Abstract: A steam turbine different material welded rotor, constructed by rotors of different materials being jointed together by welding has the strength of a jointed portion increased and inspection of the jointed portion facilitated. A bearing portion rotor 1 and high temperature portion rotor 2 are jointed at weld portion A, the high temperature portion rotor 2 and low temperature portion rotor 3 at weld portion B and the low temperature portion rotor 3 and bearing portion rotor 4 at weld portion C. Cavity portions 5, 6 are formed in the weld portions B, C, respectively. Inspection holes 7, 8 are also provided in the weld portions B, C. The high temperature portion rotor 2 is made of high heat resistant 12Cr steel and other rotors are made of low alloy steel, wherein the rotor 1 is of 2.multidot.1/4 CrMoV steel and the rotors 3, 4 are of 3.multidot.1/2 NiCrMoV steel.

Abstract: A steam-cooled type gas turbine has flange contact surfaces between adjacent rotor disks in which buffering sheets such as gaskets and the like can not be inserted. Further, the contact surfaces have a large diameter, making it difficult or impossible to ensure sufficient surface contact pressure for sealing. Yet preventing the leakage of coolant steam from these flange contact surfaces presents a very important problem. The present invention provides a seal structure for flange contact surfaces of a gas turbine which can enhance the sealability at these portions. The seal structure for flange contact surfaces includes a plurality of labyrinth-like grooves (8) which are formed in at least one of the flange contact surfaces (7). The seal structure of the present invention provides a gas turbine with high reliability and enhanced sealability. Further, a high surface contact pressure is obtained by reducing the area of the flange contact surfaces.

Abstract: In a turbine rotor, a thermal mismatch between various component parts of the rotor occurs particularly during transient operations such as shutdown and startup. A thermal medium flows past and heats or cools one part of the turbine which may have a deleterious thermal mismatch with another part. By passively controlling the flow of cooling medium past the one part in response to relative movement of thermally responsive parts of the turbine, the flow of thermal medium along the flow path can be regulated to increase or reduce the flow, thereby to regulate the temperature of the one part to maintain the thermal mismatch within predetermined limits.

Abstract: A turbomachine, especially a steam turbine, includes a casing, an inflow region formed at least in part by the casing for guiding working fluid, a feed for a cooling fluid, a rotating-blade carrier disposed in the casing and extending along a principal axis, and a shielding element disposed in the inflow region for shielding the rotating-blade carrier from the working fluid. The shielding element is attached to the casing by a mounting and the feed is guided through the mounting. A method is also provided for cooling one or more components of a turbomachine adjoining an inflow region for a hot working gas.

Abstract: A tandem blade lattice having characteristics enhanced is provided. In a high pressure ratio blade lattice, inevitable generation of an shock wave is shifted, as much as possible, toward a rear portion of an upper surface of a front blade to inhibit separation from a blade surface from being caused by interference of the shock wave and a boundary layer, and boundary layer control is performed such that a speed, a momentum and the like of a jet flowing from a trailing edge of a lower surface of the front blade onto an upper surface of a rear blade are regulated to obtain a flow along the upper surface of the rear blade, so that separation of the boundary layer on the upper surface of the rear blade is restricted to a vicinity of a trailing edge.

Abstract: A seal device between a fastening bolt and a bolthole in a gas turbine disc reduces cooling steam leaking from a gap between the fastening bolt and the bolthole. A gas turbine disc 31 carrying moving blades, a fastening bolt 33 for fixing the disc 31 passes through a bolthole 32. On a low pressure side of the disc 31, a bolthole diameter enlarged portion 39 having a larger diameter than that of the bolthole 32 is provided. Fastening bolt 33 is provided with a shaft diameter enlarged portion 33a. Seal piece 1 is fitted at one end around the shaft diameter enlarged portion 33a and is engaged at the other end with a stepped portion of the bolthole diameter enlarged portion 39. In operation of the gas turbine, the bolt 33 is biased outwardly be centrifugal force, and the gap between the bolt 33 and the bolthole 32 deforms. Nevertheless, the seal piece 1, having flexibility, deforms at bent portions R.sub.1 and R.sub.

Abstract: A gas turbine rotor, in which a plurality of discs having teeth of a bevel gear are juxtaposed to engage the teeth and are integrally fastened by a bolt extending through the discs, so that the discs may be cooled by feeding cooling air to the air passages of the individual discs sequentially at the running time, is provided whereby the cooling air is prevented from leaking by means having no wear.

Abstract: A tandem turbine-blade cascade for a turbine, turbo-engine or power engine includes at least two rows of blades disposed substantially directly in line with one another in the rotor or stator. The second row of blades has a larger number of blades than the first row of blades and the second row of blades are distributed nonuniformly. The spacing (s.sub.1) between two blades of the first row of blades is substantially equal to the sum (s.sub.2) of two successive blade spacings (s.sub.12, s.sub.22) in the second row of blades and the distribution quotient (s.sub.12 /s.sub.22) of the blade spacings in the second row is in the range between 0.4 and 1.0.

Abstract: A baffle plate (12A) is constructed such that two belt-like elements, bent in a warped arc, are joined by spot welding (13) or brazing (14) at a central portion thereof along a central circumferential portion. Thus, even if there is a difference in a radial directional deflection of grooves (11) between adjacent discs (9), the baffle plate (12A) will maintain close contact with the inner surfaces of the grooves (11) due to a spring effect and gas leakage is thereby prevented.

Abstract: An arrangement for the thermal protection of a rotor, fitted with moving blades, of a high-pressure compressor. The roots of the moving blades are inserted and locked in peripheral grooves which are at an axial distance from one another. The rotor has, between two adjacent peripheral grooves for the moving blades, at least one further peripheral groove having a hook extending over the entire periphery of the rotor. At least two plate-shaped heat-accumulation segments, each having at least one root which has a contour adapted to the hook of the rotor so that both form a contact area, are pushed radially one after the other into the further peripheral groove and locked therein. A cavity forming an insulating layer extends between the heat-accumulation segments and the rotor and between the moving-blade roots and the rotor, in which insulating layer the velocity of the compressor air is greatly reduced.

Abstract: In a sealing arrangement between two discs of a gas turbine engine a split sealing arrangement comprising a pair of sealing formations each made up of a plurality of sealing segments is provided. Each of the segments has a root accommodated in serrations of the discs. The roots of the sealing segments are positively connected to roots of the rotor blades by dovetail or T-shaped tongues and grooves. The sealing segments are also provided with internal cooling passages.

Abstract: The inter-disk cavity between turbine rotor disks is used to pressurize cooling air. A plurality of ridges extend radially outwardly over the face of the rotor disks. When the rotor disks are rotated, the ridges cause the inter-disk cavity to compress air coolant flowing through the inter-disk cavity en route to the rotor blades. The ridges eliminate the need for an external compressor to pressurize the air coolant.

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 reinforced rotor disk assembly includes a rotor disk having a rim, hub, and web therebetween. The web includes at least one annular extension spaced radially inwardly of the rim. A plurality of rotor blades extend outwardly from the rim. And, a reinforcing ring is disposed radially around the extension for restraining radial outward growth thereof to react centrifugal load in the disk. The reinforcing ring preferably includes a plurality of circumferentially extending structural fibers in a corresponding matrix for carrying hoop loads therein.

Abstract: A compressor rotor includes a rim having airfoils extending radially outwardly therefrom, and a corresponding web and hub extending radially inwardly. A row of curvic coupling teeth extends axially away from one end of the rim. An imperforate support ring extends radially inwardly from the rim end for carrying hoop loads. And, a balance ring extends radially inwardly from the support ring, and includes a balance notch circumferentially splitting the balance ring.

Abstract: A work reducing composite engine system that uses ambient air for a primary energy source. The device consists of a unitary turbine/compressor assembly utilizing a turbine for producing work output and a downstream compressor for receiving fluid exhaust of the turbine and for compressing the turbine exhaust. An internal heat exchanger is provided between the turbine and the compressor so that fluid in the compressor is cooled, thereby reducing compression work requirements and the turbine exhaust is heated by the compressor, thereby decreasing input heat requirements.

Abstract: Turbines having rotor blades (3, 5) fixed in dovetail grooves (14) in the rotor periphery have bridge pieces (17) which provide in effect a false floor to the inter-stage recess (8, 11) to close off the machining recess from the fluid path. This invention provides a method of fixing this bridge piece which is simple, positive and avoids loading the rotor disc rims with additional centrifugal force. The dovetail groove (14) for the blade root is continued into a raised portion or the rotor recess periphery. This raised portion is grooved circumferentially (21) and the stem (19) of the `T` section bridge piece fits snugly in the groove. A dovetail section key (23) is inserted through the blade root dovetail groove (14) and into the raised portion of the rotor, passing through a hole in the stem (19) of the bridge piece. The latter is thus positively located and locked in position.

Abstract: Particulates are removed from the coolant used to cool gas turbines by subjecting the coolant to the centrifugal acceleration of the gas turbine rotor. Axially oriented channels are formed in the rotor at a radial distance from its longitudinal axis. The channels are in fluid communication with a coolant supply passage so that coolant coming onboard the rotor will first pass through the channels. The high centrifugal force produced by rotor rotation causes particulates in the coolant passing through the channel to move radially outward and deposit on a fixed surface in the channel. Thus, the particulates are collected in the channel and removed from the coolant discharged from the channel. The channels may be provided with removable liners.

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: A multi-stage centrifugal pump has a shorter shaft length compared to conventional multi-stage pump with the same number of impellers on the drive shaft (e.g. about 17-28% shorter length). The shorter length is obtained by utilizing first and second annular slide bearings. Adjacent at least one end (and preferably both) of a rotatable elongated shaft of the pump (which mounts the impellers) within a casing the first slide bearing is mounted to a stationary end structure while the second slide bearing is mounted to the shaft for rotation with it. A plurality of O-rings may be provided to mount the second slide bearing to the shaft. A sleeve with shoulder engaging opposite ends of the second slide bearing may be provided, and the slide bearings may have a clearance of about 0.04-0.1 mm between them, with a lubricant in the clearance. A labyrinth seal is typically provided in the most remote shoulder.

Abstract: Power generation turbines having different power outputs for different power grid frequency applications have modular second and third stages, rotors, bucket wheels for all stages and other ancillary parts. The first and second turbines have sizes not geometrically scaled according to speed. Four-stage turbines having different outputs for different power grid frequencies not geometrically scaled have an identical annulus through the first, second and third stages, different geometry in the first and fourth stages, and identical geometry in the second and third stages.

Abstract: The gas turbine has a bladed rotor welded together from a plurality of disks. Hollow spaces are present between the disks and axial passages are present in the periphery of the rotor between the rotor surface and platforms formed by the rotor blades and segmental heat barrier plates. In accordance with the invention, these axial passages are fed with cooling air from at least one hollow space between two rotor disks. The at least one hollow space is in connection with the axial passages mentioned, preferably by of connecting openings. It is fed from a central cooling air supply passage starting from the downstream end of the rotor. The cooling air is preferably tapped from the cycle air at the central part of the compressor so that low-pressure cooling occurs.

Abstract: Turbomachinery rotor components having a metallic body with at least a portion of the body subject to a tensile stress field due to centrifugal and thermal growth induced forces generated by the rotor when the rotor is rotating, at least one stress riser in the stress field portion that causes stress concentration when the rotor is rotating, and at least one region of the component around the stress riser having deep compressive residual stresses imparted by laser shock peening (LSP).

Abstract: The span of the overhung flanges at the rim of the disks of gas turbine engine's compressors are minimized by slotting the one of the adjacent flanges at the distal end to receive the bolt head of the attaching bolt and including an anti-rotational clip allowing the nut to be fastened without the necessity of holding the bolt head. The complementing flange of the adjacent rotor includes mating holes. The anti-rotational clip includes bendable tangs bent in situ to engage the flats of the bolt head and a bent tang to fit snugly into the when radially inserted therein slot.

Abstract: In an assembly of spaced rotor discs, mounted to rotate about a common axis, one or more discs are provided that are removably joined to the other discs but so joined, away from potential fatigue points in the disc webs. Thus a pair of discs have a spacer arm extending therebetween in contact therewith. Further, each disc of such pair, has a flange that extends between the discs toward the flange of the other disc, which flanges (and thus the discs) are removably bolted together at a junction removed from the disc webs for greater disc durability and lower replacement costs thereof. The so joined flanges and spacer arm (which is held in a piloted joint under compressive pre-load) define an annular cavity around a pair of the discs and thus redundant structural support therebetween.

Abstract: An axial retention system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk and a second stage disk. The interstage seal includes a web portion having an aft arm extending from said web, the aft arm having a peripheral rim adjacent the second stage disk. The axial retention system comprising a split ring having two overlapping ends and a plurality of radially outwardly extending tabs for engaging a plurality of inwardly extending tabs located on the second stage disk adjacent the peripheral rim, in a bayonet connection. The retaining ring is located within a slot formed in the peripheral rim and the outwardly extending tabs are positioned in a passageway formed by the disk tabs.

Abstract: A drum rotor for an impulse steam turbine having moving wheels constituted by rotor blades whose roots are provided with dovetails are locked in dovetail shaped grooves formed in the rotor. The grooves are longitudinal over at least a portion of the rotor. The roots of the blades of a moving wheel are separated from the roots of the blades of an adjacent moving wheel by dovetail shaped spacers. An optimum filling of the longitudinal grooves is effected for better interconnection of the caps of the rotor blades.

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: There is provided a rotor arrangement comprising primary blades 16 mounted on a support disc 15 and secondary blades 18 mounted on a support disc 17. The secondary blades are disposed between respective primary blades with some axial overlap. The set of secondary blades is movable relative to the set of primary blades so that each secondary blade can be moved between end positions abutting the associated pair of primary blades.

Abstract: In a drum rotor for an axial flow turbomachine, the blades are fastened via their roots (22) in circumferential blade grooves (1-13) with support indentations at the side. A circumferential forward groove (0), which is not fitted with blades, is located upstream of the first blade groove (1). This forward groove (0) is fitted with axially split closing segments (24).

Abstract: A rotor disk assembly includes rotor disks and structural spacer arms adapted to transmit axial loads and bending moments between adjacent disks. The spacer arms include cooling fins for convective cooling of the spacer arms. The spacer arm is preferably a self supporting wheel structure. The cooling fins are preferably circumferentially continuous and extend radially into a relatively cooler rotor bore cavity in which the disk hubs are supported. The cooling fins can be positioned on the spacer arms to reduce thermal distortion of the spacer arms, and thereby reduce bending stresses transmitted to the disks. The spacer arm includes a body section adjacent a relatively higher temperature seal cavity, which can be purged by cooling air from the relatively lower temperature rotor bore cavity.

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 means 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 slip joint connects coaxially oriented tubular members in a manner to allow axial slippage while maintaining concentricity without generating large axial loads. The joint comprises a first tubular member having a smaller outside diameter than an inside diameter of a second member whereby the first member is slidable into the second member. A pair of spaced lands circumscribe the first member and define a groove therebetween. The slip joint has a seal ring position in the groove. The lands have a plurality of circumferentially spaced nodes extending radially outward so as to contact the inner diameter of the second member.

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 gas turbine engine compressor module subassembly construction and associated assembly method and tooling includes a threaded inner bore on the first stage compressor adapted to receive a tubular tool that slips axially between the compressor bores and the engine central shaft. Securement of the accessible tooling to the module's stationary structure permits assembly and handling of the module independently of the engine shaft.

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 turbine support assembly includes a turbine rotor joined to a fan shaft through a support shaft. The support shaft is joined to the fan shaft in a V-configuration having first and second legs joined together at an apex and inclined axially apart, with at least the first leg forming an integral part of the fan shaft. The second leg is rotatably supportable to a frame. The V-configuration increases the stiffness of the turbine support to reduce blade tip clearances. The present invention also provides an annular integral bolt heat shield and axial retention apparatus to axially retain bolts used for holding together two rotor elements during assembly when the bolts are otherwise subject to sliding into a closed cavity of the assembled engine or one of its modules.

Abstract: The present invention provides for the removable attachment of sealing segments about the entire circumferential periphery of the rotor spacer discs. To this end, the conventional annular grooves provided in the peripheral surface of each spacer disc (as part of the high/low sealing surface configuration) are reconfigured as dovetail grooves which are designed to receive complimentary or mating portions of the sealing segments. In other words, each adjacent annular groove receives a plurality of sealing segments, the totality of which substantially prevent or at least minimize the impingement of hot gases directly on the peripheral surface of the spacer disc.

Abstract: A connection between flanged elements of a gas turbine engine rotor. The connection includes a first annular flange on a first rotor element having a plurality of radially outwardly opening slots, an annular locking ring having a plurality of bolt holes, a second annular flange on a second rotor element, and a plurality of bolts each having a shank with a head at one end and a screw thread at the other end and a locking shoulder therebetween. The bolts are installed radially in the slots so that minimum clearance is required behind the first annular flange. The locking ring fits over the bolt shanks and is press fitted onto the locking shoulders of the bolts so that radial and axial dislodgment of the bolts from the slots is foreclosed. The second annular flange is fitted over the bolt shanks and nuts are screwed onto the bolts to retain the second annular flange.

Abstract: A high temperature turbine engine includes a rotor portion having axially stacked adjacent ceramic rotor parts. A ceramic/ceramic joint structure transmits torque between the rotor parts while maintaining coaxial alignment and axially spaced mutually parallel relation thereof despite thermal and centrifugal cycling.

Abstract: A gas turbine engine rotor having a turbine on a tubular shaft of the rotor and a compressor rotating group adapted for attachment to the shaft. The shaft has a radial flange at one end with an annular face in a plane perpendicular to the axis of the shaft and interrupted by a symmetrical array of bolt holes. The compressor rotating group has an annular face juxtaposed the annular face on the shaft and interrupted by a corresponding symmetrical array of bolt holes. An adjustable annular shim pack consisting of a pair of identical wedge-shaped annular shims is disposed between the juxtaposed annular faces and is adjusted by relatively rotating the shims until the wedge angle of the shim pack equals the angle between the planes of the annular faces when the longitudinal axes of the shaft and compressor rotating group are collinear. The compressor rotating group is bolted to the shaft with the shim pack captured between the juxtaposed annular faces.

Abstract: A segmented seal (36) is provided for sealing between two adjacent rotor disks (18, 20). The individual segments (36) includes sideplate members (42, 44) and integral hook members (50, 52) which engage the facing sides of the respective disks (18, 20). Strut members (60, 62) support the central portion (64) of the axially and circumferentially extending wall members (40) which collectively establish the radially inner gas boundary for an annular working fluid stream (30).

Abstract: A gas turbine rotor warming structure comprises a tubular member having an axially extending central through hole and a plurality of fine holes formed in a side wall thereof. The tubular member is inserted in central holes of rotor disks each having blades so as to form an annular gap between the inner surfaces of the central holes and the outer surface of the tubular member. The plurality of fine holes of the tubular member are formed so as to face the inner peripheral surface of the central holse of the rotor disks, so that gas extracted from a compressor is injected into the annular gap through the fine holes and impinges on the inner peripheral surfaces of the rotor disks, whereby inner peripheral portions of the rotor disks are warmed at the time of starting of the gas turbine. The extracted compressor gas which has warmed the inner peripheral portions of the rotor disks passes between the disks and cools the turbine blades.

Abstract: Tie bolt 10 has a reduced shank 34 and a tapered head 50. A split sleeve 38 has a complimentary flare 46 at the head end and surrounds the shank 34. The sleeve accepts shear loading and the tie bolt accepts shock axial loading with low stress concentrations in highly stressed areas.

Abstract: The present invention relates to a fastening spindle and a method of attaching the rotor elements together utilizing the spindle. The system according to the invention reliably permits the visual inspection of the rotor assembly and to determine if it is properly tightened without the need for any additional post assembly inspection. The fastening spindle according to the invention has a central portion having a generally oblong cross-section with a first, major transverse dimension d.sub.1 which is greater than a second, minor transverse dimension d.sub.2 ; a first cylindrical portion which extends from the central portion in a first direction, the first cylindrical portion having a threaded distal end and a diameter d.sub.3 such the d.sub.3 is less than d.sub.2 ; and a second cylindrical portion extending from the central portion in a second direction, the second cylindrical portion having a threaded distal end and a diameter d.sub.4 such that d.sub.4 is less than d.sub.2.

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

Abstract: A gas turbine engine disc having integral, radially extending aerofoil blades and an integral shroud interconnecting the radially outer extents of the blades is described. In the manufacture thereof continuous fibres are wound around an annular array of inserts provided in a dividable disc. The inserts define the spaces between adjacent blades on the disc. A mixture of chopped carbon fibre and an epoxy resin matrix material is then injected into the central portion of the die interior. Any part of the wound fibres which has not been impregnated by the chopped fibre/resin matrix material is subsequently impregnated by a matrix material whereupon the die is opened to release the thus produced bladed disc.

Abstract: A rotor has an inner disk member including a web and a circumferential widened outer portion. A blade member has a continuous circumferential inner edge. At least one of the members has a plurality of axially spaced circumferential rings extending toward the other member. The two members are diffusion bonded together. A stiff lightweight assembly is achieved.

Abstract: The centrifugal pump has a pair of multi-stage sub-blocks wherein the impellers are shrink fitted onto the shaft. The impellers on the drive-side sub-block have shrunk fit regions in the side away from the inflow while the shrunk fit regions of the impellers remote from the drive are located on the inflow side. The shaft is made with a reduced shaft section to receive the impellers of the remote sub-block and permit the hubs of the impellers of this sub-block to be radially enlarged for shrink-fitting purposes. A center piece which separates the sub-pumps is connected via screw bolts and nuts with the last guide wheel of the drive-side sub-block.

Abstract: A compressor rotor assembly comprises a shaft and at least one disc having integral radially extending aerofoil blades which disc is integral with the shaft. The assembly comprises a matrix material in which a plurality of short reinforcing fibres are so disposed that the majority thereof within the shaft are generally axially aligned while the majority thereof within the aerofoil blades are generally radially aligned. At least one filament wound support ring provides radial support for the aerofoil blades.