Divided Blade Root Patents (Class 416/217)
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Publication number: 20130195668Abstract: A turbomachine rotor includes a rotor blade mounted to a rotation element. The rotor blade includes a root for mounting the rotor blade to the rotation element. The root has a protrusion structure forming a stop face supporting the mounted root against the rotation element under action of a radially inwardly directed force. The protrusion structure defines a maximum clearance between the stop face and the rotation element. The root is radially moveable to a certain extent where in a radially outermost position the protrusion structure has the maximum radial clearance from the rotation element. The rotation element includes a groove therein. The groove has a groove face bearing the stop face of the rotor blade under action of a radially inwardly directed force. The groove is a circumferential groove extending in a circumferential direction with regard to an axis of rotation of the rotation element.Type: ApplicationFiled: September 7, 2011Publication date: August 1, 2013Inventor: Trevor Milne
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Patent number: 8459952Abstract: A device for connecting a blade to a rotor shaft of a continuous flow machine, includes a first fork foot which has a quantity of first foot lugs with first bore holes, a second fork foot which has a quantity of second foot lugs with second bore holes, and at least one connection bolt which passes through first and second bore holes to connect the first fork foot to the second fork foot. The device has a first area with a predetermined first diameter difference between a first inner diameter of one of the bore holes and a first outer diameter of the connection bolt, and a second area with a predetermined second diameter difference between a second inner diameter of one of the bore holes and a second outer diameter of the connection bolt, wherein the first diameter difference and the second diameter difference differ from one another.Type: GrantFiled: March 10, 2010Date of Patent: June 11, 2013Assignee: MAN Turbo AGInventors: Klaus Behnke, Uwe Quitmann
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Patent number: 8251667Abstract: A retaining system is provided for circumferential entry rotor dovetails inserted into dovetail slot in a rotor. A plurality of rotor blade dovetails are circumferentially slidable into and along the dovetail slot, with each rotor blade dovetail having a neck and a pair of oppositely oriented lobes. A plurality of rail segments are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops. The rail segments define a first pressure face that engages against an outward pressure face of the dovetail lobes, and a second pressure face that engages against an inward pressure face of the respective disk hoop component.Type: GrantFiled: May 20, 2009Date of Patent: August 28, 2012Assignee: General Electric CompanyInventors: Ian David Wilson, Kenneth Damon Black, Bradley Scott Carter
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Patent number: 8157530Abstract: A closing assembly is provided. The closing assembly closes the gap remaining between the first blade and the last blade of a blade ring that is inserted in a peripheral groove of a turbo machinery, the assembly consisting of at least two lateral parts, at least one of which may be hooked onto a projection that forms an undercut in the peripheral groove and at least one securing element, which secures the parts from coming detached from the peripheral groove. To provide a particularly reliable closing assembly, the securing element is configured as a pin, joining the parts of the closing assembly in a non-positive fit.Type: GrantFiled: December 27, 2006Date of Patent: April 17, 2012Assignee: Siemens AktiengesellschaftInventors: Joachim Krützfeldt, Markus Kunze, Silvio-Ulrich Martin, Stefan Mutke, Kang Qian, Christoph Richter, Oliver Schneider, Peter Schröder, Michael Schwarz, Ulrich Waltke
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Patent number: 8157531Abstract: A closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery is provided. The assembly includes at least two parts each of which can be hooked onto projections that form an undercut in the peripheral groove and includes a securing element, which secures the parts from becoming detached from the peripheral groove. For closing the remaining gap, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web. The web can be positioned by rotation is such a way that to fit the parts in the peripheral groove. The parts can be displaced in relation to one another and to secure the parts from being detached from the groove. The web can be placed against at least one lateral face of one of the parts.Type: GrantFiled: December 27, 2006Date of Patent: April 17, 2012Assignee: Siemens AktiengesellschaftInventors: Joachim Krützfeldt, Markus Kunze, Silvio-Ulrich Martin, Stefan Mutke, Kang Qian, Christoph Richter, Oliver Schneider, Peter Schröder, Michael Schwarz, Ulrich Waltke
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Patent number: 8061994Abstract: A rotorcraft rotor blade (1) has a blade root (1?) and a free end opposite from the blade root (1?), the blade (1) being provided at least with a spar (2) laid flat on a suction-side face (3) and a pressure side-face (4) of the blade (1), the main spar (2) being secured to an attachment fitting (5) at the blade root (1?). The attachment fitting (5) then includes first and second horizontal fastener bushings (10, 20), the first and second fastener bushings (10, 20) being both perpendicular to the span of the blade (1) and substantially perpendicular to an elevation direction (Z) that is substantially parallel to gravity (W), the elevation direction (Z) being perpendicular to the span.Type: GrantFiled: November 13, 2008Date of Patent: November 22, 2011Assignee: EurocopterInventors: Jean-Marie Parisy, Rémi Metivier
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Publication number: 20100296936Abstract: A retaining system is provided for circumferential entry rotor dovetails inserted into dovetail slot in a rotor. A plurality of rotor blade dovetails are circumferentially slidable into and along the dovetail slot, with each rotor blade dovetail having a neck and a pair of oppositely oriented lobes. A plurality of rail segments are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops. The rail segments define a first pressure face that engages against an outward pressure face of the dovetail lobes, and a second pressure face that engages against an inward pressure face of the respective disk hoop component.Type: ApplicationFiled: May 20, 2009Publication date: November 25, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: IAN DAVID WILSON, KENNETH DAMON BLACK, BRADLEY SCOTT CARTER
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Patent number: 7766621Abstract: A shroudless turbine rotor blade of the type having a platform damper interface, is provided with at least one slot which extends from the aerofoil side of a platform flow boundary to a point in the root. The slot extends between opposing flanks of the blade so as to divide the platform and partially divide the root. The segregated root is made more flexible by the slot which provides for greater platform vibratory amplitudes for a given length of root. The increased platform motion provides for improved dampability when the blade vibrates. The slot also provides a pair of confronting platform surfaces which are urged into mutual contact by centrifugal load acting on the blade to create an additional damping interface.Type: GrantFiled: November 16, 1995Date of Patent: August 3, 2010Assignee: Rolls-Royce PLCInventors: Peter J Maggs, Steven M Bagnall, Neil M Evans
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Patent number: 7387494Abstract: A bucket to wheel dovetail attachment includes axially spaced radially extending wheel fingers having discrete sections of decreased axial thickness in a radial outward direction with transition fillets between sections of different thicknesses. The wheel fingers define wheel finger slots for receiving correspondingly shaped bucket dovetail fingers. Pins interconnect the buckets and rotor wheel. The slot bottoms likewise have fillets. The fillets on the wheel fingers and slot bottoms have a blend of different radii with the larger radii outward of the smaller radii to reduce stress concentrations and to avoid stress corrosion cracking in steam turbine applications.Type: GrantFiled: April 28, 2005Date of Patent: June 17, 2008Assignee: General Electric CompanyInventors: Gary Edward Yehle, Thomas Joseph Farineau, Yavuz Kadioglu
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Patent number: 7104758Abstract: A rotor of a steam or gas turbine is equipped with rotor blades, which are held in the rotor (6) in a plurality of radial rows and comprise a blade foot 1 installed in the rotor (6), a blade leaf (2) and a cover plate (3). An open pocket (5) is prepared in the sloping surfaces of the cover plates (3) of a row of rotor blades, which the sloping surfaces are located opposite each other. The pockets (5) of two adjacent cover plates (3) form together an essentially closed cavity, which expands in the radial direction of the rotor (6). A pin, whose largest cross section is smaller than the largest cross section of the cavity but larger than the smallest cross section of the cavity, is placed freely movably into each cavity.Type: GrantFiled: August 25, 2004Date of Patent: September 12, 2006Assignee: MAN TURBO AGInventors: Hans-Egon Brock, Günter Neumann, Hans Jeske
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Patent number: 6422820Abstract: A fan blade includes perforated anchor tangs, one with inboard corners and the remainder without. The corners are disposed in a complementary seat in a rotor disk for limiting blade pivoting during assembly.Type: GrantFiled: June 30, 2000Date of Patent: July 23, 2002Assignee: General Electric CompanyInventors: Bernard Joseph Anderson, Jeffrey Howard Nussbaum, Juan Mario Gomez
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Patent number: 5919032Abstract: The blades (10) of a turbine or a compressor are here fixed to the disk (1) by three roots (7, 8 and 9) inserted in the same number of circular grooves (4, 5 and 6). This assembly makes it possible to provide a good distribution of stresses during functioning.Type: GrantFiled: January 7, 1998Date of Patent: July 6, 1999Assignee: Societe Nationale d'etude et de Construction de Moteurs d'Aviation "Snecma"Inventors: Jacky Naudet, Christophe Poy
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Patent number: 5584658Abstract: A turbocompressor disk having on its periphery a circular groove able to receive blade roots having a substantially hammer shape, said circular groove comprising an upstream lip and a downstream lip against which bear the blade roots. The upstream lip has a curvature of gradient inclined by an angle .alpha. with respect to the plane perpendicular to the rotation axis and the downstream lip has a curvature of gradient inclined by an angle .beta. with respect to the plane perpendicular to the rotation axis, .alpha. being strictly different from .beta..Type: GrantFiled: July 21, 1995Date of Patent: December 17, 1996Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"Inventor: Jacques M. P. Stenneler
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Patent number: 5580219Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine flange having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine flange includes a first upstanding flange and a second upstanding flange having a groove formed therebetween. The turbine flange further includes a recess. Each of the first and second upstanding flanges have a plurality of bores therein. A turbine blade has a first member and a second member positioned in one of the groove and the recess. Each of the first member and the second member have a plurality of bores therein. And, a pin is positioned in respective ones of the plurality of bores in the first and second upstanding members and the first and second members and attach the blade to the turbine flange. The pin has a preestablished rate of thermal expansion being substantially equal to the rate of thermal expansion of the blade.Type: GrantFiled: March 6, 1995Date of Patent: December 3, 1996Assignee: Solar Turbines IncorporatedInventors: Gary A. Frey, deceased, Oscar D. Jimenez
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Patent number: 5511948Abstract: In an axial-flow turbine, at least one of front and rear side contact surfaces of shrouds (3a or 3b) of blades (1a or 1b) with respect to the turbine rotational direction is formed at certain angle with respect to a radial line connecting the rotor center and the contact surface. The shroud (3a) of the blade (1a) of a first kind is formed in a trapezoidal shape converging radially outward in cross section taken in a plane perpendicular to the turbine axial direction, and the shroud (3b) of the blade (1b) of a second kind is formed in an inverted trapezoidal shape converging radially inward in the cross section. Further, half of an angle (2.alpha.) between the front and rear side contact surfaces of the shrouds (3a or 3b) is made smaller than a static frictional angle of the contact surface.Type: GrantFiled: October 11, 1994Date of Patent: April 30, 1996Assignee: Kabushiki Kaisha ToshibaInventors: Atsuhide Suzuki, Hirotsugu Kodama, Toshio Suzuki
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Patent number: 5494408Abstract: In a steam turbine rotor wheel and bucket dovetail joint construction wherein the wheel dovetail includes three radially aligned hooks each interconnected by a neck having an upper and lower fillet, an improvement includes redesigned fillet radii which, in a first embodiment, include the upper fillet having a radius greater than the lower fillet radius. In certain embodiments, the upper fillet may have a radius twice that of the lower fillet. In other embodiments, the radii in both the upper and lower fillets have been enlarged.Type: GrantFiled: October 12, 1994Date of Patent: February 27, 1996Assignee: General Electric Co.Inventors: Robert E. Seeley, Raymond J. Jones, Carl L. De Cesare, James H. Vogan, Joseph H. Stocks, III, Carlos E. Silva
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Patent number: 5425622Abstract: The multi-lug attachment of the blades to the disk of a turbine rotor of a gas turbine engine, where the blades are air-cooled, optimizes weight reduction and tensile stress by attachment including a pair of lugs that transitions from a contoured airfoil to a pair of parallel rails releasably attached to complementary recesses formed in the disk. One lug is transitioned from the pressure surface to the attachment surface and the other lug is transitioned from the suction surface to the attachment surface. The lugs are tapered to optimize the attachment.Type: GrantFiled: December 23, 1993Date of Patent: June 20, 1995Assignee: United Technologies CorporationInventor: Thomas R. Murray
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Patent number: 5409353Abstract: 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.Type: GrantFiled: January 13, 1994Date of Patent: April 25, 1995Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"Inventor: Jean-Francois Imbault
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Patent number: 5354176Abstract: A variable pitch propeller blade system includes a conductive clevis attached to a rotor, a mating non-conductive clevis fastened to a non-conductive propeller blade, a pin journaling through bores in each clevis, joining the clevises to form a hinge joint, and a conductive path along a substantial part of the propeller blade.Type: GrantFiled: September 29, 1993Date of Patent: October 11, 1994Assignee: General Electric CompanyInventors: Jan C. Schilling, Charles E. Steckle
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Patent number: 5310317Abstract: A gas turbine engine rotor blade includes an airfoil joined to a dovetail. The dovetail includes a shank from which extends two pairs of dovetail tangs being defined by a bifurcating slot disposed therebetween. The dovetail is configured for retention in a complementary dovetail groove in a rotor disk with the bifurcating slot remaining empty for reducing weight of the blade while transferring centrifugal loads from the blade to the rotor disk.Type: GrantFiled: August 11, 1992Date of Patent: May 10, 1994Assignee: General Electric CompanyInventors: Mark J. Bailey, Robert K. Mitchell, Jr.
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Patent number: 5271718Abstract: A rotor blade for a gas turbine engine includes an airfoil, platform and dovetail. The platform has top and bottom surfaces, with a plurality of pockets disposed in the bottom surface for reducing weight of the platform, with the pockets defining a plurality of continuous beams extending along the platform which provide structural stiffness to the platform to avoid resonance vibration thereof during operation.Type: GrantFiled: August 11, 1992Date of Patent: December 21, 1993Assignee: General Electric CompanyInventors: Robert K. Mitchell, Jr., Mark J. Bailey
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Patent number: 5205714Abstract: 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.Type: GrantFiled: March 16, 1992Date of Patent: April 27, 1993Assignee: General Electric CompanyInventors: Samir I. Shah, Ramon Themudo, Michael Even-Nur
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Patent number: 5165856Abstract: An aircraft propeller system of the unducted fan type includes a plurality of propeller blades which are respectively fastened to a rotor, rotate about an axis of rotation and also rotate about a pitch axis. Each blade is fastened to the rotor by a hinge which has a pivot axis to reduce the effective stiffness of each blade, the pivot axis being non-parallel to the axis of rotation.Type: GrantFiled: February 20, 1991Date of Patent: November 24, 1992Assignee: General Electric CompanyInventors: Jan C. Schilling, Charles E. Steckle
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Patent number: 5145319Abstract: An axial flow turbomachine rotor comprises a disc having a plurality of annular flanges extending outwardly from its periphery, a plurality of blades secured to the disc and extending radially outwardly from the periphery thereof, each of the blades having its root notched to define heels which are received in the grooves formed between the annular flanges of the disc, and a plurality of separate platforms which are secured to the disc and are disposed between the blades to define the inner boundary of the fluid flow path through the rotor, the blades each being fixed to the disc by two parallel pins which are equidistance from the axis of the disc and are received in corresponding bores passing through the annular flanges and the heels of the blade, the pins also serving to secure the platforms to the disc.Type: GrantFiled: November 21, 1990Date of Patent: September 8, 1992Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviations S.N.E.M.C.A.Inventor: Pierre A. Glowacki
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Patent number: 5131814Abstract: 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.Type: GrantFiled: April 3, 1990Date of Patent: July 21, 1992Assignee: General Electric CompanyInventors: James C. Przytulski, Richard L. Horvath, Philip H. Stoughton, Christopher C. Glynn, Richard A. Wesling, Robert J. Corsmeier
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Patent number: 5131813Abstract: 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.Type: GrantFiled: April 3, 1990Date of Patent: July 21, 1992Assignee: General Electric CompanyInventors: James C. Przytulski, Richard L. Horvath, Philip H. Stoughton
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Patent number: 5129787Abstract: A lightweight propulsor blade (10) is constructed 10 of a hollow internal spar (30) and an exterior airfoil shell (20) which defines and encompasses a hollow interior cavity (26). The internal spar (30) is disposed within the cavity 26 and extends spanwisely from its tip portion to terminate in a spar root portion (40). The spar has at least forward and aft spanwisely extending, chordwisely spaced, hollow box-like cavities (52A, 52B), a leading edge shear web (53) projecting chordwisely forward from the forward cavity (52A), a trailing edge shear web (55) projecting chordwisely rearward from the aft cavity (52B), and an intermediate chordwise shear web (57) spanning the space between and interconnecting the forward and aft cavities (52A, 52B). An additional intermediate box-like cavity (52C) may be incorporated in the intermediate chordwise shear web (57) in spaced relationship between the forward and aft cavities (52A, 52B).Type: GrantFiled: February 13, 1991Date of Patent: July 14, 1992Assignee: United Technologies CorporationInventors: John A. Violette, Eugene J. Delgrosso
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Patent number: 5104290Abstract: A bladed rotor (19) suitable for a gas turbine engine (10) comprises a plurality of aerofoil blades (21) mounted on the periphery of a disc (20). Each of the aerofoil blades (21) has a root part (25) which locates in the disc (20) and is constituted by two radially extending circumferentially spaced apart root portions (26,27). The circumferentially outward flanks of the root portions (26,27) are configured to define a fir-tree type blade fixing which locates in a correspondingly shaped recess (34) in the disc (20). The root part (25) configuration provides weight reduction in the rim region of the disc (20), thereby reducing stresses within the disc (20).Type: GrantFiled: October 1, 1990Date of Patent: April 14, 1992Assignee: Rolls-Royce plcInventor: Ronald Catlow
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Patent number: 5100296Abstract: An integral control stage blade group for use in a steam turbine having a rotor, the rotor including radially extending flanges provided with opened and smooth faces defining at least one pair of spaced annular grooves. The blade group comprises a plurality of blades attached to a unitary platform. Secondly, the blade group comprises a plurality of root portions depending from the platform in a direction opposite from the blades. The root portions extend along the platform in a circumferential direction when said blade group is mounted on the rotor. Each of the root portions fits within a respective one of the annular grooves in the rotor. Finally, the blade group comprises at least three spaced apertures formed in said root portion and arranged to align with corresponding apertures in the rotor flanges when the blade group is mounted on the rotor.Type: GrantFiled: April 9, 1990Date of Patent: March 31, 1992Assignee: Westinghouse Electric Corp.Inventors: Albert J. Partington, Martin E. Schlatter
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Patent number: 5073084Abstract: 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.Type: GrantFiled: September 17, 1990Date of Patent: December 17, 1991Assignee: Rolls-Royce plcInventor: Roy T. Hirst
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Patent number: 5062769Abstract: Steam turbine blades and buckles are attached to a rotor with pins which fit through dove-tailed connections. In one extremity of the blade and a mating position on the rotor. The pins are composed of a first material which is in a state of compression due to shot peening, a second metallic material being on the surface of the pins. The second metallic material is not as hard as the first material and provides a relative lubricating surface to facilitate removal from a mating aperture in the dove-tail formations.Type: GrantFiled: November 22, 1989Date of Patent: November 5, 1991Inventor: Ralph J. Ortolano
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Patent number: 5018941Abstract: Each blade of a turbomachine rotor is secured to the drum of the rotor by upstream and downstream legs on the radially inner side of the blade platform cooperating with upstream and downstream annular beads on the periphery of the durm, and a locking plate holding the legs in position. The end of the upstream leg is received in an annular groove in the upstream bead, and the downstream leg has an aperture which receives a tongue projecting from a collar on the downstream bead. the downstream leg ends in a cylindrical bearing surface acting on a cylindrical bearing surface of the drum, and includes two hooks on its donwstream face. The locking plate is located in an annular groove of the drum at the downstream edge of the cylindrical bearing surface and has first tongues engaging with the hooks on the downstream leg and second locating tongues at each end.Type: GrantFiled: January 4, 1990Date of Patent: May 28, 1991Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation"S.N.E.C.M.A.Inventors: Bertrand J. J. M. Heurtel, Pierre-Louis Mondoloni, Jacques R. Serre
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Patent number: 5007800Abstract: The rotor of a turbomachine has a rotor blade stage formed by sectors which are each secured to a rotor drum by radially inwardly directed, axially spaced flanges on the blade platform of the sector cooperating with radially outwardly directed, axially spaced flanges on the drum. The cooperating downstream flanges of the drum and the blade platform have at least one pair of registering holes through which a cylindrical pin extends, the pin having a radial collar interposed between the two flanges and an annular groove positioned downstream from the collar. The assembly is held in position by scalloped segments which are inserted into an annular groove in the drum on the downstream side of the downstream flange, and which are shifted circumferentially to engage edges thereof in the grooves of the pins before being locked by tongues at opposite ends of the segments.Type: GrantFiled: October 4, 1989Date of Patent: April 16, 1991Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."Inventors: Michel G. P. Hacault, Bertrand J. J. M. Heurtel, Jacques R. Serre
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Patent number: 4781532Abstract: In the case of saddle-type rotor blades of axial-flow turbomachines, the locking blade (6a), without its root part engaging in the fir trees (2) on the radially outer part of the rotor disk (1), is located under a large prestress between its neighboring blades (6b, 6c). It is fastened in the root part by means of axial pins (7). The blade root (4') of the locking blade (6a) is dimensioned more narrowly in the region of its fir trees (2') in its axial extension than that (4) of the neighboring blades (6b, 6c). By this means, a removal recess (10) is produced on both the inlet and outlet sides, in each of which a compression jack (11) can be introduced for pressing apart the neighboring blades (6b, 6c). The locking blade, relieved of loads in this manner, can be removed without being destroyed.Type: GrantFiled: June 3, 1986Date of Patent: November 1, 1988Assignee: BBC Brown, Boveri & Company, Ltd.Inventors: Peter Novacek, Paul Slepcevic, Toni von Arx
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Patent number: 4767274Abstract: Structure for retaining rotor blades of a disk and blade assembly of a rotary machine is disclosed. A plurality of blade lugs extend from beneath the platform of each rotor blade into engagement with a corresponding plurality of disk slots. In a preferred form the disk slots are formed to a helical geometry across the periphery of the disk.Type: GrantFiled: December 29, 1986Date of Patent: August 30, 1988Assignee: United Technologies CorporationInventor: Jerry D. Walter
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Patent number: 4730984Abstract: An axial flow rotor disc apparatus of the radial blade entry type wherein bifurcated roots of the blades engage opposite sides of a circumferential rib member of the disc has shims or root liners between at least some of the blades for adjusting the blade spacing to match the circumference of the disc. The root liners are split into pairs for separate insertion from opposite sides of the rib member at convenient locations around the periphery of the disc, without requiring insertion at an entry slot for the blades. In one version of the apparatus, the liners are retained against the rib member by deforming corners of the roots circumferentially over the liners. In another version, the liners have dogs that engage cavities in the adjacent root. The liners can also be joined along an interlocking split line for holding each pair together.Type: GrantFiled: September 8, 1986Date of Patent: March 15, 1988Inventor: Ralph J. Ortolano
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Patent number: 4492517Abstract: A gas turbine nozzle guide vane assembly is formed of individual arcuate nozzle segments. The arcuate nozzle segments are elastically joined to each other to form a complete ring, with edges abutted to prevent leakage. The resultant nozzle ring is included within the overall gas turbine stationary structure and secured by a mounting arrangement which permits relative radial movement at both the inner and outer mountings. A spline-type outer mounting provides circumferential retention. A complete rigid nozzle ring with freedom to "float" radially results. Specific structures are disclosed for the inner and outer mounting arrangements. A specific tie-rod structure is also disclosed for elastically joining the individual nozzle segments. Also disclosed is a method of assembling the nozzle ring subassembly-by-subassembly into a gas turbine employing temporary jacks.Type: GrantFiled: January 6, 1983Date of Patent: January 8, 1985Assignee: General Electric CompanyInventor: Nicholas Klompas
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Patent number: 4462756Abstract: A filler member for a rotor of a turbomachine in which the rotor is of the type comprising a body provided with a peripheral groove. Each side of the groove has a flange which has a surface facing radially inwards. A circumferential array of blades, each of which has a root shaped to engage the inward facing surfaces of the flanges and is capable of sliding along the groove. At least one of the flanges has a first recess therein to enable the blades to be loaded into, and removed from the groove. The filler member comprises, a base portion extending along the groove below the roots of one or more of said blades and has at least one tab connected to the base portion extending outwardly therefrom. The tab is movable relative to the base portion between a first position in which the tab is clear of said first recess and thereby allows the filler member to move along the groove and a second position in which the tab is located in the recess and so prevents said filler member from moving along the groove.Type: GrantFiled: December 20, 1982Date of Patent: July 31, 1984Assignee: Rolls Royce LimitedInventors: Simon D. Muggleworth, Colin G. Sparrow
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Patent number: 4460316Abstract: A plurality of rotatable turbine blades are formed integral with a shroud and platform and a plurality of arcuate plate root portions which are received by circumferential grooves in a rotor and are fastened to the rotor by three pins extending axially through the root portions and the rotor, the shroud and platform portions having a protrusion on one corner to support the trailing edge of one of the blade portions and a notch in the shroud and the platform on the corner opposite the protrusion whereby the protrusions on one group of blades register with the notch on an adjacent group of blades when the groups of blades are disposed in a circular array on the rotor.Type: GrantFiled: December 29, 1982Date of Patent: July 17, 1984Assignee: Westinghouse Electric Corp.Inventor: Albert J. Partington
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Patent number: 4321012Abstract: A moving blade fastening construction comprising moving blade fingers formed in the moving blade root portion and rotor wheel fingers formed in the rotor wheel root portion and arranged so that the fingers of the moving blade are inserted in spaces defined between the fingers of the rotor wheel, thereby to provide at least two engaging portions radially spaced from each other. An average thickness of the moving blade finger is larger than that of the rotor wheel finger which is made of material larger in Young's modulus than the moving blade fingers, whereby stresses induced in the moving blade root portion are made uniform.Type: GrantFiled: December 11, 1979Date of Patent: March 23, 1982Assignee: Hitachi, Ltd.Inventors: Toshimi Tan, Katsukuni Hisano
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Patent number: 4135849Abstract: A pinned root blade having a predictable center of rotation when tangentially oscillated and also having a predetermined, axial contact surface which is engageable with a rotatable rotor and which is disposed about the center of rotation in such manner as to provide maximum friction damping of the tangential oscillations.Type: GrantFiled: January 21, 1977Date of Patent: January 23, 1979Assignee: Westinghouse Electric Corp.Inventor: Ronald Pigott
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Patent number: 4076455Abstract: A rotor blade system which is adapted for long term reliable operation in a gas turbine engine is disclosed. Techniques for altering the natural frequency of the blade system to reduce the detrimental combined effects of external excitation and self-excitation are developed. One structure shown utilizes a shroud for the control of self-excitation in combination with a pin root to lower the fundamental first natural bending frequency of the blade system below the level of the 2E frequency at idle.Type: GrantFiled: June 28, 1976Date of Patent: February 28, 1978Assignee: United Technologies CorporationInventor: Hans Stargardter
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Patent number: RE37900Abstract: A plurality of rotatable turbine blades are formed integral with a shroud and platform and a plurality of arcuate plate root portions which are received by circumferential grooves in a rotor and are fastened to the rotor by three pins extending axially through the root portions and the rotor, the shroud and platform portions having a protrusion on one corner to support the trailing edge of one of the blade portions and a notch in the shroud and the platform on the corner opposite the protrusion whereby the protrusions on one group of blades register with the notch on an adjacent group of blades when the groups of blades are disposed in a circular array on the rotor.Type: GrantFiled: January 26, 1998Date of Patent: November 5, 2002Assignee: Siemens Westinghouse Power CorporationInventor: Albert J. Partington