Abstract: A method of shot blasting a part comprising at least one thin wall (12″) defining two opposite main faces, the square root of the area of each face being greater than the mean distance between said two faces by a factor of at least five, and preferably by a factor of at least ten, in which method said part is caused to rotate at least intermittently relative to one or more vibrating surfaces, with at least one of the main faces being exposed to projectiles (6) set into motion by means of one or more of said vibrating surfaces, treatment taking place progressively on said face(s) so as to impart compression stresses thereto, with a portion only of the part being treated at any one time and with regions of the part preferably being exposed on several occasions to the projectiles, with relative rotation taking place between said exposures.

Abstract: Method for making an electrical connector, comprising the following steps. Step 1: defining first carrier and first terminal sections along a first material sheet. Step 2: defining at least a first pilot hole on the first carrier section and at least two first terminals on the first terminal section. Each first terminal has a body portion extending between front and rear contact portions. Step 3: forming a first bridging rib around the first terminals aligned by the first carrier section through a first inserting mold. Step 4: making a second insert molding around the body portions of the terminals supportably aligned by the associated first bridging rib.

Abstract: A five-part rotor assembly is easily disassembled for cleaning and/or sterilization. The five parts comprise a rotor sleeve, a rotor head, a weir plate, a rotor cover and an internal vane package. Each of these parts is machined as a unitary piece or otherwise fabricated without weldments.

Abstract: In a method of manufacturing a plurality of steam turbines for use in various applications which differ in the respective thermodynamic parameters such as, for example, cooling-water temperature, ambient temperature, given boiler data, process-steam requirement, etc., the steam turbines in each case having at least one high-pressure part with first blading and a control-wheel stage for part-load operation, a simplification and cost saving is achieved owing to the fact that standard blading, which is identical for all the steam turbines, is used as first blading, and in that the adaption of the individual steam turbine to the thermodynamic parameters of the respective application is carried out by appropriate design or variation of the control-wheel stage.

Abstract: A compact steam turbine power-generation plant has a compact steam turbine that operates at a high temperature in a range of 600 to 660° C. Ferrite based heat resisting steels provide for thermal efficiency. The main steam temperature and the reheated steam temperature can be set in a range of 600 to 660° C. by making the main parts exposed to the high temperature atmosphere, such as the rotor shaft, from ferrite based forged steels and cast steels and by making a final stage blade of a low pressure turbine from a martensite steel. The final stage blade is made from a ferrite based forged steel having a tensile strength of 120 kgf/mm2 or more; the rotor shaft is made from a ferrite based forged steel having a 105 h creep rupture strength of 11 kgf/mm2 or more; and the inner casing is made from a ferrite based cast steel having a 105 h creep rupture strength of 10 kgf/mm2 or more.

Abstract: A method for making a torque converter includes the steps of forming a blade having a tab extending outward from the blade and along a portion of a length of the blade. A recess is formed in the housing sized to receive the first tab. The recess defines an edge adjacent the tab and extending along the tab. The tab is inserted within the recess to form a housing assembly. A brazing material is provided between the tab and the housing.

Abstract: A method of forming an internal channel within an article, such as a cooling channel in an air-cooled blade, vane, shroud, combustor or duct of a gas turbine engine. The method generally entails forming a substrate to have a groove recessed in its surface. A sacrificial material is then deposited in the groove to form a filler that can be preferentially removed from the groove. A permanent layer is then deposited on the surface of the substrate and over the filler, after which the filler is removed from the groove to yield the desired channel in the substrate beneath the permanent layer.

Abstract: A method for assembling a rotary machine, such as a gas turbine engine, having rotor elements and associated seal lands. Various details of the method are developed for facilitating assembly of the rotary machine that are, in one embodiment, applicable to installing fan blades to a fan rotor disk while rotating the rotor disk by hand. In one embodiment, a lubricant is applied to a seal land to reduce friction between the rotor element and the seal land during assembly.

Abstract: A turbine pump impeller provided with vanes of the double-curvature type, obtained monolithically by die casting and comprising, between two disk-shaped elements, a plurality of double-curvature vanes. In each vane, the two surfaces that are struck by the fluid are obtained from a sequence of transverse curved portions formed by circular arcs centered on a common spatial central axis.

Abstract: An integrally cast, non-welded coal spreader for a furnace or boiler burner has integrally cast swirl vanes. A shaft of the spreader extends into the hollow interior of a cap of the spreader and the vanes extend outwardly of the cap and are cast as one piece with the cap.

Abstract: The object is to provide a novel compressor-wheel arrangement for turbochargers, the compressor-wheel fastening of which is designed to be especially robust but nonetheless easily releasable. A simplified mounting/dismantling method and a corresponding method are specified for this purpose.

Abstract: A propulsion engine fan incorporates two sets of blades with recessed portions formed along the surface of each blade. One set of blades has a higher resonant frequency than the other set of blades. In an illustrative embodiment of the invention, first and second blade groups each comprise an airfoil portion forming a surface for directing the flow of a working fluid through the engine. Each of the first group of blades has first and second recessed regions formed from the blade surface and has a first resonant frequency. Each of the second group of blades has third and fourth recessed regions formed from the blade surface and has a second resonant frequency less than the first resonant frequency. The first and second group blades are arranged in an alternating pattern along the rotor portion of the fan.

Abstract: The method includes the following steps: producing a preform of the blade comprising a blade root section for connecting to a hub and an aerodynamically profiled main blade section, the preform including, in the blade root section, a pile of fabrics transverse to the span axis of the blade projecting with respect to the blade root section, so as to form a pitch control lever; arranging the preform in an injection mold; injecting a thermosetting liquid resin into the mold; and heating the mould to make the thermosetting resin set.

Abstract: An impeller shell 40a of a torque converter includes a main portion 41, a connection portion 42 and a stepped portion 43. The main portion 41 has a curved inner peripheral surface 41a carrying impeller blades, and is opposed to a turbine 5. The connection portion 42 has a cylindrical form larger in diameter than an outer periphery of the inner peripheral surface 41a, and is fixed to a front cover 3. The stepped portion 43 couples an end of the main portion 41 near an engine to an end of the connection portion 42 near a transmission. A corner portion formed of the inner peripheral surface 41a and a surface 43a near the engine has a radius set to 4 mm or less by preliminary forming by a press and subsequent finish forming by a press.

Abstract: The cantilevered stator vanes of the compressor section of the gas turbine engine are treated by including a rotating hub having a by-pass passage for removing the low momentum fluid from the main air stream adjacent to the tips of the stator vanes in the compressor and returning it back into the main air stream after having treated the air while avoiding penalties and excessive heating. A plurality of vanes are circumferentially spaced in the by-pass passage for removing vortices and streamlining the flow before injected the air back into the airstream. The vane passage hub treatment is fabricated in a single cast piece in one embodiment, in a three ring configuration in another embodiment and in a segmented ring configuration in still another embodiment.

Abstract: A turbomachine rotor stage having a thin annular body comprising a metal alloy part reinforced by at least one fibrous ring which has a radial height h of at least 1.5 times its axial width l and which is embedded in the metal alloy part so that it projects radially outwardly from the inner wall thereof in order to stiffen the body and reduce the quantity of fibre material to be used.

Abstract: A method of producing numerous small passages within a turbomachinery component is disclosed. The method comprises providing a turbomachinery component substrate having grooves, filling the grooves with a filler, condensing a vapor onto the surfaces of the substrate and the filler, and removing the filler. The method enables the formation of small passages located close to the component surface without the low yield rate associated with conventional methods of turbomachinery component production. Turbomachinery components having numerous small passages for cooling are also disclosed. Such passages may diminish fluid pressure losses of a cooling medium passing therethrough.

Abstract: A fan wheel for high-temperature operation, especially in ovens, includes a star-like or ray-like base plate having a central middle region, protrusions protruding substantially radially beyond the central middle region and having an outer contour, axially drawn up blades disposed on the protrusions and a base plate surface with axially drawn up segments extending from the middle region into the vicinity of the protrusions. According to one embodiment, the segments include a central, annular segment and star-like or ray-like segments adjoining the central, annular segment and extending through the protrusions of the base plate substantially symmetrically with the outer contour. According to another embodiment, the segments include a central, annular segment and star-like or ray-like segments adjoining the central, annular segment, originating from the central, annular segment and following the outer contour of the base plate.

Abstract: A fixture for use in the final machining operation of the integral bladed rotor (IBR) of a gas turbine engine comprises a rigid ring for surrounding the outer periphery of the IBR and supporting tapered pins that fit into the space between the blades and then molded therein with a plaster or plastic medium for securing the unit to the IBR for enhancing its structural integrity. The method of finishing the airfoils of the IBR includes inserting the pins in alternate spaces and working half of the blade surfaces in the pinless spaces and then removing the pins and inserting pins in the previously worked spaces and then molding the pins in place. The other half of the bladed surface is then worked in the pinless spaces until the airfoils are finally contoured. The unit is removed and heated to melt the residual cast medium to produce the finished product.

Abstract: A lightweight high temperature multiproperty rotor disk and method of manufacture for use in a gas turbine engine. The rotor disk of a nickel super alloy and having a plurality of lightweight high temperature single crystal blade attachment lugs bonded thereto. The single crystal high temperature rotor blade attachment lugs being cast in a substantially rectangular shape and bonded to the circumference of the disk. A method of manufacturing the rotor includes positioning the plurality of single crystal attachment lugs on a positioning ring that has locating nests formed thereon. Subsequently, the rotor disk is placed within the bonding ring and a restraining ring is placed around the entire subassembly. Upon subjecting the assembly to high temperature the rotor disk, having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the restraining member, forces the components into a mating relationship.

Abstract: The repair method includes removing eroded or damaged trailing edge portions of partitions in the diaphragm of a turbine, over 50% of the length of the partitions being removed commencing at the trailing edge. A coupon which is a precise replication of a portion of an originally specified partition is welded to the remaining or extant partition portion by a seal weld along the radial length of the coupon on the suction side of the repaired partition and two full penetration welds at the ends of the coupon to secure it to the inner and outer rings or side walls of the diaphragm. The repaired partition is thus substantially identically contoured as the original partition.

Abstract: A method and apparatus for centrifugal casting a blank separable into a plurality of preforms having a required configuration for forging to a finished component. Individual molds are symmetrically located around the axis of rotation of a casting table and have mold cavities that are filled by molten alloy under the centrifugal force created by rapidly rotating the table. Alternatively, a cylindrical mold is centered on the axis of rotation and the centrifugal force created by rapidly rotating the table causes the molten alloy to fill cavities in the wall of the mold. Centrifugal forces of at least 20 g may be employed.

Abstract: A heavy-duty gas turbine includes a compressor; a combustion liner; a turbine blade in a single stage or multi-stages; and a turbine nozzle provided in correspondence to the turbine blade. The turbine blade has a dovetail secured to a turbine disk and has an overall length of not less than 180 mm, and it is made of a single-crystal Ni-base alloy whose .gamma. phase is a single crystal. Operating gas temperature is not less than 1400.degree. C., and metal temperature of a first blade is not less than 1000.degree. C. under working stress.

Abstract: A method of manufacturing a vane for a counter torque device includes extruding a hollow metal section of cross-section corresponding to the aerodynamic profile of the vane, in cutting off a section portion of length not substantially less than the span of the vane, and in arranging each end of the section portion as an end fitting with at least one fastening tab, either by machining and deformation of the ends of the section portion, or by fitting end fittings attached to its ends.

Abstract: A fixed angle rotor and method of manufacture of a fixed angle rotor has a frustum shaped rotor having rounded surfaces reinforced by filament tow windings against both vertical and horizontal forces generated during centrifugation. A so-called "high speed" rotor has a bottom composite disc, a top composite disc, and a frustum shaped hollow fiber reinforced molded insert between the respective discs having a stepped exterior surface. An "ultra speed" rotor has a bottom composite disc, a top composite disc, and composite discs therebetween defining a stepped exterior surface. In both cases, these exterior steps have surfaces which capture the windings to the exterior of the rotor. A first class of individual fiber windings about the rotor is applied having a vertical reinforcement component parallel to the spin axis and normal to the laminate layers.

Abstract: A vane wheel driven by a shaft for transferring a gas, comprises, vortex flow chambers opening in a direction substantially parallel to the shaft to receive the gas, to urge the gas in a substantially circumferential direction of the vane wheel, and to generate and accelerate a vortex flow of the gas. A vane member includes a hub through which the vane member is connected to the shaft, with the vane member including a plurality of vanes each extending integrally from the hub in a substantially radial direction of the vane wheel. Each of the vanes includes a front surface for urging the gas in the substantially circumferential direction of the vane wheel. A vortex flow chamber wall extends integrally from both the hub and each of the vanes, and a cover contacts with the vortex flow chamber wall to form the vortex flow chambers together with the vortex flow chamber wall and the vanes.

Abstract: A method and apparatus for making a globoid screw for use as a mainrotor in a compressor or expander wherein a cylindrical rotor body is mounted for rotation about the longitudinal axis thereof, a cutter having a plurality of teeth at spaced locations around a circumference disposed in a plane and having an axis of rotation disposed perpendicular to that plane is mounted for rotation about its axis and is disposed so that the plane thereof is parallel to the rotor body longitudinal axis and so that the cutter rotational axis is perpendicular to the rotor longitudinal axis, and the rotor body and the cutter are rotated at synchronized speeds.

Abstract: Convenient access for quick and thorough clean-out and maintenance of an openable mixing chamber and both rotors in two-rotor continuous mixers for plastic materials is advantageously achieved by making each rotor in three separate pieces: a drive journal, a rotor body (also called a "rotor section" or a "rotor") and a driven journal. These three separate pieces of each rotor are axially aligned, with the rotor body being positioned between the drive journal and the driven journal. Each rotor body is disengageably coupled to its respective drive and driven journals. The drive and driven journals are rotatably mounted in bearing assemblies which are separate from the mixing chamber barrel (also called a "mixing chamber housing").

Abstract: A swinging bucket rotor constructed of composite material has a central rotor body including strap retaining surfaces. Wound endless composite fiber straps are provided having central portions which are attached to the respective top and bottom of the central rotor body and loop portions remote from the central rotor body for mounting the swinging buckets. These wound endless straps attach centrally to the central rotor body at the strap retaining surfaces and define bucket retaining loops symmetrically spaced from the spin axis of the rotor at the central rotor body. In the preferred embodiment, each bucket retaining loop holds spaced apart bushings for receiving a trunion shaft. Paired trunions on either side of a central sample tube receiving ring are provided. The trunions fit to the composite loop portions of the endless composite material straps. Typically, four sample receiving buckets are placed within and held by the central sample tube receiving rings.

Abstract: A heavy-duty gas turbine includes a compressor; a combustion liner; a turbine blade in a single stage or multi-stages; and a turbine nozzle provided in correspondence to the turbine blade. The turbine blade has a dovetail secured to a turbine disk and has an overall length of not less than 180 mm, and it is made of a single-crystal Ni-base alloy whose .gamma. phase is a single crystal. Operating gas temperature is not less than 1400.degree. C., and metal temperature of a first blade is not less than 1000.degree. C. under working stress.

Abstract: A method and apparatus which facilitate separation of a gas turbofan powerplant into modules for shipping, maintenance and repair is disclosed. Various construction details are developed which provide means for mounting a fan cowling to an engine core in a manner which permits transference of operational loads from the fan cowling to the engine core and separation of the fan cowling from the engine core. In one embodiment, a fan cowling (46) is attached to an engine core (18) by a plurality of radially extending through struts (64). The through struts include a bolted joint (72) which permits separation of a powerplant (12) into a first module and a second module. For this embodiment, a method for varying between an assembled and disassembled condition is comprised of manipulating the joints between an engaged and disengaged position and axially moving the separate modules along a longitudinal centerline (14).

Abstract: A process and a device for the simultaneous tensioning and loosening of eccentric tension rods (19) of gas turbine rotors assembled from several turbine disks (23). An improved hydraulic tensioning device is used to provide an optimal circular and flat impact quality, and the quiet running of the gas turbine rotor is improved overall at high speeds. Further, it is guaranteed that the same forces act on each tension rod (19), the elongation of each tension rod (19) can be measured as accurately as possible, and a minimization of the setting force losses is achieved. A solid cylindrical ring (1) forms a piston chamber (11) in each case, whereby the piston chambers (11) are connected together with cross holes and are acted on by the hydraulic medium. The catch pin (3), through which a measuring rod (5) is guided, which makes contact with the head of the tension rod (19) by a pressure spring (18), is inserted through a boring in the piston (2).

Abstract: A vibration isolation assembly for use in securing a fan blade, particularly a ceiling fan blade, to a mounting surface having a plurality of mounting holes formed herein, the blade having an equal number of through holes in a proximate end thereof alignable with the mounting holes. The vibration isolation assembly comprises a plurality of first resilient members securable to the mounting surface adjacent each mounting hole, a plurality of second resilient members disposable within the through holes in the blade, with each second resilient member having a longitudinal hole formed therethrough, and a plurality of screws insertable through the holes in the first and second resilient members and engageable within the mounting holes in the mounting surface for fastening the blade to the mounting surface.

Abstract: A high strength, monolithic shrouded impeller is made from a single blank by a method that includes the following four steps: Turning and boring a rough forging to an impeller profile; Using a three-dimensional CNC milling machine with end mills, removing as much material as possible from what are to be passageways in the impeller, defining leading and trailing edge zones of vanes defining the passageways, by removing material in direct line of sight from the outside diameter or from the eye of the impeller or both; Forming a hole through a central zone of what will be each impeller passageway, and removing the remainder of the material to define the passageways by three dimensional planning controlled by the CNC machine using a non-rotating tool.

Abstract: A method for producing a rotor of a turbine, particularly a steam turbine, from individual rotor parts being welded together to make a unit, includes assembling parts of a rotor required for a given turbine in a modular system having supply steam shaft ends, single rotor disks, double rotor disks, exhaust steam shaft ends and optionally condensation-end-stage drums, for producing various rotor variants. The parts of the rotor are produced at parallel times according to orders and/or taken from stock. Still required remachining of the assembled rotor during production of the parts, especially machining grooves in final form for receiving rotor blade roots in the remachining step, is minimized. The parts are joined together with low warping with a beam of high power density, preferably an electron beam. Required rotor blades are selected and the rotor disks are equipped with the blades before or after the parts are joined together. The rotor put together from the individual parts is machined in final form.

Abstract: The contour and dimensions of the radial-inflow turbine is obtained by an iteration process that includes calculating by use of a three dimensional fluid dynamic flow analysis the parameters that will produce the desired fluid flow velocities, pressures and other aerodynamic properties until the optimum configuration is obtained. The wrap distribution is obtained in accordance with the formulae:When 0.0<X<0.22135: .delta..theta./.delta..theta.(total)=0.0When 0.22135<X<1.00: .delta..theta./.delta..theta.(total)=A+B.times.X+C.times.X.sup.2 +D.times.X.sup.3 +E.times.X.sup.4 +F.times.X.sup.5 =0.0Where:.delta..theta./.delta..theta.(total)=local normalized wrap angleA=0.101596B=-1.007604C=2.672787D=-1.0125510E=0.713005F=-0.469075X=non-dimensional axial chord for a given configurationAdditional reduction in size and inertia is obtained by leaning and contouring the leading edge into an elliptical shape.

Abstract: A brush auger machine for assembling a brush to an auger is disclosed. The machine includes a frame for supporting an auger having a shaft and a spiral blade. A welding station is adjacent the frame. A guide chute receives the continuous brush and defines a diameter approximately equal to the outer diameter of the completed brush auger assembly. A discharge frame is positioned adjacent the welding station and includes a motor driven chuck which holds and rotates the end of the auger shaft. The motor and chuck are mounted on a movable platform. Welding is completed at the welding station and rotation of the auger shaft moves the assembly and the platform along the discharge frame.

Abstract: A method for manufacturing a screw rotor for use in a hydraulic machine which has a pair of rotors engageable with each other to compress fluid, pump fluid or expand fluid. The screw rotor includes a shaft, a screw body including a number of stacked thin plates bonded with one another, and a cavity provided in the screw body and formed by openings of the stacked thin plates. The method of manufacturing a screw rotor includes the steps of preparing a number of thin plates having at least one opening, stacking the thin plates in such a manner that a through hole of the thin plate receives a shaft, filling a cavity formed by the openings of the stacked thin plates with powdery pressure medium, and bonding the stacked thin plates with one another by diffusion bonding under a hot isostatic pressing process.

Abstract: A method for producing a profiled part from a blank, wherein the cross-sectional profile of the part to be produced differs in some portions both quantitatively and qualitatively from the cross-sectional profile of the blank, so that different amounts of material must be removed between a starting profile of the blank and a desired final profile of the part includes pre-shaping and finish-grinding the part to be produced in one chucking position with at least one profiled grinding wheel. The blank is translated and rotated relative to the at least one profiled grinding wheel during the pre-shaping step for giving the blank approximately a desired profile. The finish-grinding step is performed at least partially after the pre-shaping step for smoothing surfaces and producing the final profile to accurate dimensions. A turbomachine blade, an intermediate product for the turbomachine blade and a method of manufacturing the interim product are also provided.

Abstract: Setting pitch on a windmill airfoil having a longitudinal axis, a rotor blade and a rotor base secured to the rotor blade is accomplished by marking a windmill rotor hub for receiving the rotor base with a reference mark at a location corresponding to a first plane parallel to a plane of rotation of the windmill airfoil in use. The airfoil is positioned along a second plane relative to and substantially completely intersecting the longitudinal axis of the airfoil. The rotor base is marked at a location substantially parallel to the second plane. The airfoil is positioned relative to the windmill rotor hub so that the rotor base is in substantial engagement with the hub. The airfoil is moved relative to the hub so that the mark on the rotor base is aligned with the reference mark on the windmill rotor hub and the rotor base is secured to the windmill hub. An apparatus for marking pitch on a windmill airfoil is also provided.

Abstract: A method of making a titanium fan disc for a gas turbine engine comprises the steps of providing a pair of identical forged titanium cylinders each having a central bore and a flat end surface at right angles to its central axis, preparing the flat end surface of each cylinder to a high degree of smoothness, abutting the prepared surfaces of the cylinders one against the other in axial alignment, removing air from between said surfaces, and diffusion bonding the cylinders end-to-end by hot isostatic pressing to form the disc.

Abstract: The present invention discloses an improved rotor disc for a refiner and its method of formation. The invention comprises a plurality of blade members spaced apart by a spacer between each adjacent blade member. Dams may be provided on the spacers. In forming the preferred disc, the plurality of blades and spacers are secured one to the other to form a blade segment. A plurality of blade segments are affixed one to the other to, in turn, form the disc. The invention is characterized by an absence of any mounting plate or base member. The method of the invention is characterized by a continuous weld along either of the inner circumference or the outer circumference of the disc.

Abstract: A centrifuge rotor having a balancing ring integrally formed with and raised from the upper surface thereof is manufactured by removing material from the ring to balance the rotor in the upper plane. The balancing ring is on the same radius as the rotor tube cavities and of width less than the diameter of said cavities such that the ring, when the tube cavities are drilled, is broken into segments of precisely known area which make the amount of material to be removed to balance the rotor readily determinable.

Abstract: A drum compressor rotor (10) for use in a gas turbine engine comprises a plurality of high strength, low density filaments (18a-d) which are covered with a high temperature adhesive resin and tightly wound around the hub (12) between rows of fan blades (14). The filaments allow an increase in the maximum compressor rotor operating speed thereby increasing the potential performance of the turbine engine. The filament windings (18a-d) are significantly lighter and less expensive than conventional welded metal support disks (106a-c).

Abstract: A dual alloy disk made from a rim alloy having high stress rupture and creep resistance as well as good hold time fatigue crack resistance and a hub alloy having high tensile strength and good low cycle fatigue crack resistance is described. The dual alloy disk is designed for use as a disk in gas turbine engines operating as high as 1500.degree. F. The hub and rim are joined together at a substantially defect-free joint to form a turbine disk having improved properties in both the hub and rim regions.

Abstract: A method of repairing rotor blades on a turbine comprises the steps of removal of a rotor from the turbine, selecting predetermined desired position of the blades and, after removing any inter blade ties necessary to enable any required repair processes to be carried out, aligning all the blades to said predetermined aligned position prior to the carrying out of any repair step which may incorporate cutting, welding, machining etc., such alignment considerably facilitates semi-automated repair of each blade and has further benefits in facilitating reinsertion of inter blade ties and ensuring that the blades are not only in an aligned position but in a stress free condition when returned to the turbine.

Abstract: A method for shear forge bonding two or more metal parts having forging compatible compositions is comprised of the steps of sizing parts to be joined across a forged bond line, disposing those parts in forging dies configured to present them in a bonding-effective orientation, shearing surfaces, one on each of the metal parts, located proximately and opposite one another across a gap, under controlled conditions of temperature and atmosphere selected to prevent the formation of any bonding disruptive surface contamination on the sheared surfaces, and then finally forging those parts to close the gap and bring the sheared surfaces into contact under controlled conditions of temperature, pressure, atmosphere, and outer diameter constraint to yield a shear forged bond between the sheared surfaces.

Abstract: In a pipe diffuser, a plurality of circumferentially spaced generally radially extending passages, are formed in a disc in such a way as to eliminate the need for plugs to prevent wandering of the drill bit during the drilling process. The passages are drilled, but not to the point of any substantial intersection between the adjacent passages. Material is then removed from the inner periphery of the disc to the radial extent of a leading edge circle defined by the leading edge of the islands between the passages. The resulting structure is substantially equivalent in performance but is obtained with a much easier process.

Abstract: The impeller includes a hollow shaft member screwing therein and thereto a hollow fixing shaft rotatably mounted in nozzle of a motorboat having a propeller shaft projecting into the nozzle to drive the fixing shaft, in which the shaft member has a truncated cone-shaped leading end having a cross-sectionally polygonal inner hole.

Abstract: A method is taught for the isostatic forging of integrally bladed rotors, in which deformable hollow single crystal blades are protected from deformation during diffusion bonding to the disk by encapsulation in a ceramic protective shell. The ceramic shell serves to occupy the areas between the blades and the surrounding forging die set, so that during application of high temperatures and pressures, damage to the blades is prevented without the use of complex segmented die assemblies.