Abstract: A multifunctional labyrinth seal support disk for a turbojet engine rotor is disclosed which also serves to axially lock the rotor blades onto the rotor wheel. A radial support disk has a generally conical, labyrinth seal means extending from the disk in an upstream direction and a conical collar extending from the disk in a downstream direction. The collar has a generally annular bearing surface which bears against an upstream side of the rotor blade roots. Several blade-retaining teeth extend from the collar in a downstream direction and are dimensioned so as to fit within axial grooves between the blade root and the rotor blade wheel. Radially extending spurs bear against the downstream portion of the rotor blade root to axially lock the rotor blade onto the disk. An attaching ring is interposed between the blade retaining teeth and the rotor blade wheel so as to axially lock the multifunctional disk with respect to the rotor blade wheel.

Abstract: The sole support for the rear disk rim side plate of the 1st turbine stage is the seal extending between the 1st and 2nd stage turbines. The fir tree broach on the side plate fits into the broached rim of the turbine disk which is extended axially to radially restrain each side plate. This configuration eliminates the heretofore used bolts and nuts or rivets.

Abstract: A rotor assembly for a gas turbine engine has platformless blades and the inner wall of the compressed air annulus is made up of separate annulus members bridging the spaces between pairs of adjacent blades. The invention provides salient feet on the annulus members which are fitted through the narrow necks of re-entrant grooves in a direction radially inwardly of the rotor disc. Wedges are slid between feet and the walls of the grooves to prevent removal of the feet and therefore the annulus members in a reciprocal direction.

Abstract: A rotor blade 14 having a spar 138 and shell 134 is disclosed. Various construction details are developed for efficiently transferring rotational loads on the rotor blade to the root section 28 of the spar. The spar has a projection 139 over which extends a portion 100 of the shell and a platform 36 of the rotor blade.

Abstract: Disclosed is a bladed disk assembly having a new and improved rotor blade. The blade includes a shank and dovetail extending from an airfoil portion thereof. The shank includes a pocket extending therein from an end surface thereof. The shank pocket allows for reduced weight of the blade while maintaining acceptable bending stiffness thereof. In an exemplary embodiment of the invention, the bladed disk assembly is effective for being interchangeable with a blisk assembly having an inlet hub radius ratio of about less than about 0.5 and a root solidity of greater than about 2.2.

Abstract: A turbomachine seal for reducing fluid flow through the gap between circumferentially adjacent blade platforms is disclosed. The seal comprises a pair of radially inwardly extending elastomeric members. Each member has an inwardly extending first face and is bonded at a second face to respective ones of adjacent platforms. Each elastomeric member is circumferentially deflectable under a centrifugal load so that respective first faces meet.

Abstract: A blade vibration damper for a rotor assembly of an axial flow machine seats simultaneously on a radially inwardly facing surface of a blade platform and the radially inwardly facing surface of an adjacent element, such as the platform of a circumferentially adjacent blade. The damper has its mass center of gravity nearer one contact area than the other so as to reduce the normal load on the blade platform generated by centrifugal force. By properly locating the center of gravity of the damper, the size of the normal force can be optimized to maximize damping.

Abstract: A device for securing an annular blade retaining plate to a rotor disk includes an annular groove around the disk for receiving an off-set annular flange on the inner end of said blade retaining plate. A split retainer ring extends from a second groove intersecting said first groove to fix the blade retainer ring to the disk. A locking ring is positioned between said split retainer ring and said blade retaining plate to maintain said split retainer ring in its groove.

Abstract: In an axial flow compressor rotor stage having a blade mount rail about the eriphery thereof, a seal is positioned below the blade platforms to provide improved compressor gas path efficiency. Each blade platform has a seal bonded to the underside thereof, said seals extending toward adjacent blade platforms and providing sealing means in the interstices between said platforms as well as between said platforms and said blade mount rail.

Abstract: In a gas turbine engine the turbine blade has protective flanges closely overlying the rim of the rotor to shield the rotor from the hot power gases and to form a path for cooling air. These flanges are spaced radially inward from the flanges on the blade that define the inner wall of the gas path through the turbine.

Abstract: An end seal for root manifolds at the bases of air cooled turbine blades disposed in retention slots in a turbine wheel; the end seal including an annular groove in the upstream face of the wheel having an outboard cylindrical edge outboard of the root manifold, an inboard cylindrical edge inboard of the retention slots and a slot face parallel to the upstream face of the wheel; an imperforate seal ring in the annular groove with a right circular flange adjacent the outboard edge, an annular foot engaging the groove slot face inboard of the retention slots, and a body portion defining an accordion fold in transverse cross section; and seal plate segments on the wheel over the groove.

Abstract: A retractable damping device for the blades of a turbojet, located between two consecutive blades against the lower face of the platforms of said blades. The damping element, mounted to rotate by one of its ends in the middle part of the space formed between the blades and a rotor disk positioned along an axis perpendicular to a radial axis of the disk, exhibits an upper part which constitutes a projecting dihedral that takes the form of the protruding dihedral consisting of the platforms of the two consecutive blades under the action of centrifugal force.

Abstract: An end seal for cooling air manifolds below the bases of a stage of air cooled turbine blades on a turbine wheel, the end seal including a seal ring having an annular planar portion abutting an end face of the turbine wheel inboard of the air manifolds and a right cylindrical flange perpendicular to the planar portion and underlying a corresponding cylindrical shoulder on the wheel and on the blade bases outboard of the air manifolds, and a plurality of end plates on the wheel having lugs underlying the cylindrical flange. The planar portion is axially clamped to the wheel to define a 360.degree. inboard seal while centrifugal forces developed by the end plates during rotation of the wheel cause the lugs to radially clamp the cylindrical flange against the cylindrical shoulder on the wheel and blade bases to define a 360.degree. outboard seal.

Abstract: A sheet metal seal for sealing the gap between adjacent blade platforms in a rotor assembly fits within a pair of spaced apart slots on the underside of one of the platforms and is trapped in position by a lug disposed between the slots and which passes through a hole in the seal. The seal is attached to the blade prior to its assembly in the disk. A portion of the seal overhangs the edge of the platform to which it is attached and, when the blade is inserted into the disk, the extended portion of the seal overlies the underside surface of the adjacent blade platform. This seal is preliminarily shaped to the contour of those portions of the underside surfaces of the platforms against which they are to bear during rotation of the assembly.

Abstract: A coolable rotor blade 14 for an axial flow rotary machine and a method for making the rotor blade are disclosed. The rotor blade includes a spar 38 and a shell 34 for defining the airfoil surface of the rotor blade. A platform 36 extends over the shell and the spar. The spar has a root 42 and an airfoil section 40. The shell is spaced from the spar and is joined to the airfoil section of the spar for defining cooling passages in the blade. The shell and the platform are each attached to the spar for support against rotational force. The method includes the steps of joining a shell to the airfoil section of the spar which extends over a portion of a projection 139 on the spar and forming a platform about the spar and the shell such that the platform is attached to the spar and extends over the projection and a portion of the shell. In one embodiment, the spar is formed of a first material, the shell of a second material, and the platform a third material.

Abstract: A damping device for the turbojet engine fan blades which includes a wedge placed between the platforms of the blades, the shanks of the blades, and the disc. The wedge consists of a hollow, bellows-shaped body fitted with an axial stop member, the body being inflated after mounting so that it takes up all the space between the platforms of the blades, the blade shanks and the teeth of the disc. The invention is used for damping device of turbojet engine blades.

Abstract: An aerofoil blade/disc assembly suitable for the compressor or turbine of a gas turbine engine comprising a rotor disc which has a circumferential, part-circular cross-section channel provided in its periphery for the reception of the correspondingly part-circular cross-section roots of an annular array of aerofoil blades. The arrangement is such that upon disc rotation, the aerofoil blades pivot with respect thereto until their platforms sealingly engage a circumferential radially extending flange provided on the disc periphery. A seal is provided between the aerofoil blades and the disc which reduces the leakage of gases between the aerofoil blade roots and their retaining channel.

Abstract: The clearance necessary for the assembly of the nozzle ring of an axial flow steam turbine is localized through a temporary bolting. The localized clearance is compartmentalized by making a generally radially extending hole centered on the clearance at the circumferential location of the boundary between each pair of adjacent nozzle banks. Pins are driven into the holes and provide a seal between adjacent nozzle banks.

Abstract: A turbine rotor provided with a sealing member for preventing air leaks through a gap between the under side surface of a projection extending from one of discs of the rotor and the upper side surface of a outward end portion of the spacer interposed between the discs. The spacer is formed with an annular groove on the upper side surface of the outward end portion for receiving a sealing wire in its entirety. The sealing wire has its outer portion forced against the underside surface of the projection by centrifugal forces while its inner portion remains inside the groove during turbine operation, to thereby seal the gap to prevent leaks of air therethrough.

Abstract: A damper for damping the vibration of blades in a turbine rotor including a plate having at least one bumper extending outwardly from one side of the plate to be positioned in recesses on the underside of the platforms on adjacent blades for locating the bumper circumferentially and with a tab extending inwardly from the plate on the side opposite to the bumper to hold the damper in radial position. A wear strip extending upwardly from the plate near its periphery serves as a seal to minimize gas leakage past the damper.

Abstract: The sideplates of a turbine rotor assembly that seal between turbine stages are retained by a retention assembly that hooks onto the front sideplate and is riveted onto the rear plate negating the necessity of rivet holes in the front sideplate. A plurality of segmented sideplates circumscribe the full hoop of the rotor and each sideplate carries a retention assembly rather than providing a retention assembly for each blade which is greater in number.

Abstract: A bladed flow duct, for example in an axial flow turbo engine, is defined between two adjacent blades and the respective duct floor. In order to reduce secondary flow losses, the flow duct is provided with an arched zone (13, 13') projecting from the duct floor (10, 10') and extending along a portion of the suction side of the adjacent blade wall for producing a pressure rise or a reduction in the transverse pressure gradient over a relatively long forward and/or central portion of the duct as viewed in the flow direction (17) from the entrance end (21) to the exit end (22) of the duct. For this purpose the arched zone (13, 13') has a number of sections in the flow direction (17). A first section (23) starting in the entrance side of the duct is substantially or completely concave for causing said pressure rise. A second or central section (24) forms a convex peak and particularly a duct throat near the exit side of the duct. A third section (25) slopes down to the exit end (22).

Abstract: A turbojet turbine stage having air cooling of the turbine wheel disc is disclosed which has, on the one hand, devices for blowing in a flow of air A in the direction of the upstream surface of the disc (20) intended in particular to flow into the several passages delimited by the periphery (22) of the disc and by the shanks (14) and platforms (12) of the blade feet (11) of the wheel, and, on the other hand, a number of trough-shaped dampers (30) each of which is inserted in a passage and supported by its edges against the periphery of the disc while its back pushes against the platforms delimiting the passage. The upstream edge of each damper forms a peak (33) which extends beyond the upstream side of the disc.

Abstract: Apparatus for dampening rotor blade vibratory energy in a rotary machine is disclosed. Concepts employing blade to blade damping are discussed.In one detailed form, a damper (52) is disposed to seat against the undersides of adjacent blade platform sections (20) and a seal (42) is spaced sufficiently close to the damper so as to be deflected against the damper under centrifugal loads to augment dampening of the rotor blades by the damper.

Abstract: A rotor assembly and methods for securing rotor blades within and removing rotor blades from rotor assemblies. The rotor assembly comprises a rotor disc defining a plurality of blade grooves, and including a plurality of tenons disposed between the blade grooves and defining a plurality of pin sockets radially extending inward from outside surfaces of the tenons; and a plurality of rotor blades, each blade including a root disposed within a blade groove to secure the blade against radial movement, and a blade platform overlaying a tenon and defining a radially extending pin aperture. The rotor assembly further comprises a plurality of locking pins radially extending through the pin apertures and into the pin sockets to secure the rotor blades against axial movement, each pin including a head and a base to limit radial movement of the pin.

Abstract: A blade assembly for use in an axial flow compressor or turbine. The blade assembly includes a disc provided with a circumferential blade root retaining channel in its periphery and an annular array of aerofoil blades having roots located in the channel so that gaps are defined between adjacent roots. Each root is provided with two circumferentially extending sealing skirts which are arranged so that they cooperate with the blade roots to define an annular sealing surface which is in operation in sealing engagement with an annular portion of the internal surface of the root retaining channel.

Abstract: A turbine rotor for a flow meter comprises a cylindrical rotor disk having a rotor axis, a plurality of rotor vanes extending radially from the rotor disk and a flat surface between the bases of each of the vanes. This construction permits the efficient start-up of the turbine rotor at flows of low viscosity.

Abstract: A turbine rotor assembly 10 for providing cooling air to a turbine blade 28 is disclosed. An annulus 24 is formed between the rotor disk 12 and a segmented sideplate 20 in which the segments have overlapping ends 22. A thin flexible metal strip 36 having overlapping ends 38 is disposed about the radially inward edge of the sideplate segments to seal the leakage flowpath between the overlapping ends 22 of the sideplate segments 20 as the sideplate segments expand and contract with the supporting disk 12.

Abstract: The neck portion of a rotor blade includes an annular, axially projecting segment integral with the neck and having side edges abutting corresponding segments of adjacent blades to form a segmented annular ring which cooperates with static structure to define an interstage annular seal. Each blade also includes an air dam extending laterally from each side of the root neck and extending radially between the blade platform and the annular seal segment. The air dams of adjacent blades also abut each other to define an annular seal which prevents the axial flow of air across the rotor stage under the blade platforms between the blade root necks. In a preferred embodiment thin strips of silicone rubber are used to seal any gaps between the abutting edges of adjacent blades.

Abstract: A rotor assembly and methods for securing rotor blades within and removing rotor blades from rotor assemblies. The rotor assembly comprises a rotor disc defining a plurality of blade grooves, and including a plurality of tenons disposed between the blade grooves and defining a plurality of pin sockets radially extending inward from outside surfaces of the tenons; and a plurality of rotor blades, each blade including a root disposed within a blade groove to secure the blade against radial movement, and a blade platform overlaying a tenon and defining a radially extending pin aperture. The rotor assembly further comprises a plurality of locking pins radially extending through the pin apertures and into the pin sockets to secure the rotor blades against axial movement, each pin including a head and a base to limit radial movement of the pin.

Abstract: This invention relates to the construction of a turbine rotor having a rotor disc with a plurality of blades, said blades having roots fitted into slots around the periphery of the disc with each blade engaging a stop means to properly position it, said blades being held in place by a cover plate fixed to the rotor disc and said stop means; a pocket is formed on the front face of each blade while an annular groove on said cover plate is positioned over said circumferential ring of pockets. Each pocket has an outer flat surface placed at an angle so that each surface intersects the outer surface of the annular groove; a stiff solid damper having a rectangular surface is positioned in each pocket so that one end of said surface will be supported by the outer surface of the annular groove while the other end of said surface will be supported by the outer surface of the pocket when the damper is thrown outwardly by centrifugal force.

Abstract: Effective damping of blade vibratory energy is sought by the apparatus described herein. The concepts relate specifically to what is known as blade to blade damping as is distinguished from blade to ground damping.The dampers employed have a "T" shaped cross section geometry and are designed to extend circumferentially on an engine rotor between the platform sections of each pair of rotor blades. The dampers are of extreme light weight such that the slipload forces required to generate sliding contact between the damper and the blade platforms is low.

Abstract: The present invention provides an improved sideplate of the type adhered to the side of a rotor disk for the retention of rotor blades and for blocking the leakage of working medium gases across the rotor disk. The elimination of retaining bolts and rivets is sought.In one effective embodiment of the present invention, the sideplate is adhered to the disk at a bayonet type joint. The sideplate is elastically deformable to enable assembly of the sideplate onto the disk with abutting surfaces of the disk and sideplate in interference engagement at release. The side surface of the disk is tapered in cross section geometry to accommodate deformation of the sideplate.

Abstract: A turbofan engine fan blade made of composite material, and a method of making the fan, are taught. The fan blade essentially comprises an airfoil section having a root end and made of a plurality of bonded plies of composite material which are splayed and which are in a staggered condition at the root end; a two-piece platform section made of titanium or of aluminum, with one piece of the platform on each side of the airfoil section; and a steel outsert section which holds and secures the platform section to the airfoil section, with the outsert section having a triangular shaped cavity located at the root end of the airfoil section, between the splayed and staggered plies of the airfoil section. Among other advantages, the cavity eliminates the "insert plies" (or wedge) used in the prior art and the inherent disadvantages associated with such use.

Abstract: This invention relates to a bladed rotor for a gas turbine engine which comprises a disc having blade carrying slots in its periphery. In order to seal the spaces between the blade platforms and the disc an annular array of sealing plates is provided. The plates are supported directly from the disc by a rivet, pin or the like which passes through the disc in between the blade carrying slots, in this way avoiding any additional loading on the blades themselves.

Abstract: A combination ceramic and metal turbine rotor for use in high temperature gas turbine engines includes a metal rotor disc having a rim with a plurality of circumferentially spaced blade root retention slots therein to receive a plurality of ceramic blades, each including side platform segments thereon and a dovetail configured root slidably received in one of the slots.

Abstract: An object of the invention is to prevent the leakage of working medium gases across a rotor stage beneath the platforms of the rotor blades.A rotor assembly structure in which the concepts of the present invention are employable is disclosed. Techniques for blocking the leakage of working medium gases around a rotor stage beneath the platforms of the blades are discussed.

Abstract: A rotor for jet engines includes a drum formed by disks and carrying blad Between the blades of two adjacent stages, braces are interspaced, the braces being projections which engage in sockets provided for this purpose on the disks. Each disk has two series of sockets, one receiving the roots of the blades, and the other, interspaced between the preceding, the projections of the braces. The blades are immobilized in translation at the upstream end by one ring and downstream by another ring, against which the roots of the blades of the terminal stages abut. The invention is particularly applicable to the building of axial type compressor rotors having several stages.

Abstract: Turbine blades having heat localization segments, especially for use in gas turbines, are disclosed. The segments are provided with covering elements in the form of thin cover plates that are supported against the blade root. The segments are formed as one piece together with both the actual blade and with reinforcing elements. The segments are used to impede access of a hot working medium to the turbine rotor.

Abstract: A shrouded blade for insertion into an axial disk slot and having a radial spacer and a circumferential groove is provided with a segmented retainer bar which fits into the circumferential groove to axially retain the blade. The retainer bar includes flanges which extend radially inward on either side of the spacer such that the spacer provides positive placement for the retainer bar in both the radial and circumferential directions.

Abstract: A device to secure and insure the tightness of vanes of a turbine is an alar plate which carries on the side toward its external edge a plurality of studs and toward its internal edge a plurality of hangers. The disk of the rotor has on its lower edge a series of teeth or indentations, the top of the teeth having a configuration to cooperate with the inner surface of the hangers. The vanes have on their rims a plurality of grooves. Two adjacent vanes form a groove into which the studs enter when the hangers cooperate with the teeth. The studs are borne by tongues cut radially into the annular plate.

Abstract: A sealing arrangement for preventing compressor fan air loss through the relatively wide gaps between adjacent blade platforms required in order to allow for rotation of the blades around their minor root axes in response to bird impact and the like. A thin flexible ribbon-like seal is bonded to one of the two adjacent blade platforms in the fan structure. At the gap, the seal includes a thickened wedge shaped portion with at least one invagination on the inner side facing the rotor axis. At the operating speed of the compressor fan, centrifugal force causes the thickened portion to be forced into the gap between adjacent platforms producing the required seal.

Abstract: A vibration damper for use in a turbine rotor of a high temperature gas turbine is disclosed. The damper is loosely mounted in an opening formed between adjacent blade rails, the end of the rotor disk connector, and sections of adjacent blade necks between the rails and the disk connector. A cover plate positioned against one side of the turbine blade and a projection extending downwardly from the other side of the turbine blade confines the damper axially in the opening.

Abstract: In a blade cooling system for a turbine of a gas turbine engine each blade root is provided with individual pitot receivers which collect a portion of a cooling fluid flow supplied from an annular array of pre-swirl nozzles, which have a circumferentially continuous outlet flow area, and direct said flow into a portion only of the interior of the blade, preferably adjacent the leading edge.

Abstract: A rotor blade stage for a gas turbine engine comprises an annular array of aerofoil blades. Each blade is provided with circumferentially extending platforms which are arranged so as to circumferentially spaced apart from the platforms of adjacent blades. Elastomeric dampers are interposed between adjacent blades and are so adapted that upon rotation of the array of blades, each of the elastomeric dampers is centrifugally urged into engagement with the radially inner faces of adjacent platforms of adjacent blades.

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

Abstract: Both the disk and the blade retainer have a radially inward extending flange which axially abuts the other. A U-clip ring with its open side disposed radially outward is placed over the two flanges to hold them axially together and means is provided to maintain the U-clip ring in its holding position. In a preferred embodiment, the ring is constructed with its side farthest from the disk having a substantially greater radial height than that of the side closest the disk, and the circumferential length of the U-clip is so sized that there is a relatively small gap between its ends when it is in the installed position. With these features, the ring will remain in its assembled position without any other holding means. Removal can be effected by first radially moving one end of the ring inwardly with respect to the other and then axially moving it until it clears the other end.

Abstract: A turbine blade comprised of at least a pair of abutting blade parts with each part having a root coupled to an attachment piece, the latter adapted to be coupled to a turbine rotor. The blade parts can be curved and each blade part may have a hollow space in the region where it abuts the other blade part to reduce the weight of the blade. The blade parts may be spigoted or mated with tongue and groove structure to reduce fluid leakage through the junction between the blade parts.

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

Abstract: Effective damping of blade vibratory energy is sought by the apparatus described herein. The concepts relate specifically to what is known as blade to blade damping as is distinguished from blade to ground damping.The dampers employed have a "T" shaped cross section geometry and are designed to extend circumferentially on an engine rotor between the platform sections of each pair of rotor blades. The dampers are of extreme light weight such that the slipload forces required to generate sliding contact between the damper and the blade platforms is low.