US3508844A - Blade lock - Google Patents

Blade lock Download PDF

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Publication number
US3508844A
US3508844A US747524A US3508844DA US3508844A US 3508844 A US3508844 A US 3508844A US 747524 A US747524 A US 747524A US 3508844D A US3508844D A US 3508844DA US 3508844 A US3508844 A US 3508844A
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US
United States
Prior art keywords
lock
blade
root
disk
root portion
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
US747524A
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English (en)
Inventor
George P Le Blanc
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.)
RTX Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Application granted granted Critical
Publication of US3508844A publication Critical patent/US3508844A/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

  • a turbomachine having a rotor assembly construction wherein a blade lock construction is employed between the blade root and the rotor disk to prevent any axial movement of the blade root in the rotor disk.
  • This invention relates to a rotor assembly for use in a turbomachine and more particularly to a blade lock therein.
  • the pin-type locking device weakens the wheel at a point of very high stress with the result that the entire wheel must be made heavier than would otherwise be necessary, and this type of locking device also tends to reduce the tangential blade tip wobble when the assembly is cold.
  • the key or blade lock retention is normally weak in the axial direction with the result that the blades may walk out of the wheel slots.
  • the rotor assembly which employs the blade lock construction hereinafter described, contains a blade which when inserted in the rotor disk slot is prevented from moving axially in one direction by stop means on the blade root, which cooperate with or abut against the rotor disk face.
  • stop means on the blade root After insertion of the blade in the blade receiving slots within the rotor disk, the one end of the blade extends axially beyond the rotor disk, this end being the root portion remote from the root end having the stop means.
  • the blade root at this end contains a circumferential slot which extends transversely from one side of the blade root to the other side. This slot is positioned in the blade root portion such that when the blade is inserted into the disk slot the circumferential slot is past the disk face and lies in a plane which is generally parallel to the plane of the disk.
  • This plate lock Inserted within this slot is a plate lock, this plate lock once inserted within the circumferential slot being in abutting relationship with the face of the disk and retaining or preventing an axial movement of the blade.
  • This plate lock includes two outwardly extending legs which straddle 3,508,844 Patented Apr. 28, 1970 or abut the blade root portion on each side of the root and thereby limit or prevent any side movement of the plate lock.
  • a deformable retaining lock is employed.
  • This retaining lock consists of a normally outwardly extending tab at one end, the end remote therefrom being a generally axially extending tab.
  • the outwardly extending portion abuts the blade root face, and the axially extending portion extends beneath the plate lock and past the root portion face containing the stop means.
  • This latter stop means in the embodiment herein illustrated comprises a pair of radially extending tabs with a space therebetween. The deformable retaining lock passes through this space and is deformed upward from its normally axial position to an outwardly extending position and abuts the face of the root portion.
  • the blade lock construction of the present invention provides a construction which is strong in the direction where failures generally occur. More specifically, before a blade will fall out of a rotor assembly employing the construction described herein, the blade lock must fall in four positions; that is, two at the plate lock and two at the integral blade tabs forming the stop means. Additionally, the construction by employing a deformable retaining lock provides a construction which is readily removable or replaceable.
  • FIGURE 1 is a fragmentary sectional View of a blade root portion.
  • FIGURE 2 is a fragmentary side view of a rotor assembly showing the blade root portion assembled to the rotor disk.
  • a compressor rotor 10 supports a series of radially extending blades 12 mounted in peripheral slots 14 extending from the rear or first face 16 of the rotor to its forward or second face 18 in a direction substantially axial with respect to general disposition of the rotor.
  • Each blade 12 includes a root section 20 and in the embodiment illustrated in FIGURE 1, root section 20 has a pair of integral inwardly extending flanges 22 and 24, each of these integral flanges abutting against first face 16, thereby effectively preventing axial movement of the blade in one direction.
  • the end of blade root 20 opposite flanges 22 and 24 contains a circumferential slot 26.
  • Circumferential slot 26 extends transversely from side 28 of root portion 20 to side 30 of root section 20 and is positioned within the root section such that it lies in a plane that is generally parallel to the plane of rotor disk 10. Additionally, the slot 26 is positioned within root 20 such that when plate lock 32 is inserted into the circumferential slot 26, the extending portions of plate lock 32 abut against second face 18 of rotor disk 10.
  • Plate lock 32 includes means for limiting or preventing any side movement of plate lock 32. These means comprise a pair of outwardly extending legs 34 and 36 which straddle the blade root portion 20 and are substantially in abutting relationship with each side of the root portion 20. Locking the plate lock 32 into position and connecting the blade root portion to rotor disk 10 is retaining lock 40.
  • Retaining lock 40 is preferably a sheet metal member which is deformable at one end. As herein illustrated, end 42 is preformed into an outwardly extending tab 44 which abuts against first face 116.
  • Retaining lock 40 includes an axially extending portion 46 which passes through circumferential slot 26 and beneath the plate lock 32 thereby positioning or securing the plate lock 32 within the slot.
  • the end remote from the deformed end is initially an axially extending member which is deformable into an outwardly extending tab 48.
  • the axially extending tab prior to being deformed, passes through slot 26 beneath the plate lock 32 and between the space 50 of the integral tabs 22 and 24 of root portion 20.
  • the retaining lock 40 After the retaining lock 40 has been positioned in such a manner, the deformable end is deformed upward and the retaining lock then has two outwardly extending tabs, this being illustrated in FIGURE 2. Any outward or radial movement of plate lock 32 and retaining lock 40 is limited by the height of circumferential slot 26.
  • a rotor assembly for a turbomachine comprising a disk having blade receiving slots in the periphery thereof extending generally axially from the first side of the disc, and removable blades including a root portion slideably mounted in the slots, wherein the improvement comprises:
  • one end of the root portion having stop means which means for securing the lock plate to the blade root
  • stop means cooperating to limit any movement of the blade root when positioned in the blade receiving slots in the disk.
  • the stop means comprise a pair of integral tabs extending radially inward and which abut against the first side of the disk and thereby position the blade axially.
  • the plate lock means for limiting side movement of the plate lock comprises a pair of outwardly extending legs which straddle the blade root portion and are substantially in abutting relationship with each side thereof.
  • a rotor assembly for a turbomachine comprising a disk bearing blade receiving slots in the periphery thereof extending generally axially from one face of the disk to the opposite face of the disk, and removable blades including a root portion slideably mounted in the slots wherein the improvement comprises:
  • one end of the root portion having stop means abutting against one face of the disk and preventing axial movement of the root in one direction, the end of the blade root opposite the one with the stop means having a slot which extends transversely from one side of the root to the other side, the transverse slot being positioned in the root portion such that it is axially beyond the blade receiving slots and lies in a plane which is generally parallel to the plane of the disk;
  • a plate lock positioned in the transverse slot, the plate lock being in abutting relationship with the face of the disk and including means positioned on either side of the root portion to limit side movement of the lock plate;
  • a retaining lock extending from the face of the root portion containing the transverse slot to the face containing the stop means, the lock passing through the transverse slot and beneath the lock plate thereby locking the lock plate in position and preventing any axial movement of the root portion in the blade receiving slots.
  • the retaining lock is deformable, one end thereof being an outwardly extending tab, the end opposite therefrom being a normally axially extending tab which is deformable to an outwardly extending tab.
  • the height of the transverse slot in the root portion limits the radial movement of the retainer lock and lock plate.

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)
US747524A 1968-07-25 1968-07-25 Blade lock Expired - Lifetime US3508844A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US74752468A 1968-07-25 1968-07-25

Publications (1)

Publication Number Publication Date
US3508844A true US3508844A (en) 1970-04-28

Family

ID=25005438

Family Applications (1)

Application Number Title Priority Date Filing Date
US747524A Expired - Lifetime US3508844A (en) 1968-07-25 1968-07-25 Blade lock

Country Status (4)

Country Link
US (1) US3508844A (enrdf_load_stackoverflow)
DE (1) DE1932701B2 (enrdf_load_stackoverflow)
FR (1) FR2013647A1 (enrdf_load_stackoverflow)
GB (1) GB1222926A (enrdf_load_stackoverflow)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4466776A (en) * 1982-01-14 1984-08-21 S.N.F.C.M.A. Axial locking device for turbomachine blades
US4566857A (en) * 1980-12-19 1986-01-28 United Technologies Corporation Locking of rotor blades on a rotor disk
US4846628A (en) * 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine
US5622476A (en) * 1994-12-14 1997-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Axial fixing arrangement for rotor blades of a turbomachine
US6010304A (en) * 1997-10-29 2000-01-04 General Electric Company Blade retention system for a variable rotor blade
US20150037161A1 (en) * 2013-07-30 2015-02-05 MTU Aero Engines AG Method for mounting a gas turbine blade in an associated receiving recess of a rotor base body
FR3139360A1 (fr) * 2022-09-02 2024-03-08 Safran Aircraft Engines Roue mobile pour turbomachine comprenant des aubes bloquées axialement
FR3139596A1 (fr) * 2022-09-12 2024-03-15 Safran Aircraft Engines Ensemble de turbomachine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2492906A2 (fr) * 1976-03-25 1982-04-30 Snecma Dispositif de retenue pour aubes de soufflantes
DE8001586U1 (de) * 1980-01-22 1980-04-17 Siemens Ag, 1000 Berlin Und 8000 Muenchen Druckknopfantrieb für Tastschalter
FR2502690B1 (fr) 1981-03-27 1985-09-13 Snecma Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur
FR2535793B1 (fr) * 1982-11-08 1987-04-10 Snecma Dispositif de verrouillage axial d'aubes de soufflante
FR2575590B1 (fr) * 1984-12-28 1987-01-23 Telemecanique Electrique Appareil interrupteur d'urgence
RU2146767C1 (ru) * 1998-02-23 2000-03-20 Открытое акционерное общество "Авиадвигатель" Рабочее колесо турбомашины
EP1402152B1 (de) * 2001-07-03 2007-01-17 ABB Turbo Systems AG Sicherungssystem für laufschaufeln axial durchströmter turbomaschinen
GB201417039D0 (en) 2014-09-26 2014-11-12 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641443A (en) * 1951-03-17 1953-06-09 A V Roe Canada Ltd Rotor blade locking
US2755062A (en) * 1951-07-13 1956-07-17 Bristol Aeroplane Co Ltd Blade-locking means for turbine and the like rotor assemblies
US2994507A (en) * 1959-01-23 1961-08-01 Westinghouse Electric Corp Blade locking structure
US3137478A (en) * 1962-07-11 1964-06-16 Gen Electric Cover plate assembly for sealing spaces between turbine buckets
US3216699A (en) * 1963-10-24 1965-11-09 Gen Electric Airfoil member assembly

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641443A (en) * 1951-03-17 1953-06-09 A V Roe Canada Ltd Rotor blade locking
US2755062A (en) * 1951-07-13 1956-07-17 Bristol Aeroplane Co Ltd Blade-locking means for turbine and the like rotor assemblies
US2994507A (en) * 1959-01-23 1961-08-01 Westinghouse Electric Corp Blade locking structure
US3137478A (en) * 1962-07-11 1964-06-16 Gen Electric Cover plate assembly for sealing spaces between turbine buckets
US3216699A (en) * 1963-10-24 1965-11-09 Gen Electric Airfoil member assembly

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4566857A (en) * 1980-12-19 1986-01-28 United Technologies Corporation Locking of rotor blades on a rotor disk
US4466776A (en) * 1982-01-14 1984-08-21 S.N.F.C.M.A. Axial locking device for turbomachine blades
US4846628A (en) * 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine
US5622476A (en) * 1994-12-14 1997-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Axial fixing arrangement for rotor blades of a turbomachine
US6010304A (en) * 1997-10-29 2000-01-04 General Electric Company Blade retention system for a variable rotor blade
US20150037161A1 (en) * 2013-07-30 2015-02-05 MTU Aero Engines AG Method for mounting a gas turbine blade in an associated receiving recess of a rotor base body
FR3139360A1 (fr) * 2022-09-02 2024-03-08 Safran Aircraft Engines Roue mobile pour turbomachine comprenant des aubes bloquées axialement
FR3139596A1 (fr) * 2022-09-12 2024-03-15 Safran Aircraft Engines Ensemble de turbomachine

Also Published As

Publication number Publication date
FR2013647A1 (enrdf_load_stackoverflow) 1970-04-03
DE1932701B2 (de) 1971-04-08
GB1222926A (en) 1971-02-17
DE1932701A1 (de) 1970-05-14

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