the radially extending component by ridges of one fitting into radial grooves of the other near the base of the vanes. Greater thermal expansion of the radially extending component is accommodated by the claw ridge slipping radially in its groove.

Abstract: A ceramic turbine rotor fitted to a metal shaft has an integral shaft stub, extending into the hollow end of the metal shaft, and is resiliently retained therein. In order to prevent relative rotation between the rotor and the shaft during torque transfer, the stub shaft and a clamping and tightening member, within the metal shaft, are provided with interengaging parts. The stub shaft, the clamping member and the hollow metal shaft may be formed with mating, interengaging corrugations and grooves running substantially axially. The stub shaft may alternatively have a polygonal cross section, and the clamping member and the void in the hollow shaft will then have mating, but successively bigger cross sections.

Abstract: A rotor blade stage for the compressor of a gas turbine engine comprising a rotor disc having a plurality of equally spaced apart rotor blades mounted on its periphery. The spaces between the rotor blades in the region of the periphery of the rotor disc are infilled with a mixture comprising reinforcing filaments enclosed in a matrix of a cured epoxy resin and filler material. Means are provided to retain the mixture in position between the rotor blades upon rotation of the rotor disc.

Abstract: A flow directing apparatus for use in an axial flow turbomachine is disclosed. Techniques for reducing aerodynamic drag along the walls of the flow directing apparatus are developed. In one embodiment, rotor blades have multiplanar platform surfaces which reduce aerodynamic drag pressure losses at the interface between each blade platform and the adjacent structure.

Abstract: The disclosure concerns a Francis-type hydraulic machine, i.e., a turbine, pump-turbine or pump, having a bladed wheel of large diameter, and in which bearing apparatus for supporting the rotor is arranged in a peripheral region of the bladed wheel spaced radially from the axis.

Abstract: A radial turbine wheel for a gas turbine which consists of two parts and more particularly of a first part adjoining the turbine inlet which includes the outer sections of the blades and of a second part leading to the turbine outlet which includes the inner essentially curved section of the blades whereby the two parts are made of materials having different properties.

Abstract: A rotor-shaft assembly comprising a ceramic turbine rotor, a metal shaft and a metal connector disposed between the rotor and the shaft. The metal connector is fixed to the rotor by some suitable means and coupled with the metal shaft by mutual engagement of teeth provided at the ends of the connector and the shaft.

Abstract: A design technique, method and apparatus for containing failure of the rotors of axial flow fluid machines. A rotor disk is constructed of at least three disk sections. Each disk section is shaped such that the loading on that section will be distributed in an optimum manner from the rim to the hub of the disk. To prevent crack propagation from one disk section to another, and to minimize structural weaknesses in the disk sections, the live disk sections are bolted together in a single bolt circle. In order to reduce overall disk weight while maintaining a maximum level of failure containment, the inner disc sections are made thicker than the outer disk sections. Embodiments for the fan, compressor and turbine rotor sections of a gas turbine engine are disclosed.

Abstract: This turbine wheel has a plurality of blades radiating from a central hub and is manufactured by a novel method including the steps of assembling a plurality of preformed ceramic or superalloy blades into a ring with foot portions on the blades projecting into the central region of the assembly, filling such central region with powdered ceramic material, such as silicon carbide, or a superalloy material, heating and isostatically pressing, at least the central region, to compact the powdered material around the foot portions into a unitary hub. The blade feet are suitably shaped to provide a precise interlocking engagement between the blades and the unitary hub.

Abstract: A rotatable disc comprising a plurality of generally parallel plates tightly joined together for rotation about a hub. Each plate is provided with a plurality of angularly spaced lands projecting from a face thereof, the lands of each plate interposed in alternating relationship between the lands of the next adjacent plate. In this manner, circumferential displacement of adjacent sectors in any one plate is prevented in the event that a crack develops therein. Each plate is redundantly sized such that, in event of structural failure of one plate, the remaining plates can support a proportionate share of the load of the failed plate. In one embodiment, the plates are prevented from separating laterally through the inclusion of generally radially extending splines which are inserted to interlock cooperating, circumferentially adjacent lands.

Abstract: The subject rotor comprises a disklike body having hub and rim sections joined by a web section. The body is cast, molded or otherwise suitably formed of powdered silicon (and a binder, if necessary, to make it retain its shape until finally treated) which is reaction bonded to convert the silicon particles into a unitary mass. During the casting, molding or other forming step, one or more reinforcing rings of hot pressed silicon nitride or other suitable ceramic are embedded in the body. The ceramic selected must be one which will unite with the silicon during the reaction bonding operation to make a unitary mass. The reinforcing ring or rings are located in regions exposed to unusual stress in the use of the rotor to achieve the required strength.

Abstract: An integrally cast turbine blade and wheel assembly has a plurality of circumferentially spaced radially outwardly directed blades on a peripheral rim that is connected by a wheel web to a central hub having a bore therethrough. The assembly includes a plurality of circumferentially spaced, pairs of grooves to define a plurality of weakened sections in the wheel rim and web that will selectively crack in shear to relieve stresses during either a tensile or compressive phase of wheel assembly operation produced during thermal cycling of an associated engine; and wherein resultant stress relief cracks define a labyrinth seal path to control gas bypass across the blade row.

Abstract: An impeller for a high-speed turbomachine, in which the impeller includes a hub which is frictionally fastened on a shaft of the machine by a tapered fit. A resilient, axially extending connecting portion of the hub is interposed between the impeller and hub and is welded to the impeller. The impeller encompasses the shaft and the hub so as to form a narrow radial gap therebetween.

Abstract: A rotor for a gas turbine engine has a wrought superalloy disk with ceramic blades. The rotor is formed by placing ceramic blades in a fixture with their ceramic blade roots extending inwardly and between the upper and lower rims of a disk or disk halves. The facing upper and lower circumferential rims are cut away to provide for the ceramic blade roots. Said disk or disk halves being of a wrought superalloy having a fine grain size microstructure which can be placed in a superplastic condition. A compliant layer material is placed between the ceramic blade roots and the rims of the disk, and the disk and compliant layer are then heated so as to place the disk in a superplastic condition and pressed into intimate contact with the ceramic blade root, and if disk halves are being used, they are bonded together at inner mating surfaces. The rotor is then heat treated to return the disk to its normal condition of high strength and hardness.

Abstract: A centrifugal pump assembly, having a removable impeller assembly for use in conjunction with ink reservoirs of printing press apparatuses. There is provided a centrifugal pump assembly comprising motor mounting means for mounting the motor with respect to the cover member of an ink reservoir. The shaft of the motor extends downwardly into the reservoir and has secured thereto a coupling sleeve. The coupling sleeve includes means for securing the same to the motor shaft and means for releasably engaging the impeller shaft of the pump assembly. The impeller shaft is provided with a positive drive pin adapted to fit into a slot formed in the coupling sleeve to thereby properly align said impeller shaft with respect to the impeller housing and to insure proper positive connection of the impeller shaft with respect to the motor shaft for corresponding rotational movement therewith. An alternate embodiment utilizes a hollow barrier sleeve to prevent ink from traveling upwardly into the motor.

Abstract: A turbine wheel including blades and rim made in one piece, a notch in the peripheral surface of the rim between each two successive blades, and a through-hole in the rim radially inwardly of and parallel to each notch. The through-holes permit cooling air to flow from one side of the turbine wheel to the other. Each through hole is spaced closely to its respective notch to define a narrow rated breaking point between the two. The through-holes may be of circular, oval, or elliptical cross-sectional shape. A tubular baffle is arranged in each through-hole, the baffle being open at one end to receive cooling air, but the other end of the baffle being blocked. The wall of the baffle is perforated. Longitudinally-extending webs may support each baffle in spaced relation to the wall of the through hole. Annular plates may be arranged over opposite sides of the wheel to define air flow openings to and exhaust openings from the through-holes.

Abstract: An improved resilient member is provided in a clamping connection between two members of a gas turbine rotor, said resilient member taking the form of a rim or outer ring provided with an annular row of inwardly protruding fingers. The resiliency is due partly to deflection of the fingers and partly to a twisting of the outer ring with the fingers.

Abstract: The disclosure of this invention pertains to a bladed rotor for gas turbine engines wherein each blade has a root portion connected to a blade support element spaced radially outwardly from the rim of a single disc and being of greater axial extent than the rim. The element is connected to the rim by a web extending in part radially outside the rim and in part at the sides of the rim.

Abstract: The invention concerns a turbine shaft having stepped bearings on which ds are shrunk on. It is characterized in that the connecting surface between two successive bearings consists of two conical portions separated by a cylindrical portion and toroidal connecting portions between the cylindrical portion and the conical portions. The invention reduces the concentrations of stresses and applies more particularly to elastic fluid turbine shafts.

Abstract: A compressor or turbine rotor stage includes a wheel with a circumferential slot for retention of the roots of blades mounted on the wheel. Each side of the rim of the wheel is approximately symmetrical about a line parallel to the axis of rotation of the wheel through the centroid of the section of the rim side and is of such asymmetrical configuration about a line normal to the axis of rotation that the shear center of each side of the rim is inboard of the centroid and preferably close to or inboard of the plane of action of the radial component of the forces exerted by the blade roots on the sides of the rim due to the centrifugal force pull of the blades.

Abstract: A rotor for a gas turbine engine comprises an outer shell formed in hot pressed silicon nitride and having substantially uniform thickness in a direction parallel to the axis about which the rotor is rotatable and a heat resistant insert which can be either graphite or reaction sintered silicon nitride which fills the space within the shell and is attached to the shell. A row of blades which can be either hot pressed or reaction sintered silicon nitride can be attached to the periphery of the rotor by diffusion bonding.

Abstract: A runner hub for a propeller type hydraulic turbine wherein the hub is constructed of at least a pair of arcuate segments. When the arcuate segments are assembled together, they form a hollow hub. Turnbuckles are provided within the hub attached to opposite hub segments and are adjustable to forcibly hold the hub segments in the assembled position.

Abstract: A disk having a closed channel construction and which is especially suited for supporting the rotating blades of a gas turbine engine is disclosed. In one embodiment, the disk supports the fan blades of a turbofan engine which extend radially therefrom. The disk structurally includes an upstream web, a downstream web and a plurality of arcuate plugs disposed in end to end relationship between the webs to form a toroidal type structure having a substantially rectangular cross section. The disk is contoured to provide a level of torsional and bending stiffness which limits the most critical stage vibratory frequencies to values above the engine operating range while limiting the maximum value of the disk hoop stress during operation to a level below the durability limits of the disk material utilized. A method for making the disk is further disclosed.

Abstract: A radial flow fan of short axial length and large radial dimensions and of the type having the drive motor arranged coaxially with respect to the fan wheel and at least partly inside of the fan wheel. The housing for the fan wheel and motor includes a flat metallic square plate forming an axial end face and a synthetic resinous material circumferential housing attached to the metal plate. The circumferentially extending housing portion also includes a portion defining the opposite end wall of the casing with respect to the metal plate end wall, which opposite end wall has a central opening for inlet of air. The synthetic resinous housing portion includes an exit port for radial exit of the air. The metal plate is connected with good heat conductivity with the stator of the drive motor by way of a flange of a bearing for the shaft of the drive motor and by way of a contact disc which axially supports the rotor shaft at the metal plate.

Abstract: The parts of a gas turbine plant exposed to the highest temperature are made of ceramic material and are mounted by resilient clamping members permitting freedom for thermal movements. These clamping members are located in passages between spaces containing air and gas, respectively, with the air having the higher pressure. The clamping members are slotted to permit the flow of air through the passages in which they are mounted and will thus be effectively cooled.

Abstract: An impeller and shaft assembly suitable for use in an overhung compressor for facilitating mounting and rearranging impellers upon a shaft. A stud is threaded into the end of the shaft and the impeller slidably mounted thereon. An elongated key is inserted between the stud, the shaft, and the impeller to cojoin the three elements. In another embodiment, a second impeller is mounted upon the stud adjacent the first impeller with the two impellers being locked to the stud by a common key.