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 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: A driving connection is provided for torque transfer in the drive line of a motor vehicle for releasable connection of a crankshaft with a pump wheel of a coaxially mounted hydrodynamic torque converter in which the pump wheel is mounted so that it is rotatably supported integrally with the housing by a radial bearing.

Abstract: In a turbine having a rotor wheel with axially extending female dovetails spaced circumferentially one from the other about the circumference of the wheel, buckets having male dovetails at their radially inner ends are axially inserted relative to the rotor wheel to secure the buckets to the wheel. Where the buckets have shrouds at their radial outer ends prohibiting axial entry and assembly of the final or closure bucket onto the wheel, an axial entry dovetail segment having radially opposite male dovetails is employed to secure the final or closure bucket to the wheel. The final bucket includes a female dovetail at its radial inner end while the axial entry dovetail segment has radial inner and outer male dovetails.

Abstract: The invention provides a blade-rotating device for rotating a plurality of radially-oriented blades having a blade base with two grooved base sides. The device has a portion, such as a disc or a rotor disc of a turbine, for rotating the blades with the portion having an outer cylindrical surface. The device also has a plurality of steel steeples each having a steeple base and two opposite grooved steeple sides extending therefrom. Each of the opposite steeple sides complements at least one of the grooved sides of at least one of the blade bases. The steeple bases are linear friction welded to the outer cylindrical surface in an approximately longitudinal direction such that the blade bases are engagable with the steel steeples.

Abstract: A turbine rotor comprising a radially-inward portion of a steel alloy and a radially-outward rim portion circumscribing the radially-inward portion, the rim portion being formed by a weldment that includes a nickel-base superalloy region joining the rim portion to the inward portion of the turbine rotor, the nickel-base superalloy having a room temperature ultimate tensile strength of at least about 690 MPa.

Abstract: Damping disposition for vanes (3) fitted with stilts (4, 5) engaged in the alveoles of the rotor disk (1). Damping elements (10) are added including a portion (11, 12) extending along the flanks (6) of the stilts (4) and including a portion (15) leaning against them. The beating vibrations of the vanes (3) and dampened by these elements able to be used on smooth vanes without any platform, such as large blower vanes. Application for turbo-engines.

Abstract: A formed disc for use in a low pressure rotor has a rim made of a high alloy metal of between approximately 9% and 17% chromium. The rim can be annular in shape and slide onto the perimeter of an unformed disc for the two components to be fused together, thus fabricating a formed disc. Additionally, the rim can be split into a number of components and fused together on the perimeter of a rotor disc to form a complete rim. Further, an entire disc can be made out of the high alloy metal.

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 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 present invention relates to a monobloc rotor having a disk and hollow blades which are secured to the disk. The disk includes a protuberance and a projection on a periphery of the disk such that the projection forms a block having a shape which approximately corresponds to a shape of an inside of a radially internal extremity of the blade. The present invention further relates to a monobloc rotor in which a block is welded to the protuberance with the block forming a projection having a shape which approximately corresponds to a shape of an inside of a radially internal extremity of the blade.

Abstract: A refrigerant or coolant compressor of the radial type with an impeller hng a plurality of vane elements can be used for compressing water vapor as a refrigerant or coolant under vacuum conditions. The impeller of the compressor is constructed to produce a high volume flow rate at the required compression ratio, in view of the low density of water vapor as the preferred flow medium. The impeller has sufficient strength to operate at the required high circumferential velocities. The impeller includes vane elements, disk elements, vane support elements and a hub. The vane elements are individually connected to the hub by the support elements. The support elements may be either ring-shaped elements connecting a rear surface of the disk elements to the hub, or may be pin-shaped insert members connecting the root of each vane element to the hub. The components of the impeller are made of a polymer composite material reinforced preferably with carbon fibers.

Abstract: In a turbine, a plurality of blades are attached to a turbine wheel by way of a plurality of joints which form a rolling contact between the blades and the turbine wheel. Each joint includes a pin and a pair of rollers to provide rolling contact between the pin and an adjacent pair of blades. Because of this rolling contact, high stress scuffing between the blades and the turbine wheel reduced, thereby inhibiting catastrophic failure of the blade joints.

Abstract: A hybrid gas turbine engine rotor blade includes an airfoil and a dovetail integrally joined thereto. The airfoil includes an inner portion disposed adjacent to the dovetail to provide a structural transition, and an outer portion disposed thereabove for effecting a pressure rise in airflow channeled thereacross. A nosepiece is disposed adjacent to the leading edge of the airfoil inner portion, and a tailpiece is disposed adjacent to the trailing edge of the airfoil inner portion. The nosepiece, tailpiece, and airfoil inner portion are collectively aerodynamically configured for effecting a pressure rise in the airflow channeled thereacross.

Abstract: A variable pitch propeller blade system includes a conductive clevis attached to a rotor, a mating non-conductive clevis fastened to a non-conductive propeller blade, a pin journaling through bores in each clevis, joining the clevises to form a hinge joint, and a conductive path along a substantial part of the propeller blade.

Abstract: A disk attachment system for a high pressure turbine section of a gas turbine engine, the high pressure turbine section including a first stage disk and a second stage disk. The first stage disk includes a first conical aft shaft extending rearwardly from a bore of the first state disk and the second stage disk has a second conical aft shaft extending rearwardly from a bore of the second stage disk, and the second aft shaft is attached to the first aft shaft at a splined connection. The second aft shaft includes an arm having a mate face and pilot for centering the second stage disk relative to the first stage disk. Rotational energy from the second stage disk is transmitted through the first aft shaft to the first stage disk.

Abstract: Nonmetallic airfoil blades are mounted to a rotor disk via a circumferentially spaced array of metal support members. Each support member includes a pair or circumferentially spaced arcuate or airfoil shaped dovetail engagement surfaces. The metal support members are secured to the rotor disk via straight dovetails while the rotor blades are secured to the support members via airfoil shaped dovetails. The support members may include hollow portions for channeling cooling air to the airfoil blades.

Abstract: An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal therebetween. The thermal shield includes complementary hook members shaped to engage slotted hook members formed on the first stage disk to form a bayonet connection, and complementary lip members for engaging lobe members formed on the second stage disk by virtue of split rings, thereby eliminating the need for a bolted connection between the thermal shield and disks and facilitating attachment and removal of the thermal shield. The thermal shield includes an annular impeller which is positioned rearwardly of the first stage disk, the impeller including bayonet connection with the disk which restrains the impeller from axial deflection, but permits radial deflection in response to thermal changes.

Abstract: A rotor assembly for supporting rotor blades includes a plurality of axially adjoining discrete disks each having a rim, web, and hub. The rims include axial dovetail grooves for collectively supporting a respective blade dovetail therein. Each of the disks includes at least one axially extending annular arm joined integrally with the disk and fixedly joined to an adjacent one of the arms. The disks are fixedly joined together solely by the blade dovetails in the rim dovetail grooves and by the arms so that upon a crack failure of one of the disks, centrifugal load from the failed disk is transferred to an adjacent disk.

Abstract: A turbocharger includes a compressor wheel and shaft assembly in which a threaded connection is provided between the shaft and the compressor wheel. A pair of pilot surfaces on the shaft and on the compressor wheel are located on either end of the threaded sections of the shaft and compressor wheel, and are displaced radially from the threads. Accordingly, the piloting functions which assure concentricity between the shaft and compressor wheel are kept entirely separate from the attachment function provided by the threads, thereby permitting the concentricity between the compressor wheel and shaft to be held to tighter tolerances than would be possible if the threads also performed a piloting function.

Abstract: An improved compressor wheel assembly for a a turbocharger or the like includes a centrifugal compressor wheel having a boreless hub to substantially improve wheel fatigue life. The compressor wheel is formed as by casting from an aluminum alloy to include an integral mounting sleeve extending coaxially from the boreless hub and adapted for connection as by threading with a turbocharger shaft. An annular spacer ring of wear resistant material is mounted on the wheel mounting sleeve and defines wear resistant surfaces for supporting one or more seal rings within the bore of a compressor backplate opening, and for axially engaging an adjacent thrust bearing unit associated with the turbocharger shaft.

Abstract: To attach blades (5) on a rotor wheel for turbines or compressors, the wheel (1) has threads (2) running to the inside in a spiral shape on both sides of the outer edge. The blades (5) have segments on their feet (7) of counter-threads shaped accordingly. The threads are designed to have one turn, and their beginnings are staggered 180.degree. to one another on both sides of the wheel to offset inbalances. The threads on the wheel and on the blade feet there are self-locking and prestressed.

Abstract: An aircraft propeller system of the unducted fan type includes a plurality of propeller blades which are respectively fastened to a rotor, rotate about an axis of rotation and also rotate about a pitch axis. Each blade is fastened to the rotor by a hinge which has a pivot axis to reduce the effective stiffness of each blade, the pivot axis being non-parallel to the axis of rotation.

Abstract: A rotor blade (1) is disclosed which recenters itself in relation to the retention member (10) in which it is installed. Imposition of an external force (A) upon the rotor blade (1) creates a moment (M) which acts about the rotor blade's root (3). Recentering is accomplished by centrifugal forces acting through an offset distance (C") resulting from an off-center rotation of the blade and its captivated shaped retaining pin (6) within a plurality of retention member tenons (12), achieving an enhanced opposing restorative moment (M'.sub.R) on the rotor blade (1). The retention member tenons (12) contain arcuate bearing surfaces (8) which bear against a corresponding arcuate surface (9) with a smaller radius of curvature lengthwise disposed on the shaped retaining pin (6).

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: An apparatus and method are provided for preventing axial movement of a disc along the shaft on which it is shrunk. The apparatus features a set of arcuate retainers having one portion disposed in a circumferentially extending groove in the disc face and another portion disposed in a circumferentially extending groove in the shaft outer surface. The retainers are installed by inserting them one at a time into an entry slot in the disc adjacent the groove. The last retainer is a locking retainer and is attached to a closure piece by locking screws threaded into two holes drilled at the intersection between the closure piece and locking retainer so that one half of the circumference of the hole is formed in the closure piece and the other half of the circumference of the hole is formed in the locking retainer.

Abstract: A laminated airfoil for use in a high bypass engine. The airfoil preferably has a large tip chord and is comprised of alternating layers of thin metallic foil and elastomeric layers. The exterior surfaces of the airfoil are comprised of a thin, metallic foil. The airfoil also has a metal sheath secured to the leading edge. High strength metal members extend through the dovetail root sections.

Abstract: In an aircraft propeller which can change in pitch, each propeller blade is mounted upon a hinge, which reduces the effective stiffness of each blade. The angle of the hinge pin can be constructed such that the angle between torsional and flexural nodes is favorable.

Abstract: An integral control stage blade group for use in a steam turbine having a rotor, the rotor including radially extending flanges provided with opened and smooth faces defining at least one pair of spaced annular grooves. The blade group comprises a plurality of blades attached to a unitary platform. Secondly, the blade group comprises a plurality of root portions depending from the platform in a direction opposite from the blades. The root portions extend along the platform in a circumferential direction when said blade group is mounted on the rotor. Each of the root portions fits within a respective one of the annular grooves in the rotor. Finally, the blade group comprises at least three spaced apertures formed in said root portion and arranged to align with corresponding apertures in the rotor flanges when the blade group is mounted on the rotor.

Abstract: A structural arrangement for detecting improper positioning between a hub. The structural arrangements utilize a bore which axially penetrates a stepped-down end portion of the shaft to receive a fastening means by which the hub may be secured to the shaft. A blocking bore extends radially through the stepped-down end portion of the shaft to communicate between the bore and the exterior of the shaft. A blocking member is received within the blocking bore and is movable radially therealong. A cam flange extends radially inwardly from the hub member and presents a blocking surface and a releasing surface on the radially inner extent thereof. The blocking surface is disposed in radial opposition to the blocking bore when the hub member is improperly positioned with respect to the shaft and the releasing surface is disposed in radial opposition to the blocking bore when the hub member is properly disposed with respect to the shaft.

Abstract: A retention system for a rotor blade (10) utilizes the combinatioin of a fixed retention flange (13) and a removable retention plate (16) with a closed-sided retention member (12). This system enables the rapid replacement or removal of the rotor blade (10) for inspection, maintenance, or replacement purposes without requiring removal of surrounding major engine components or structural members. The rotor blade (10) is installed in a retention member (12) contained in a rotatable hub (not shown) by inserting an outwardly extending portion (20) of a shaped blade root (22) of the rotor blade (10) below a radially-inwardly projecting shaped flange (13) peripherally disposed within the interior of the retention member's structure. A removable shaped retention plate (16), which is releasably secured to, and adapted to mate with, the retention member (12), then captures and secures another outwardly extending portion (21) of the shaped root of the rotor blade (10) with a releasable fastener (18).

Abstract: The normally multi-part gas turbine engine labyrinth seal outer portion which carries an abradable lining, is formed from a single piece and has a groove machined in its periphery for the receipt of the feet of respective stator vanes. Pins are fitted in pairs through the walls of the groove to provide lateral location for the feet. The pins and a groove liner are made from an anti-frettage material.

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 rotatable shaft assembly comprises a shaft having a generally cylindrical first section and a generally cylindrical second section. The diameter of the first section is greater than the diameter of the second section. A shoulder having a generally annular face extends between the first and second sections of the shaft. A member to be mounted on the shaft, such as an impeller blade, has a face and an axial bore sized to receive the second section of the shaft and is adapted to confront the face of the first section of the shaft when the member is mounted on the shaft. The member is secured against rotation relative to the shaft by a plurality of pins. Each pin comprises a pin head and a pin shaft formed integrally with, and extending generally perpendicularly from, the pin head. A plurality of bores are formed radially symmetrically in the second section of the shaft proximate the first section and adapted to securely receive the pin shafts in a press fit.

Abstract: A rotor blade (1) is disclosed which recenters itself in relation to the rotatable hub in which it is installed. Imposition of an external force (A) upon the rotor blade (1) creates a moment (M) which acts about the rotor blade's root (2). Recentering is accomplished by centrifugal forces acting through an offset distance (C) resulting from rotation of the blade root (2) about a shaped retaining pin (6), achieving an enhanced opposing restorative moment (M') on the rotor blade (1). The rotor blade (1) contains an arcuate bearing suface (8) within a chordwisely disposed slot (7) in the rotor blade's root (2). This arcuate surface (8) bears against a mating arcuate surface (9) with a smaller radius of curvature lengthwise disposed on the shaped retaining pin (6).

Abstract: An improved compressor wheel assembly for a turbocharger or the like includes a centrifugal compressor wheel having a boreless hub to substantially improve wheel fatigue life. The compressor wheel is formed as by casting to include an integral and internally threaded mounting sleeve extending coaxially from the boreless hub. In the assembly, the mounting sleeve extends through an opening in a compressor backplate for threaded connection to a turbocharger shaft, with a thrust collar spacer being interposed between axially facing shoulders defined respectively on the mounting sleeve and shaft to ensure accurate axial positioning of the components. An annular seal flange on the thrust collar spacer extends axially into the backplate opening in generally concentric spaced relation about the mounting sleeve. This seal flange is adapted to carry one or more seal rings for engaging the backplate, thereby sealing the passage of the mounting sleeve and shaft through the backplate opening.

Abstract: A circular hole through which a main shaft of a fuel pump is inserted is defined at the central portion of an impeller, one or plural pin holes are so defined around the circular hole that the centroidal position is not deviated from the rotational central axis, a first engaging portion is formed at an end of the main shaft to be inserted into the impeller, and a coupler provided with a second engaging portion which engages with the first engaging portion and a pin or pins to be inserted into the pin holes is used to secure the impeller to the main shaft. These members are so arranged that the impeller and the coupler are located respectively in point or line symmetry with respect to the rotational central axis of the armature in the pump or the main shaft, i.e. the respective centers of gravity of the main shaft, impeller and coupler are positioned on the rotational central axis of the armature in the pump so that the armature keeps its balance.

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 gas turbine engine rotor (18) and shaft (28) are secured against radial loosening between the shaft (28) and axially spaced rotor spigots (24, 26) by annular spacer rings (42, 43) which are fabricated from a material having a thermal coefficient of expansion significantly higher or lower than the thermal coefficients of the shaft (28) or rotor (18). The ring (42, 43) is pre-assembled during production of the engine in an interference fit with either the rotor hub (22) or the shaft (28), being sized to remain tight with the pre-assembled member over a range of operating temperatures, and becoming more tightly fit with the other member due to differential thermal expansion therebetween.

Abstract: A cylindrically shaped spacer between a shaft and hub of a turbine rotor of a gas turbine engine as fabricated from a flexible resilient material and interference fitted at discrete points on either side of the transverse axis of the spacer between the shaft and spacer and between the hub and spacer to impart a twist of the spacer about this axis to remain in contact with the hub and shaft throughout its entire rotating envelope.

Abstract: A composite support disc for a row of fan blades in a bypass turbine engine in which the ring is made up of plies of high strength fibers so oriented as to carry the loading developed on the ring by the fan and with the fan blades mounted to minimize the loading on the composite disc. The orientation of the fibers are different in selected areas of the disc to provide a high strength disc with a minimum weight.

Abstract: An improved rotary machine such as centrifugal type compressor adapted to rotate under high load of the type including a plurality of impellers fixedly mounted (shrinkage-fit) on a main shaft. To effectively inhibit the rotor from vibrating due to loosened fitting of the impellers onto the main shaft the improvement consists of each of the impellers being provided with a sleeve portion which is made integral with the impeller. The sleeve portion is located at a position removed from the main part of the impeller along the axial direction of the main shaft with the position being determined in accordance with the theory of strength of materials in such a manner that displacement of the impeller in the radial direction due to centrifugal force resulting from rotation of the rotary machine has no effect on determination of the position of the sleeve portion, wherein the sleeve portion is shrink fit onto the main shaft of the impellers.

Abstract: A rotor assembly 10 having a coolable rotor blade 14 for a gas turbine engine is disclosed. Various construction details are discussed which enable the rotor blade to satisfy the aerodynamic requirements of the engine and the requirements of fatigue life for the rotor assembly. The rotor blade includes a spar 38 and a shell 34 which extends chordwisely beyond the root 42 of the spar. In one embodiment, an axis of symmetry A.sub.r of the root of the spar is parallel to the axis of rotation A of the rotor assembly.

Abstract: A fan drive system comprising a main drive shaft 13 which drives the fan through a frangible coupling 27 and an auxilliary drive shaft 30 which by-passes the coupling 27. The auxilliary shaft 30 is pre-twisted elastically in the opposite direction to the direction of rotation of the main shaft 13, and is held in the pre-twisted state by the coupling 27. When the coupling 27 disconnects the drive from the main shaft 13, for example when the fan becomes unbalanced and transverse loads exceed a predetermined magnitude, the auxilliary shaft 30 unwinds. Unwinding of the shaft 30 cushions the fan against suddenly applied loads when the coupling 27 breaks and also reduces the loads on the coupling 27 during normal balanced running.

Abstract: A rotor assembly comprising a drive shaft 13 mounted in a first bearing means 22 at a location spaced from a first end of the shaft 13 and supported at the first end by a support means 23 which is more flexible in bending and in torsion than the drive shaft 13. The support means 23 is mounted for rotation in a second bearing 24 which is co-axial with the first bearing 22. A rotor 10 is connected to the first end of the drive shaft 13 to be driven thereby, and is also supported directly in the second bearing means 24 through a frangible coupling 33. The frangible coupling 33 is designed to break the connection between the rotor 10 and the second bearing means 24 only when the rotor 10 is subjected to a predetermined out-of-balance load to allow the rotor 10 and drive shaft 13 to run inverted.

Abstract: A mounting arrangement for the fan rotor of a ducted fan engine includes a first drive which supports and rotates the fan under normal operating conditions but which includes a frangible connection which breaks when an excessive out-of-balance force is applied to the fan rotor for example after loss of one or more blades. A second supporting and driving structure is provided which has built-in transverse flexibility but which can transmit torque. This structure is redundant during normal operation of the engine but comes into use when the frangible connection is broken and allows the fan rotor to rotate eccentrically around a new axis in an inverted condition.

Abstract: A mounting arrangement for the fan rotor of a ducted fan engine includes a first drive which supports and rotates the fan under normal operating conditions but which includes a frangible connection which breaks when an excessive out-of-balance force is applied to the fan rotor for example after loss of one or more blades. A second supporting and driving structure is provided which has built-in transverse flexibility but which can transmit torque. This structure is redundant during normal operation of the engine but comes into use when the frangible connection is broken and allows the fan rotor to rotate eccentrically around a new axis in an inverted condition.