US3328867A - Turbine blading - Google Patents

Turbine blading Download PDF

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Publication number
US3328867A
US3328867A US290430A US29043063A US3328867A US 3328867 A US3328867 A US 3328867A US 290430 A US290430 A US 290430A US 29043063 A US29043063 A US 29043063A US 3328867 A US3328867 A US 3328867A
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US
United States
Prior art keywords
blades
blade
heads
twist
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US290430A
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English (en)
Inventor
Guengant Paul
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BBC Brown Boveri AG Germany
BBC Brown Boveri France SA
Original Assignee
BBC Brown Boveri France SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by BBC Brown Boveri France SA filed Critical BBC Brown Boveri France SA
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Publication of US3328867A publication Critical patent/US3328867A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the present invention relates to a process for placing these blades in position with an initial twist, hereinafter called the ultimate twist, which process is particularly advantageous in the case in which all the blades are similar and are itted by being slid by the foot into circumerential grooves in the periphery of the rotor element of the turbine.
  • This process resides, when a row of n blades is being fitted, in imparting to the body of each of the first (n-l) blades a twist of a greater value that the said ultimate twist and lower than the elastic limit of the blade, so as temporarily to reduce the total bulk of their heads in the peripheral direction, such reduction being sufiicient to allow for insertion of the head of the last blade in the sp-ace remaining for it, at least obliquely with respect to its ultimate position, after which this last blade is placed in this ultimate position and the adjacent blades are then brought into contact with it, via suitable spacing wedges in the case of the feet and directly in the case of the heads, the twist being reduced to its ultimate value, and so forth for the other blades in the row.
  • FIGURE l shows a group of blades.
  • FIGURE 2 shows one of them seen in profile.
  • FIGURE 3 is a sectioned view of FIGURE l in the plane III, III.
  • FIGURE 4 is a plan view of FIGURE 1 in the direction of the arrow F.
  • FIGURES 5 and l0 are explanatory diagrams.
  • FIGURE 6 shows the insertion of the foot of the last blade.
  • FIGURES 7 to 9 show a device for imparting a twist in plan and section respectively, in the planes VIII, VIII and IX, IX.
  • FIGURE l shows three adjacent blades in elevation, outside their fixing groove.
  • 1 designates the foot of a blade
  • 2 are notches enabling the fixing to be carried out by sliding into the said groove
  • 3 is the body or active part of the blade
  • 4 is the head of the 3,328,867 Patented July 4, 1967 ICC blade which is integral with the part 3.
  • the profile of the blade may be seen in FIGURE 3.A
  • the face 5 of the foot of the blade at the base of the body 3, and likewise the external face 6 of the head, are projected to form elongated parallelograms which may be seen in FIGURES 3 and 4 respectively.
  • Their respective sides 5a, 6a are oblique with respect to a direction parallel to the axis of the turbine, and are at a definite angle to this direction.
  • spacing wedges 7 which include fixing notches '7a aligned with the notches 2 in the blade feet 1. These wedges are, in known manner, cut into two equal parts, as illustrated, in a plane perpendicular to the axis of the turbine.
  • the foot of each one is introduced into the groove G on the turbine rotor with the narrow sides of the parallelogram configured blade foot generally parallel to the sides of the groove, the width of the rotor groove being greater than the distance between the longer sides 5a of the foot as is evident from FIG. 6 so as to permit insertion of the blade foot in the groove.
  • the blade foot is then turned until the shorter sides 5b come to bear against the corresponding edges of the groove.
  • the feet of the first (n-1) blades are introduced without the wedges 7.
  • the corners of the foot of this last blade may, if required or desired, be slightly cut oli, as shown at 8 in FIG.
  • FIGURE 5 shows the result of the operation diagrammatically.
  • Rotating the head of a blade, having the shape of a parallelogram with the angle /8 through an angle a and circumferentially displacing the adjacent blade in order to bring the adjacent faces of their heads into contact reduces the length occupied in the peripheral direction by the edge 6b from tto sin a te (a+)
  • the value of u is so determined that the total gain over the heads of the (n-l) blades corresponds to the desired space for the head of the last blade, that is to say is greater than the major diagonal of the parallelogram.
  • This angle is also such that the twist on the body of the blade is lower than the elastic limit of the latter.
  • FIGURES 7 to 9 show a device for applying the aforementioned twisting torque to the heads of the blades. It is a stirrup in the form of a sector 9 carrying screws 10.
  • the invention provides for temporarily giving each blade a head 4a radially larger than the ultimate head 4, for making therein a groove 12 equal in length to the sides 6b and centered on the transverse plane passing through the center of gravity of the body 3 of the blade, and for inserting a wedge 11 with an easy tit in this groove.
  • the stirrup is intended to cover a few blades, five for example, and its internal outline matches the external outline of the heads 4a, with a certain amount of clearance in order to allow the latter to rotate.
  • the screws 10 exert their pressure ⁇ on the wedges 11 in parallel fashion to the axis of the turbine. They are so accommodated in the stirrup as to come to bear in groups of 3 two at the ends yand on each side of each wedge 11 (FIGURE 7).
  • Apertures 13 enable the edges 6a of the heads to be seen. The twist on the first blade having been checked by suitable measurement, these apertures enable the other heads to be subsequently aligned with the first.
  • FIGURE 10 shows these three stirrups diagrammatically at 14, and 16, and a few blades at 17.
  • the desired twist is successively applied to each blade by means of the screws 10, and then a sliding motion is i-mparted to the blades by a mallet so as to make all the heads contiguous again.
  • the screws in the stirrup 15 are slackened, and it is transferred to 18, whereupon the stirrup 16 is transferred to 19 in the same manner, and so forth.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US290430A 1962-07-11 1963-06-25 Turbine blading Expired - Lifetime US3328867A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR903628A FR1382057A (fr) 1962-07-11 1962-07-11 Perfectionnement aux ailetages de turbines à vapeur

Publications (1)

Publication Number Publication Date
US3328867A true US3328867A (en) 1967-07-04

Family

ID=8782949

Family Applications (1)

Application Number Title Priority Date Filing Date
US290430A Expired - Lifetime US3328867A (en) 1962-07-11 1963-06-25 Turbine blading

Country Status (7)

Country Link
US (1) US3328867A (no)
BE (1) BE634692A (no)
CH (1) CH404694A (no)
DE (1) DE1426778B1 (no)
FR (1) FR1382057A (no)
GB (1) GB994537A (no)
NL (1) NL295111A (no)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0081436A1 (fr) * 1981-12-09 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Rotor de compresseur ou de turbine dans lequel un disque supporte des aubes à pied marteau et procédé de montage d'un tel rotor
US4474534A (en) * 1982-05-17 1984-10-02 General Dynamics Corp. Axial flow fan
US4533298A (en) * 1982-12-02 1985-08-06 Westinghouse Electric Corp. Turbine blade with integral shroud
US4576551A (en) * 1982-06-17 1986-03-18 The Garrett Corporation Turbo machine blading
US4602412A (en) * 1982-12-02 1986-07-29 Westinghouse Electric Corp. Method for assembling in a circular array turbine blades each with an integral shroud
US4643645A (en) * 1984-07-30 1987-02-17 General Electric Company Stage for a steam turbine
US4765046A (en) * 1987-05-22 1988-08-23 Westinghouse Electric Corp. Row assembly process for integral shroud blades
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud
EP1028232A1 (de) * 1999-02-12 2000-08-16 ABB Alstom Power (Schweiz) AG Befestigung von Laufschaufeln einer Strömungsmaschine
EP1028231A1 (de) * 1999-02-12 2000-08-16 ABB Alstom Power (Schweiz) AG Befestigung von Laufschaufeln einer Strömungsmachine
US6454534B1 (en) 2000-12-21 2002-09-24 General Electric Company Flush bucket cover
EP1899581A1 (de) * 2005-06-28 2008-03-19 Man Turbo Ag Rotor für eine turbine sowie verfahren und vorrichtung zur herstellung des rotors
WO2011057622A2 (de) 2009-11-13 2011-05-19 Mtu Aero Engines Gmbh Gasturbinenschaufel für eine strömungsmaschine
RU167493U1 (ru) * 2016-03-22 2017-01-10 Закрытое акционерное общество "Уральский турбинный завод" Устройство для сборки бандажей с телом диафрагм паровых турбин
US20170350262A1 (en) * 2015-01-12 2017-12-07 Siemens Aktiengesellschaft Method of mounting rotor blades on a rotor disk, and clamping device for performing such a method
RU2669117C2 (ru) * 2013-05-21 2018-10-08 Нуово Пиньоне СРЛ Узел турбомашины и способы его сборки и разборки
JP2020023921A (ja) * 2018-08-07 2020-02-13 株式会社東芝 タービン動翼

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2337251A1 (fr) * 1975-12-29 1977-07-29 Europ Turb Vapeur Etage mobile de turbomachine
FR2612249B1 (fr) * 1987-03-12 1992-02-07 Alsthom Aubage mobile pour turbines a vapeur
DE19520274A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Vorrichtung und Verfahren zur Montage von Laufschaufeln
DE10014189A1 (de) * 2000-03-23 2001-09-27 Alstom Power Nv Befestigung der Beschaufelung einer Strömungsmaschine
US7344359B2 (en) * 2005-06-02 2008-03-18 General Electric Company Methods and systems for assembling shrouded turbine bucket and tangential entry dovetail
DE102008051935A1 (de) * 2008-10-09 2010-04-15 Mtu Aero Engines Gmbh Verfahren zum Montieren eines Schaufelkranzes für einen Rotor und Schaufelkranz hierzu

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB377593A (en) * 1931-02-17 1932-07-28 Asea Ab Method of and means for manufacturing blade rings for radial flow turbines
CA468547A (en) * 1950-10-03 Albert Lombard Adrian Manufacture of guide vanes for axial-flow turbines and compressors
US3185441A (en) * 1961-08-10 1965-05-25 Bbc Brown Boveri & Cie Shroud-blading for turbines or compressors

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH157414A (de) * 1931-09-01 1932-09-30 Oerlikon Maschf Schaufelschloss an Turbinenbeschaufelungen.
US2198784A (en) * 1937-11-27 1940-04-30 Westinghouse Electric & Mfg Co Turbine blade vibration damper
US2220914A (en) * 1938-07-30 1940-11-12 Gen Electric Elastic fluid turbine bucket wheel
NL64087C (no) * 1946-05-04 1900-01-01
GB720802A (en) * 1953-03-10 1954-12-29 Parsons C A & Co Ltd Improvements in and relating to assembly of blades for turbines and compressors
CH349624A (de) * 1957-03-05 1960-10-31 Oerlikon Maschf Axiale Strömungsmaschine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA468547A (en) * 1950-10-03 Albert Lombard Adrian Manufacture of guide vanes for axial-flow turbines and compressors
GB377593A (en) * 1931-02-17 1932-07-28 Asea Ab Method of and means for manufacturing blade rings for radial flow turbines
US3185441A (en) * 1961-08-10 1965-05-25 Bbc Brown Boveri & Cie Shroud-blading for turbines or compressors

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0081436A1 (fr) * 1981-12-09 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Rotor de compresseur ou de turbine dans lequel un disque supporte des aubes à pied marteau et procédé de montage d'un tel rotor
US4474534A (en) * 1982-05-17 1984-10-02 General Dynamics Corp. Axial flow fan
US4576551A (en) * 1982-06-17 1986-03-18 The Garrett Corporation Turbo machine blading
US4533298A (en) * 1982-12-02 1985-08-06 Westinghouse Electric Corp. Turbine blade with integral shroud
US4602412A (en) * 1982-12-02 1986-07-29 Westinghouse Electric Corp. Method for assembling in a circular array turbine blades each with an integral shroud
US4643645A (en) * 1984-07-30 1987-02-17 General Electric Company Stage for a steam turbine
US4765046A (en) * 1987-05-22 1988-08-23 Westinghouse Electric Corp. Row assembly process for integral shroud blades
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud
EP1028232A1 (de) * 1999-02-12 2000-08-16 ABB Alstom Power (Schweiz) AG Befestigung von Laufschaufeln einer Strömungsmaschine
EP1028231A1 (de) * 1999-02-12 2000-08-16 ABB Alstom Power (Schweiz) AG Befestigung von Laufschaufeln einer Strömungsmachine
US6299411B1 (en) 1999-02-12 2001-10-09 Abb Alstom Power (Schweiz) Ag Fastening of moving blades of a fluid-flow machine
US6454534B1 (en) 2000-12-21 2002-09-24 General Electric Company Flush bucket cover
EP1899581A1 (de) * 2005-06-28 2008-03-19 Man Turbo Ag Rotor für eine turbine sowie verfahren und vorrichtung zur herstellung des rotors
JP2008544157A (ja) * 2005-06-28 2008-12-04 マン ターボ アーゲー タービンのためのロータとロータを製造するための方法および装置
US20090116964A1 (en) * 2005-06-28 2009-05-07 Man Turbo Ag Turbine rotor and method for producing the rotor
WO2011057622A2 (de) 2009-11-13 2011-05-19 Mtu Aero Engines Gmbh Gasturbinenschaufel für eine strömungsmaschine
WO2011057622A3 (de) * 2009-11-13 2011-10-13 Mtu Aero Engines Gmbh Gasturbinenschaufel für eine strömungsmaschine
US8622704B2 (en) 2009-11-13 2014-01-07 Mtu Aero Engines Gmbh Gas turbine blade for a turbomachine
RU2669117C2 (ru) * 2013-05-21 2018-10-08 Нуово Пиньоне СРЛ Узел турбомашины и способы его сборки и разборки
US10267166B2 (en) 2013-05-21 2019-04-23 Nuovo Pignone Srl Turbomachine rotor assembly and method
US20170350262A1 (en) * 2015-01-12 2017-12-07 Siemens Aktiengesellschaft Method of mounting rotor blades on a rotor disk, and clamping device for performing such a method
US10047615B2 (en) * 2015-01-12 2018-08-14 Siemens Aktiengesellschaft Method of mounting rotor blades on a rotor disk, and clamping device for performing such a method
RU167493U1 (ru) * 2016-03-22 2017-01-10 Закрытое акционерное общество "Уральский турбинный завод" Устройство для сборки бандажей с телом диафрагм паровых турбин
JP2020023921A (ja) * 2018-08-07 2020-02-13 株式会社東芝 タービン動翼
JP7021027B2 (ja) 2018-08-07 2022-02-16 株式会社東芝 タービン動翼

Also Published As

Publication number Publication date
BE634692A (no) 1963-11-18
CH404694A (de) 1965-12-31
DE1426778B1 (de) 1969-11-20
GB994537A (en) 1965-06-10
FR1382057A (fr) 1964-12-18
NL295111A (no)

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