US3632228A - Device for locking turbomachinery blades - Google Patents

Device for locking turbomachinery blades Download PDF

Info

Publication number
US3632228A
US3632228A US59045A US3632228DA US3632228A US 3632228 A US3632228 A US 3632228A US 59045 A US59045 A US 59045A US 3632228D A US3632228D A US 3632228DA US 3632228 A US3632228 A US 3632228A
Authority
US
United States
Prior art keywords
bolt
spacer
rotor
blade
tang
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
US59045A
Other languages
English (en)
Inventor
Ronald C Acres
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
Application granted granted Critical
Publication of US3632228A publication Critical patent/US3632228A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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

  • the present invention relates to improvements in turbomachinery rotors and, more specifically, to an improved device for locking blades in place on such rotors.
  • the object of the present invention is to provide an improved blade lock which is particularly suited for shrouded blades which must be shifted radially relative to the rotor for removal and insertion and which comprises a unitary assembly to reduce the time required for insertion and removal as well as to minimize loss or misplacement of its component parts.
  • a unitary assembly comprising a spacer, a headed bolt extending through the length of the spacer, a plate telescoped over a threaded end of the bolt and a nut threaded onto this threaded end.
  • the bolthead is aligned with the spacer and the assembly may be inserted into the spacing between blade tang and the bottom of the rotor groove which receives the tang.
  • the bolt is then rotated so that its head overlies the side of the rotor and the blade tang.
  • the nut is then tightened to clamp the plate against the other side of the rotor and the blade tang. Additional features prevent relative rotation and the bolt, spacer and plate to insure proper positioning of these parts when the blade is locked in place.
  • FIG. I is a generally longitudinal section of a portion of an axial flow compressor taken in part along the centerline of a blade-retaining groove;
  • FIG. 2 is a section, on a reduced scale, taken on line Il-II in FIG. 1 and showing a larger portion of the compressor;
  • FIG. 3 is a section, on an enlarged scale, taken on line III- III in FIG. 1;
  • FIG. 4 is a view on an enlarged scale, taken on line lV-IV in FIG. 1; view,
  • FIG. 5 is a section, on an enlarged scale, taken on line VV in FIG. 2 with one of the blades removed;
  • FIG. 6 is an exploded view, in perspective, of the bladelocking device of the present invention.
  • FIG. 7 is a perspective view of the blade lock unitary assembly with portions broken away.
  • FIGS. 1 and 2 illustrate the first stage of an axial flow compressor of the type employed in gas turbine engines. From the engine inlet, air passes through an annular passageway defined I at its outer bounds by the compressor casing 10 and at its inner bounds by platform elements 12, some of which are stationary and some of which are integral with the compressor rotor.
  • Air first passes through a circumferential row of inlet guide vanes 14 and then past a circumferential row of blades 16 which are mounted on the compressor rotor 17.
  • the compressor rotor comprises a first-stage disc 18 which is connected by a web 20 to a conical torque shaft 22 which comprises a part of the compositely formed rotor structure.
  • Downstream of the blades 16 is a row of stator vanes 25 which are mounted on the compressor casing 10.
  • the outer portions of the blades 16 are of a cambered airfoil shape and, due to their length, are provided with midspan shrouds 26 which extend from opposite sides of the airfoil into abutting relation with corresponding shroud portions on adjacent blades. Such shrouds are known means for minimizing blade vibration.
  • the inner ends of the blades 16 are provided with dovetail tangs 28 which are received by correspondingly shaped slots 30 formed in a circumferential rim 32 of the disc 18.
  • the slots 30 are formed at an angle to the axis of the rotor which is indicated by the line X in FIG. 5. This angled relationship cor responds to the angled relationship of the airfoil portion of the blade and minimizes stress loadings into the tang resulting from centrifugal force on the blade during rotation.
  • Each blade is locked in place by a locking device 34 which will be described in detail with reference to FIGS. 5-7.
  • the locking device 34 comprises four elements: a spacer 36, a bolt 38, a plate 40 and a nut 42.
  • the spacer 36 preferably comprises upper and lower strips 44, 46 which are connected and spaced apart by integral, vertical ribs 48. Wings 50 project from the upper strip 44 and apertured at 52 at reduce weight.
  • the bolt 38 passes through aligned holes 54in the ribs 48.
  • the blade 40 passes over the threaded end portion 39 of the bolt 38 and the nut 42 is then turned onto the threaded end of the bolt 38 to provide a unitary assembly as illustrated in FIG. 7.
  • the bolt 38 has a flathead 43 at its opposite end.
  • the locking device 34 has a horizontal slot 56, defined by the strips 44, 46, in one end of the spacer 36 which receives a lug 58 formed beneath the bolthead 43.
  • the bolt 38 when assembled as shown in FIG. 7, has a length greater than that of the spacer so that its headed end may be projected beyond as indicated in that figure.
  • the plate 40 has a lug 60 for preventing relative rotation between the spacer and the plate 40 when they are in their assembled relation.
  • the bolthead 43 has a height which is equal to or less than the height of this spacing while the height of the spacer 36 closely approximates this spacing. This is further illustrated by the broken line position of bolthead 43 in FIG. 4.
  • the locking device may be simply inserted beneath the blade tang from the downstream side of the rotor disc 18.
  • the bolt 38 After being inserted in place essentially as illustrated in FIG. 5, the bolt 38 is rotated to bring the bolthead 43 to the position illustrated by the broken lines in FIG. 7 and the solid lines in FIG. 4.
  • the width of the bolthead 43 is greater than the height of the spacing between the tang and the bottom of the slot and less than the width of the slot so that it may be inserted as described and then rotated to overlie one side of the rotor disc and one end of the tang.
  • the bolt 38 is rotated in the proper direction so that the angled inner face of the head 43 is aligned with the side face of the disc and the end face of the tang 28, thus taking into account the angled relation of the slot.
  • the bolt 38 is then drawn in a downstream direction so that the lug 58 will be received by the slot 56.
  • the nut 42 is fully tightened on the bolt 38 securely clamping the locking device 34 in place as illustrated in FIGS. 3, 4 and 5.
  • the wings 50 position the locking device 34 centrally in the slot 30 and that the length of the spacer is slightly greater than the length of the slot 30 to avoid excessive stresses in the bolthead 43.
  • the plate 40 is angled to align with the side of the rotor disc. The outer surface of the plate 40 is formed on a plane normal to the bolt to provide a firm seat for the nut 42. Also, the plate 40 has an outline greater than that between the tang and the bottom of the groove to block flow of pressurized air from the downstream side of the rotor to the upstream side.
  • Removal of the locking device to facilitate removal or replacement of a blade 16 is the reverse of the procedure described above. Again, it is capable of being carried out where there is access only to the downstream surface of the rotor disc 18.
  • a blade-locking device for locking radially projecting blades on a rotor where each blade has a dovetail tang at its inner end and the rotor has dovetail slots extending across its peripheral from one side to the other thereof, each blade being received in a slot with a spacing between the tang and the bottom of the groove,
  • said blade-locking device comprising a spacer having a height approximating the spacing between the blade tang and the bottom of the rotor slot
  • a bolt having a length greater than that of the spacer and a head at one end and a threaded portion at the other end, said bolthead having a height no more than the height of said spacer and a width greater than the height of said spacer and less than the maximum width of the rotor slot,
  • said spacer having a passageway along its length through which the bolt extends and within which the bolt is rotatable
  • a nut threaded onto said threaded portion to form a unitary assembly which may be slipped into the spacing between the tang and the bottom of the groove, the bolt rotated to register its head with both the tang and one side of the rotor and the nut tightened to clamp the latter against tang and the other side of the rotor.
  • a blade-locking device as in claim 1 further including means, acting between said spacer and bolt, for locking the bolt against rotation relative to the spacer when the bolthead is in a selected position to engage the blade tang and the one side of the rotor and when the bolthead is drawn into close proximity to the spacer.
  • the plate has an outline greater than that of the space between the blade tangs and rotor slots
  • spacer comprises upper and lower, relatively thin strips having a length approximating that of the rotor slots and spaced apart by integral, vertical, transverse ribs, said spacer further having wings projecting laterally from one of said strips, which are engageable with the sides of said slot to position the spacer centrally thereof,
  • said ribs have aligned holes therethrough forming the passageway for said bolt
  • a short lug is formed on the bolt underneath said head, said lug being receivable between the ends of the spacer strips when the bolthead is rotated to a selected position to engage the blade tang and the one side of the rotor and when the bolthead is drawn into close proximity to the spacer,
  • the plate has an outline greater than that of the space between the blade tangs and the bottom of the rotor slot, and has a lug engageable with the spacer for positioning said plate in overlying relation to said spacing when said bolt is fully threaded on the threaded portion of said bolt.
  • the portion of the outer surface of the plate surrounding the bolt is normal to the bolt for efiective clamping action when the nut is threaded thereagainst.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US59045A 1970-07-29 1970-07-29 Device for locking turbomachinery blades Expired - Lifetime US3632228A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US5904570A 1970-07-29 1970-07-29

Publications (1)

Publication Number Publication Date
US3632228A true US3632228A (en) 1972-01-04

Family

ID=22020465

Family Applications (1)

Application Number Title Priority Date Filing Date
US59045A Expired - Lifetime US3632228A (en) 1970-07-29 1970-07-29 Device for locking turbomachinery blades

Country Status (5)

Country Link
US (1) US3632228A (fr)
BE (1) BE765708A (fr)
CA (1) CA937872A (fr)
DE (1) DE2120472A1 (fr)
FR (1) FR2097764A5 (fr)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US3936234A (en) * 1975-02-10 1976-02-03 General Electric Company Device for locking turbomachinery blades
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
RU2143561C1 (ru) * 1998-03-13 1999-12-27 Открытое акционерное общество "А.Люлька-Сатурн" Устройство для фиксирования рабочей лопатки компрессора в пазу ротора
US6231287B1 (en) * 2000-02-28 2001-05-15 General Electric Co. Rotor windage nut
US6457942B1 (en) * 2000-11-27 2002-10-01 General Electric Company Fan blade retainer
RU2330965C2 (ru) * 2002-10-23 2008-08-10 Дженерал Электрик Компани Запирающая рабочая лопатка для рабочего колеса первой ступени турбины и рабочее колесо первой ступени турбины
US20110176925A1 (en) * 2010-01-19 2011-07-21 Anderson Carney R Torsional flexing energy absorbing blade lock
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
CN104285041A (zh) * 2012-06-15 2015-01-14 三菱日立电力系统株式会社 叶根弹簧插入夹具以及叶根弹簧插入方法
US9112383B2 (en) 2011-10-31 2015-08-18 General Electric Company System and method for Var injection at a distributed power generation source
EP3611385A3 (fr) * 2018-08-14 2020-04-22 Rolls-Royce North American Technologies, Inc. Dispositif de retenue d'aube pour turboréacteur
CN112943685A (zh) * 2021-03-10 2021-06-11 哈电发电设备国家工程研究中心有限公司 一种拉杆式叶根连接结构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2753149A (en) * 1951-03-30 1956-07-03 United Aircraft Corp Blade lock
US2801074A (en) * 1952-10-01 1957-07-30 United Aircraft Corp Blade retaining means
US2937849A (en) * 1955-10-06 1960-05-24 Gen Electric Structural dampener for turbo-blading

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2753149A (en) * 1951-03-30 1956-07-03 United Aircraft Corp Blade lock
US2801074A (en) * 1952-10-01 1957-07-30 United Aircraft Corp Blade retaining means
US2937849A (en) * 1955-10-06 1960-05-24 Gen Electric Structural dampener for turbo-blading

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US3936234A (en) * 1975-02-10 1976-02-03 General Electric Company Device for locking turbomachinery blades
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
RU2143561C1 (ru) * 1998-03-13 1999-12-27 Открытое акционерное общество "А.Люлька-Сатурн" Устройство для фиксирования рабочей лопатки компрессора в пазу ротора
US6231287B1 (en) * 2000-02-28 2001-05-15 General Electric Co. Rotor windage nut
JP2001254717A (ja) * 2000-02-28 2001-09-21 General Electric Co <Ge> ロータウインデイジナット
US6457942B1 (en) * 2000-11-27 2002-10-01 General Electric Company Fan blade retainer
RU2330965C2 (ru) * 2002-10-23 2008-08-10 Дженерал Электрик Компани Запирающая рабочая лопатка для рабочего колеса первой ступени турбины и рабочее колесо первой ступени турбины
US20110176925A1 (en) * 2010-01-19 2011-07-21 Anderson Carney R Torsional flexing energy absorbing blade lock
US8459954B2 (en) 2010-01-19 2013-06-11 United Technologies Corporation Torsional flexing energy absorbing blade lock
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
US9112383B2 (en) 2011-10-31 2015-08-18 General Electric Company System and method for Var injection at a distributed power generation source
CN104285041A (zh) * 2012-06-15 2015-01-14 三菱日立电力系统株式会社 叶根弹簧插入夹具以及叶根弹簧插入方法
EP3611385A3 (fr) * 2018-08-14 2020-04-22 Rolls-Royce North American Technologies, Inc. Dispositif de retenue d'aube pour turboréacteur
US11339674B2 (en) 2018-08-14 2022-05-24 Rolls-Royce North American Technologies Inc. Blade retainer for gas turbine engine
CN112943685A (zh) * 2021-03-10 2021-06-11 哈电发电设备国家工程研究中心有限公司 一种拉杆式叶根连接结构

Also Published As

Publication number Publication date
CA937872A (en) 1973-12-04
DE2120472A1 (de) 1972-02-03
FR2097764A5 (fr) 1972-03-03
BE765708A (fr) 1971-08-30

Similar Documents

Publication Publication Date Title
US3395891A (en) Lock for turbomachinery blades
US3632228A (en) Device for locking turbomachinery blades
US3572970A (en) Turbomachinery blade spacer
EP0369926B1 (fr) Ensemble d&#39;aubes d&#39;un compresseur axial
US4527952A (en) Device for locking a turbine rotor blade
US3986779A (en) Locking device for releasably fastening parts to rotors of fluid flow machines
US3904317A (en) Bucket locking mechanism
US8122785B2 (en) Rotor balancing system for turbomachinery
US1719415A (en) Turbine-blade attachment
US3165294A (en) Rotor assembly
US3727660A (en) Bolt retainer and compressor employing same
US4465432A (en) System for mounting and attaching turbine and compressor prismatic rooted blades and mounting process
US5720596A (en) Apparatus and method for locking blades into a rotor
US5242270A (en) Platform motion restraints for freestanding turbine blades
JPS58187503A (ja) タ−ビンエンジンのロ−タ円板における羽根の付根の軸方向固定装置
GB2038959A (en) Turbomachinery blade retaining assembly
GB2171150A (en) Turbomachine rotor blade fixings
US4189282A (en) Device to secure vanes to a rotor
GB805319A (en) Improvements relating to turbine wheels
US3955898A (en) Locking device for the rotor blades of a flow machine
GB905582A (en) Improvements relating to the sealing of blades in a bladed rotor
EP2299064B1 (fr) Ensemble d&#39;aubes statoriques variables et compresseur associé pour un moteur à turbine à gaz
US3689176A (en) Turbomachinery rotor consturction
US3832092A (en) Device for locking turbomachinery blades
US5913660A (en) Gas turbine engine fan blade retention