Abstract: A turbine installation having reduced inner and outer gaps comprises a water passageway and a turbine runner disposed in the passageway downstream of a discharge ring. The turbine runner includes a hollow hub having spaced apart inner and outer surfaces and a longitudinal axis and a plurality of runner blades. Each blade comprises a hydrofoil having an inner edge and a distal outer edge, a leading edge and a trailing edge separated by a water directing surface. Each blade is pivotally connected to the hub about a rotational axis extending in a direction generally perpendicular to the longitudinal axis so that its inner edge is proximate the hub. Each blade is rotatable between a maximum pitch position and a minimum pitch position. The discharge ring has a spherical configuration cooperable with the outer edge of each of the blades to reduce an outer gap formed between the outer edge of each of the blades and the passageway.

Abstract: A load transferring system wherein a composite turbine disk mounted on a shaft is in contact with a backup disk which is secured to the shaft. The turbine disk is made of layers of woven carbon fibers held in a rigid configuration in a ceramic matrix. The composite disk has a plurality of lugs which have trapezoidal cross sections when cut by planes which are perpendicular to each other, with both planes being normal to the disk. The backup disk is provided with recesses which are the negative of the trapezoidal lugs to lock the two disks together. A second backup disk may be secured to the shaft to secure the composite turbine disk between the backup disks.

Abstract: The present invention provides a gas turbine engine blade having a dovetail, a shank extending radially outward from the dovetail, and a platform joined to the shank. An inner surface of the platform faces radially inwardly and an opposite outer surface of the platform faces radially outwardly. An airfoil extends radially outwardly from the platform and has pressure and suction airfoil sides that define pressure and suction blade sides of the blade. The platform extends axially between leading and trailing platform edges and transversely between pressure and suction side platform edges of the platform. At least one transversely extending bracing rib is in a corner of the shank and the platform between one of the blade sides and the inner surface of the platform. The preferred embodiment further includes the bracing rib, the shank, and the platform being integrally cast. The bracing rib is preferably wider along the platform and the shank than at a distal edge of the rib.

Abstract: A windmill having a plurality of radially extending blades, each being an aerodynamic-shaped airfoil having a cross-section which is essentially an inverted pan-shape with an intermediate section, a leading edge into the wind, and a trailing edge which has a flange doubled back toward the leading edge and an end cap. The blade is of substantial uniform thickness. An air compressor and generator are driven by the windmill. The compressor is connected to a storage tank which is connected to the intake of a second compressor.

Abstract: In a friction- and form-grip connection of rotating components (1, 2) which have different expansion behavior in the region of the connection during rotation, the form grip is effected via a stepped centering seat (3). The friction grip between the two components is effected by way of axially prestressed elements. At least one of the components has a cavity (6) in the interior, in which cavity (6) an insert ring (7), which exerts a radial force on the centering seat (3) during operation, is arranged. The prestressed insert ring (7) bears with only part of its axial extent against the component (1) interacting with it.

Abstract: The invention provides a turbine blade retention device installed in an axially extending gap between the blade root bottom and the slot floor. The retention device has two parts: a blade root retention clip and a spacer bar. The clip has an elongated web of a selected web thickness and width less than the width of the slot floor. The clip includes a forward and a rearward transverse flange extending radially outwardly and extending laterally from forward and rearward ends of the web. The flanges serve to engage the forward and rearward faces of the rotor hub disk respectively, and to engage forward and rearward faces of an associated blade root. The height of at least one flange is less than the gap depth to permit conventional sliding installation the blade root. The spacer bar is installed in the gap between the clip and slot floor to hold the clip radially outward in engagement with the forward and rearward faces of the blade root.

Abstract: The object of the invention is to provide a safe and reproducible compressor impeller fastening for high speed turboengines, which, moreover, possesses more accurate concentricity.This is achieved, according to the invention, in that both the hub cone (9) and the shaft cone (11) each have a mean diameter (23, 24) and these mean diameters (23, 24) are arranged at an axial distance (25) from the mass center of gravity (14) of the compressor impeller (4), said distance corresponding at least to half the mean diameters (23, 24). On the shaft side of the hub cone (9), the through bore (8) of the hub (6) is designed at least partially as a cylindrical bore (16).

Abstract: A turbine rotor consisting of a wheel made of a TiAl alloy of good heat resistance and a rotor shaft made of a steel with good bonding strength is disclosed. As the shaft material a structural steel or a martensitic heat resistant steel is used. A TiAl turbine wheel made by precision casting is butted to the shaft with insertion of a brazing filler in the butted interfaces and stress of 0.01 kgf/mm.sup.2 or higher but lower than yield stress of the shaft is applied on the butted interfaces under heating by high frequency induction heating in atmosphere of an inert gas or a reducing gas to a temperature higher than the liquidus temperature of the brazing metal but not exceeding 100.degree. C. above the liquidus temperature.

Abstract: A rotor disk for a gas turbine engine having an axis of rotation and an axial centerline is provided which includes a rim, forward and aft hubs, and forward and aft webs. The forward web extends between the rim and the forward hub, and the aft web extends between the rim and the aft hub. The forward and aft hubs are separated. Each web is skewed from the axial centerline. A circumferentially extending cavity is formed between the webs and the hubs.

Abstract: A turbine, disposed in water flowing therethrough, includes a hub and associated runner blades. Each blade comprises an inner surface and a distal outer surface, a leading edge and a trailing edge separated by a water directing surface. Each blade is rotatable relative to the hub about a blade rotational axis. The hub includes a spherically-shaped outer surface in a region of the hub swept by the inner surface of the blades when the blades are rotated from maximum to minimum pitch. The hub may also be associated with blades in which the chord is reduced in the root region of the blade. The turbine may also include seals attached to the blade inner surface and an essentially spherically-shaped discharge ring to improve certain turbine parameters such as cavitation, efficiency, flow disturbance, and fish survivability.

Abstract: A turbine, adaptable to improve the survivability of fish present in water flowing therethrough, includes a hub and associated runner blades. Each blade comprises an inner edge and a distal outer edge, a leading edge and a trailing edge separated by a water directing surface. Each blade is rotatable relative to the hub about a blade rotational axis. The turbine is provided with features designed to shield a gap formed between the hub and the blade inner edge as the blade is rotated about its axis.

Abstract: The turbine comprises a plurality of blades disposed around a hub between two end plates, with the blades, the hub, and the end plates being made of thermostructural composite material. The hub is made by stacking plane annular plates of thermostructural composite material along a common axis. Each blade is made individually by shaping a two-dimensional fiber fabric in plate or sheet form to obtain a blade preform, by densifying the preform with a matrix to obtain a blade blank made of thermostructural composite material, and by machining an outline for the densified preform. Each end plate is obtained by making an annular preform by means of a two-dimensional fiber fabric in plate or sheet form, and by densifying the preform with a matrix to obtain a part made of thermostructural composite material. The blades are assembled to the hub between the end plates, with each blade being connected to the hub by a portion forming a blade root.

Abstract: A bearing support structure for a gas turbine engine comprises an annular array of stator vanes and a radially inner bearing support portion which are interconnected by an annular array of radially extending U-shaped cross-section parts. The U-shaped cross-section parts are interconnected at their radially outer extents and are arranged so that adjacent parts are open in generally opposite axial directions. Such a bearing support structure can carry service pipes with good accessibility and be produced by casting, thereby reducing its cost.

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 fastening structure has a screw rotor fixing a rotor shaft to a shaft hole of a rotor body. A casing includes the rotor therein, and a positioning portion and a screw portion are arranged between the shaft hole and the rotor shaft. Press fit portions are arranged at both axial ends of the shaft hole. The screw portion receives driving torque inputted to the rotor shaft and moves the rotor body so that the shaft hole and the rotor shaft hit against each other in the positioning portion. Accordingly, a fixing function of the rotor body and the rotor shaft is strengthened as the input torque to the rotor is increased. Further, the rotor has a simple structure and is cheaply manufactured. Furthermore, it is possible to prevent reductions in performance and durability of the rotor caused by any shift in position between the rotor body and the rotor shaft.

Abstract: A ceramic-metal composite assembly includes an intermediate member made of a material having a thermal expansion efficiency between those of the materials forming a ceramic member and a metallic shaft member. The intermediate member is metallurgically joined to the ceramic member whilst being mechanically joined to the metallic member to constitute a single unit.

Abstract: A gas turbine has a gas turbine rotor including a plurality of rotary disks each having an opening of a circular shape formed through its central portion, the rotary disk including a pair of hub portions formed respectively on opposite sides thereof, and a pair of in-low portions formed respectively at the opposite sides thereof. The gas turbine rotor also includes a plurality of spacers each having an opening of a circular shape formed through its central portion, the spacer having a pair of in-low portions formed respectively at opposite sides thereof. The rotary disks and the spacers are alternately stacked together in such a manner that the opposite sides of each of the spacers contact opposed side surfaces of the adjacent hub portions, respectively, and that the in-low portions of each of the spacers are engaged respectively with the in-low portions of the adjacent rotary disks. The stack of rotary disks and spacers are fastened together in an axial direction by stacking bolts.

Abstract: A rotor disc (15) has an axially enlarged hub portion (18) with a bore (20) through which a turbine shaft (19) extends in a coaxial, radially spaced apart relationship, the annular gap between the hub portion (18) and the shaft (19) receives a flow of temperature regulating fluid. The shaft (19) is provided with axially extending elongate projections (22) to increase the turbulence and relative velocity of the temperature regulating fluid adjacent the projections (22).

Abstract: A turbine engine rotor assembly disk is provided which includes a forward web, an aft web, a plurality of first stub shafts, and a plurality of second stub shafts. The first and second stub shafts have axial ends and web ends. The stub shafts are attached to the respective forward or aft web, at the web end. The first and second stub shafts are equal in number, similarly spaced around the axial centerline, and attached to one another by fasteners.

Abstract: A low pressure steam turbine and generator low alloy steel disc rotors with extended useful life properties. A ring member of the disc rotor has disposed on it multiple weld layers of ferrous material, forming a weld region. The ring member is made of a low alloy ferrous metal alloy having less than about six weight percent alloying ingredients including chromium. The chromium content of the weld region increases overall from a portion of the weld region adjacent to the ring member to a portion of the weld region farthest from the ring member. This general increase is accomplished using weld metal of a single chromium concentration of between 9% and 17% chromium and varying the welding parameters.

Abstract: The present invention provides an apparatus for minimizing the blade opening between the blade shank of propeller and spinner in order to improve the overall efficiency of an aircraft and propeller system. The present invention consists of a two piece blade opening filler; the bulkhead insert which attaches to the bulkhead, and the spinner insert which maybe attached to bulkhead insert after installation of the propeller blade. The blade opening filler fills the blade opening between the spinner and blade shank while facilitating maintenance of the system.

Abstract: A lightweight gas turbine rotor having a pair of high specific strength support ring members positioned fore and aft a center hub member. The unitary center hub member for carrying a plurality of airfoils that extend radially outward therefrom. The pair of high specific strength support ring members are connected to the blade carrying member at a location to compressively transmit the centrifugal force generated by the rotating rotor to a radially inward location on the support ring members. The support ring members being utilized to resist a majority of the centrifugal force generated by the components of the rotor. The center hub member and the pair of support ring members are made of different materials. More particularly the pair of support ring members are made of a metal matrix composite, and the center hub member when utilized in a compressor is formed of a high temperature titanium alloy, and the center hub member when utilized in a turbine is formed of a nickel alloy.

Abstract: A turbine wheel for a turbocharger or the like is mounted to an impeller shaft and optionally an additional drive shaft by annular rows of coupling teeth preferably of the CURVIC.TM. coupling type having radially and rotationally locking convex sided and concave sided interlocking teeth. Flexible webs connecting coupling rings on the turbine allow thermo and mechanical growth of the turbine wheel without excessive deflection of the coupling rings and the associated shaft flanges. A single central stud threaded into one of the shafts and retained by a bolt against the other maintains the components in assembly with the coupling teeth fully engaged. A radial slot formed in the coupling flange for one of the shafts prevents thermal distortion of the flange from substantially affecting an adjacent thrust bearing portion of the flange. The arrangement simplifies rotor assembly and avoids the need for rebalancing after disassembly and reassembly.

Abstract: Turbomachinery rotor component, which may be a disk or drum rotor, having an annular rim disposed about a centerline for securing the blades to the rotor and that is subject to a tensile stress field due to centrifugal and thermal growth induced forces generated by the rotor when the rotor is rotating. An annular channel slot is cut around the rim, has outer annular overhanging rails, and has at least one stress riser in the form of a three sided slot cut in the radial direction through one of the rails. A region around rounded corners of the stress riser has deep compressive residual stresses imparted by laser shock peening and extends inward from a laser shocked surface of the component encompassed by the region.

Abstract: A brush seal for an apparatus having a stationary member and a rotating member is provided comprising a seal element and a seal ring. The seal element includes a plurality of bristles and is attached to one of the stationary or rotating members. The seal ring is detachably attached to the other of the stationary or rotating members, aligned with the seal element. The seal ring may be readily detached from the stationary or rotating member and may be replaced in the event of mechanical damage to the seal ring by the seal element. The seal ring isolates the stationary or rotating member, to which the seal ring is attached, from mechanical damage caused by the seal element.

Abstract: A method of preventing galling between first and second metallic surfaces which are disposed in contacting, substantially stationary relation, one to each other, includes coating at least one of the first and second metallic surfaces with a layer of hard chromium plating.

Abstract: A retainer ring is arranged to mount turbine blades to a turbine disk so that aerodynamic forces produced by a gas turbine engine are transferred from the turbine blades to the turbine disk to cause the turbine blades and turbine disk to rotate, but so that centrifugal forces of the turbine blades resulting from the rotation of the turbine blades and turbine disk are not transferred from the turbine blades to the turbine disk.

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: The wheel comprises a central portion, or rim provided with blades at its peripheral portion and is made of a single piece of composite material formed by a fibrous reinforcement densified by a matrix. The fibrous reinforcement is formed from a helical fabric with radially oriented fibers and circumferentially oriented fibers. The density of fibers in a radial direction and the density of fibers in a circumferential direction varies along a radius of the wheel as a function of the variations of the radial stresses and circumferential stresses that are exerted on the wheel when it is in operation. At least part of the circumferentially oriented fibers in the rim are made of a material having high mechanical resistance, while at least part of circumferentially oriented fibers in the blades and at least part of the axially oriented fibers are made of a material having good resistance to high temperatures and chemical attacks.

Abstract: A rotor assembly for supporting rotor blades includes a plurality of axially adjoining discrete disks each having a rim. The rims include axial dovetail posts defining therebetween dovetail grooves for collectively supporting a respective blade dovetail therein. The disks are fixedly joined together by integral beams so that upon a crack failure of one of the disks, centrifugal load from the failed disk is transferred to an adjacent disk and crack propagation thereto is inhibited.

Abstract: The wheel (10), which is made from a composite material having a ceramic matrix comprises a hub that bears a drive gear (16) formed of teeth (20) that extend radially on one of the wheel's surfaces (10a). Each tooth is asymmetrical with respect to the meridian plane (21) that passes through its apex, and has first shoulder (20b) that subtends an angle a, preferably between 15.degree. and 45.degree., relative to that plane, and a second shoulder (20c) that subtends an angle b, preferably between 55.degree. and 85.degree., relative to that plane. Advantageously, the sum of the two angels is at least equal to 100.degree.. The turbine wheel has an improved resistance against inter-laminar shear stresses that result from tightening to a drive gear wheel.

Abstract: A ceramic turbo charger rotor having a bearing structure in which an inner race of an angular ball bearing and a spacer are assembled to a journal shaft as one unit in such a manner that one end of the spacer is assembled to a turbine-side connecting portion of the journal shaft by a pressure inserting manner and the other end of the spacer is assembled to a compressor-side connecting portion of the journal shaft by a clearance fitting manner. Therefore, the deviation between a center axis and a rotational axis of the rotor caused by the pressure insertion of the spacer is released at the compressor side and the amount of the unbalance before correcting of the rotor is remarkably reduced.

Abstract: A rotor blade includes a root, tip, leading edge, trailing edge, forward surface, and aft surface, and a pitch section disposed equidistantly between the root and tip. The blade has a forward sweep from at least the pitch section to the blade tip relative to incoming streamsurfaces of a fluid flowable over the blade.

Abstract: A turbocharger impeller has a lock ring that is flexed in assembly to clampingly center and lock an impeller wheel on its drive shaft. The lock ring is also applicable to other driving or driven shaft and wheel combinations. The lock ring is made part of a two-piece spacer for the illustrated rotor applications but is not limited to that arrangement. Alternative impeller wheel structures including drive means and locking nose cone features are included.

Abstract: The invention concerns a cowling for aircraft propulsion systems of the counterrotating propeller type. The cowling includes a pair of mounting rings located fore and aft of a propeller array. Removable panels extend between the mounting rings and contain openings through which the propeller blades extend.

Abstract: A ceramic-metal joined composite body including a ceramic member having a projection formed thereon, and a metallic member having a recess formed therein. The projection of the ceramic member is fitted into the recess of the metallic member, and a corner of a bottom of the recess has a rounded dimension such that R/D.gtoreq.0.04, in which R and D are the rounded dimension of the corner of the bottom of the recess and an outer diameter of the projection, respectively. The ceramic-metal joined composite body particularly is useful in a rotary shaft for a turbocharger rotor or a gas turbine rotor.

Abstract: A ceramic jointed body composed of two molded bodies which are individually molded by different methods, respectively, and integrally jointed by isostatic pressing, wherein a difference between "amounts of spring back" of the two molded bodies satisfies the formula ##EQU1## thereby preventing cracks from occurring in the jointed body.

Abstract: The invention relates to a connection system for connecting a ring which carries aircraft propeller blades to a turbine which the ring surrounds. Brackets extend between the ring and the turbine and accommodate thermal expansion of the turbine without significant deformation.

Abstract: This invention provides stream turbine components, such as rotor disc, which include a ring member comprising a low alloy ferrous base metal having less than about 6 wt. % alloy ingredients and a ferrous graded layer disposed on the ring member which includes a plurality of layered weldments having an increasing weight percentage of a layering metal containing Cr. Disposed on the graded layer of this invention is a Cr-containing steeple alloy disposed on the graded layer for optimizing a life extending property of the steeple region of the turbine component.

Abstract: A rotor attachment assembly for securing a rotor, such as a compressor impeller, to a rotor shaft. The assembly comprises a locking nut, a rotor having a flush mounting surface for the flush mounting of the locking nut, and a nut-receiving rotor shaft. The shaft comprises a smooth body and a threaded end which is of less diameter than the shaft body. The nut includes an unthreaded bore portion and a threaded portion. When the rotor is in place on the shaft, part of the smooth body extends beyond the nut flush mounting surface of the rotor. The bore portion of the nut is deeper than the length of the part of the smooth body extending beyond the rotor. Accordingly, when the nut is tightened onto the shaft to press against the rotor, a gap is left between the body of the shaft and the threaded portion of the nut. Coaxiality of the shaft and the rotor is assured by this construction which provides against bending of the shaft.

Abstract: A high temperature turbine engine includes a hybrid ceramic/metallic rotor member having ceramic/metal joint structure. The disclosed joint is able to endure higher temperatures than previously possible, and aids in controlling heat transfer in the rotor member.

Abstract: A joint structure for joining a ceramic member to a metallic member where the two members have substantially cylindrical end portions. The end portions are place in an abutting relationship and joining member adherent to both connect the two members. A sleeve member covers the joint and is affixed at least to the surface of the end portion of the device having a composition most like the sleeve member. Where the sleeve member is metallic, the surface of the sleeve member is affixed to the metallic portion of the device.

Abstract: Ceramic and metal shafts are joined at their ends by brazing, with a buffer member being interposed therebetween. The joined ends of the ceramic and metal shafts and the buffer member are received within a metal sleeve and joined by brazing to part of the inner circumferential wall of the metal sleeve in such a manner than an axial end of the joint where the inner circumferential wall is securely joined to the ceramic and metal shafts is positioned between opposite axial ends of the metal sleeve and at the same time between opposite axial ends of the ceramic shaft. The outer circumferential wall of the metal sleeve is formed with an annular groove in the place corresponding to the above mentioned axial end of the joint with respect to the axial direction of the metal sleeve.

Abstract: A fitting assembly having a ceramic piece fitted to a cup-shaped metal piece filled with solder. Through the use of the difference in thermal expansion coefficients of ceramics and certain metals, an assembly for properly gripping the ceramic by the metal cup is created.

Abstract: An improved boreless compressor wheel and method for making same by utilizing an internally threaded nut member. The compressor wheel is either cast about the nut, or includes a cup friction welded to the compressor wheel, and carrying the nut member.

Abstract: A high temperature turbine engine includes a hybrid ceramic/metallic rotor member having ceramic/metal joint structure. The disclosed joint is able to endure higher temperatures than previously possible, and aids in controlling heat transfer in the rotor member.

Abstract: A runner is provided which consists of a radial turbine ceramic rotor with an integrated ceramic shaft and a non-ceramic compressor impeller which are connected by a releasable, thermally and mechanically loadable mechanical coupling in such a way that the releasable mechanical coupling is located with the compressor impeller. This coupling consists of a cylindrical slotted sleeve which, on the one hand, is fitted into a cylindrical fitting bore in the compressor impeller and, on the other hand, accepts the end of the ceramic shaft in a fitting bore. In addition, the coupling has a tie rod with a screw thread and a pair of conical clamping elements between the cylindrical sleeve and the compressor impeller.

Abstract: A dual alloy gas turbine rotor is heat treated by HIP bonding a cast superalloy blade ring to a consolidated, powdered-metal hub. After bonding, the assembly is solution treated and aged at certain specific temperatures so as to optimize the mechanical properties of the dual alloy assembly for use in a high performance gas turbine engine.

Abstract: A method for manufacturing parts for rotary machines, especially turbine wheel disks, having a hub bore in a hub region, as well as turbine wheel disks manufactured by the method, includes pre-turning a contour at the hub region having a profile differing from a hub contour to be produced. At least the hub region is initially treated. At least the hub region having the pre-turned contour is cooled with a coolant fluid after the initial treatment to produce internal compressive strains in the hub region. The pre-turned contour is reduced after the cooling to the hub contour to be produced.

Abstract: A method for producing an outer stabilizing band or bands at the unsupported end portion of the air foils changes the configuration from an unsupported cantilevered airfoil to a baband supported airfoil during the forming of the mold and casting of the product. Such band or bands, which are later shaved away, permit dimensional stabilization and provide an outer wall for venting, fill-out, and inclusion trapping. The stabilizing band or bands are extremly thin, normally in the range of 20 to 60 one thousandths of an inch, which avoids the need for gating and minimizes the amount of machining required to remove such stabilizing band or bands from the integral airfoil and hub casting. The bands may be outside the end of the airfoil or flush with the ends of the airfoil. The procedure and method for incorporating the outer band or bands into the casting begins with the process of making the pattern. It also aids in the stabilizing of the configuration of the pattern thereby achieving more dimensional accuracy.