US2658718A - Manufacture and attachment of turbine and like blading - Google Patents

Manufacture and attachment of turbine and like blading Download PDF

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Publication number
US2658718A
US2658718A US634592A US63459245A US2658718A US 2658718 A US2658718 A US 2658718A US 634592 A US634592 A US 634592A US 63459245 A US63459245 A US 63459245A US 2658718 A US2658718 A US 2658718A
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United States
Prior art keywords
blade
root
wall
rotor
blades
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Expired - Lifetime
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US634592A
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English (en)
Inventor
Walker Daniel Norman
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to the manufacture of ripherally spaced axially disposed sheet metal blades for that kind of gas turbine having an Wall portions each of which is a generally radial axial flow bladed rotor assembly Whose blades are continuation of the blade wall base and has a made separately therefrom and re retained deformation in the peripheral direction produced thereon by fixing their roots at anchorages pro- 5 by pressing, stamping, or a like sheet metal workvided on the rotor, and to the manner of attaohing operation by which it is adapted to make ment of the blades in machines of that type.
  • the blade-retaining engagement with a correspondinvention relates in particular to the use of holing formation afforded in a ganerally radial and low tubular blades of sheet metal, which exaxially disposed slotted anchorage formed in said pression is used herein and in the appended claims rotor, the blade roots so formed being held in to mean metal of such thin section as to be sussecure relationship with their anchorages by ceptible of local shaping by pressing, stamping, spacing means within said slots acting to prevent or like operations, Whether formed from flat sheet displacement of the blade-retaining formations or tube or otherwise. of said wall portions in the peripheral direction Hollow sheet metal blades, whether manufacwith the corresponding formation of its anchortured from tube or fabricated from flat sheet, age.
  • the root construction and anchorage proposed of their anchorage is a difficult one, particularly enables root loads to be properly balanced and in their application to gas turbine rotors in airprovides adequate stability; further to improve craft power plants where the need for light Weight stability, the two spaced walls may be suppleand cheapness of manufacture has to be reconmented by one or more further walls to form a oiled with severe operating conditions, in which threeor a four sided box construction. Morethe blading is exposed to elevated temperatures over, the blade rootmay have at least one wall and subjected to high centrifugal stress and mayoutside and axially spaced from the flank of the be to intermittent loads which in some cases may bladed element to form a radially extending air excite damaging vibrations.
  • One object of the duct which is arranged to communicate with a invention, accordingly, is to provide a blade and passage through the blade to allow a flow of coolmounting therefor in which there is adequate dis ing air therethrough.
  • the invention in the axial or the peripheral direction, as the is concerned with providing a construction of case may be, but may be inclined thereto; the blade, and manner of attachment thereof to a expressions referred to, when used in relation to turbine rotor, which will be economical in manuthe direction of anchorages or formations, are facture and will reduce expensive or highly pretherefore to be read as including the inclined arcise operations to a large extent, to which end a gement.
  • F u e 1 is a fragmentary Sectional S e vawith comparative ease and without disturbing tion of a turbine rotor blade mounting dythe remaind r, ing a simple form of blade root and anchorage in Broadly speaking the invention resides in prowhich the root has axially extending walls coviding an axial flow turbine rotor assembly havoperating with axially extending slots; ing hollow tubular sheet metal blades mounted
  • Figure 2 is a section on line 2--2 of Figure 1;
  • Figure .3 is a perspective view illustrating a blade root of three-sided box-like construction
  • Figure 4 is a fragmentary section in the axial plane ofa rotorhavingapplied' thereto a blade as illustratedwin "Figure 3;
  • Figures 5 and 6 are perspective views illustrating methods of making a blade root of four sided
  • a V Figure 7 is a peripheral section;thro ugh the blade roots assembled as in Figure '6.
  • Adjacent 'bla'de roots are entered over successive teeth lyea'chrootwith its walls 6 in --adjacent*slits 2- and their respective ribs 1 en-- gaging the grooves ailorded by thebores 3at one side of the corresponding slits Locking means in the form of cylindrical or very slightly tapered *pins Bare then inserted ordriven into the practically circular-bores formed by the adjacent ribs lof the adjacent blade walls 6.
  • Adjacent blades are thus locked both to the wheel and in respect of each othenthednserted pins 8 effectively resistingradial-load tending to 'pull the blades off, and the'multiplicity of the anchorage pointsso'provided eiiecting a distribution'of the loadover the-root wall.
  • -Such distribution may be; and in practice preferably is further improved byincreasing the number of grooves.
  • the pins may be made hollow, both with the- -object- -of allowing ooolant air or the V equivalent topass through'them and to permit 1 such slight distortionduring their insertion as *may be desirable to:accommod-ate elasticity or "manufacturing:error-ofthe blade roots.
  • the 'remaining blades are of course entered and se- -cured in'the-same-way all around the wheel. In 1 the example illustrated; axial disturbance oftthe 1 blades is prevented by riveting overthe ends of the pins.
  • the modified construction illustrated in Figures 3 and 4 follows the same general principles as that illustrated in Figures 1 and 2, but the root has a third wall s so as to form a rectangu- -lar u shape inperipheral cross section, the wall 9 in addition to forming a tie which renders the whole structure more rigid, preventing-displacement of the blade in one axial direction. Since t m use," theaxial thrust tending to displace t e a 4 blade is unidirectional, the wall 9 will be sufilcient in itself to resist such displacement if rpositionedi atthe appropriate.
  • the third wall 9 is arranged to be spaced away from the flank of the rotor, as by the indentations H, so as to form a ductileading: from a radially inner locality into tna-interior of the blade for the passage of coolcylindr'ical grooves running axially.
  • the blades have hollow-sheet metal bodies '5 made, for example, by processing lengths "of tubeyradially inward extensions of whichiorm spaced parallel ing air..v Asin the previously described embodimentjthe number of grooves may be more than .two.
  • the wall 9 arev formed by downward extensions 'ofuthe blade body 5 'separatefromthe wall's 6 to allow the grooves 17in the latter to extend 'fr'omedge to edge, the Walls '9 "and-1'2 having at itlieiredges corresponding r'ecesses' l 3 which iregistervwith the ends of the "grooves;
  • One :or bOthL'Of liheWaHS 9, [2 may be ieftiirrthefidtted po'sitionzshovm until the blade has been applied to .ithemotor, and then turned down, being then held in place'by inserting locking-pins-8: asabeforeiaandsriveting over the heads, and if desired; by welding 'to the edges of the walls' 6.
  • Figure 6 shows an extension 1 2 of awall .6; with; theicorrugations 1- extending into-it, before bending.
  • the extension 12 is :bent toilieqagainstithe face ofthe rotor and so:form acfourth: wall tot-he bladeroot the corrugationswbecome turneddromthe "axial into the :peripheral direction and are 1 received by the -re Des lai-nzthe rotor.
  • Thefinishediformation is that of the middle blade'inthe perspectiveview of Figure 6,
  • the end wall 9 in this case also ;maybe formed to provide an air duct, as by the methods of Figures 4 or 5 V If it-be-desired 'to improve the distribution of loads in the anchoragejt'he rimofthe wheel may 1 be indentedbetween-the' anchorages, as at It in 5 1 6 ;"S aSiOfiifO'I'd appreciable resilience and therefore to enable radially spaced ribs and grooves the better to share the main loads, whilst incidentally aiTording the possibility of substantial frictional gripping between the fiat surfaces of the slots and walls.
  • the indentation may also be used to afiord an inlet for cooling air by carrying it lower than the skirt of the blade as seen in Figure 1.
  • An axial fiow gas turbine rotor assembly comprising a rotor wheel having around its periphery a plurality of axially extending slits each opening out, below the periphery, into an axially extending blade anchorage hole, a plurality of hollow tubular sheet-metal blades disposed around the periphery of said wheel, two peripherally spaced and separately anchored root portions on each said blade, one being a generally radially inward continuation of one of the axially extending sheet metal walls of the blade fitting in one of said slits and passing therethrough into a blade anchorage hole wherein it is bulged out to fit the hole, the other of said root portions being a similar continuation of the opposite wall of the blade likewise disposed in another one of the said slits and holes, in combination with a blade-retaining peg extending through each said anchorage hole and engaging said bulged blade-root portion.
  • each said blade has at least a third root portion which is a wall also continuing radially inward from the blade and joining the other two root portions, said third wall lying beside the flank of said rotor wheel and having a spacing member engaging said flank and separating said third wall from said fiank to leave open a passage into the interior of said hollow blade.
  • An axial flow gas turbine rotor assembly comprising a rotor wheel having around its periphery a plurality of axially extending slits each opening out, below the periphery, into an axially extending blade anchorage hole, a plurality of hollow tubular sheet-metal blades disposed around the periphery of said wheel, two peripherally spaced root portions on each said blade, anchored separately from each other, one being a generally radially inward continuation of one of the axially extending sheet metal Walls of the .blade abutting against a like root port-ion of one neighbouring blade, the other of said root portions being a similar continuation of the opposite wall of the blade abutting similarly against the other neighbouring blade root, each pair of said abutting blade root portions fitting in a separate one of said slits and passing therethrough into a blade anchorage hole, wherein they are bulged apart to fit said hole, in combination with a blade-retaining peg extending through each said anchorage hole and
  • An axial flow gas turbine rotor assembly comprising a rotor wheel pierced in the axial direction by a plurality of keyhole slots extending inwards from its periphery, a plurality of hollow tubular sheet-metal blades disposed around the periphery of said wheel, two peripherally spaced root portions on each said blade, anchored separately from each other, one being a generally radially inward continuation of one of the axially extending sheet metal walls of the blade abutting against a like root portion of one neighbouring blade, the other of said root portions being a similar continuation of the opposite wall of the blade abutting similarly against the other neighbouring blade root, each pair of said abutting blade-root portions fitting in a separate one of said keyhole slots, the walls being spread apart to conform to the shape of the cylindrical part of the keyhole slot and leave a central opening, in combination with a bladeretaining peg extending through each said central openings in said keyhole slots.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US634592A 1944-12-22 1945-12-12 Manufacture and attachment of turbine and like blading Expired - Lifetime US2658718A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB17626/48A GB650437A (en) 1944-12-22 1944-12-22 Improvements in and relating to the manufacture and attachment of turbine blading
GB265006X 1944-12-22

Publications (1)

Publication Number Publication Date
US2658718A true US2658718A (en) 1953-11-10

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Country Status (6)

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US (1) US2658718A (de)
BE (1) BE462182A (de)
CH (1) CH265006A (de)
FR (1) FR919171A (de)
GB (2) GB650437A (de)
NL (1) NL70887C (de)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2872156A (en) * 1956-08-20 1959-02-03 United Aircraft Corp Vane retaining device
US2974924A (en) * 1956-12-05 1961-03-14 Gen Electric Turbine bucket retaining means and sealing assembly
US4084922A (en) * 1976-12-27 1978-04-18 Electric Power Research Institute, Inc. Turbine rotor with pin mounted ceramic turbine blades
US4466776A (en) * 1982-01-14 1984-08-21 S.N.F.C.M.A. Axial locking device for turbomachine blades
US4809420A (en) * 1987-12-16 1989-03-07 Fatigue Technology, Inc. Method and apparatus for backing up mandrel exit holes in knuckle structures
US5022825A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pitch retention member
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
US5102300A (en) * 1988-10-07 1992-04-07 United Technologies Corporation Pinned airfoil propeller assembly
US5129786A (en) * 1990-11-08 1992-07-14 United Technologies Corporation Variable pitch pan blade retention arrangement
US5368444A (en) * 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
US7661931B1 (en) 2007-02-20 2010-02-16 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US7686571B1 (en) 2007-04-09 2010-03-30 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US7704044B1 (en) 2006-11-28 2010-04-27 Florida Turbine Technologies, Inc. Turbine blade with attachment shear inserts
US20110206519A1 (en) * 2010-02-24 2011-08-25 United Technologies Corporation Fastener aperture having an elongated geometry
US20150104319A1 (en) * 2013-10-16 2015-04-16 Doosan Heavy Industries & Construction Co., Ltd. Turbine with bucket fixing means
CN113814672A (zh) * 2021-10-27 2021-12-21 三门峡三星智能装备制造有限公司 一种桥壳成型工艺

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE926397C (de) * 1952-09-25 1955-04-18 Ernst Heinkel Dr Dr Hohlschaufel, vorzugsweise fuer axial durchstroemte Turbinen
DE1049872B (de) * 1953-06-04 1954-02-05
DE1109310B (de) * 1953-08-19 1961-06-22 Siemens Ag Axialverdichter mit zwischen den umlaufenden Laufschaufelkraenzen angeordneten Leitschaufelkraenzen
DE1074594B (de) * 1961-02-23 1960-02-04 D Napier &. Son Limited, London Befestigung hohler tragflugelprofilierter Axialturbmen oder Axialverdichter Schaufeln
FR2453294A1 (fr) * 1979-04-04 1980-10-31 Snecma Dispositif de fixation d'aubes sur un rotor de compresseur pour turbo-reacteur
FR2587060B1 (fr) * 1985-09-12 1989-08-18 Snecma Dispositif de fixation de flasques sur une roue de turbine
DE102011100221B4 (de) * 2011-05-02 2017-03-09 MTU Aero Engines AG Integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US754984A (en) * 1903-04-01 1904-03-22 Ernst Elis Fridolf Fagerstroem Detachable blade for steam-turbines.
US849992A (en) * 1906-06-22 1907-04-09 Johann Rudolf Frikart Turbine-blade.
GB190706640A (en) * 1907-03-19 1908-03-19 Belliss & Morcom Ltd Improvements in the Construction of Guide-blades and Vanes for Turbine Motors.
GB190815893A (en) * 1908-07-27 1909-01-28 Arthur William Cooper Improvements in Turbine Engines.
US927515A (en) * 1905-04-21 1909-07-13 Westinghouse Machine Co Fluid translation device.
US1014350A (en) * 1909-05-21 1912-01-09 Guy B Collier Turbine.
US1387304A (en) * 1920-06-16 1921-08-09 Said Parsons Turbine-blade attachment
US1534415A (en) * 1924-07-07 1925-04-21 Westinghouse Electric & Mfg Co Turbine blade
US1601402A (en) * 1921-01-15 1926-09-28 Lorenzen Christian Gas turbine
US1603966A (en) * 1924-01-29 1926-10-19 Lorenzen Turbinen Ag Turbine rotor
DE550328C (de) * 1932-05-11 Siemens Schuckertwerke Akt Ges Verfahren zur Befestigung von Hohlschaufeln im Radkranz einer Dampf- oder Gasturbine
US1967962A (en) * 1933-09-09 1934-07-24 John F Metten Steam turbine rotor
US2220420A (en) * 1938-02-08 1940-11-05 Bbc Brown Boveri & Cie Means for cooling machine parts
US2236426A (en) * 1938-07-27 1941-03-25 Bbc Brown Boveri & Cie Turbine blade
US2440069A (en) * 1944-08-26 1948-04-20 Gen Electric High-temperature elastic fluid turbine

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE550328C (de) * 1932-05-11 Siemens Schuckertwerke Akt Ges Verfahren zur Befestigung von Hohlschaufeln im Radkranz einer Dampf- oder Gasturbine
US754984A (en) * 1903-04-01 1904-03-22 Ernst Elis Fridolf Fagerstroem Detachable blade for steam-turbines.
US927515A (en) * 1905-04-21 1909-07-13 Westinghouse Machine Co Fluid translation device.
US849992A (en) * 1906-06-22 1907-04-09 Johann Rudolf Frikart Turbine-blade.
GB190706640A (en) * 1907-03-19 1908-03-19 Belliss & Morcom Ltd Improvements in the Construction of Guide-blades and Vanes for Turbine Motors.
GB190815893A (en) * 1908-07-27 1909-01-28 Arthur William Cooper Improvements in Turbine Engines.
US1014350A (en) * 1909-05-21 1912-01-09 Guy B Collier Turbine.
US1387304A (en) * 1920-06-16 1921-08-09 Said Parsons Turbine-blade attachment
US1601402A (en) * 1921-01-15 1926-09-28 Lorenzen Christian Gas turbine
US1603966A (en) * 1924-01-29 1926-10-19 Lorenzen Turbinen Ag Turbine rotor
US1534415A (en) * 1924-07-07 1925-04-21 Westinghouse Electric & Mfg Co Turbine blade
US1967962A (en) * 1933-09-09 1934-07-24 John F Metten Steam turbine rotor
US2220420A (en) * 1938-02-08 1940-11-05 Bbc Brown Boveri & Cie Means for cooling machine parts
US2236426A (en) * 1938-07-27 1941-03-25 Bbc Brown Boveri & Cie Turbine blade
US2440069A (en) * 1944-08-26 1948-04-20 Gen Electric High-temperature elastic fluid turbine

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2872156A (en) * 1956-08-20 1959-02-03 United Aircraft Corp Vane retaining device
US2974924A (en) * 1956-12-05 1961-03-14 Gen Electric Turbine bucket retaining means and sealing assembly
US4084922A (en) * 1976-12-27 1978-04-18 Electric Power Research Institute, Inc. Turbine rotor with pin mounted ceramic turbine blades
US4466776A (en) * 1982-01-14 1984-08-21 S.N.F.C.M.A. Axial locking device for turbomachine blades
US4809420A (en) * 1987-12-16 1989-03-07 Fatigue Technology, Inc. Method and apparatus for backing up mandrel exit holes in knuckle structures
US5022825A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pitch retention member
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
US5102300A (en) * 1988-10-07 1992-04-07 United Technologies Corporation Pinned airfoil propeller assembly
US5129786A (en) * 1990-11-08 1992-07-14 United Technologies Corporation Variable pitch pan blade retention arrangement
US5368444A (en) * 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
US7704044B1 (en) 2006-11-28 2010-04-27 Florida Turbine Technologies, Inc. Turbine blade with attachment shear inserts
US7661931B1 (en) 2007-02-20 2010-02-16 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US7686571B1 (en) 2007-04-09 2010-03-30 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US20110206519A1 (en) * 2010-02-24 2011-08-25 United Technologies Corporation Fastener aperture having an elongated geometry
US9863250B2 (en) * 2010-02-24 2018-01-09 United Technologies Corporation Fastener aperture having an elongated geometry
US20150104319A1 (en) * 2013-10-16 2015-04-16 Doosan Heavy Industries & Construction Co., Ltd. Turbine with bucket fixing means
US10012096B2 (en) * 2013-10-16 2018-07-03 Doosan Heavy Industries & Construction Co., Ltd. Turbine with bucket fixing means
CN113814672A (zh) * 2021-10-27 2021-12-21 三门峡三星智能装备制造有限公司 一种桥壳成型工艺
CN113814672B (zh) * 2021-10-27 2022-12-06 三门峡三星智能装备制造有限公司 一种桥壳成型工艺

Also Published As

Publication number Publication date
FR919171A (fr) 1947-02-28
CH265006A (de) 1949-11-15
NL70887C (de) 1900-01-01
GB650437A (en) 1951-02-21
BE462182A (de) 1900-01-01
GB650424A (en) 1951-02-21

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