US3383095A - Lock for turbomachinery blades - Google Patents

Lock for turbomachinery blades Download PDF

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Publication number
US3383095A
US3383095A US667169A US66716967A US3383095A US 3383095 A US3383095 A US 3383095A US 667169 A US667169 A US 667169A US 66716967 A US66716967 A US 66716967A US 3383095 A US3383095 A US 3383095A
Authority
US
United States
Prior art keywords
retainer
rotor
tang
keeper
rim
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
US667169A
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English (en)
Inventor
Bernard J Anderson
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 US667169A priority Critical patent/US3383095A/en
Priority to GB12983/68A priority patent/GB1195171A/en
Priority to FR1562385D priority patent/FR1562385A/fr
Priority to DE19681751071 priority patent/DE1751071A1/de
Priority to BE712967D priority patent/BE712967A/xx
Priority to SE04289/68A priority patent/SE325748B/xx
Application granted granted Critical
Publication of US3383095A publication Critical patent/US3383095A/en
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
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor

Definitions

  • the disclosure illustrates a fragmentary portion of a compressor rotor rim having tanged blades which are locked thereon by retainers lying between the bottoms of the tangs and slots in the rim.
  • Each retainer comprises a bridge with legs at its opposite ends which embrace opposite ends of a tang and opposite sides of the rim.
  • a keeper disposed between the tang and bridge maintains the retainer in its locking position. Absent the keeper, the retainer may be positioned in a slot in the bottom of the tang with its lower legs clear of the rim for assembly or removal of the blade.
  • the present invention relates to improvements in turbomachinery rotors and, more specifically, to an improved mechanism for locking blades in place on such rotors.
  • the object of the invention is therefore to provide an improved lock for a blade mounted on a rotor and in doing so to eliminate any substantial axial loading on any portion of the lock which is bent on assembly, and, particularly, to do so in a manner suitable for blades which are mounted in slots angled relative to the rotor axis, as well as for wide base tangs.
  • a turbomachinery rotor is employed with the usual circumferential rim having slots thereacross. Blades are mounted in these slots by means of tangs at their inner ends. A clearance is provided between the slot and the lower surface of the tangs.
  • a blade lock comprising a retainer and a keeper are employed to maintain each blade in its mounted position.
  • the retainer has a bridge disposed in the clearance between the slot and the tang and further has outwardly and inwardly extending legs at its opposite ends respectively, embracing the opposite ends of the tang and the faces of the rim when in its locking position.
  • the keeper is also inserted into this clearance and maintains the retainer in its locking position.
  • At least one of the retainer legs is sulficiently short relative to the clearance that, absent the keeper, the retainer may be radially shifted in the clearance so that the one leg will be moved out of locking engagement thereby providing for assembly and removal of the blades from the rotor.
  • FIGURE 1 is a perspective view of a fragmentary portion of a rotor with the blade and blade lock shown in exploded relation;
  • FIGURE 2 is a view partially in section looking inwardly at a portion of the circumference of the rotor
  • FIGURES 3 and 4 are sections taken on lines IIIIII in FIGURE 2, illustrating assembly of the present lock
  • FIGURE 5 is a view taken on lines V--V in FIGURE 2;and
  • FIGURE 6 is a section taken on lines VIVI in FIG- URE 2.
  • Turbomachinery rotors can be fabricated in many different ways, and the fragmentary peripheral portion of the compressor rotor seen in FIGURE 1 is representative.
  • This rotor comprises a drum portion 14 around which is formed an integral rim 16.
  • Flanges 17 provide platforms which in combination with the blade define the inner bounds of the flow path through the compressor.
  • An inwardly extending disc 18 provides strength and rigidity for the radial loads resulting from the centrifugal force on blades mounted in slots 20 formed in the rim 16.
  • the blades represented by the blade 22 have tangs 24 formed at their inner ends to be received by the slots 20.
  • the locking device of the present invention comprises simply a retainer 26 and a keeper 28. More specifically, the retainer comprises a bridge 30, having inwardly extending legs 32, at its opposite ends and outwardly extending legs 34, also respectively at its opposite ends. The legs 34 have notches 36 aligned with a shallow groove 37 in the top of the bridge 30.
  • the keeper 28 is simply a flat, metal strip, having a tab 31.
  • the slots 20 in the rotor rim 16 are angled relative to the axis of the rotor. as indicated by the representation of this axis illustrated by broken line x in FIGURE 2.
  • the radial faces on opposite sides of the rim 16 are, however, formed in planes normal to the rotor axis.
  • the tank 24 is formed with its end faces disposed in planes matching those of the radial faces of the rim and at an angle to the divergently tapered tang surfaces.
  • the divergently tapered tang surfaces provide a broad base tang which has become an accepted design practice in many modern rotor constructions.
  • the angled relationship of the slot minimize stress concentrations between the tang and the working surfaces of the outer end of the blade, which are similarly angled as seen in FIGURE 2.
  • the retainer 26 would be positioned below the tang 24 and introduced into a groove 38 formed along the lower surface of the tang 24.
  • the height of the groove 38 is sufficient so that when the bridge 30 in introduced therein, with the legs 34 embracing opposite end surfaces of the tang, the legs 32 are above the lower surface of the slot 20'.
  • This enables the tang with the keeper assembled thereon to be introduced into the slot 20, as illustrated in FIGURE 3.
  • the keeper may then be shifted radially inwardly so that the legs 32 embrace the radial faces of the rim 16, while the legs 34 remain in engagement or embracing relation with the end faces of the tang 24 FIGURES 4 and 5.
  • the unbent portion of the keeper 28 may then be slid through one notch 36 through the groove 37, beneath the tang 24, and finally through the notch 36 at the opposite end of the retainer.
  • the protruding end of the keeper is then bent upwardly, as illustrated in FIGURES 4 and 5 to form a tab 40 and thus positively lock the retainer in place.
  • the retainer thus locks the blade relative to the rim 16 and any axial loadings tending to shift the blade in the slot 20 are taken by the legs 32, 34 and not by the bent tabs of the keeper 28.
  • pre-bent tab 31 and the tab 42 bent upon final assembly, extend upwardly between the slotted portions of the legs 34 to minimize the profile of the locking device in an axial direction, and thus minimize windage effects as the rotor rotates.
  • the described locking device provides an effective seal preventing interstage air leakage through the tang and slot connection for mounting the blade.
  • the legs 32 extend from central portions of the bridge 30. This provides machining access to the lower marginal edge surfaces of the bridge so that they may be machined and better correspond to the profile of the slot. Further, this provides, in combination with groove 37 sufficient strength for both the bridge and the body portion of the keeper 28.
  • a turbomachinery rotor comprising a circumferential rim with slots thereacross and blades having tangs received by said slots wherein there is a clearance from one end to the other of the tang between the slot and at least a portion of the lower surface of the tang,
  • a blade lock for each blade comprising,
  • a retainer having a bridge, disposed in said clearance, with outwardly and inwardly extending legs at its opposite ends respectively embracing the opposite ends of the tang and the OppOSile radial faces of the rim when in its locking position, and
  • At least one leg of said retainer being sufficiently short relative to said clearance that, absent the keeper, the retainer may be radially shifted in said clearance so that the one leg will be moved out of locking relation thereby providing for assembly and removal of the blades from the rotor.
  • the keeper comprises a metal strip inserted through said notches between the bridge and the lower surface of the tangs and has its ends bent outwardly to secure the keeper in position.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US667169A 1967-09-12 1967-09-12 Lock for turbomachinery blades Expired - Lifetime US3383095A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US667169A US3383095A (en) 1967-09-12 1967-09-12 Lock for turbomachinery blades
GB12983/68A GB1195171A (en) 1967-09-12 1968-03-18 Improvements in Lock for Turbomachinery Blades.
FR1562385D FR1562385A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1967-09-12 1968-03-28
DE19681751071 DE1751071A1 (de) 1967-09-12 1968-03-28 Turbinentriebwerkrotor
BE712967D BE712967A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1967-09-12 1968-03-29
SE04289/68A SE325748B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1967-09-12 1968-04-01

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US667169A US3383095A (en) 1967-09-12 1967-09-12 Lock for turbomachinery blades

Publications (1)

Publication Number Publication Date
US3383095A true US3383095A (en) 1968-05-14

Family

ID=24677099

Family Applications (1)

Application Number Title Priority Date Filing Date
US667169A Expired - Lifetime US3383095A (en) 1967-09-12 1967-09-12 Lock for turbomachinery blades

Country Status (6)

Country Link
US (1) US3383095A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
BE (1) BE712967A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (1) DE1751071A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
FR (1) FR1562385A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
GB (1) GB1195171A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
SE (1) SE325748B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2092118A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) * 1970-04-30 1972-01-21 Gen Electric
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
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
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
FR2519072A1 (fr) * 1981-12-29 1983-07-01 Snecma Dispositif de retenue axiale et radiale d'aube de rotor de turboreacteur
US4685863A (en) * 1979-06-27 1987-08-11 United Technologies Corporation Turbine rotor assembly
WO2000031378A1 (en) * 1998-11-23 2000-06-02 Pratt & Whitney Canada Corp. Turbine blade to disk retention device
US6837686B2 (en) 2002-09-27 2005-01-04 Pratt & Whitney Canada Corp. Blade retention scheme using a retention tab
EP1382800A3 (en) * 2002-07-20 2006-08-23 Rolls Royce Plc A fan blade assembly
US20090220343A1 (en) * 2008-02-29 2009-09-03 General Electric Company Hub pitch gear repair method
US20100290914A1 (en) * 2009-05-15 2010-11-18 Souers Philip F Blade Closing Key System for a Turbine Engine
US20110255982A1 (en) * 2010-04-20 2011-10-20 Shihming Jan Turbine blade retention device
US20120257981A1 (en) * 2011-04-11 2012-10-11 Rolls-Royce Plc Retention device for a composite blade of a gas turbine engine
US20130189021A1 (en) * 2012-01-20 2013-07-25 Fluor Technologies Corporation Rotor pole support ribs in gearless drives
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
CN104564801A (zh) * 2014-11-18 2015-04-29 东方电气集团东方汽轮机有限公司 压气机叶片在叶轮轮槽中的轴向定位结构
US9112383B2 (en) 2011-10-31 2015-08-18 General Electric Company System and method for Var injection at a distributed power generation source
CN105525950A (zh) * 2011-06-09 2016-04-27 通用电气公司 涡轮机叶片锁定系统
EP3611385A3 (en) * 2018-08-14 2020-04-22 Rolls-Royce North American Technologies, Inc. Blade retainer for gas turbine engine
WO2021008815A1 (de) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Schaufelkranz für eine axiale turbomaschine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2146767C1 (ru) * 1998-02-23 2000-03-20 Открытое акционерное общество "Авиадвигатель" Рабочее колесо турбомашины
DE102011084153B4 (de) * 2011-10-07 2014-05-15 MTU Aero Engines AG Sicherungsvorrichtung zur Sicherung eines Schaufelelements in einer Nut einer Laufscheibe

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2786648A (en) * 1950-04-04 1957-03-26 United Aircraft Corp Blade locking device
US3057598A (en) * 1960-07-01 1962-10-09 Ass Elect Ind Locking means for turbine or compressor blading
US3076634A (en) * 1959-06-12 1963-02-05 Ass Elect Ind Locking means for compressor and turbine blades
US3216699A (en) * 1963-10-24 1965-11-09 Gen Electric Airfoil member assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2786648A (en) * 1950-04-04 1957-03-26 United Aircraft Corp Blade locking device
US3076634A (en) * 1959-06-12 1963-02-05 Ass Elect Ind Locking means for compressor and turbine blades
US3057598A (en) * 1960-07-01 1962-10-09 Ass Elect Ind Locking means for turbine or compressor blading
US3216699A (en) * 1963-10-24 1965-11-09 Gen Electric Airfoil member assembly

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3661475A (en) * 1970-04-30 1972-05-09 Gen Electric Turbomachinery rotors
FR2092118A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) * 1970-04-30 1972-01-21 Gen Electric
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
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
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4685863A (en) * 1979-06-27 1987-08-11 United Technologies Corporation Turbine rotor assembly
US4474535A (en) * 1981-12-29 1984-10-02 S.N.E.C.M.A. Axial and radial holding system for the rotor vane of a turbojet engine
EP0083289A1 (fr) * 1981-12-29 1983-07-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Roue de rotor de turbomachine munie d'un dispositif de retenue axiale et radiale d'aubes sur le disque
FR2519072A1 (fr) * 1981-12-29 1983-07-01 Snecma Dispositif de retenue axiale et radiale d'aube de rotor de turboreacteur
WO2000031378A1 (en) * 1998-11-23 2000-06-02 Pratt & Whitney Canada Corp. Turbine blade to disk retention device
US6109877A (en) * 1998-11-23 2000-08-29 Pratt & Whitney Canada Corp. Turbine blade-to-disk retention device
CZ298544B6 (cs) * 1998-11-23 2007-10-31 Pratt & Whitney Canada Corp. Upevnovací zarízení turbínové lopatky a zpusob sestavení
EP1382800A3 (en) * 2002-07-20 2006-08-23 Rolls Royce Plc A fan blade assembly
US6837686B2 (en) 2002-09-27 2005-01-04 Pratt & Whitney Canada Corp. Blade retention scheme using a retention tab
US8287238B2 (en) * 2008-02-29 2012-10-16 General Electric Company Hub pitch gear repair method
US20090220343A1 (en) * 2008-02-29 2009-09-03 General Electric Company Hub pitch gear repair method
US20100290914A1 (en) * 2009-05-15 2010-11-18 Souers Philip F Blade Closing Key System for a Turbine Engine
US8215915B2 (en) 2009-05-15 2012-07-10 Siemens Energy, Inc. Blade closing key system for a turbine engine
US20110255982A1 (en) * 2010-04-20 2011-10-20 Shihming Jan Turbine blade retention device
CN102235184A (zh) * 2010-04-20 2011-11-09 哈米尔顿森德斯特兰德公司 涡轮机叶片保持装置
US8562301B2 (en) * 2010-04-20 2013-10-22 Hamilton Sundstrand Corporation Turbine blade retention device
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
US9039379B2 (en) * 2011-04-11 2015-05-26 Rolls-Royce Plc Retention device for a composite blade of a gas turbine engine
US20120257981A1 (en) * 2011-04-11 2012-10-11 Rolls-Royce Plc Retention device for a composite blade of a gas turbine engine
CN105525950B (zh) * 2011-06-09 2017-08-29 通用电气公司 涡轮机叶片锁定系统
CN105525950A (zh) * 2011-06-09 2016-04-27 通用电气公司 涡轮机叶片锁定系统
US9112383B2 (en) 2011-10-31 2015-08-18 General Electric Company System and method for Var injection at a distributed power generation source
US9246372B2 (en) * 2012-01-20 2016-01-26 Fluor Technologies Corporation Rotor pole support ribs in gearless drives
US20130189021A1 (en) * 2012-01-20 2013-07-25 Fluor Technologies Corporation Rotor pole support ribs in gearless drives
US10298080B2 (en) 2012-01-20 2019-05-21 Fluor Technologies Corporation Rotor pole support ribs in gearless drives
CN104564801A (zh) * 2014-11-18 2015-04-29 东方电气集团东方汽轮机有限公司 压气机叶片在叶轮轮槽中的轴向定位结构
EP3611385A3 (en) * 2018-08-14 2020-04-22 Rolls-Royce North American Technologies, Inc. Blade retainer for gas turbine engine
US11339674B2 (en) 2018-08-14 2022-05-24 Rolls-Royce North American Technologies Inc. Blade retainer for gas turbine engine
WO2021008815A1 (de) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Schaufelkranz für eine axiale turbomaschine

Also Published As

Publication number Publication date
FR1562385A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1969-04-04
GB1195171A (en) 1970-06-17
SE325748B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1970-07-06
DE1751071A1 (de) 1971-03-04
BE712967A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1968-07-31

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