US3904317A - Bucket locking mechanism - Google Patents

Bucket locking mechanism Download PDF

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Publication number
US3904317A
US3904317A US527586A US52758674A US3904317A US 3904317 A US3904317 A US 3904317A US 527586 A US527586 A US 527586A US 52758674 A US52758674 A US 52758674A US 3904317 A US3904317 A US 3904317A
Authority
US
United States
Prior art keywords
slot
disc
block
blade
platform
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
Application number
US527586A
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English (en)
Inventor
Robert A Cardin
Kenneth P Zeman
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US527586A priority Critical patent/US3904317A/en
Priority to DE2516061A priority patent/DE2516061C2/de
Priority to NO751348A priority patent/NO147427C/no
Priority to NL7504670A priority patent/NL7504670A/xx
Priority to JP50047599A priority patent/JPS5848729B2/ja
Priority to GB16783/75A priority patent/GB1499379A/en
Priority to IT22872/75A priority patent/IT1037743B/it
Application granted granted Critical
Publication of US3904317A publication Critical patent/US3904317A/en
Priority to CA240,210A priority patent/CA1037870A/en
Priority to FR7536281A priority patent/FR2292856A1/fr
Anticipated expiration legal-status Critical
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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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

  • U S Cl, 416/220 blade in its associated disc slot includes a locking key, [51] Int. Cl, v v F011) 5/32 a keyway formed in the blade platform and a circum- (581 Field of S ar h 416/193 220 ferential slot formed in the periphery of the disc.
  • the locking key is recessed in the platform keyway to per [56] i References Cit d mit insertion of the blade and is then dropped into the diSC S10 and rotated 90 to lock the blade to the disc,
  • This invention relates to turbomachines and, more particularly, to improved means for axially retaining a blade or bucket in a turbomachinery rotor or disc.
  • Blade locks which have been heretofore proposed for use in axially locking a blade within a generally axially extending rotor or disc slot have usually included a member which extends axially across the disc adjacent the blade or bucket root.
  • a great number of these locking devices have included one or more tabs that are bent after assembly to axially lock the rotor in its slot. Such arrangements are, however, undesirable in that the axial forces required to retain the blade in its slot are usually reacted by a member which has been bent during assembly.
  • the bent tab usually has some residual strain which may result in spring-back of the bent tab and axial looseness of the blade.
  • Another solution has employed the use of both a spacer and a locking clip so that the tab that is bent at assembly retains only the spacer. While this solution overcomes the problem of reacting axial blade forces through a tab that is bent at assembly and the problem of tab spring-back. it does require two parts, access to at least one side of the turbomachinery disc, and the bending at assembly of one tab to retain the spacer.
  • a primary object of this invention is to provide a blade retainer or lock that does not require the bending of any tabs at assembly; that permits the blade to be locked to the disc without access to either side of the disc; and that enables removal and replacement of a single blade.
  • the present invention provides a locking key which includes a rectangular block portion with a generally cylindrical stem extending therefrom.
  • a keyway is formed in the platform portion of the turbomachinery blade to receive the locking key from the underside of the platform, with the block portion recessed into a slot and the stem projecting through an opening formed in the platform.
  • a keyway slot is formed in outer circumferential surface of the disc in a position under the platform keyway.
  • the block portion of the key has a length dimension greater than its width dimension.
  • the axial length of the platform slot is sized to correspond to the smaller width dimension of the locking key block, whereas the axial length of the disc keyway slot is sized to correspond to the longer length dimension of the locking key block. In this manner. the locking key may be dropped radially into the disc keyway slot and rotated 90to axially lock the blade to the disc.
  • Suitable means such as a screw driver slot may be provided at the distal end of the locking key stem to facilitate rotating the locking key into and out of its locked position.
  • the stem may be conveniently staked or otherwise suitable secured to the platform to prevent the locking key from rotating out of its locked position during operation of the bladed turbomachinery disc.
  • FIG. 1 is a partial perspective view showing an exemplary bladed turbomachinery disc employing the blade locking means of this invention
  • FIG. 2 is an enlarged perspective view showing the locking key of this invention
  • FIG. 3 is an enlarged partial cross-sectional view taken along lines 33 of FIG. 1;
  • FIG. 4 is a view like that of FIG. 3 showing the locking key of FIG. 2 in its position enabling insertion of the blades into its associated disc slot;
  • FIG. 5 is an enlarged fragmentary plan view taken along lines 5-5 of FIG. 3 and showing the locking key of FIG. 2 in its locked position;
  • FIG. 6 is a view like FIG. 5 taken on lines 66 of FIG. 4 and showing the locking key of FIG. 2 in its unlocked position;
  • FIG. 7 is a partial perspective view like that of FIG. I. but with the blade removed from its disc slot;
  • FIG. 8 is an enlarged fragmentary cross-sectional view taken along lines 8-8 of FIG. 4 and showing the locking key of FIG. 2 in its unlocked position;
  • FIG. 9 is a view taken on lines 99 of FIG. 3 showing the locking key of FIG. 2 in its locked position.
  • a bladed turbomachinery rotor or disc has been shown generally at 10 as comprising a rotatable annular disc 12 supporting at its periphery a plurality of radially extending blades or buckets I4.
  • the blades 14 include an airfoil portion 16, a platform portion I8 and a root portion 20.
  • the disc I2 is formed with a slot 22 for each blade I4 which extends generally axially across the disc 12 at its periphery and is shaped, in cooperation with the blade root 22, to axially receive the blade root and to radially lock the blade I4 to the disc against centrifugal forces.
  • the blade platforms extend over the outer circumferential surface 23 of the disc I2 so as to form the inner boundary of fluid flow across the blade airfoils 16.
  • the means of this invention for axially locking the blade root 20 in the disc slot 22 include a locking key 24 and associated keyways 26 and 28 formed, respectively, in the blade platform and the outer peripherial surface 23 of the disc I2.
  • the locking key 24 has been shown as including a block portion 30 and a stem portion 32.
  • the block portion 30 is generally rectangular in shape and has a radial thickness 1, a width w, and a length l.
  • the stem portion 32 is preferably cylindrical and extends normally from the central portion of the radially outwardly facing surface of the block 30.
  • outer radial end 34 of the stem 32 is formed with a screw driver slot or other suitable means 35 to enable rotation of the key 24 into its locked position as will be hereinafter described.
  • the platform keyway 26 includes a slot 36 formed in the radially inner side of the platform 18 and an opening 38 communicating with the slot 36 and extending radially through the blade platform 18.
  • the axial width W of the platform slot 36 is sized to receive the width dimension w of the locking key block 30 and has a radial height sized to receive the thickness dimension t of the key block 30 in noninterfering relationship with the disc periphery 23, with the stem por tion 32 extending through the keyway opening 38 as shown in FIG. 4.
  • the disc keyway 28 takes the form of a circumferential slot which has an axial length L and radial height T, as shown in FIG. 3, which are sized, respectively, to correspond to the length dimension 1 and the thickness dimension of the block 30.
  • the slot 28 is located axially so that when the blade 14 and root portion are inserted in the disc slot 22, the slot 28 will be aligned with the keyway 26 formed in the blade platform 18.
  • the locking key 24 is inserted into the platform keyway 26 shown in FIGS. 4 and 6, with the block portion received within platform slot 36 and the stem portion 32 projecting through platform opening 38.
  • the blade I4 is then axially inserted into its re spective rotor slot 22.
  • the locking key 24 is dropped radially inward so that the block portion 30 engages the disc keyway 28.
  • the locking key 24 is then rotated 90, using slot means 35. from the unlocked position of FIGS. 6 and 8 to the locked position of FIGS. 5 and 9, wherein the length dimension I of the block 30 is oriented in an axial direction.
  • Opposed corners of the block 30 are appropriately contoured. as at in FIGS. 2, 6 and 8, so as to permit the key 24 to be rotated or cammed 90into locking en gagement with the slot 28.
  • the locking key is radially retained in its locked position of FIGS. 3, 5 and by abutment of the radially outer face of block 30 with the radially inner side of the blade platform I8. At the same time. axial movement of the blade is prevented by abutment of the locking key stem 32 with the walls of platform opening 38 and by abutment of the block 30 with the disc slot 28.
  • the stem 32 is preferably sized, for aerodynamic reasons, so that when the locking key 24 is engaged in its locked position in the disc slot 28, the distal or outer radial end 34 will be generally flush with the outer surface of the platform.
  • the distal end of the stem 32 may be staked to the platform 18 as shown in FIG. 5 or otherwise suitably secured.
  • suitable slots 42 may be provided in the platform, adjacent the keyway opening 38 to facilitate such staking operation.
  • the slot 35 of the stem 32 will be at right angle to the slots 42 to assure a positive locking of the turbine blade 14 and the disc I2.
  • the above procedure is reversed.
  • the locking key is rotated to its un locked position of FIG. 8, moved radially outwardly, out of engagement with disc slot 28 and into platform slot 36 of the keyway 26, and the turbine blade 14 is slid axially out of engagement with the disc dovetail slot 22.
  • the stem portion may be sheared from the block portion 30 by applying a sharp blow to an axial face of the root portion 20.
  • the present invention provides means for axially locking a blade or bucket to a turbomachinery disc which does not require the bending of any retaining tabs at assembly and which permits a single blade to be removed and replaced without disturbing adjacent blades.
  • a turbomachine of the type including a rotatable disc formed with at least one slot extending generally axially of said disc at its periphery, a blade extending generally radially from said disc and having a root portion engaged in said axial slot and a platform portion, extending over a portion of the periphery of said disc, said axial slot and said root portion sized and formed to abut and radially lock the blade to the disc against centrifugal forces.
  • means for axially retaining said blade root in said axial slot comprising:
  • a locking key having a block portion and an elongated stern portion extending therefrom and terminating at a distal end;
  • said block portion having a thickness defined by radially inwardly and outwardly facing surfaces, a width, and a length of greater extent than said width, said stern extending normally from a central position ofsaid radially outwardly facing block surface;
  • said platform portion formed with a circumferentially extending slot in its radially inner side, said platform slot having an axial width sized to receive the width dimension of said block in close fitting relationship thereto and having a radial height sized to receive said block in noninterfering relation with said disc, a radial opening formed through said platform portion and communicating with said platform groove for receiving said stem portion, in close fitting relationship therewith, when said block is engaged in said platform groove and for providing access to the distal end of said stem;
  • a circumferential slot formed in the periphery of said disc adjacent said axial slot, said disc circumferential slot having an axial length sized to receive the length dimension of said block in close fitting relationship therewith, said disc circumferential slot located and having a radial depth such that when said blade is inserted into said axial disc slot, said locking block may be dropped radially out of engagement with said platform slot and into engagement with said disc peripherial slot and then roin that said block is generally rectangular and includes diametrically opposed arcuate surfaces to permit rotation into its locking position.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Fire-Extinguishing Compositions (AREA)
US527586A 1974-11-27 1974-11-27 Bucket locking mechanism Expired - Lifetime US3904317A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
US527586A US3904317A (en) 1974-11-27 1974-11-27 Bucket locking mechanism
DE2516061A DE2516061C2 (de) 1974-11-27 1975-04-12 Turbinenrad
NO751348A NO147427C (no) 1974-11-27 1975-04-16 Laaseinnretning for turbinskovler.
NL7504670A NL7504670A (nl) 1974-11-27 1975-04-18 Turbomachine voorzien van middelen voor het vergrendelen van de schoepen.
JP50047599A JPS5848729B2 (ja) 1974-11-27 1975-04-21 動翼固定機構
GB16783/75A GB1499379A (en) 1974-11-27 1975-04-23 Turbomachines
IT22872/75A IT1037743B (it) 1974-11-27 1975-04-30 Meccanismo di bloccaggio di palette di turbina
CA240,210A CA1037870A (en) 1974-11-27 1975-11-20 Bucket locking mechanism
FR7536281A FR2292856A1 (fr) 1974-11-27 1975-11-27 Dispositif de calage d'une aube de turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US527586A US3904317A (en) 1974-11-27 1974-11-27 Bucket locking mechanism

Publications (1)

Publication Number Publication Date
US3904317A true US3904317A (en) 1975-09-09

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ID=24102083

Family Applications (1)

Application Number Title Priority Date Filing Date
US527586A Expired - Lifetime US3904317A (en) 1974-11-27 1974-11-27 Bucket locking mechanism

Country Status (9)

Country Link
US (1) US3904317A (no)
JP (1) JPS5848729B2 (no)
CA (1) CA1037870A (no)
DE (1) DE2516061C2 (no)
FR (1) FR2292856A1 (no)
GB (1) GB1499379A (no)
IT (1) IT1037743B (no)
NL (1) NL7504670A (no)
NO (1) NO147427C (no)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
DE2824282A1 (de) * 1977-06-09 1978-12-21 United Technologies Corp Stroemungsleitanordnung fuer eine axialstroemungsmaschine und insbesondere mit einer solchen anordnung versehene laufradschaufel
EP0055415A1 (en) * 1980-12-29 1982-07-07 Carrier Corporation A rotor assembly and methods of securing a rotor blade therewithin and removing a rotor blade therefrom
US4451959A (en) * 1980-12-29 1984-06-05 Elliott Turbomachinery Company, Inc. Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom
US4676723A (en) * 1986-03-26 1987-06-30 Westinghouse Electric Corp. Locking system for a turbine side entry blade
US4820126A (en) * 1988-02-22 1989-04-11 Westinghouse Electric Corp. Turbomachine rotor assembly having reduced stress concentrations
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
US5522702A (en) * 1994-06-28 1996-06-04 Rolls-Royce Plc Gas turbine engine fan blade assembly
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
US20040115059A1 (en) * 2002-12-12 2004-06-17 Kehl Richard Eugene Cored steam turbine bucket
GB2397854A (en) * 2003-01-30 2004-08-04 Rolls Royce Plc Securing blades in a rotor assembly
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
EP1657404A1 (de) * 2004-11-13 2006-05-17 MTU Aero Engines GmbH Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
US20090290983A1 (en) * 2008-05-26 2009-11-26 Kabushiki Kaisha Toshiba Turbine blade assembly and steam turbine
US20120114490A1 (en) * 2010-11-10 2012-05-10 General Electric Company Turbine assembly and method for securing a closure bucket
US20130052024A1 (en) * 2011-08-24 2013-02-28 General Electric Company Turbine Nozzle Vane Retention System
CN106015086A (zh) * 2016-06-02 2016-10-12 东方电气集团东方汽轮机有限公司 一种压气机叶片在叶轮轮槽中的轴向锁定结构
US20180087386A1 (en) * 2016-09-26 2018-03-29 Safran Aircraft Engines Fan blisk for aircraft turbomachine
CN113623270A (zh) * 2021-08-24 2021-11-09 中国联合重型燃气轮机技术有限公司 锁紧装置及含有该锁紧装置的压气机、燃气轮机
US11927114B2 (en) * 2021-12-17 2024-03-12 Mitsubishi Heavy Industries Compressor Corporation Rotor of steam turbine, steam turbine, and method for fixing rotor blade

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5482505A (en) * 1977-12-14 1979-06-30 Hitachi Ltd Steam turbine
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
GB2299834B (en) * 1995-04-12 1999-09-08 Rolls Royce Plc Gas turbine engine rotary disc
JP5149831B2 (ja) * 2009-02-12 2013-02-20 三菱重工コンプレッサ株式会社 タービン動翼の固定構造及びタービン
US9051845B2 (en) * 2012-01-05 2015-06-09 General Electric Company System for axial retention of rotating segments of a turbine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2867408A (en) * 1953-04-10 1959-01-06 Parsons C A & Co Ltd Axial locking of rotor blades for turbines and the like
US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention
US3198485A (en) * 1963-09-26 1965-08-03 Gen Motors Corp Turbine blade lock

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2867408A (en) * 1953-04-10 1959-01-06 Parsons C A & Co Ltd Axial locking of rotor blades for turbines and the like
US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention
US3198485A (en) * 1963-09-26 1965-08-03 Gen Motors Corp Turbine blade lock

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
DE2824282A1 (de) * 1977-06-09 1978-12-21 United Technologies Corp Stroemungsleitanordnung fuer eine axialstroemungsmaschine und insbesondere mit einer solchen anordnung versehene laufradschaufel
FR2393930A1 (fr) * 1977-06-09 1979-01-05 United Technologies Corp Plates-formes d'aubages a trainance reduite
EP0055415A1 (en) * 1980-12-29 1982-07-07 Carrier Corporation A rotor assembly and methods of securing a rotor blade therewithin and removing a rotor blade therefrom
US4400137A (en) * 1980-12-29 1983-08-23 Elliott Turbomachinery Co., Inc. Rotor assembly and methods for securing a rotor blade therewithin and removing a rotor blade therefrom
US4451959A (en) * 1980-12-29 1984-06-05 Elliott Turbomachinery Company, Inc. Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom
US4676723A (en) * 1986-03-26 1987-06-30 Westinghouse Electric Corp. Locking system for a turbine side entry blade
US4820126A (en) * 1988-02-22 1989-04-11 Westinghouse Electric Corp. Turbomachine rotor assembly having reduced stress concentrations
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
ES2095790A1 (es) * 1992-01-31 1997-02-16 Westinghouse Electric Corp Limitador de los movimientos de la plataforma de los alabes de turbinaautosoportados.
US5522702A (en) * 1994-06-28 1996-06-04 Rolls-Royce Plc Gas turbine engine fan blade assembly
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
US20040115059A1 (en) * 2002-12-12 2004-06-17 Kehl Richard Eugene Cored steam turbine bucket
GB2397854A (en) * 2003-01-30 2004-08-04 Rolls Royce Plc Securing blades in a rotor assembly
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
US20060239822A1 (en) * 2004-11-13 2006-10-26 Joachim Wulf Apparatus and method for anchoring a rotor blade in a rotor of a turbo machine
US7306435B2 (en) 2004-11-13 2007-12-11 Mtu Aero Engines Gmbh Apparatus and method for anchoring a rotor blade in a rotor of a turbo machine
EP1657404A1 (de) * 2004-11-13 2006-05-17 MTU Aero Engines GmbH Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
US20090290983A1 (en) * 2008-05-26 2009-11-26 Kabushiki Kaisha Toshiba Turbine blade assembly and steam turbine
US8277186B2 (en) * 2008-05-26 2012-10-02 Kabushiki Kaisha Toshiba Turbine blade assembly and steam turbine
US8714929B2 (en) * 2010-11-10 2014-05-06 General Electric Company Turbine assembly and method for securing a closure bucket
US20120114490A1 (en) * 2010-11-10 2012-05-10 General Electric Company Turbine assembly and method for securing a closure bucket
US20130052024A1 (en) * 2011-08-24 2013-02-28 General Electric Company Turbine Nozzle Vane Retention System
CN106015086A (zh) * 2016-06-02 2016-10-12 东方电气集团东方汽轮机有限公司 一种压气机叶片在叶轮轮槽中的轴向锁定结构
US20180087386A1 (en) * 2016-09-26 2018-03-29 Safran Aircraft Engines Fan blisk for aircraft turbomachine
US10858943B2 (en) * 2016-09-26 2020-12-08 Safran Aircraft Engines Fan for aircraft turbomachine
CN113623270A (zh) * 2021-08-24 2021-11-09 中国联合重型燃气轮机技术有限公司 锁紧装置及含有该锁紧装置的压气机、燃气轮机
CN113623270B (zh) * 2021-08-24 2024-04-16 中国联合重型燃气轮机技术有限公司 锁紧装置及含有该锁紧装置的压气机、燃气轮机
US11927114B2 (en) * 2021-12-17 2024-03-12 Mitsubishi Heavy Industries Compressor Corporation Rotor of steam turbine, steam turbine, and method for fixing rotor blade

Also Published As

Publication number Publication date
FR2292856B1 (no) 1980-01-25
GB1499379A (en) 1978-02-01
IT1037743B (it) 1979-11-20
CA1037870A (en) 1978-09-05
NL7504670A (nl) 1976-05-31
JPS5162204A (no) 1976-05-29
NO147427B (no) 1982-12-27
DE2516061C2 (de) 1983-07-28
JPS5848729B2 (ja) 1983-10-31
DE2516061A1 (de) 1976-08-12
NO147427C (no) 1983-04-06
FR2292856A1 (fr) 1976-06-25
NO751348L (no) 1976-05-31

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