Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine wheel having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine blade has a root portion having a first groove and a second groove therein. The turbine wheel includes a plurality of openings in which the turbine blade is positioned. Each of the openings has a first groove and a second groove therein. The space or void formed between the first grooves and the second grooves has a plurality of spherical balls positioned therein. The plurality of spherical balls has a preestablished rate of thermal expansion being equal to the preestablished rate of thermal expansion of the turbine blade.

Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine wheel having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine blade has a root portion having a pair of recessed portions thereon. The turbine wheel includes a plurality of openings in which the turbine blade is positioned. Each of the openings have a pair of grooves therein in which are positioned a pair of pins having a generally rectangular cross-section and a reaction surface thereon. A pair of cylindrical rollers interposed respective ones of the pair of reaction surfaces and the pair of recessed portions. The attachment system or turbine assembly provides an economical, reliable and effective attachment of a component having a preestablished rate of thermal expansion to a component having a greater preestablished rate of thermal expansion.

Abstract: A fan for a ducted fan gas turbine engine comprises a hub carrying an array of generally radially extending fan blades. The hub is hollow and tapered in an axial direction. The radially outer hub surface is provided with a plurality of generally axially extending slots. The slots receive corresponding stepped teeth provided on the radially inner ends of the fan blades. A nose cone engages the upstream end of the roots of the fan blades to ensure that the teeth are retained in the slots.

Abstract: Pairs of cylindrical rolling pin elements are disposed in mating nests between blade dovetails and disk posts in a gas turbine engine rotor assembly. During periods of change of disk rim elastic strain caused by changes in rotor speed, relative movement between the blade dovetails and disk posts is afforded through rolling contact of the pin elements. High pressure load slippage between conventional pressure face portions of dovetails and posts and resultant fretting wear damage is obviated. Multiple pairs of pins and nests and pins of other than cylindrical geometry are also contemplated.

Abstract: The present invention provides an improved adjusting shim used in a valve train for an internal combustion engine for an automobile. The adjusting shim produced from a base material consisting of a ceramic material containing 80 to 98 wt. % of silicon nitride and/or sialon and has a porosity of not more than 3%, a bending strength of not less than 1.0 GPa and an impact compressive elastic limit (Hugoniot elastic limit) of not less than 15 GPa, wherein the base material is provided on the surface thereof which contacts a cam with a ceramic surface layer having a composition different from that of the base material and a hardness lower than that of the base material. The adjusting shim of the present invention enables a power loss of a valve train to be minimized; the abrasion resistance thereof to be improved; and the fuel economy, the performance and durability of an internal combustion engine to be improved.

Abstract: A blade retaining sub-assembly for use in a gas turbine engine which includes at least one radially extending blade mounted in a dovetail slot of a rotatable annular disk. The sub-assembly prevents the blade from migrating from the dovetail slot in an axially forward direction and includes a pair of circumferentially spaced lugs extending from a pair of adjacent disk posts such that each of the lugs are disposed axially forward of, and circumferentially adjacent to, respective ones of the lateral surfaces of the blade dovetail. The sub-assembly further includes a retainer plate disposed in each of the lugs and the plate restrained. The plate includes a body section and a contoured platform which is disposed in confronting relationship with the blade dovetail, wherein the contoured platform includes a periphery which is predeterminedly shaped and positioned so as to enhance a load carrying capability of the plate and lugs.

Abstract: An active cooling mechanism for a turbine disk is disclosed. Various construction details are developed which disclose a turbine section having a rotor assembly, a disk with an attachment means, a radially movable heat shield disposed therebetween, and a cooling passage which directs cooling air over the forward surface and radially outer surface of the attachment means. During operation, rotational forces urge the heat shield radially outward to create a gap between the heat shield and the attachment means, the gap defining a portion of the cooling passage.

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: An annular gasket includes, at least partially conically shaped portion and is supported on a rotor via three bearing surfaces. The conical shape makes it possible to reject the center of gravity of the sections of the rotor which provokes substantial rotational movement when centrifugal forces exist and allows for an improved imperviousness via the internal and external bearings. This invention is applicable for the rotors of aircraft engines provided with axial broachings in which blade feet are able to slide.

Abstract: A sealing and retention device for the blades of a rotor which engage with axial pin settings of the rotor wherein the device includes, in a first embodiment, a flange in the shape of a circular collar which engages the rotor and a locking ring which engages the blades and the flange wherein the locking ring has a conical portion which engages a first protuberance portion of the blades such that upon centrifugal sliding of the locking ring in a radially outward direction, the locking ring is axially displaced toward the flange. The device may also include a conical crest located on the rotor and the flange may have a conical surface for engaging the conical crest of the rotor.

Abstract: The steam transfer arrangement includes dovetail connections between a turbine bucket 14 and rotor wheel 12 wherein a steam supply passage 20 in the rotor wheel registers with a steam return passageway 28 in the bucket and a steam return passageway 30 in the bucket lies in registry with a steam return passage in the wheel. At the interface of the dovetail connection, each registering passage and passageway includes a sleeve 50, 52 disposed in an enlarged recess 54, 56, the sleeves having annular spherical sealing surfaces for engagement with annular spherical seats on the turbine bucket. The sleeves are compressible radially relative to the bucket to enable the bucket to be secured to the wheel and expand radially outwardly to ensure sealing fit between the sealing surfaces and seats.

Abstract: An anti-rotation 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, each having a plurality of dovetail slots. The interstage seal is located between the disks and includes a web portion having a forward arm and an aft arm, the aft arm having a bayonet connection for preventing relative axial movement between the second stage disk and the seal The interstage seal anti-rotation system includes a key positioned in at least one dovetail slot and having a tab for interconnecting with a slot formed in the aft arm bayonet connection. The key prevents relative circumferential movement between the interstage seal and the second stage disk An aft seal plate is provided for retaining the key in the interconnected position between the seal and the second stage disk.

Abstract: A gas turbine engine having a turbine rotor assembly with a free standing sideplate assembly is disclosed. Various construction details are developed which provide a sideplate assembly which is not radially or axially supported by the web or rim of the adjacent disk. In one particular embodiment, a rotor assembly includes a rotor disk, having a rim, a web, and a bore, and a sideplate assembly, having a web and a bore. The web of the sideplate is radially supported by the bore of the sideplate and includes a disk seal and an aperture. The disk seal is engaged with the rotor disk and has an axially directed seal force provided by an axially interfering fit between the sideplate and rotor disk. The aperture provides fluid communication between a source of cooling fluid and the rotor disk.

Abstract: A rotor for a rotary valve of the type including a housing providing a rotor chamber with a material inlet and a material outlet and a drive shaft journaled in said housing for supporting said rotor in said rotor chamber. The rotor includes a rotor shaft operatively connectable to the drive shaft and disposable in said rotor chamber. The rotor shaft has a plurality of longitudinally disposed, circumferentially spaced between recesses in which an edge of a plurality of vanes are received. The recesses include a slot preferably with a dovetail cross-sectional configuration, with the edge of the vanes having a comparable cross-sectional configuration. A pair of shrouds are included on either side of the vanes.

Abstract: A generally wedge-shaped vibration damper for rotor blades of a gas turbine engine has a pair of scrubbing surfaces and is loosely retained in a pocket incorporated in the rotor blade platform. The pocket is partly defined by a plurality of surfaces which orient the damper so that it is slidably displaceable and rotatable only in a predetermined plane. During rotation of the rotor disk, the damper of one rotor blade is displaced in a plane transverse to the rotor axis of rotation by centrifugal forces to a position at which one scrubbing surface of the damper abuts a side surface of the platform of the adjacent rotor blade and the other scrubbing surface abuts an inner surface of the platform of the rotor blade in which the damper is inserted. The scrubbing action of the damper serves to damp vibratory motion in the platforms of both blades.

Abstract: An apparatus and method for axially retaining rotor blades on a rotor disk wherein a integral split ring blade retainer is installed in a groove on a rotor disk and compressed to allow installation of rotor blades into slots on the rotor disk and releasing of the split ring blade retainer from compression causes the split ring blade retainer to engage a hook on the rotor blade and the groove on the rotor disk to react axial loads and prevent axial movement of the rotor blade with relation to the rotor disk.

Abstract: Freestanding rotor blades are mixed tuned by varying the dimensions of the blades at two locations. First, a profiled tip includes a machined-out strip, having a height which can be varied to achieve the desired tuning effect. The longer or deeper the profile, the higher the frequency will become. This tuning technique is used in conjunction with a broadened base section. Blades having a shorter profile tip are machined beginning at the base section, so as to remove enough mass from between the base section and a next upper section to provide the desired tuning effect. The lower frequency blade has a thinner base section and a shorter profile tip.

Abstract: A rotor blade retention assembly includes a rotor blade having a dovetail mounted in a complementary axial dovetail groove in a rotor disk. A primary blade retainer retains the blade in the groove against axial movement in a first direction. A secondary blade retainer retains the blade in the groove after a predetermined travel of the blade in the first direction upon failure of the primary blade retainer to restrain the predetermined travel.

Abstract: The present invention provides an axial blade to disk retaining assembly having a plurality of circumferentially disposed lugs arranged in a ring around an axial facing surface of the blade and disk assembly and a plurality of circumferentially disposed hooks arranged in a ring around the axial facing surface and in circumferential alternating positions with the hooks and radially spaced apart from and open towards the lugs. A split retaining ring is provided that is operable to be placed between said hooks and lugs to axially secure the blades on the disk. In the preferred embodiment each hook is disposed on a disk post between the blades and each lug is disposed on a blade root.

Abstract: Sheet Metal thermal control dampers are disposed in the cavities between turbine blades to bear against the undersides of opposed blade platforms portions of angularly adjacent blades under centrifugal loading to dampen blade vibrations and to seal the gaps between platforms against the radial flow of working fluid into the interblade cavities. The dampers are configured to cooperate with forward and aft seals to also block the axial flow of working fluid through the interblade cavities. Holes are provided in the dampers through which cooling air introduced into the interblade cavities can flow into contact with the platform undersides and cool the platforms, thereby controlling temperature rise in the blade attachment structure.

Abstract: A fan assembly includes a plurality of discrete platforms disposed between adjacent rotor blades extending radially outwardly from a rotor disk. Each platform includes forward and aft axially spaced apart ends, and radially upper and lower spaced apart surfaces extending between the ends. Forward and aft retainer rings capture the platform to the disk with a predetermined clearance therebetween for allowing the platform to move radially upwardly under centrifugal force for retention by the retainer rings, while also allowing the platform to move radially inwardly under a radially inwardly directed impact load on the platform, which impact load is channeled through the platform lower surface at both the forward and aft ends into the rotor disk.

Abstract: A non-integral rotor blade platform for a rotary machine is disclosed. Various construction details are developed which disclose a one-piece, non-integral rotor blade platform retained to a live rim area of a disk. In one embodiment, a rotor blade assembly (48) is comprised of a plurality of rotor blades (54) disposed on a disk (44), a plurality of platforms (60), each platform disposed between adjacent rotor blades, and a front cover plate (56) and rear cover plate (58) which, in conjunction, retain the platforms to the disk. In an alternative embodiment, each platform (102) has a supplemental mechanical fastener means (100) to provide additional retention of the platforms to a disk (104).

Abstract: A forward seal assembly located in a turbine section of a turbine engine, the turbine section having a disk including a web, a bore, and a forward shaft integral with the web, wherein the forward seal assembly includes a face plate extending from the forward shaft to an outer periphery of the disk and includes orifices for conveying cooling air to the web. The face plate includes a plurality of radially inwardly-extending tabs shaped to engage radially outwardly-extending tabs located on the web to form a bayonet connection. The forward seal assembly further includes radially extending vanes to convey cooling air along the disk, and is secured by inward and outward bayonet connections, the inward connection including locking pins which are arranged to perform a balanced function.

Abstract: A gas turbine engine impeller having a plurality of blades attached to a rotor disk and an integral, annular collar defining openings through which the blades extend which acts as a platform extending between the adjacent blades. The annular collar is formed as an integral, annular structure and may be formed from a composite material, or other material which is resistant to high temperatures and high centrifugal forces. The annular collar defines a plurality of openings to accommodate the blade portion of the plurality of blades and to enable the blades to extend radially outwardly from the collar. The openings may be formed in the annular collar when the collar itself is formed, or may be machined therein after the collar has been fabricated.

Abstract: A sealing device for compressor axial dovetail rotor blades for a gas turbine engine comprising a sealing member having a finger portion extending from a main body portion which engages a disk hook located on each disk post and forms a first point of contact about which the sealing member rotates. The sealing member further comprises an extended skirt portion which engages the blade platform of the rotor blades forming a second point of contact. The main body has a center of gravity positioned such that during operation of the engine the main body pivots due to centrifugal force about the disk hook such that the skirt portion engages the blade platform. A split ring is located between the disk posts and a tail portion extending from the lower portion of the sealing member and engages the disk post and tail portion during operation of the engine thereby forming a third point of contact.

Abstract: A rotor and blade assembly for a gas turbine engine in which blades are retained in position on the rotor by a plurality of circumferentially extending segment plates and a snap ring, the segment plates extending radially between a circumferential groove in the rotor and the underside surface of a blade platform and extends circumferentially to seal at least two blade roots, and the snap ring is installed in a groove on the underside of the blade platform and external of the platform surface contacted by a segment plate, the snap ring covering the outer peripheral portion of the segment plates.

Abstract: An improved type wear protection system for a turbine engine rotor and blade, in which a multilayer clad shim is interposed between a dovetail portion of a blade and the dovetail slot portion of a rotor, is described. The shim, preferably comprised of surface layers of phosphor bronze and a center layer of austenitic stainless steel, is especially effective in preventing fretting damage to titanium engine components.

Abstract: An underplatform damper contact portion 54 is rigid, and provides a loose seal between the underplatform cooling air 46 and the gas stream 40. At the aft end of the blade platform the pressure difference increases and a more effective seal is provided by the snap-in flexible seal 71.

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

Abstract: A seal assembly for use in a compressor stage of a turbine engine having a rotor disk which is attached to a plurality of rotor blades. Each rotor blade has an axially oriented dovetail attachment which connects to the rotor disk. Each rotor blade has an aftward side which is in contact with a high pressure region and a forward side which is in contact with a low pressure region. A plurality of seal segments form an annular ring located radially inward from the plurality of rotor blades. Each seal segment has an offset center of gravity which causes each seal segment to be securely attached to the rotor disk as centrifugal forces act upon each seal segment during rotation.

Abstract: Disclosed is apparatus to prevent vibration of a pinned root fan blade during low speed revolution of the blade comprising a damping device which extends between the airfoil of the blade and the engine structure.

Abstract: A method and apparatus for reducing thermal distress and creep of a disk post in a gas turbine engine, the disk post being defined between an adjacent pair of blade roots of a respective pair of turbine blades in a turbine disk. The blade roots extend radially outward of the turbine disk and each terminate in a blade platform to form a cavity above the disk post. A seal generally covers the cavity for preventing a flow of combustion gases over the disk post. The seal includes axial segments defining a channel over a radially outer surface of the disk post. A flow of insulative air is directed into the channel defined over the disk post and diffused to reduce its velocity. The insulative air effectively reduces heat transferred from the blade platforms and combustion gases to the disk post.

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

Abstract: An annular member is attached coaxially to a disk of a turboshaft engine by ounting element comprising two separate sets of interengageable lugs, each set consisting of one ring of equi-angularly spaced lugs on the disk and another ring of equi-angularly spaced lugs on the annular member which is interengageable with the first ring by interleaving and overlapping the lugs of the two rings in bayonet fashion, the two sets of lugs being offset radially from each other and arranged so that they are interengageable simultaneously with each other. In addition the disk and the annular member are provided with substantially cylindrical coaxial surfaces which engage each other to ensure that the annular member is centered on the disk when the two sets of lugs are interengaged to attach the member to the disk.

Abstract: Turbomachine wheel having blades mounted on a rotor including an annular peripheral ring in which are formed open axial recesses each of which receives the root of a blade. Each blade is radially retained in the recess by cooperation of complementary shapes of the fir tree type, with a direction of fitting being parallel to the axis of the rotor. The blade root is axially immobilized in the recess by a first flange and a second flange which are respectively disposed adjacent to the opposite lateral faces of the rotor, and at least partly close the opposite axial ends of the recesses for the roots of the blades. The first flange is fastened to the rotor by a bayonet type device whose lugs are formed on the first flange and are received in notches formed in the annular ring of the rotor with open ends of the notches for engagement of the lugs opening onto the transverse walls which define the recesses.

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

Abstract: A metallic reinforced shim is attached to the dovetail of turbine or compressor blades. The shim reduces frictionally induced wear damage to the rotor. In one form, a single ply shim reinforced with a metallic doubler has an anti-fretting layer deposited on the shim face contacting the dovetail slot pressure face, and a doubler layer fastened to the anti-fretting layer in the non-contacting regions to prevent slippage of the shim on the blade. In another form, a multi-layer shim has two layers interposed between the blade dovetail and the disk dovetail slot, with the layers treated so that they do not readily slip relative to the titanium pieces, but do slip relative to each other. The shim is also reinforced with a metallic doubler. Fretting is confined to the consumable shim, and therefore the disk dovetail slot and the mating blade dovetails are not subject to surface degradation with corresponding reduction in fatigue capability.

Abstract: A turbine assembly includes a unitary rotor spool having first and second rotor discs. A set of first blades having axial entry dovetails are joined to the first disc, and a set of second blades having axial entry dovetails are joined to the second disc. A unitary annular spacer is disposed axially between the first and second dovetails for preventing the first and second blades from sliding axially toward the spacer. The spacer has an inner diameter greater than an outer diameter of the first rotor disc for allowing the spacer to be assembled over the first rotor disc during assembly.

Abstract: A rotor disk 18 and rotor blade 26 assembly is disclosed having a blade lock 66 which retains the rotor blade against axial movement in an axially extending blade retention slot 58. Various construction details are developed which shield the dead rim region D.sub.d and shift at least a portion of the loads associated with the locking device from the dead rim. In one detailed embodiment, a projection 68 from the live rim D.sub.1 of the disk 18 is adapted by slots 86 to receive blade locks 66.

Abstract: A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the inner rotor. The attachment structure includes first and second male members of hook-like configurations spaced axially along and circumferentially extending about the rotor, and first and second grooves defined by flanges attached to the rotor and axially spaced along and circumferentially extending about the rotor. The grooves open in a common axial direction for receiving in mated relation respectively and concurrently the hook-like configured first and second male members. The attachment structure also includes several different locking arrangements for locking the male members in mated relation with the grooves to thereby restrain the turbine blade against radial and axial movements relative to the rotor.

Abstract: A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the outer rotor. The attachment structure includes first and second male members spaced axially along and circumferentially extending about the rotor, and first and second grooves spaced axially along and extending circumferentially about the rotor being defined by flanges attached to the rotor. Each male member has a first portion attached to an end of a turbine blade and extending therefrom in a radial direction. The first male member has a second portion attached to its first portion and extending therefrom in an axial direction to define the first male member with an overall hook-like cross-sectional configuration. The first groove is cross-sectionally shaped for receiving in mated relation the second portion of the first male member.

Abstract: To ensure retentioin of the blade tongue 16 of a prop-fan blade 10 within a receiving slot 24 in the disc arm 20 of the fan hub 4 even under the high centrifugal forces exerted on the blade 10 while rotating at high rpm, at least one pair of retaining pins 30 and 40 are provided. First seating grooves 32 and 42, respectively, are provided on opposite faces 15 and 17 of the blade tongue 16 and holes 34 and 44 are drilled transversely through the disc arm 20 so as to form corresponding second seating grooves 36 and 46, respectively, on opposite side walls 26 and 28 of the slot 24. The first and second seating grooves are arranged opposite of and parallel to each other such that each pair of grooves 32 and 36 form a retention channel between the first face 15 of the tongue 16 and the opposed side wall 26 of the slot 24 and aligned with the holes 34 and 44 for receiving the retaining pins 30 and 40 thereby locking the blade tongue within the slot 24.

Abstract: An anti-deployment device and method for preventing inadvertent deployment of a ram air turbine of an aircraft during servicing or repair of turbine employ an anti-deployment pin which can be manually inserted in a support arrangement for the pin on the aircraft when the ram air turbine is in the stowed position for preventing deployment of the turbine upon release of a lock mechanism which locks the turbine in the stowed position. The pin has an elongated body with an outer, flat contact surface portion which extends in a plane that is inclined with respect to a longitudinal center axis of the pin.

Abstract: A fan blade retention device includes a collar (13) inserted into a circumferential groove (14) cut into the hub (6) of a turbofan engine. The outward facing groove (14) is positioned aft of the fan blade fixing channel (15). When the fan blade root (11) is completely received within the blade fixing channel (15), the blade root (11) contacts the collar (13) and is prevented from traveling further aft. If the collar 13 is segmented, an annular rear cover plate (19) holds the segmented collar (13) radially within the groove (14).

Abstract: A hollow hub has around its exterior a plurality of apertures for individually receiving a respective cylindrical inner end portion of one of a plurality of axially rotatable propeller blades. Additionally, the hub has around its exterior a plurality of arcuate recesses for (a) individually receiving an inner portion of one of the respective propeller blades when the cylindrical inner end portion of that blade is received in one of the apertures, and (b) accommodating arcuate movement of the blade inner portion upon axial rotation of the cylindrical inner end portion of the blade.

Abstract: A gas turbine engine blade is disclosed which includes a dovetail having retention lobes and fillets. Compression loads are provided in the dovetail for introducing compressive prestresses at the fillets for reducing tensile stresses at the fillets due to loads in the blade such as centrifugal tension loads. In an exemplary embodiment, the compression means comprises a cavity in the dovetail and an insert disposed therein in an interference fit for generating compressive stresses at the cavity and at the fillets.

Abstract: A method and apparatus for securing or attaching a rotor blade with a turbine rotor cavity by disposing an expanding material between the blade root and the cavity walls. The expanding material comprises a naturally occurring mineral which expands to a great degree when exposed to elevated temperatures. The expanding material may be provided in the form of shims made directly from the expanding material or made from a composition of the expanding material and a binder such as a polymer or elastomer. Alternatively, the expanding material may be provided in the form of a liquid vehicle applied to surfaces of the cavity walls. The expanding material is located at specific positions within the cavity to urge certain surfaces of the blade root against certain surfaces of the cavity walls. In this manner, the blade can be forced into a tight fit and an aligned position, with respect to the rotor, upon expansion of the expanding material.

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

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

Abstract: Rotor blade and disk structures enabling the disassembly and reassembly of a single rotor blade are disclosed. The concepts are particularly suited to configurations employing interlocking mid-span shrouds which inhibit the withdrawal of a single blade from a disk.In one specific geometry the rotor blade root section (20) and the disk attachment slot (24) are contoured to provide increasing clearance between the bottom of the blade root section and the attachment slot as the blade is withdrawn axially from the slot. Rocking of the blade within the provided clearance enables withdrawal of the blade around the shroud segments (30,32) and airfoil sections (16) of the adjacent blades (12).