US2962259A - Turbine blade rings and methods of assembly - Google Patents

Turbine blade rings and methods of assembly Download PDF

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Publication number
US2962259A
US2962259A US636729A US63672957A US2962259A US 2962259 A US2962259 A US 2962259A US 636729 A US636729 A US 636729A US 63672957 A US63672957 A US 63672957A US 2962259 A US2962259 A US 2962259A
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United States
Prior art keywords
wire
blades
blade
ring
portions
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Expired - Lifetime
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US636729A
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English (en)
Inventor
Basil T G Bishop
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.)
Napier Turbochargers Ltd
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D Napier and Son 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • 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
    • 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
    • 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

Definitions

  • a problem that is frequently encountered in turbines is that of blade vibration and various proposals have been made either for preventing vibration or for reducing its harmful effects.
  • One such proposal has been to lace the blades together by means of a wire ring passing through holes in the aerofoil portions of all the blades.
  • the centrifugal force acting on the unsupported sections of the Wire between the blades presses the wire outwardly and may have the effect of bowing these unsupported sections outwardly between the blades.
  • the wire therefore exerts frictional restraint against lateral flutter or transverse vibration of the blades, and is assisted in this by the said bowing out effect.
  • the wire is disposed in the gas stream, which not only subjects the wire to high temperatures but may also "ice each wire, and it is desirable for the wire to be reasonably flexible so that the aforementioned bowing out effect will occur and to ensure that the wire will touch every blade through which it passes. It has been found that for a wire of given mass per unit length adequate flexibility can be achieved by making the (or each) wire in two separate interfere to some extent with the flow pattern of the gas stream passing through the blade channels.
  • a turbine blade ring In a turbine blade ring according to the present invention individual blades each comprising an aerofoil portion, a platform portion and a root portion are laced together by wire lacing passing through the platform portions.
  • An advantage of the invention is that the wire lacing is no longer located in the gas stream so that the aforementioned disadvantages are avoided. Nevertheless, the lacing still has the effect of reducing blade vibration by restricting transverse movements of the platform portions and hence of the blades as a whole.
  • the wire lacing comprises at least one wire ring constituted by a single wire, or by a plurality of separate wire segments arranged end to end in the form of a ring, threaded through holes in the platform portions of the blade in the blade ring and with enlarged or deformed portions in the wire or wire segments of such size that they will not pass through the said holes.
  • Assembly of the blade ring is facilitated by providing a plurality of wire segments instead of a single wire, while the enlarged or deformed portions prevent the wire or wires from being pulled out of the holes by centrifugal force.
  • the lacing comprises several short lengths of wire each of which passes through holes in two adjacent platform portions, each blade being laced by at least one such Wire to the adjacent blade on one side and by at least one other such wire to the adjacent blade on the other side.
  • each end of each of the said short lengths of wire lies adjacent to an imperforate portion of a blade platform, which limits endwise movements of the short lengths of wire. Assembly of the blade ring is facilitated if the short lengths of wire are disposed obliquely with their axes inclined to the circumferential direction.
  • the vibration damping effect of the wire depends both upon its mass per unit length and its flexibility. Strength considerations, having regard to the high centrifugal forces involved, place an upper limit upon the mass of longitudinal sections which fit together toconstitute a wire of the desired external contour.
  • Figure 1 is -a fragmentary front view of a turbine blade ring embodying the invention
  • Figure 2 is a cross section of the lacing wire used in Figure 1, on an enlarged scale;
  • Figure 3 shows one method of anchoring the lacing wire
  • Figure 4 shows another way of anchoring the lacing wire
  • Figure 5 is a front view of a lacing wire ring made up of separate segments
  • Figure 6 is a sectional developed plan view showing the application of the invention to thin metal blades.
  • Figure 7 is a sectional developed plan view showing another method of lacing using a plurality of short lacing wires.
  • the turbine blade ring shown in Figure 1 comprises a ring of turbine blades 10 mounted around a turbine rotor disc 11.
  • Each blade comprises an aerofoil portion 12, a platform portion 13 and a root portion 14.
  • the platform portions 13 constitute a transition zone between the aerofoil portions 12 and the root portions 14, providing a smooth inner boundary to the blade channels which are defined between the aerofoil portions 12 of adjacent blades and at the same time providing a shield to prevent the hot gases which pass through these blade channels from coming directly into contact with the highly stressed rotor disc 11.
  • the platform portion consists of a transverse front wall 30, a transverse rear wall 31, and at least one web 19 extending from said front wall to said rear wall.
  • the platform portion is of approximately the shape of a letter I in cross-section, which provides adequate rigidity against torsional vibration.
  • holes are drilled in the webs 19 of the platform portions 13 and a wire ring 15 is threaded through these holes. As shown in Figure 2, this ring is made in two parts 15A and 15B in order to increase its flexibility without increasing its mass per unit length.
  • the wire is a single wire ring, its two ends 16 and 17 terminating in a space 18 between the webs 19A and 19B of the platform portions of two adjacent blades 10A and 10B.
  • the blades are threaded on to the wire 15, the blades 10A and 10B being held far enough apart to permit heads to be formed on to the two ends 16 and 17 of the wire as illustrated.
  • the blades are then placed in a jig in the positions which they will occupy in the blade ring, and the turbine disc 11 is applied to them endwise so that all the root portions 14 enter their appropriate grooves in the rotor simultaneously.
  • the wire may be deformed at other places, for instance by squeezing it to form depressions 21 as shown in Figure 4, the wire bulging out laterally in the vicinity of these depressions. These depressions would be made at or near the centre of the wire, the blades being thereafter threaded on from each end.
  • this wire could be sub-divided into several different segments 15C, 15D and so on, as shown in Figure 5, each of these segments being anchored in one or other of the previously mentioned ways.
  • Such precautions may comprise inserting ferrulses 22 into the holes in the webs 33 and parts 23 of the platform portions as shown in Figure 6.
  • Each ferrule has a central portion 24 of reduced diameter which fits snugly on the wire 25.
  • the ferrules are Welded or brazed in place in the platform portions.
  • the ends of the wire 25 are provided with heads 16A and 17A, corresponding to the heads 16 and 17, respectively, shown in Figure 3.
  • the wire may be a ring made of a single length of wire or it may be segmental as shown in Figure 5.
  • each blade has two oblique holes drilled in it, the front hole in one web (e.g. 26C) being in alignment with the rear hole in the adjacent web 26B, and so on.
  • the blades are laced together with short lengths of wire.
  • the blade 27C is laced to the blade 2713 by a short length of wire 28C which passes through the forward hole in the Web 26C and through the rear hole in the web 26B.
  • the blade 27C is also laced close together in a jig into their final positions and moving the rotor disc endwise on to the root portions in the manner hereinbefore indicated. This method of assembly is facilitated by the oblique disposition of the Wires 28C, 28D etc.
  • the invention is applicable to axial flow compressors as well as to turbines, and accordingly the word turbine" is used herein in a broad sense as embracing both turbines proper and axial flow compressors.
  • a turbine blade ring comprising a rotor, a ring of individual blades mounted on said rotor each of said blades comprising an aerofoil portion, a root portion engaging said rotor, a platform portion intermediate between said aerofoil portion and ,said root portion, said platform portion having a transverse front wall, a transverse rear wall, at least one web extending from said front wall to said rear wall, and a reinforcing ferrule passing transversely through said web between said front and rear walls, and wire lacing passing through said ferrules in said webs of said blades and having unsupported portions between adjacent webs to damp transverse vibrations of said blades, said wire lacing comprising at least one wire ring constituted by a single length of wire threaded through said ferrules in said platform portions, said length of wire having enlarged portions of such size that they will not pass through said ferrules.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US636729A 1956-02-03 1957-01-28 Turbine blade rings and methods of assembly Expired - Lifetime US2962259A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB337214X 1956-02-03

Publications (1)

Publication Number Publication Date
US2962259A true US2962259A (en) 1960-11-29

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US636729A Expired - Lifetime US2962259A (en) 1956-02-03 1957-01-28 Turbine blade rings and methods of assembly

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US (1) US2962259A (en))
BE (1) BE554667A (en))
CH (2) CH337214A (en))
DE (1) DE1039535B (en))
FR (1) FR1165795A (en))
GB (1) GB818846A (en))
NL (2) NL101581C (en))

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3180616A (en) * 1961-04-20 1965-04-27 Carrier Corp Vibration damped turbo machinery
US6082970A (en) * 1997-05-26 2000-07-04 Ishikawajima-Harima Heavy Industries Co., Ltd. Vibration attenuation arrangement for rotor blades
US6494679B1 (en) * 1999-08-05 2002-12-17 General Electric Company Apparatus and method for rotor damping
US20130156584A1 (en) * 2011-12-16 2013-06-20 Carney R. Anderson Compressor rotor with internal stiffening ring of distinct material
RU2583205C1 (ru) * 2015-04-14 2016-05-10 Открытое акционерное общество "Авиадвигатель" Устройство демпфирования колебаний рабочих колес блискового типа газотурбинного двигателя
RU2610357C1 (ru) * 2015-11-10 2017-02-09 федеральное государственное бюджетное образовательное учреждение высшего образования "Пермский национальный исследовательский политехнический университет" Устройство демпфирования колебаний рабочих колес блискового типа газотурбинного двигателя
CN110566282A (zh) * 2019-10-24 2019-12-13 哈尔滨汽轮机厂有限责任公司 一种适用于低负荷工况运行的835mm末级动叶片

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
CH666326A5 (en) * 1984-09-19 1988-07-15 Bbc Brown Boveri & Cie Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates
CH666722A5 (de) * 1985-07-05 1988-08-15 Bbc Brown Boveri & Cie Laufschaufelkranz einer axial durchstroemten turbomaschine.

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US791735A (en) * 1905-03-18 1905-06-06 Westinghouse Machine Co Elastic-fluid turbine.
US1017467A (en) * 1910-08-01 1912-02-13 Gen Electric Binder for turbine-buckets.
DE393333C (de) * 1924-04-01 Karl Imfeld Dipl Ing Schaufelung fuer Turbinen
US1542402A (en) * 1924-12-17 1925-06-16 Westinghouse Electric & Mfg Co Elastic-fluid turbine
GB244518A (en) * 1924-09-16 1925-12-16 Karl Baumann Improvements relating to elastic fluid turbines
DE430429C (de) * 1925-04-05 1926-06-18 Allg Elek Citaets Ges Fa Drahtversteifung von Dampfturbinenschaufeln
FR685110A (fr) * 1928-12-13 1930-07-04 Brown Procédé et outillage pour l'exécution de la liaison entre les ailettes de turbines à vapeur ou à gaz au moyen d'un fil métallique et de pièces intermédiaires
US2141401A (en) * 1936-07-01 1938-12-27 Martinka Michael Gas turbine
FR910154A (fr) * 1943-10-05 1946-05-29 Brown Amortisseur de vibrations pour les ailettes de turbomachines
GB587588A (en) * 1943-10-05 1947-04-30 Bbc Brown Boveri & Cie Damping device for turbo machine blades
US2660400A (en) * 1948-11-25 1953-11-24 Rolls Royce Blade for turbines or compressors
US2771267A (en) * 1952-05-27 1956-11-20 United Aircraft Corp Lacing for compressor blades

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE862158C (de) * 1943-10-05 1953-01-08 Brown Ag Schwingungsdaempfer fuer die Schaufeln von Turbomaschinen
DE818806C (de) * 1949-02-17 1951-10-29 Escher Wyss Ag Beschaufelung an Rotoren von axial durchstroemten, stark verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern
GB742477A (en) * 1952-10-31 1955-12-30 Rolls Royce Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE393333C (de) * 1924-04-01 Karl Imfeld Dipl Ing Schaufelung fuer Turbinen
US791735A (en) * 1905-03-18 1905-06-06 Westinghouse Machine Co Elastic-fluid turbine.
US1017467A (en) * 1910-08-01 1912-02-13 Gen Electric Binder for turbine-buckets.
GB244518A (en) * 1924-09-16 1925-12-16 Karl Baumann Improvements relating to elastic fluid turbines
US1542402A (en) * 1924-12-17 1925-06-16 Westinghouse Electric & Mfg Co Elastic-fluid turbine
DE430429C (de) * 1925-04-05 1926-06-18 Allg Elek Citaets Ges Fa Drahtversteifung von Dampfturbinenschaufeln
FR685110A (fr) * 1928-12-13 1930-07-04 Brown Procédé et outillage pour l'exécution de la liaison entre les ailettes de turbines à vapeur ou à gaz au moyen d'un fil métallique et de pièces intermédiaires
US2141401A (en) * 1936-07-01 1938-12-27 Martinka Michael Gas turbine
FR910154A (fr) * 1943-10-05 1946-05-29 Brown Amortisseur de vibrations pour les ailettes de turbomachines
GB587588A (en) * 1943-10-05 1947-04-30 Bbc Brown Boveri & Cie Damping device for turbo machine blades
US2660400A (en) * 1948-11-25 1953-11-24 Rolls Royce Blade for turbines or compressors
US2771267A (en) * 1952-05-27 1956-11-20 United Aircraft Corp Lacing for compressor blades

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3180616A (en) * 1961-04-20 1965-04-27 Carrier Corp Vibration damped turbo machinery
US6082970A (en) * 1997-05-26 2000-07-04 Ishikawajima-Harima Heavy Industries Co., Ltd. Vibration attenuation arrangement for rotor blades
US6494679B1 (en) * 1999-08-05 2002-12-17 General Electric Company Apparatus and method for rotor damping
US20130156584A1 (en) * 2011-12-16 2013-06-20 Carney R. Anderson Compressor rotor with internal stiffening ring of distinct material
RU2583205C1 (ru) * 2015-04-14 2016-05-10 Открытое акционерное общество "Авиадвигатель" Устройство демпфирования колебаний рабочих колес блискового типа газотурбинного двигателя
RU2610357C1 (ru) * 2015-11-10 2017-02-09 федеральное государственное бюджетное образовательное учреждение высшего образования "Пермский национальный исследовательский политехнический университет" Устройство демпфирования колебаний рабочих колес блискового типа газотурбинного двигателя
CN110566282A (zh) * 2019-10-24 2019-12-13 哈尔滨汽轮机厂有限责任公司 一种适用于低负荷工况运行的835mm末级动叶片

Also Published As

Publication number Publication date
FR1165795A (fr) 1958-10-29
NL214188A (en))
GB818846A (en) 1959-08-26
CH337214A (fr) 1959-03-31
CH337215A (fr) 1959-03-31
BE554667A (en))
DE1039535B (de) 1958-09-25
NL101581C (en))

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