US2867408A - Axial locking of rotor blades for turbines and the like - Google Patents

Axial locking of rotor blades for turbines and the like Download PDF

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Publication number
US2867408A
US2867408A US420418A US42041854A US2867408A US 2867408 A US2867408 A US 2867408A US 420418 A US420418 A US 420418A US 42041854 A US42041854 A US 42041854A US 2867408 A US2867408 A US 2867408A
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Prior art keywords
blade
rotor
slot
platform
locking
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US420418A
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Kolb Paul
George F Arkless
John R Bolter
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CA Parsons and Co Ltd
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CA Parsons and Co Ltd
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    • 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

Definitions

  • This invention relates to the axial locking of rotor blades for compressors, turbines or fans, hereinafter generally referred to as turbines, the blades being of the type which are inserted into dovetailed or serrated slots machined in a generally axial direction around the periphery of the said rotor.
  • a common method of accomplishing the axial locking (i. e., against movement in a direction substantially parallel to the rotor axis) of such blades is to hammer over lightly the serrations or sides of the dovetail at either end of the rotor root. While performing its function effectively this method suffers from the disadvantage that a certain amount of local damage is done to the rotor or disc and this limits the number of times for which the operation may be repeated during subsequent reblading of the rotor. involves further damage to the rotor as the spread material must be chipped away or sheared off with or near the blade root itself.
  • the object of the invention is to provide an axial locking device for the rotor blades of turbines which is simple to make, effective, and free from the above disadvantages.
  • the invention consists in a method for the locking of rotor blades for compressors, turbines or fans herein re ferred to generally as turbines, the blades being of the type which are inserted into dovetailed or serrated slots, machined in a direction which is generally axial with respect to the rotor around the periphery of the said rotor, which method comprises providing a continuous groove in the circumferential face of the rotor, providing a slot in one of the sides of each blade platform which is disposed in a direction parallel to the rotor axis, said slot being narrower than the rotor groove and positioned so that when the blade is in position in the rotor the said slot coincides with the rotor groove, and inserting in the groove of the rotor a locking piece consisting of a base portion fitting the rotor groove and a protruding tongue which fits into the blade platform slot so as to prevent movement of the blade in a direction parallel to the rotor axis; and in the above method in which for the
  • FIG. 3 is a perspective view of a blade locking key for all blades except the last;
  • Figure 4 is a perspective view of the blade locking key for the last blade of the row
  • FIG. 5 shows again a partly developed plan of the rotor showing the last blade being inserted
  • Figure 6 shows an enlarged part plan and Figure 7 an end view of the last blade in position.
  • the blade root may be of the common fir-tree form orbulb root form solong as insertion of the blade into the rotor is made in a generally axial direction with respect to the rotor.
  • a platform 1 of each blade is provided with a small rectangular slot 2 (see Figures la and 2) preferablymidway along one axially disposed side of the platform, this slot being on the same side of the platform for. all blades.
  • a small groove 3 which, as the drawings show, is broader than the slot 2 but also of rectangular section is turned round the periphery of therotor intersecting with and interrupted by blade slots 4. The position of this peripheral groove is so chosen thatits centre line, which lies on a radial plane, is directly underneath the slot in the blade platform when the blade is in position in the rotor.
  • Such a blade is inserted into its slot in the rotor.
  • the locking piece 5, Figure 3, which is made of any suitable metal and whose various dimensions correspond with the dimensions of the peripheral groove and platform slot as indicated in Figures 1, 2 and 3 is then placed in position so that its base 5a lies in the peripheral groove and its tongue 5b protrudes up through and engages with the slot in the blade platform, so locking the blade securely against motion in a direction parallel to the rotor axis.
  • the next blade is then slid into position in the rotor into the blade slot adjacent to the locking piece just inserted, the unslotted axially disposed side of its platform coming up against the locking piece so completely restraining the key from movement. This process is repeated round the row until the last blade is reached, when a diiferent method of locking must be used.
  • the preferred method of locking the last blade of a row is as follows:
  • the first blade inserted in a row has both of the axially disposed sides of its platform equipped with rectangular slots, the extra slot being indicated by 2a in Figure 2.
  • a piece of copper, or similar ductile material shaped as shown in Figure 4 is used as the locking piece for the last blade.
  • the last blade locking piece ( Figure 4) is placed in position so that its base lies in the peripheral groove and partly under the first blades platform and its tongue protrudes up through and beyond the extra slot 2a provided in the first blade platform as in Figure 5.
  • the last blade is then inserted into its slot as in Figure 5 and pushed 'into its final position, the slot in its platform falling directly opposite the extra slot 2a in the platform of the first blade.
  • the last locking piece is then slid half out of its position in the first blade so.that its tongue is then half "in the extra slot of the first and half in the slot of the last blade, as shown clearly in Figures 6 and 7.
  • theprotruding portion 0" of the tongue is gently peened'so that the whole volume of the combined slots of thefirst and last blades is filled.
  • a bladed rotor for acompressor, turbine or fan comprising a rotor body having a plurality of axially extending circumferentially spaced dovetail slots and a corresponding :plurality of blades having faces fitting in the said dovetail'slots and held radially and circumferentially thereby, "the said blades having also circumferentially extending platforms overlying the rotor periphery at each side of the groove, so that the platform of-adjacent blades substantially touch each other, means for locking the blades to'the rotor body against axial "movement, comprising for each blade, a locking piece having a base "portion shorter in the axial direction than 'the face of the blade and a protruding tongue of less'width in the axial direction than the base portion and extending radially from the axially middle part there- "of, the'rot'or body between each adjacent dovetail slot having a slot holding and fitting the base portion of said locktion accommodating
  • Rotor blade locking means according to claim 1, in which the said blade platform recesses extend in the same circumferential direction.
  • Rotor blade locking means in which one of the blades has a slot in its platform in addition to the said recesses, the said slot facing in the opposite circumferential direction from the "first said blade platform recess of the said blade and comprising a double locking piece having a protruding tongue fitting in the said slot and the recess of an adjacent blade, the said last named protruding tongue having a circumferential Width less than the combined width of the said additional slot and recess in the platform of the said blade and sufficient circumferential width to ,permit expanding by peening so as to fill the said slot and adjacent recess.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Jan. 6,- 1959 P. KOLB ET AL I AXIAL LOCKING OF ROTOR BLADES FOR TURBINES AND THE LIKE Filed March 17. 1954 2 Sheets-Sheet 1 ill Jan. 6, 1959 P. KOLB ET AL 2,867,408
AXIAL LOCKING 0F ROTOR BLADES FOR TURBINES AND THE LIKE F1164 March 17, 1954 2 Sheets-Sheet 2 United States Patent AXIAL LOCKING F ROTOR BLADES FOR TURBINES AND THE LIKE Paul Kolb, George F. Arkless, and John R. Bolter, Newcastle-upon-Tyne, England, assignors to C. A. Parsons -& Company Limited, Newcastle-upon-Tyne, England -Application March 17, 1954, Serial No. 420,418
Claims priority, application Great Britain April 10, 1953 3 Claims. (Cl. 253-77) This invention relates to the axial locking of rotor blades for compressors, turbines or fans, hereinafter generally referred to as turbines, the blades being of the type which are inserted into dovetailed or serrated slots machined in a generally axial direction around the periphery of the said rotor.
A common method of accomplishing the axial locking (i. e., against movement in a direction substantially parallel to the rotor axis) of such blades is to hammer over lightly the serrations or sides of the dovetail at either end of the rotor root. While performing its function effectively this method suffers from the disadvantage that a certain amount of local damage is done to the rotor or disc and this limits the number of times for which the operation may be repeated during subsequent reblading of the rotor. involves further damage to the rotor as the spread material must be chipped away or sheared off with or near the blade root itself.
The object of the invention is to provide an axial locking device for the rotor blades of turbines which is simple to make, effective, and free from the above disadvantages.
The invention consists in a method for the locking of rotor blades for compressors, turbines or fans herein re ferred to generally as turbines, the blades being of the type which are inserted into dovetailed or serrated slots, machined in a direction which is generally axial with respect to the rotor around the periphery of the said rotor, which method comprises providing a continuous groove in the circumferential face of the rotor, providing a slot in one of the sides of each blade platform which is disposed in a direction parallel to the rotor axis, said slot being narrower than the rotor groove and positioned so that when the blade is in position in the rotor the said slot coincides with the rotor groove, and inserting in the groove of the rotor a locking piece consisting of a base portion fitting the rotor groove and a protruding tongue which fits into the blade platform slot so as to prevent movement of the blade in a direction parallel to the rotor axis; and in the above method in which for the purpose of locking the final blade to be inserted in the row, the platform of the first blade to be inserted is provided with a further slot similar in size, shape and position to the other slot but disposed on the axially disposed side of the platform opposite the normal slot and a locking piece, having a base portion of similar shape to the normal locking piece referred to above and a tongue of similar cross section to the tongue of the normal locking piece but of greater length, is fitted into the groove of the rotor and arranged so that its tongue fits partly into the slot of the platform of the first blade to be inserted and partly into the adjacent slot in the platform of the last blade to be inserted, said tongue being subsequently spread to fill the combined slots in the said platform so as to prevent movement of the last blade in a direction parallel to the rotor axis.
Referring to the accompanying diagrammatic drawings:
Moreover removal of a blade so locked 2,867,408 Patented J an. 6, 1959 ice Figure 3 is a perspective view of a blade locking key for all blades except the last;
Figure 4 is a perspective view of the blade locking key for the last blade of the row;
' Figure 5 shows again a partly developed plan of the rotor showing the last blade being inserted;
Figure 6 shows an enlarged part plan and Figure 7 an end view of the last blade in position.
Referring now to Figure l a type of blade root and attachment to the rotor to Which this invention is applicable is shown. Alternatively the blade root may be of the common fir-tree form orbulb root form solong as insertion of the blade into the rotor is made in a generally axial direction with respect to the rotor.
A platform 1 of each blade is provided with a small rectangular slot 2 (see Figures la and 2) preferablymidway along one axially disposed side of the platform, this slot being on the same side of the platform for. all blades. A small groove 3 which, as the drawings show, is broader than the slot 2 but also of rectangular section is turned round the periphery of therotor intersecting with and interrupted by blade slots 4. The position of this peripheral groove is so chosen thatits centre line, which lies on a radial plane, is directly underneath the slot in the blade platform when the blade is in position in the rotor.
Such a blade, then, is inserted into its slot in the rotor. The locking piece 5, Figure 3, which is made of any suitable metal and whose various dimensions correspond with the dimensions of the peripheral groove and platform slot as indicated in Figures 1, 2 and 3 is then placed in position so that its base 5a lies in the peripheral groove and its tongue 5b protrudes up through and engages with the slot in the blade platform, so locking the blade securely against motion in a direction parallel to the rotor axis. The next blade is then slid into position in the rotor into the blade slot adjacent to the locking piece just inserted, the unslotted axially disposed side of its platform coming up against the locking piece so completely restraining the key from movement. This process is repeated round the row until the last blade is reached, when a diiferent method of locking must be used.
The preferred method of locking the last blade of a row is as follows:
The first blade inserted in a row has both of the axially disposed sides of its platform equipped with rectangular slots, the extra slot being indicated by 2a in Figure 2. A piece of copper, or similar ductile material shaped as shown in Figure 4 is used as the locking piece for the last blade.
In Figures la, 2, 3 and 4 the reference letters a, b, c, d and e apply to corresponding faces of locking pieces and the slots into which they are fitted and give an indication of equivalent dimensions. The tongue c of the last blade locking piece of Figure 4 is made longer than that of the normal locking piece, that is, about twice the size because of the subsequent peening required.
With the second last blade of the row fitted in the manner previously described with its locking piece, the last blade locking piece (Figure 4) is placed in position so that its base lies in the peripheral groove and partly under the first blades platform and its tongue protrudes up through and beyond the extra slot 2a provided in the first blade platform as in Figure 5. The last blade is then inserted into its slot as in Figure 5 and pushed 'into its final position, the slot in its platform falling directly opposite the extra slot 2a in the platform of the first blade. The last locking piece is then slid half out of its position in the first blade so.that its tongue is then half "in the extra slot of the first and half in the slot of the last blade, as shown clearly in Figures 6 and 7. Finally theprotruding portion 0" of the tongue is gently peened'so that the whole volume of the combined slots of thefirst and last blades is filled.
Weclaim: 4
1. In a bladed rotor for acompressor, turbine or fan, comprising a rotor body having a plurality of axially extending circumferentially spaced dovetail slots and a corresponding :plurality of blades having faces fitting in the said dovetail'slots and held radially and circumferentially thereby, "the said blades having also circumferentially extending platforms overlying the rotor periphery at each side of the groove, so that the platform of-adjacent blades substantially touch each other, means for locking the blades to'the rotor body against axial "movement, comprising for each blade, a locking piece having a base "portion shorter in the axial direction than 'the face of the blade and a protruding tongue of less'width in the axial direction than the base portion and extending radially from the axially middle part there- "of, the'rot'or body between each adjacent dovetail slot having a slot holding and fitting the base portion of said locktion accommodating a said tongue and the blade platforms having recesses receiving and fitting the said protruding tongues.
2. Rotor blade locking means according to claim 1, in which the said blade platform recesses extend in the same circumferential direction.
3. Rotor blade locking means according to claim 1, in which one of the blades has a slot in its platform in addition to the said recesses, the said slot facing in the opposite circumferential direction from the "first said blade platform recess of the said blade and comprising a double locking piece having a protruding tongue fitting in the said slot and the recess of an adjacent blade, the said last named protruding tongue having a circumferential Width less than the combined width of the said additional slot and recess in the platform of the said blade and sufficient circumferential width to ,permit expanding by peening so as to fill the said slot and adjacent recess.
References Cited in the 'file of this patent UNITED STATES PATENTS 2,651,494 Persson t Sept. 8, 1953 FOREIGN "PATENTS 307,832 Great Britain 'Oct. 15,1927
671,960 Great Britain 'Aug. 14, 1952
US420418A 1953-04-10 1954-03-17 Axial locking of rotor blades for turbines and the like Expired - Lifetime US2867408A (en)

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Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000614A (en) * 1958-06-11 1961-09-19 Gen Motors Corp Rotor blade locks
US3001760A (en) * 1959-08-07 1961-09-26 Gen Motors Corp Turbine blade lock
US3198485A (en) * 1963-09-26 1965-08-03 Gen Motors Corp Turbine blade lock
US3867069A (en) * 1973-05-04 1975-02-18 Westinghouse Electric Corp Alternate root turbine blading
US3904317A (en) * 1974-11-27 1975-09-09 Gen Electric Bucket locking mechanism
US3930751A (en) * 1974-07-05 1976-01-06 Carrier Corporation Bucket locking mechanism
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
US4120607A (en) * 1976-03-26 1978-10-17 Rolls-Royce Limited Rotor blade for a gas turbine engine
US4676723A (en) * 1986-03-26 1987-06-30 Westinghouse Electric Corp. Locking system for a turbine side entry blade
US4767247A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for preventing relative blade motion in steam turbine
US4895490A (en) * 1988-11-28 1990-01-23 The United States Of America As Represented By The Secretary Of The Air Force Internal blade retention system for rotary engines
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
US20090290983A1 (en) * 2008-05-26 2009-11-26 Kabushiki Kaisha Toshiba Turbine blade assembly and steam turbine
JP2010185367A (en) * 2009-02-12 2010-08-26 Mitsubishi Heavy Industries Compressor Corp Fixing structure of turbine blade and turbine
US20110229328A1 (en) * 2010-03-17 2011-09-22 Sudhir Rajagopalan Turbomachine Blade Locking Structure Including Shape Memory Alloy
US20130052024A1 (en) * 2011-08-24 2013-02-28 General Electric Company Turbine Nozzle Vane Retention System
US8485785B2 (en) 2007-07-19 2013-07-16 Siemens Energy, Inc. Wear prevention spring for turbine blade
US20170037736A1 (en) * 2014-04-29 2017-02-09 Siemens Aktiengesellschaft Wheel disk assembly and method for assembling a wheel disk assembly
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 (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL99070C (en) * 1953-07-28
US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention
DE1032753B (en) * 1956-10-05 1958-06-26 Maschf Augsburg Nuernberg Ag Locking of rotor blades of flow machines held in a form-fitting manner in axial grooves of a rotor disk
DE1115992B (en) * 1959-08-07 1961-10-26 Entwicklungsbau Pirna Veb Protection against axial displacement of rotor blades with a fir tree base on gas turbines
US3986793A (en) * 1974-10-29 1976-10-19 Westinghouse Electric Corporation Turbine rotating blade
US4050134A (en) * 1974-10-29 1977-09-27 Westinghouse Electric Corporation Method for removing rotatable blades without removing the casting of a turbine
DE3211073A1 (en) * 1982-03-25 1983-10-06 Kraftwerk Union Ag DEVICE FOR VIBRATION DAMPING ON A LEAD Vane

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB307832A (en) * 1928-03-14 1929-10-24 Ljungstroms Angturbin Ab Blade ring for radial steam- or gas-turbines and method of manufacturing the same
GB671960A (en) * 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
US2651494A (en) * 1949-11-24 1953-09-08 Svenska Flygmotor Aktiebolaget Turbine disk

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
GB704882A (en) * 1951-03-08 1954-03-03 W H Allen Sons & Company Ltd Improvements in and relating to the securing of blading to turbine wheels and other high speed rotary members

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB307832A (en) * 1928-03-14 1929-10-24 Ljungstroms Angturbin Ab Blade ring for radial steam- or gas-turbines and method of manufacturing the same
GB671960A (en) * 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
US2651494A (en) * 1949-11-24 1953-09-08 Svenska Flygmotor Aktiebolaget Turbine disk

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000614A (en) * 1958-06-11 1961-09-19 Gen Motors Corp Rotor blade locks
US3001760A (en) * 1959-08-07 1961-09-26 Gen Motors Corp Turbine blade lock
US3198485A (en) * 1963-09-26 1965-08-03 Gen Motors Corp Turbine blade lock
US3867069A (en) * 1973-05-04 1975-02-18 Westinghouse Electric Corp Alternate root turbine blading
US3930751A (en) * 1974-07-05 1976-01-06 Carrier Corporation Bucket locking mechanism
US3904317A (en) * 1974-11-27 1975-09-09 Gen Electric Bucket locking mechanism
DE2516061A1 (en) * 1974-11-27 1976-08-12 Gen Electric SHOVEL LOCKING MECHANISM
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
US4120607A (en) * 1976-03-26 1978-10-17 Rolls-Royce Limited Rotor blade for a gas turbine engine
US4676723A (en) * 1986-03-26 1987-06-30 Westinghouse Electric Corp. Locking system for a turbine side entry blade
US4767247A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for preventing relative blade motion in steam turbine
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
EP0374387A1 (en) * 1988-10-24 1990-06-27 Westinghouse Electric Corporation Locking of side-entry blades
US4895490A (en) * 1988-11-28 1990-01-23 The United States Of America As Represented By The Secretary Of The Air Force Internal blade retention system for rotary engines
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
US8485785B2 (en) 2007-07-19 2013-07-16 Siemens Energy, Inc. Wear prevention spring for turbine blade
US8277186B2 (en) * 2008-05-26 2012-10-02 Kabushiki Kaisha Toshiba Turbine blade assembly and steam turbine
US20090290983A1 (en) * 2008-05-26 2009-11-26 Kabushiki Kaisha Toshiba Turbine blade assembly and steam turbine
JP2010185367A (en) * 2009-02-12 2010-08-26 Mitsubishi Heavy Industries Compressor Corp Fixing structure of turbine blade and turbine
US20110229328A1 (en) * 2010-03-17 2011-09-22 Sudhir Rajagopalan Turbomachine Blade Locking Structure Including Shape Memory Alloy
US8496439B2 (en) 2010-03-17 2013-07-30 Siemens Energy, Inc. Turbomachine blade locking structure including shape memory alloy
US20130052024A1 (en) * 2011-08-24 2013-02-28 General Electric Company Turbine Nozzle Vane Retention System
US20170037736A1 (en) * 2014-04-29 2017-02-09 Siemens Aktiengesellschaft Wheel disk assembly and method for assembling a wheel disk assembly
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

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DE951871C (en) 1956-11-08
CH324304A (en) 1957-09-15
GB725461A (en) 1955-03-02

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