Abstract: The present invention relates to a damping element for independent blades of a turbomachine in which the blades fastened in the rotor are connected together, preferably in the radially outer region, the connection between two blades consists of an elastically deformable platelet curved towards the center of the rotor, which platelet engages in retention features on the suction side of one blade and on the pressure side of a second, neighboring blade. The retention features on the blades can be either recesses or protruding lugs, in or on which the platelets are supported.

Abstract: In order to damp blade vibrations, the shroud plates of the blades are equipped with magnet inserts.

Abstract: Turbine blades are held in long arc groups by a shroud structure, with gaps between segments of the shroud structure. These gaps are Z-shaped, the gaps tending to close due to untwisting of the blades when the blades are subjected to high centrifugal forces.

Abstract: In the rotor blade ring of an axial flow turbomachine, the rotor blades are each provided at their radially outer ends with a shroud plate and are fastened at their radially inner ends, by means of a root, in a corresponding groove of the machine rotor. The shroud plates are connected together in the peripheral direction by means of wires rolled into turned recesses. Grooves (10), with a clear width (w.sub.1) which is dimensioned larger than the width (w.sub.2) of the shroud plate turned recess (8) provided for the wire (7) to be rolled in, are machined in the end surface (6) of the shroud plate (2). A spacer means (11), surrounding the wire at least in the region of the rolling positions and removable after rolling, is laid in the grooves during the rolling procedure. This material is preferably a hard paper which is burnt to ashes during machine operation.

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 stage of an axial flow turbine includes a plurality of spaced apart buckets and a plurality of spaced apart nozzle partitions, each plurality respectively circumferentially aligned about and axially spaced from each other along a rotor of the turbine. The nozzle partitions are circumferentially spaced such that a minimum throat extends a predetermined radial distance from the root, thereby forming a converging-diverging flow passageway between nozzle partitions. The trailing edge of the nozzle partitions are disposed to include axial and tangential lean with respect to the rotor. Buckets include a plurality of covers respectively connecting the tips and having a single outward radially extending sealing rib on the radially outer surface of each cover, wherein each rib is tangentially aligned with respective adjacent ribs. Buckets are overtwisted to compensate for untwist at operational speed to achieve optimum efficiency.

Abstract: A fixture 34 for positioning a shroud 22 of a worn rotor blade 14 with respect to an apparatus for removing material is disclosed. The fixture is formed of a base 42, an axial locator 44 which is adapted to engage the root 18 of the rotor blade, and a tangential locator 46 which engages the root of the rotor blade at a hinge joint 58 and which engages the airfoil 20 of the rotor blade. A method of restoring a shroud of the rotor blade axially with respect to the root and tangentially with respect to the airfoil is also disclosed. In an alternate embodiment, a second locator 160 for indexing the locator from an airfoil edge is included.

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: An air guide ring arrangement is disclosed for guiding air flow around an axial fan of a liquid cooled internal combustion engine having a radiator through which air is drawn by the fan. To facilitate construction of a minimal sized air gap between the air guide ring and the fan blades, the air guide ring is supported by a gibbet or bracket arm fixed to the engine and by a spoked support wheel rotatably borne at the outer circumference of the fan hub.

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: 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: A circumferentially extending structure 30 for containing particles having an axial component and a radial component of velocity is disclosed. The apparatus is comprised of a support structure 46 and a fabric 44 wrapped under tension about the support structure such that the installed length of the fabric is greater than the free length of the fabric. In one particular embodiment the fabric is coated with a layer of epoxy resin such that the resin penetrates only the top layer of the fabric to form a shield 95 which protects the containment fabric from injury. A method for forming the circumferentially extending structure is disclosed which includes the steps of forming a support structure and wrapping a fabric about the support structure under a preload to cause an elongation of the fabric and tension in the fabric in the installed condition.

Abstract: A circumferentially extending structure 30 for containing particles having an axial component of velocity and a radial component of velocity is disclosed. The structure includes an inner casing, such as the first casing 48, and an outer casing, such as the second casing 50. The outer casing is flexible. The outer casing is formed of a plurality of layers of fabric and a means for applying a load to the fabric such as a plurality of bars 80, 82 and turnbuckles 74. A method of forming the structure is disclosed. The method includes the step of wrapping a fabric having a first length about the inner casing and the step of stretching the fabric to a second length to affect the operative response of the fabric to the impact of a particle.

Abstract: A circumferentially extending apparatus 46 for containing particles having an axial component and a radial component of velocity is disclosed. The apparatus is comprised of a support structure 48 and a flexible casing 50 formed of a fabric 78. The external surface of the support structure has a first diameter and a second diameter not equal to the first diameter at a location spaced axially from the location of the first diameter. The fabric is preloaded to increase the length of the fabric and is wrapped under tension about the surface of the support structure such that the installed length of the fabric is greater than the free length of the fabric. A method for forming the circumferentially extending structure is disclosed which includes the steps of forming a support structure and wrapping a preloaded fabric about the support structure to cause an elongation of the fabric and tension in the fabric in the installed condition, which varies depending on the diameter of the support structure.

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 circumferentially extending structure 30 for containing particles having an axial component and a radial component of velocity is disclosed. The apparatus is comprised of a hollow annular beam 48 and a fabric 46 wrapped under tension about the annular beam such that the installed length of the fabric is greater than the free length of the fabric. In one particular embodiment the fabric is coated with a layer 116 of epoxy resin such that the resin penetrates only the top layer of the fabric to form a shield. The shield layer protects the containment fabric from injury.

Abstract: A circumferentially extending structure 30 for containing particles having an axial component of velocity and a radial component of velocity is disclosed. The structure includes an inner casing 48 and an outer casing 50. The outer casing is formed of a plurality of layers of flexible fabric and includes layers having differing masses per unit length in the fabric. The layers of fabric extend about the inner casing. A means for applying a load to the fabric engages the fabric to place the fabric in tension. One such means is a plurality of bars 80, 82 and turnbuckles 74. In one embodiment, the fabric has a greater mass per unit length in the leading edge region and a greater tension is applied to the leading edge region than other regions of the fabric. A method of forming the structures is disclosed.

Abstract: An improved blade rotor structure for an axial flow turbine substantially reduces vibratory stress at resonant frequencies by rigidly connecting the blades to each other in groups equal in number to an integer multiple of the resonant frequency of the blades (i.e. a harmonic frequency) divided by the rotor running speed. Flexible tie means are used for connecting adjacent groups of blades together for substantially reducing axial-torsional vibration of the blades.

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: A device for interconnecting turbine blades comprises a pair of projections extending towards each other from the opposing sides of the tips of adjacent blades, having an inclined inward surface, and having a radially extending perforation. A cover piece has a pair of inclined outward surfaces conforming to the inward surfaces of the projections. The cover piece also has lugs extending through the perforations in the projections. One of the lugs has its end peened to form an overhang for abutting the projection. The perforation of the opposite projection is elongated to permit untwist of the turbine blades.

Abstract: A turbomachinery blade, which includes an airfoil and a projection from the airfoil for the purpose of abutting contact with the surface of an adjacent member is provided with a surface means having an improved combination of adhesive wear resistance and impact toughness through the attachment to the contact surface of a discreet wear pad. The pad comprises a substantially fully dense, compacted, sintered member of a material selected from carbides, nitrides and borides, with or without a suitable binder, the pad being of a thickness of at least about 0.01 inches and having thermal expansion characteristics compatible with the projection over the range of intended operating temperature.

Abstract: A turbomachine rotor arrangement is provided having a rotor wheel and blades thereon with a tie pin for interconnecting adjacent blades. A plurality of blades respectively define tie holes wherein the tie holes of adjacent blades are disposed with the radial heights of said holes being different and with the tie pin disposed in the tie holes so as to be acted upon by respective different amplitudes of vibration than said adjacent blades during rotation.

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: An interblade seal and vibration damper to be positioned in the damper cavity defined between a rotor disc, adjacent blades and adjacent blade platforms so as to seal across an interplatform gap by providing line contact between the damper and the platforms on opposite sides thereof for the full axial dimension of the cavity and with the damper shaped so as to have a low center of gravity for operational stability and which damper also responds to centrifugal force during rotor operation to establish damping friction between said damper and said platforms when the platforms move circumferentially.

Abstract: A rotor apparatus comprising a blade having a root adapted to swing laterally within a supporting spindle under impact loading is provided with a flow path defining platform. The platform comprises an inner shroud extending generally laterally of the blade airfoil portion and adapted to swing laterally therewith. In one embodiment wherein the blade primarily comprises a laminate of composite filament plies, the inner shroud is bonded to the laminate. An outer shroud, fixed with respect to the supporting spindle, forms a lateral extension of the inner shroud with the blade in its normal operating position. The inner and outer shrouds are provided with a pair of complementary adjacent surfaces contoured to pass in relatively close-fitting relationship to each other when the blade swings under impact loadings.

Abstract: A turbine rotor construction in which the disk has radially extending tubes on which ceramic blades are slidable, and the centrifugal load on the blades is carried by an external filament wound ring surrounding and engaging the outer ends of the row of blades.

Abstract: A vibration, damper, or snubber device is disposed on the radially outward surface of a shroud member mounted on a turbine rotor. The rotor has an annular array of twisted blades connected together to form blade groups by a first and a second shroud member. The vibration damper, or snubber, is mounted on the first shroud member and extends therefrom across a gap between the shroud members to circumferentially overlap a portion of the second shroud member. A predetermined axial gap is defined between a portion of the second shroud and the snubber. When an untwist motion is imposed upon the blades due to rotation of the rotor, the axial gap closes and an abutment between the snubber and the second shroud occurs to inhibit further untwist motion and to simultaneously provide a friction interface to inhibit circumferential motion between the second shroud and the vibration damper.

Abstract: Continuous connection device for the mobile turbine blades of a turbo-mace, characterized in that the caps of the turbine blades comprise recesses accomodating clamping blades whose ends press against the neighbouring caps, becoming deformed elastically. The invention applies more particularly to elastic fluid turbines.

Abstract: Damping of turbine or compressor vanes loosely supported in an outer shroud is accomplished by means of resilient metal damping pads which have slots to accommodate the outer ends of the vanes. The damping pads engage the opposite sides of the vanes and the slots are formed so as to provide gaps or relief areas between the pads and the side and end edges of the outer ends of the vanes.

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.