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: An interchangeable fan blade system for a ceiling fan, made up of a set of adapters having a plurality of elongated attachment apertures that allow the adapter to be threadably fitted to virtually any type of fan support arm, and a complimentary set of interchangeable fan blades. The adapters include one of a variety of connectors for attaching one end of the fan blades to the support arm. The one end of the fan blade is configured and adapted, or otherwise provided with mating connector elements adapted to engage the connectors of the adapters, thereby allowing the fan blades to be removably attached to the adapters. A second embodiment of the interchangeable fan blade system is a set of interchangeable fan blades having a plurality of elongated attachment apertures which allow the fan blades to be secured to virtually any type of fan arm, by threading a plurality of shoulder cap screws and a plurality of male-female connectors though the plurality of attachment apertures.

Abstract: A lock is provided for closing an entry point of a circumferential slot undercut on both sides and intended for accommodating blade roots of moving blades of a turbine rotor. A filling piece with a contour adapted to the blade roots is supported against a supporting side in the turbine rotor through the use of a fitting piece. A step provided in a base region of the lock serves to axially support the filling piece. The fitting piece may be provided with a slit into which a wedge for expanding the fitting piece can be pressed.

Abstract: A compliant sleeve for attaching a ceramic member to a metal member is comprised of a superalloy substrate having a metal contacting side and a ceramic contacting side. The ceramic contacting side is plated with a layer of nickel followed by a layer of platinum. The substrate is then oxidized to form nickel oxide scale on the ceramic contacting side and a cobalt oxide scale on the metal contacting side. A lubricious coating of boron nitride is then applied over the metal contacting side, and a shear-stress limiting gold coating is applied over the ceramic contacting side.

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 rotary assembly of a turbine stage of a gas turbine engine comprising a disc carrying internally air cooled blades around its periphery has a cover plate of one face of the disc to create a plenum for a cooling air supply to the blades. The cover plate is fitted to the disc by means of an annulus of bayonet connections at a first radius and is retained at a second radius, less than the first radius, by a split ring arrangement. The split ring is fitted into a groove in the disc and engages an inner rim on the cover plate to restrain axial movement. An anti-rotation key is engaged in a slot in the cover plate and in the disc and is also retained by the split ring.

Abstract: A joint between a first and a second joint partner where each joint partner has at least one flat, cylindrical surface section via which force is applied to the other joint partner. The joint partners being brought into contact with one another in a sliding fashion such that the flat, cylindrical surface sections of the joint partners partially overlap and form a common bearing surface in the contact region. The flat, cylindrical surface sections of the joint partners are each bonded on one side by an undercut and the joint partners are joined such that the common bearing surface of the joint partners is bounded in one direction by the undercut of the first joint partner and in the opposite direction by the undercut of the second joint partner. This arrangement allows zones of maximum stress gradient to be shifted into the region of the undercut structures and for crack-opening, surface-parallel stresses to be substantially avoided.

Abstract: An arrangement for attenuating vibrations of blades attached to a peripheral surface of a rotor of an axial turbine. A through hole is formed in each rotor blade in a generally thickness direction of the blade so that the through holes in combination define a single annular passage near a rotor surface when all of the rotor blades are attached to the rotor. A wire is provided to extend through the aligned through holes. Thus, the wire frictionally contacts the through holes when the blades are caused to vibrate due to a gas pressure and a centrifugal force generated upon operation of the axial turbine. Friction contact between the wire and the through holes attenuates vibrations of the blades.

Abstract: A turbine (10) for a gas turbine engine includes an annular array of turbine aerofoil blades (12) which are mounted on a disc (19). Each of the aerofoil blades (12) is provided with a radially inner platform (21). Each platform (21) includes a passage (37) into which leaked cooling air flows. The passages (37) are disposed in a direction having a circumferential component so that cooling air is exhausted from them in a direction that is generally opposite to that in which the disc (19) operationally rotates.

Abstract: A rotor for a turbomachine has slots formed therein at an angle to an axis of rotation of the rotor. Blades have at least one blade root with at least two regions of different rigidity that are adapted and preferably matched to different regions of rigidity of the slot. The blade roots can be fitted into the slots. A blade for a rotor is also provided. The invention is especially suitable for use in gas-turbine compressors, as a result of which local stresses at slots can be greatly reduced.

Abstract: A damper for the blades of a turbine rotor for attenuating the vibrations excited in a radial direction by configuring the damper to have at least two legs bearing against the blade and the disc supporting the blade for grounding the radial vibrations transmitted radially through the damper and offsetting the center of gravity of the damper from the point of contact with the blade.

Abstract: A rotor blade includes an airfoil, an integral platform, and a dovetail integrally joined to the platform. The dovetail includes a neck extending between a pair of dovetail lobes configured to engage a complementary slot in a rotor disk. The dovetail includes an undercut extending between an outer face of the dovetail lobes and the neck for introducing a stress concentration thereat. The stress concentration relieves stress at the outer face at the expense of the neck for increasing the high cycle fatigue life of the blade.

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: In connection with a turbine rotor disk in whose disk grooves air-cooled turbine blades have been inserted, at least two cooling air channels, respectively extending from the same disk front face, terminate in each disk groove. The outlet openings of two cooling air channels in each disk groove preferably lie essentially next to each other in a common sectional plane, which is normal to the disk axis. Because of this it is possible to supply a larger cooling air flow without drastically increasing the weakening, or respectively the stress of the disk in the groove bottom.

Abstract: A turbine or compressor disk assembly comprises a plurality of blades attached to a central hub by means of the blade root of each blade engaging a corresponding slot in the hub. According to the principles of the present invention, a turbine or compressor disk assembly includes one or more locally bulging regions extending axially away from the surface of the disk in the vicinity of the bottom contact plane of the disk attachment firtree. The locally bulging regions reduce the peak Macke stress in the disk bottom fillet and blade attachment root. In an illustrative embodiment, two locally bulging regions are incorporated into the disk and the corresponding blades, one of which extends forward from the leading edge of the disk and the other of which extends rearward from the trailing edge of the disk. The rearward locally bulging region has an exaggerated extension which allows the stress reduction ring to form an aft flow discourager as well as functioning to reduce peak stress.

Abstract: A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a plurality of compressor blades extending radially between a stator hub and a housing. The hub (2) of the rotor (1), and/or the hub of the stator, and/or the housing of the stator, have a circumferential surface contour that is not continuously rotationally symmetrical. Namely, a concave contour (K) is provided in the circumferential surface of the hub near the base of each blade (3) on the pressure side (PS) thereof, while the circumferential surface on the suction side (SS) of the base of each blade has a contour that is linear, slightly convex, convex/concave, or slightly concave to a lesser degree than the concave contour (K) on the pressure side of each blade.

Abstract: A blade retention system which allows a blade to be rotated about a blade stack axis by utilizing a cover, an anti-rotational key, and strap is described. The substantially cylindrical cover rotatably couples to a rotor disk opening using a thrust bearing. The cover includes a dovetail-load slot for receiving a rotor blade dovetail key. The anti-rotation key is positioned between the dovetail key and the dovetail-load slot to secured the blade to the cover. The strap holds the key in place and is clamped between the cover and the control mechanism.

Abstract: A gas turbine engine fan blade includes an airfoil and dovetail having an integral aluminum core and a fatigue resistant reinforcing sheath.

Abstract: An adjustable propeller is provided with a receptacle on its hub which is shaped to receive a base portion of a propeller blade. First and second pluralities of alignment devices are provided to allow an operator to select a desired pitch angle and attach the blades of the propeller to the hub so that the desired pitch angle is selected. Alignment devices can comprise a plurality of holes in each receptacle which are tapped to receive a bolt in threaded association therein. Associated holes in the base portion of the propeller can allow free passage of the bolt by selecting one of the holes in the base portion of the propeller and aligning that hole with an associated hole in the receptacle of the hub, an operator can quickly and easily select a desired pitch angle for the blade. A bolt passes through a hole in the base portion of the blade and threads into an associated hole in the propeller hub to select the pitch and attach the base portion to the hub.

Abstract: A cover plate for a bladed rotor in a turbine section of a gas turbine engine which comprises an annular plate segment comprising a plurality of spaced-apart seats with each seat coincident with a rivet. The rivets are the rivets used for anchoring the root of the blade in the disc, and the seats and the covers have frusto-conical surfaces having an axis which is the axis of the rivet.

Abstract: The present invention relates to a blade retention apparatus for a bladed rotor in a turbine section of a gas turbine engine which comprises a rivet grip which has serration at one end and an upset head at the other end, and a sleeve made of a soft metal which is compressed to the serration actually against the surfaces of the disk and the blade. The retention apparatus of the present invention provides a reliable attachment and only requires a simple hand-held pneumatic riveting tool to install.

Abstract: A cooling medium path structure for cooling a gas turbine blade. The structure includes a disk-side cooling medium path, a blade-side cooling medium path formed at the root portion of the blade and a delivery block disposed between the two cooling medium paths so as to establish communication therebetween. The delivery block is provided with an elastic engaging section which comes into elastic and line-contact with the disk-side cooling medium path and the blade-side cooling medium path. Thus, the sealing property of the contact portions of the structure is secured so as to allow a cooling medium to be supplied without leaking from the cooling medium paths. The heat of the cooling medium, generated as a result of cooling the high-temperature portion of the gas turbine, can be recovered so as to make the best use of the heated medium.

Abstract: A fan for a gas turbine engine comprises a rotary disc carrying an annular array of radially extending fan blades. Each fan blade has a root portion which is radially constrained within a generally axially extending groove formed within a disc rim. The blade root comprises two portions each radially convergent toward one another with respect to the axis of rotation of the disc. The groove within the disc also comprises two base portions each being correspondingly radially convergent toward one another. Axial retention of the blade root within the groove is achieved by the centrifugal component of the blade load acting in an opposite direction to any applied axial load in the forward or rearward direction.

Abstract: A sealing apparatus and method for delivering a sealing material to gaps between gas turbine blade roots and the corresponding grooves of a rotor disc are disclosed. The sealing apparatus comprises a tank for housing a pressurized sealing material, a delivery tube for delivering the sealing material from the tank to the rotor disc, a control valve for controlling the flow of the sealing material, a sealing fixture for distributing the sealing material to the gaps between the blade roots and the corresponding grooves, an O-ring seal for effecting a tight seal between the sealing fixture and the rotor disc, and jack screws for maintaining the sealing fixture securely in place.

Abstract: A bladed rotor has blades fitted in grooves around its rim. The blades are prevented from making significant movement lengthways of their grooves by abutment members which are so formed as to enable fitting and removal without the use of special tooling.

Abstract: A labyrinth disk includes a main stiffener placed in the middle of the rim immediately below labyrinth elements. Attachment elements are preferably in the form of a bayonet attachment system using teeth fixed on the labyrinth disk crown and teeth fixed on the rotor. Attachment by bolting may optionally be used. The disk may be utilized with turbojets, on the cooling circuit, on the upstream side of the high pressure turbine.

Abstract: Rotor blades (1) are held by means of toothed roots (3) in correspondingly profiled axial grooves (4) of a rotor wheel rim (5). Between each root end and the base of an axial groove (4), there is formed a radial gap (S) accommodating a rivet (6). Each rivet (6) is centrally guided on two inserts (9, 9') resting against the base of the axial groove (4) in the radial gap (S) and having bent or angled end parts (10, 10') resting against the front and rear faces of the wheel rim (5). Seating wedges (11, 11') surround the upset head (8) and the set head (7) of the rivet (6) and are axially and radially clamped to wedge-shaped complementary surfaces (G, G') of the root end and of the respective insert (9, 9') by riveting. As a result, an improved radial and axial clamping of the rotor blades is achieved.

Abstract: The blades of a turbine rotor are secured to a rotor disk by inserting the blade foot with its serrations into a respective serrated groove in the rim of the rotor disk, whereby serrations of blade foot side surfaces mesh with corresponding serrations in the side walls of the grooves in the rotor rim to interlock the blade foot with the rotor disk in the radial direction. The axial locking of the blade foot in the groove is accomplished by a rivet connection having a rivet shaft positioned in a gap between the radially inwardly facing sole of the blade foot and the radially outwardly facing bottom of the groove. The rivet heads rest against washers or washer rings. If flat head rivets are used, these heads are received in countersunk recesses in the washers or washer rings that bear partially against the side surface of the rotor disk rim and partially against an axial end surface of the respective blade foot.

Abstract: A blade is locked into groove in the periphery of a turbo-machine rotor by forming mating notches in opposing faces of the blade root and groove so as to form a blind hole. At assembly, a slotted radial pin is installed into the blind hole so as to prevent axial motion of the blade root. The pin is rotated so as to align its slot with a slot formed along the length of the rotor groove. A retaining strip is slid into the rotor groove slot so that it extends through the slot in the radial pin, with a pre-bent end of the strip resting against one face of the rotor. A tab formed on the other end of the strip is bent against another face of the rotor so as to lock the retaining strip in place. At dis-assembly, one of the retaining strip tabs is unbent and the retaining strip slid out. The pin is then extracted, thereby allowing the blade to be removed.

Abstract: One form of a retention system includes a pair of aft segments of 180.degree. in length disposed in annular grooves about a compressor spool, the segments having radial projections against which the aft end faces of the base portions of rotor blades abut. The blade base portions are shaped and are received in complementary-shaped slots of the spool. The forward retention system includes a plurality of arcuate segments approximately 30.degree. in length disposed in grooves adjacent the forward end faces of the blades. With the exception of the final pair of blades, the blade base portions thereof are located in the axial complementary slots in pairs, with each forward arcuate segment, except the final segment, being disposed in the groove at a circumferentially spaced location and displaced circumferentially to abut the forward end faces. The final arcuate segment is radially reduced and disposed in the remaining portion of the groove to lie flush with the spool.

Abstract: A bladed rotor for the high pressure compressor of a gas turbine engine comprises a disc carrying an annular array of aerofoil blades in axially extending fir tree root slots. Retention plates carried in radially inner and outer slots prevent axial movement of the blade roots in their slots. A locking member is interposed between an adjacent pair of retention plates to prevent their circumferential movement relative to the disc. The locking member in turn interacts with the disc to anchor itself to the disc.

Abstract: A cooling system for use in a rotor assembly of a gas turbine engine, the rotor assembly including an annular disk rotatable about a centerline axis of the engine and a plurality of blades mounted on the disk. The disk includes alternating posts and slots, with each slot receiving a blade dovetail. The cooling system comprises an axially extending plenum disposed inward of each blade dovetail and a thermal isolation chamber, formed by a seal body, disposed over the outer surface of each disk post. An annular forward blade retainer is attached to the disk and sealed with adjacent structures via inner and outer seals. Alternative structures are disclosed for diverting the cooling air from the plenums, past the inner and outer seals, and into the isolation chambers during operation of the engine so as to cool each disk point, without compromising the structural integrity of the forward blade retainer.

Abstract: A rotor disc which is suitable for carrying the fan blades of a ducted fan gas turbine engine is constituted by two sub-discs which are maintained in axially spaced apart relationship by a plurality of spacer members. The spacer members are generally axially extending and at least partially define the operational air flow path over the disc.

Abstract: A fixing arrangement for axially fixing a blade in position on a rotor disk of a turbomachine rotor includes a relatively flexible locking wedge inserted between the root of the blade and the bottom of the axial groove in the periphery of the rotor disk in which the root is received in a radially interlocking manner, the locking wedge having a retaining hook which is received in a groove in the blade root to hold the locking wedge in position. In one embodiment the locking wedge holds a plate in position in the recesses defined by undercut projections on the upstream face of the blade root and the rotor disk to prevent axial movement the blade relative to the disk.

Abstract: A turbine rotor assembly includes a rotor disk, rotor blades joined thereto, and a blade retention plate for axially retaining the blades on the disk. The disk includes an outer rim, an inner hub, and an annular web extending therebetween. An axial extension extends from the web and is spaced radially below a corner of the rim. The blades have dovetails axially disposed in respective dovetail slots in the disk rim. The retention plate includes an outer rim which abuts the disk rim and blade dovetails, an inner hub, and a web extending therebetween. The plate hub has an outer rabbet disposed in abutting contact with the rim corner, and an inner rabbet radially adjoining the axial extension for maintaining abutting contact therewith upon differential radial contraction between the retention plate and the disk which separates the outer rabbet from the rim corner.

Abstract: A disc for use in an axial flow turbomachine having a main flow annulus which includes an inner flow boundary defined by axially adjacent stator vane and rotor blade platform sections. The disc comprises an axially extending sealing member which extends from its radially outer periphery to bridge the gap between adjacent rotor blade and stator vane platform sections. The sealing member is formed integrally with the disc. The arrangement minimises the unsealed stator well region between the rotatable and non-rotatable platforms and thereby provides for improved operational flow stability.

Abstract: A fan assembly has a circular disc with a rotational axis and first and second sides. A cylindrical side wall extends around the periphery of the disc. The side wall has axially spaced first and second rims and is circumferentially subdivided into a plurality of wall segments, each wall segment has inner and outer surfaces, with the second rim of the wall protruding axially beyond the second side of the disc. Fan blades are carried on the outer surfaces of the side wall segments. Mounting members protrude from the first side of the disc at locations spaced circumferentially around the periphery thereof. Connecting members on the inner surfaces of the wall segments coact in separable interlocked engagement with the mounting members to fasten the wall segments to the disc. A first ring on the first side of the disc prevents the connecting members from separating from their interlocked engagement with the mounting members. A second ring on the second side of the disc interconnects the wall segments.

Abstract: A rotor assembly for a gas turbine engine has a disc with dovetail grooves and a plurality of blades with dovetail roots contoured to be received within the grooves. The inner surface of a flexible, high temperature, low compression set seal is bonded to the inner surface of each root portion. The outer surface of the seal has two portions inclined at an angle and spaced apart to define a surface portion for sealingly contacting the base of the groove. The longitudinal edges of the outer surface are curved to facilitate assembly.

Abstract: A turbine engine rotor includes two bolted, coaxial sections. One of the sections carries blades engaged by their roots in through broachings. The axial force exerted on the blades by the centrifugal operating component due to the inclination of the broaching is not transmitted to the bolts joining the two sections as a result of a mounting where the flanges are joined at their rear faces. The blades abut against the flange of the other of the sections. The invention is more particularly applicable to highly curved, so-called large chord blades of a turbine engine fan and the other of the sections is then a low pressure compressor drum.

Abstract: To manufacture a turbine wheel having blades made of a ceramic or composite material and inserted into a metal hub, firstly blades (16) are manufactured that are right cylindrical, each blade having a base (18) through which a hole is formed; a cylindrical ring (20) is formed, the ring being provided with orifices through which the bases (18) of the respective blades (16) are inserted; the blade bases (18) are successively threaded onto an open annular rigid metal wire (30); the resulting assembly (16, 20, 30) is disposed inside a sealed housing (161); hot isostatic compaction is performed so as to compact a metal alloy in powder form (41) inside the sealed housing (161) so as to make the hub of the turbine wheel (100) while embedding the blade bases (18) and the metal wire (30) by using the powder metallurgy technique; and the outside portion of the sealed housing (161) delimiting the hub of the turbine wheel (101) is machined. Application, in particular, to the field of aeronautical or space engineering.

Abstract: The attachment of the blade to the disk of a gas turbine engine includes a sloped deep slot formed in the rim of the disk for accepting the dovetail of the root of he fan or compressor blade allowing the removal of a single blade from the disk and includes a segmented retainer plate disposed at the aft end of the bearing against the blade root to react out the slope induced axial blade loads providing a low hub-tip ratio configuration. A blade support disposed between the live rim of the disk and the bottom of the blade serves to support the blades radially during non-operating conditions and includes pockets for retaining weights for dynamic balance of the rotor. A forward mounted snap ring prevents forward movement of the blade during non-operating conditions.

Abstract: A blade support includes first and second abutting disks, with the first disk having a plurality of axial dovetail slots at one end thereof, and a circumferential dovetail first half-slot at an opposite end thereof, with the second disk having a circumferential dovetail second half-slot therein. A plurality of rotor blades have axial dovetails disposed in respective ones of the axial dovetail slots, and circumferential dovetails disposed in part in each of the first and second half-slots. The first and second disks are retained together so that the first and second half-slots collectively support the circumferential dovetails.

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: A fan blade assembly for a ducted fan gas turbine engine comprises a hub which carries an annular array of radially extending fan blades. Each fan blade has a root portion which locates in a corresponding groove in the hub. Aligned radial slots in the root portion and groove accommodate a U-shaped key which provides axial retention of the root portion in its groove. A flat spring attached to the underside of the root portion maintains the key in position and permits manual deflection of the key to assist blade assembly and disassembly.

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 turbine blade assembly is provided which comprises a rotor which is rotatable about a turbine axis of rotation and a plurality of turbine blades supported by the rotor where each of the turbine blades has a root and the rotor is provided with a plurality of grooves which terminate in a projection. Each groove is shaped for holding each root in a manner such that the root and the groove have mutually contacting surfaces which apply a radially inwardly directed restraining force to the root. The root has a bottom facing the turbine axis and the groove has a base which is located radially inwardly of, and faces, the root bottom. Positioned between the root bottom and the groove base is a lock strip and disc spring assembly for pressing together the mutually contacting surfaces of the root and the groove.

Abstract: A device for axially securing a moving blade and for eliminating rotor unbalances is provided. The moving blade has a blade base. A wheel disk has circumferentially distributed axial grooves. The blade base is anchored in one of the axial grooves wherein the axial groove encloses an indentation formed between a bottom of the axial groove and an end of the blade base. A filler piece operatively arranged on the bottom of the axial groove, and a securing plate having two ends, are insertable into the indentation. The securing plate is arranged to bridge a gap formed between the end of the blade base and the filler piece along an axial length of the indentation with the two ends projecting beyond the indentation. The securing plate is bent at each of its two ends in a mutually opposite manner with respect to end faces of the filler piece, wheel disk and blade base. One rotor unbalance of the blade is compensated by at least one filler piece.

Abstract: A turbomachine rotor includes a disk having a plurality of annular ribs projecting from its periphery to define a plurality of annular grooves, and a plurality of blades, preferably made of composite material, evenly distributed around the periphery of the disk, each blade having a notched root defining heels which fit into the grooves of the disk and which are divided into two groups, one group being offset on the pressure side of the blade and the other group being offset on the suction side so that the heels of the second group align with the heels of the first group of an adjacent blade, the blades being fixed to the disk by pins which extend through the aligned heels of adjacent blades and the ribs of the disk. Each blade is thus secured by two pins, and each pin helps to secure two blades.

Abstract: A system for locking the radial extremity of vanes, wherein the extremities include heels situated behind a ring for delimiting the flow of gases, the heels including hooks between which extend other hooks of the ring. Bolts are disposed in the notches of both types of hooks and fasteners are used to secure the bolts. The assembly obtained is compact, rigid and able to be embodied easily and effectively. It is also virtually free of clearances and vibrations.

Abstract: The present invention discloses a system for cooling turbine rotor disk posts in a gas turbine engine with a preferred embodiment illustrating an application for a high pressure turbine stage 1 rotor disk. The disk includes a plurality of circumferentially alternating posts and slots disposed about the periphery of the disk with each slot receiving a dovetail of a radially extending blade. The cooling system comprises a plurality of seal bodies with each seal body including a relatively low volume thermal isolation chamber positioned over the top of a corresponding disk post; a plurality of axially extending blade cooling plenums supplied with cooling air with one of the plenums positioned radially inward of each of the blades; a plurality of shallow, radially extending slots formed in a relatively low stressed axially facing surface of each of the blade dovetails for diverting cooling air from the blade cooling plenums to the thermal isolation chambers.