US3395891A - Lock for turbomachinery blades - Google Patents

Lock for turbomachinery blades Download PDF

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Publication number
US3395891A
US3395891A US669454A US66945467A US3395891A US 3395891 A US3395891 A US 3395891A US 669454 A US669454 A US 669454A US 66945467 A US66945467 A US 66945467A US 3395891 A US3395891 A US 3395891A
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US
United States
Prior art keywords
blade
blades
rotor
retainer
spacer
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
US669454A
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English (en)
Inventor
Joseph C Burge
Beal Richard
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 US669454A priority Critical patent/US3395891A/en
Priority to GB26294/68A priority patent/GB1213408A/en
Priority to SE07458/68A priority patent/SE326790B/xx
Priority to BE716192D priority patent/BE716192A/xx
Priority to FR1570396D priority patent/FR1570396A/fr
Application granted granted Critical
Publication of US3395891A publication Critical patent/US3395891A/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 blade Upon removal of the bolt and the spacer, the blade may be dropped radially inwardly to clear a midspan shroud between adjacent blades and thus enable the blade to be removed from the slot.
  • the bolt is threaded into a captured nut on the inner member so that assembly and disassembly can be had from one side of the rotor.
  • 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 providevan improved lock for a blade mounted on a rotor and in doing so to overcome the several problems identified above.
  • 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 tang. Blade locks are disposed in these clearances, each comprising a retainer having legs embracing either the opposite ends of the tang or the opposite sides of the rotor rim, and a third leg extending in an opposite direction to engage either one side of the rotor rim or one end of the tang. A spacer lies against the retainer to maintain the blade in is radially outward position and is provided with a leg which engages the other side of the rotor rim or the other end of the slot.
  • the retainer and spacer are held in locking position by a bolt which is preferably threaded into a threaded element on the retainer.
  • the spacer can be removed, permitting the blade to be shifted radially inwardly to clear shroud portions thereon for removal of the blade from the slot, and, in reverse fashion, the blade may be assembled on the rotor.
  • FIGURE 1 is a longitudinal section of a portion of an axial flow compressor
  • FIGURE 2 is alongitudinal section, on an enlarged scale, through the tanged root of a blade seen in FIG- URE l and taken on line II-II in FIGURE 6;
  • FIGURE 3 is a view taken on line III-III in FIG- URE 2;
  • FIGURE 4 is a section taken on line IV-IV in FIG- URE 2;
  • FIGURE 5 is a section taken on line V-V in FIG- URE l;
  • FIGURE 6 is a section, on an enlarged scale, taken generally on line VI-VI in FIGURE 5;
  • FIGURE 7 is a section taken on line VII-VII in FIGURE 2;
  • FIGURE 8 is a perspective view of one of the locking elements employed herein.
  • FIGURE 9 is a perspective view of another of the locking elements employed herein.
  • FIGURES 1 and 5 illustrate the iirst stage of an axial ow compressor of the type employed in gas turbine engines. From the engine inlet, air passes through an annular flow passageway, defined at its outer bounds by the compressor casing 10 and at its inner lbounds 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 lblades 16 which are mounted on the .compressor rotor 17.
  • the compressor rotor comprises a 4first stage disc 18, which is connected iby 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 blades 2S which are mounted on the compressor casing 27.
  • the compressor casing comprises two semicylindrical shells secured to a frame member 29 which encompasses the inlet guide vanes 14.
  • the outer portions of the blade 16 are of an airfoil shape and, due to their length, are provided with midspan shrouds 24 (FIGURES 5 and 6) which extend from opposite sides of the airfoil into abutting relation with corresponding shroud portions 24 on adjacent blades.
  • midspan shrouds are a known means for minimizing blade vibration.
  • the inner ends of the 'blades 16 are provided with tangs 26 which are received by corresponding slots 28, formed in a circumferential rim 30 peripherally of the disc 18.
  • the slots 28 are formed at an angle to the axis of the rotor which is illustrated by line x in FIGURE 6. This angled relationship corresponds to the angled relationship of the airfoil portion of the blade and minimizes stress loadings resulting from centrifugal force on the
  • Each blade is locked by a spacer 32, a retainer 34, and a bolt 44 which are disposed between the clearance between the lower end of the tang 26 and the bottom of the slot 28.
  • the retainer 34 has inwardly extending legs 36 at opposite ends of a bridge portion 38. The legs 36 are angled relative to the bridge 38 corresponding to the angled relationship of the slot 28. The bridge 38 thus tits snugly against the Ibottom of the slot 2S with the legs 36 embracing opposite radial faces of the rim 30.
  • the retainer 34 also has an outwardly extending leg 40 which is angled to engage the forward end face of the tang 26.
  • the spacer 32 Overlies the bridge 38 and has an outwardly extending leg 42 which engages the rearward end of the tang 26.
  • a bolt 44 passes through a hole 46 in the spacer 32 and is threaded into a self-locking nut 47 captured on the forward end of the retainer 34.
  • the described lock thus provides by means of the legs 36 a positive clamping relative to the rim 30 and by means of the legs 40, 42 a positive clamping to the opposite end faces of the tang 26, and, at the same time, functions to positively maintain the blade 16 in a radially outwardly shifted position.
  • the blade would be mounted by iirst placing a retainer 34 in an empty slot, next inserting the blade in the slot and shifting it outwardly.
  • the spacer 32 ⁇ would then be inserted beneath the blade as pictured in the drawings, and the -bolt 44 threaded into the nut 47 t0 secure the locking device for operation.
  • the spacer 32 is provided with wings 48 which block air flow through the clearance between the bottom of the slot and the lbottom of the blade tang. These wings also prevent the retainer and spacer from shifting in this clearance under the influence of the high centrifugal forces encountered during rotation of the rotor.
  • 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 the lower surface of the tang,
  • a blade lock for each blade, comprising,
  • a retainer having a bridge disposed in said clearance and having a pair of legs, at opposite ends thereof, extending in one radial direction and a third leg, at one end thereof, extending in an opposite radial direction,
  • said pair of legs extend radially inwardly of the retainer bridge to engage opposite faces of said rim and retainer in assembled relation said third retainer leg and said spacer leg extend radially outwardly to engage opposite ends of said tang.
  • the retaining means comprise a bolt, threadably connected with said retainer with its head clamped against the end of the spacer having the leg extending therefrom,
  • the blade lock may be assembled and removed from one side of the turbomachinery rotor.
  • a lock. nut is attached to the end of the retainer having legs extending in opposite directions,
  • the spacer comprises a relatively narrow body portion through which the bolt extends and laterally extending wings, conforming to the remainder of the said Iclearance not filled by the body portion of the spacer or by the retainer,

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US669454A 1967-09-21 1967-09-21 Lock for turbomachinery blades Expired - Lifetime US3395891A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US669454A US3395891A (en) 1967-09-21 1967-09-21 Lock for turbomachinery blades
GB26294/68A GB1213408A (en) 1967-09-21 1968-05-31 Improvements in lock for turbomachinery blades
SE07458/68A SE326790B (enrdf_load_stackoverflow) 1967-09-21 1968-06-04
BE716192D BE716192A (enrdf_load_stackoverflow) 1967-09-21 1968-06-06
FR1570396D FR1570396A (enrdf_load_stackoverflow) 1967-09-21 1968-07-03

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US669454A US3395891A (en) 1967-09-21 1967-09-21 Lock for turbomachinery blades

Publications (1)

Publication Number Publication Date
US3395891A true US3395891A (en) 1968-08-06

Family

ID=24686376

Family Applications (1)

Application Number Title Priority Date Filing Date
US669454A Expired - Lifetime US3395891A (en) 1967-09-21 1967-09-21 Lock for turbomachinery blades

Country Status (5)

Country Link
US (1) US3395891A (enrdf_load_stackoverflow)
BE (1) BE716192A (enrdf_load_stackoverflow)
FR (1) FR1570396A (enrdf_load_stackoverflow)
GB (1) GB1213408A (enrdf_load_stackoverflow)
SE (1) SE326790B (enrdf_load_stackoverflow)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572970A (en) * 1969-01-23 1971-03-30 Gen Electric Turbomachinery blade spacer
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
US3734646A (en) * 1972-02-02 1973-05-22 Gen Electric Blade fastening means
US3817657A (en) * 1971-11-08 1974-06-18 Motoren Turbinen Union Integral turbine wheel with axial through-openings at the outer rim and with controlled rim cracks
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
US4279572A (en) * 1979-07-09 1981-07-21 United Technologies Corporation Sideplates for rotor disk and rotor blades
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
US4505640A (en) * 1983-12-13 1985-03-19 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
US4778342A (en) * 1985-07-24 1988-10-18 Imo Delaval, Inc. Turbine blade retainer
US4797065A (en) * 1986-10-17 1989-01-10 Transamerica Delaval Inc. Turbine blade retainer
US5727927A (en) * 1995-05-06 1998-03-17 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Device for securing rotor blades to a rotor, especially of a gas turbine propulsion plant
US5749706A (en) * 1996-01-31 1998-05-12 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Turbine blade wheel assembly with rotor blades fixed to the rotor wheel by rivets
US5984639A (en) * 1998-07-09 1999-11-16 Pratt & Whitney Canada Inc. Blade retention apparatus for gas turbine rotor
US5993160A (en) * 1997-12-11 1999-11-30 Pratt & Whitney Canada Inc. Cover plate for gas turbine rotor
US20030002987A1 (en) * 2001-06-27 2003-01-02 Davidson Dwight Eric Compressor rotor blade spacer apparatus
US20060073021A1 (en) * 2004-10-06 2006-04-06 Siemens Westinghouse Power Corporation Remotely accessible locking system for turbine blades
US20090004012A1 (en) * 2007-06-27 2009-01-01 Caprario Joseph T Cover plate for turbine rotor having enclosed pump for cooling air
US20100284805A1 (en) * 2009-05-11 2010-11-11 Richard Christopher Uskert Apparatus and method for locking a composite component
RU2525817C2 (ru) * 2009-05-06 2014-08-20 Снекма Ротор вентилятора турбореактивного двигателя самолета
US8979502B2 (en) 2011-12-15 2015-03-17 Pratt & Whitney Canada Corp. Turbine rotor retaining system
US20150252678A1 (en) * 2014-03-07 2015-09-10 United Technologies Corporation Fan blade spacer
CN106015093A (zh) * 2016-07-13 2016-10-12 上海电气燃气轮机有限公司 一种压气机动叶轮盘的锁紧结构
US10352175B2 (en) * 2015-09-21 2019-07-16 Rolls-Royce Plc Seal-plate anti-rotation in a stage of a gas turbine engine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2507679A1 (fr) * 1981-06-12 1982-12-17 Snecma Dispositif de verrouillage d'une aube de rotor de turbomachine
US4451205A (en) * 1982-02-22 1984-05-29 United Technologies Corporation Rotor blade assembly
FR2535794A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de retenue axiale et radiale d'aubes de soufflante
GB2408296A (en) * 2003-11-22 2005-05-25 Rolls Royce Plc Compressor blade root retainer with integral sealing means to reduce axial leakage
GB2410531B (en) 2004-01-29 2006-03-01 Rolls Royce Plc Fan blade disk assembly
FR2881174B1 (fr) * 2005-01-27 2010-08-20 Snecma Moteurs Dispositif de positionnement d'une aube et disque aubage comportant un tel dispositif
ES2630046T3 (es) * 2013-04-09 2017-08-17 MTU Aero Engines AG Surtido de chapas de sujeción, turbina de gas correspondiente y método de ensamblaje

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801074A (en) * 1952-10-01 1957-07-30 United Aircraft Corp Blade retaining means
US2971744A (en) * 1956-11-27 1961-02-14 Szydlowski Joseph Blade lock
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801074A (en) * 1952-10-01 1957-07-30 United Aircraft Corp Blade retaining means
US2971744A (en) * 1956-11-27 1961-02-14 Szydlowski Joseph Blade lock
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

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572970A (en) * 1969-01-23 1971-03-30 Gen Electric Turbomachinery blade spacer
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
US3817657A (en) * 1971-11-08 1974-06-18 Motoren Turbinen Union Integral turbine wheel with axial through-openings at the outer rim and with controlled rim cracks
US3734646A (en) * 1972-02-02 1973-05-22 Gen Electric Blade fastening means
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
US4279572A (en) * 1979-07-09 1981-07-21 United Technologies Corporation Sideplates for rotor disk and rotor blades
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
US4505640A (en) * 1983-12-13 1985-03-19 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
US4778342A (en) * 1985-07-24 1988-10-18 Imo Delaval, Inc. Turbine blade retainer
US4797065A (en) * 1986-10-17 1989-01-10 Transamerica Delaval Inc. Turbine blade retainer
US5727927A (en) * 1995-05-06 1998-03-17 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Device for securing rotor blades to a rotor, especially of a gas turbine propulsion plant
US5749706A (en) * 1996-01-31 1998-05-12 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Turbine blade wheel assembly with rotor blades fixed to the rotor wheel by rivets
US5993160A (en) * 1997-12-11 1999-11-30 Pratt & Whitney Canada Inc. Cover plate for gas turbine rotor
WO2000003125A1 (en) * 1998-07-09 2000-01-20 Pratt & Whitney Canada Corp. Blade retention apparatus for gas turbine rotor
RU2213229C2 (ru) * 1998-07-09 2003-09-27 Прэтт энд Уитни Кэнэдэ Корп. Облопаченный ротор для газотурбинного двигателя и способ фиксации лопатки в нем
US5984639A (en) * 1998-07-09 1999-11-16 Pratt & Whitney Canada Inc. Blade retention apparatus for gas turbine rotor
US20030002987A1 (en) * 2001-06-27 2003-01-02 Davidson Dwight Eric Compressor rotor blade spacer apparatus
US6582195B2 (en) * 2001-06-27 2003-06-24 General Electric Company Compressor rotor blade spacer apparatus
US20060073021A1 (en) * 2004-10-06 2006-04-06 Siemens Westinghouse Power Corporation Remotely accessible locking system for turbine blades
US7264448B2 (en) 2004-10-06 2007-09-04 Siemens Power Corporation, Inc. Remotely accessible locking system for turbine blades
US8708652B2 (en) 2007-06-27 2014-04-29 United Technologies Corporation Cover plate for turbine rotor having enclosed pump for cooling air
US20090004012A1 (en) * 2007-06-27 2009-01-01 Caprario Joseph T Cover plate for turbine rotor having enclosed pump for cooling air
RU2525817C2 (ru) * 2009-05-06 2014-08-20 Снекма Ротор вентилятора турбореактивного двигателя самолета
US8439635B2 (en) 2009-05-11 2013-05-14 Rolls-Royce Corporation Apparatus and method for locking a composite component
US20100284805A1 (en) * 2009-05-11 2010-11-11 Richard Christopher Uskert Apparatus and method for locking a composite component
US8979502B2 (en) 2011-12-15 2015-03-17 Pratt & Whitney Canada Corp. Turbine rotor retaining system
US20150252678A1 (en) * 2014-03-07 2015-09-10 United Technologies Corporation Fan blade spacer
US9840922B2 (en) * 2014-03-07 2017-12-12 United Technologies Corporation Fan blade spacer
US10352175B2 (en) * 2015-09-21 2019-07-16 Rolls-Royce Plc Seal-plate anti-rotation in a stage of a gas turbine engine
US10443402B2 (en) 2015-09-21 2019-10-15 Rolls-Royce Plc Thermal shielding in a gas turbine
CN106015093A (zh) * 2016-07-13 2016-10-12 上海电气燃气轮机有限公司 一种压气机动叶轮盘的锁紧结构
CN106015093B (zh) * 2016-07-13 2018-06-29 上海电气燃气轮机有限公司 一种压气机动叶轮盘的锁紧结构

Also Published As

Publication number Publication date
SE326790B (enrdf_load_stackoverflow) 1970-08-03
GB1213408A (en) 1970-11-25
BE716192A (enrdf_load_stackoverflow) 1968-11-04
FR1570396A (enrdf_load_stackoverflow) 1969-06-06

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