US3198485A - Turbine blade lock - Google Patents

Turbine blade lock Download PDF

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Publication number
US3198485A
US3198485A US311865A US31186563A US3198485A US 3198485 A US3198485 A US 3198485A US 311865 A US311865 A US 311865A US 31186563 A US31186563 A US 31186563A US 3198485 A US3198485 A US 3198485A
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United States
Prior art keywords
blade
wheel
key
slots
serrations
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Expired - Lifetime
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US311865A
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Melenchuk Samuel
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Motors Liquidation Co
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Motors Liquidation Co
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Publication date
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Priority to US311865A priority Critical patent/US3198485A/en
Priority to GB38511/64A priority patent/GB1011713A/en
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Publication of US3198485A publication Critical patent/US3198485A/en
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Expired - Lifetime legal-status Critical Current

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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

  • My invention relates to rotors of turbines and analogous machines, and particularly to improved means for locking aerodynamic blades in the slots in which they are mounted in the rotor of a turbomachine.
  • compressors and turbines are of the structural type in which the wheel has blade slots extending transversely of the rim of the wheel, or generally parallel to r the axis of the wheel, and in which these slots are serrated and the blades have roots which are serrated complementarily to the wheel serrations.
  • the blades are mounted on the wheel by sliding the blade roots into the slots of the wheel.
  • the assembly is completed by some device which holds the blades against sliding in the slots.
  • Many structures for this purpose have been proposed. The one which I have devised is characterized by simplicity, ease of installation, very light weight, and a minimum of interference with the structural strength of the turbine rotor.
  • FIGURE 1 is a partial sectional view of a turbine or compressor rotor wheel taken in a plane transverse to the axis of the wheel.
  • FIGURE 2 is a plan View of FIGURE 1 with parts cut away, taken on the plane indicated by the line 22 in FIGURE 1.
  • FIGURE 3 is an axonometric view of a turbine blade lock.
  • FIGURES 1 and 2 show a portion of a rotor structure which, apart from the blade lock structure of my invention, may be regarded as known or conventional.
  • the Wheel 4 has at its rim or periphery 5 a ring of blade slots 6 formed with multiple dovetails or serrations or, in other words, what is commonly known as a fir-tree blade slot. These slots, as seen most clearly in FIGURE 2, extend across the rim of the wheel.
  • a turbine blade 8 is mounted in each slot. Two such blades are illustrated.
  • Each blade 8 comprises an airfoil portion 9, a platform 11, and a root 12.
  • the root is multiply serrated so that it is complementary to the serrations in the wheel.
  • the platforms overlie the outer surface of the. rotor and are approximately in contact so that the outer surface of the platforms defines a more or less smooth boundary for the flow path through the turbine.
  • the rim of the rotor bears a notch 14 which cuts into the upper portions of each of the projections 16 of the rotor between the blade slots 6.
  • the margin of the platform of each blade overlies approximately half of the upper part of projection 16 and notch 14.
  • a kerf 18 extends radially through one edge of the platform 11 and a small part of the outer portion of the root 12. The kerf 18 of each blade aligns with the notch 14 when the blade is in position on the rotor.
  • the key 20 comprises a stem 22 which is radially dispoesd, lying'within the kerf 18, and a lug 24 extending laterally from the inner end of the key.
  • the lug 24 has two projections or serrations 26 and 28 which are of the same outline as the serrations of the blade slots so as to mate with and lie under the two outermost serrations of the blade root 12. It will be noted that the key is extremely simple and of light weight, and that the slot and kerf which receive it are in positions of low stress in the wheel and blade, respectively.
  • the key is positively retained by one blade root and positively interlocks the next blade root with the rim of the rotor so that the blade cannot slide out of the slot.
  • the mode of assembly will be apparent to those skilled in the art, but may be stated briefly.
  • it is slid into its slot and the key 24) adjacent to it to the right (as shown in FIGURES 1 and 2) is dropped into place in the kerf in the blade root and the notch in the wheel.
  • the next blade is then slid into position in its slot and, as will be obvious, holds the key in position.
  • the key is inserted in each blade and the next blade is inserted to retain the key until the last blade is put in, which cannot be retained in this manner.
  • the final blade is retained by any other suitable means, the simplest and preferred being a radial pin. extending through a hole in the blade platform into the wheel rim between the blade root grooves, and secured in position by staking the metal of the blade platform (not illustrated). While the scale of the structure will vary with the size of turbine, it will be apparent that the key 20 is relatively small compared to the blades. In the particular installation shown on the patent drawings, the overall length of the key is only of an inch and its thickness about inch.
  • a bladed rotor wheel assembly for a turbine or the like comprising, in combination, a wheel having a rim with blade slots extending transversely of the rim, the rim portion bounding the slots having multiple serrations,
  • blades having roots with multiple serrations slidably insertable into the slots and having the blade root serrations interlock with the serrations on the wheel rim,
  • each blade having a portion radially outwardly of the rim overlying the blade root

Description

Aug. 3, 1965 s. MELENCHUK TURBINE BLADE LOCK Filed Sept. 26, 1963 INVENTOR. Jazrzzze/ fl/mcdw? dz%gdm United States Patent 3,198,485 TURBINE BLADE LOCK Samuel Melenchuk, Indianapolis, Ind., assignor to General Motors Corporation, Detroit, Mich, a corporation of Delaware Filed Sept. 26, 1963, Ser. No. 311,865 1 Claim. (Cl. 253-77) My invention relates to rotors of turbines and analogous machines, and particularly to improved means for locking aerodynamic blades in the slots in which they are mounted in the rotor of a turbomachine.
Many compressors and turbines are of the structural type in which the wheel has blade slots extending transversely of the rim of the wheel, or generally parallel to r the axis of the wheel, and in which these slots are serrated and the blades have roots which are serrated complementarily to the wheel serrations. In such a structure, the blades are mounted on the wheel by sliding the blade roots into the slots of the wheel. The assembly is completed by some device which holds the blades against sliding in the slots. Many structures for this purpose have been proposed. The one which I have devised is characterized by simplicity, ease of installation, very light weight, and a minimum of interference with the structural strength of the turbine rotor.
The nature of the invention and the advantages thereof will be clear to those skilled in the art from the succeeding detailed description of the preferred embodiment of the invention and the accompanying drawings thereof.
FIGURE 1 is a partial sectional view of a turbine or compressor rotor wheel taken in a plane transverse to the axis of the wheel.
FIGURE 2 is a plan View of FIGURE 1 with parts cut away, taken on the plane indicated by the line 22 in FIGURE 1.
FIGURE 3 is an axonometric view of a turbine blade lock.
FIGURES 1 and 2 show a portion of a rotor structure which, apart from the blade lock structure of my invention, may be regarded as known or conventional. The Wheel 4 has at its rim or periphery 5 a ring of blade slots 6 formed with multiple dovetails or serrations or, in other words, what is commonly known as a fir-tree blade slot. These slots, as seen most clearly in FIGURE 2, extend across the rim of the wheel. A turbine blade 8 is mounted in each slot. Two such blades are illustrated. Each blade 8 comprises an airfoil portion 9, a platform 11, and a root 12. The root is multiply serrated so that it is complementary to the serrations in the wheel. The platforms overlie the outer surface of the. rotor and are approximately in contact so that the outer surface of the platforms defines a more or less smooth boundary for the flow path through the turbine.
Proceeding now to the blade locking structure of my invention, it will be noted that the rim of the rotor bears a notch 14 which cuts into the upper portions of each of the projections 16 of the rotor between the blade slots 6. The margin of the platform of each blade overlies approximately half of the upper part of projection 16 and notch 14. A kerf 18 extends radially through one edge of the platform 11 and a small part of the outer portion of the root 12. The kerf 18 of each blade aligns with the notch 14 when the blade is in position on the rotor.
3,198,485 PatentedAug. 3, 1965 of suitable cross-section. The key 20 comprises a stem 22 which is radially dispoesd, lying'within the kerf 18, and a lug 24 extending laterally from the inner end of the key. The lug 24 has two projections or serrations 26 and 28 which are of the same outline as the serrations of the blade slots so as to mate with and lie under the two outermost serrations of the blade root 12. It will be noted that the key is extremely simple and of light weight, and that the slot and kerf which receive it are in positions of low stress in the wheel and blade, respectively. The key is positively retained by one blade root and positively interlocks the next blade root with the rim of the rotor so that the blade cannot slide out of the slot. The mode of assembly will be apparent to those skilled in the art, but may be stated briefly. Starting with any given blade 11, it is slid into its slot and the key 24) adjacent to it to the right (as shown in FIGURES 1 and 2) is dropped into place in the kerf in the blade root and the notch in the wheel. The next blade is then slid into position in its slot and, as will be obvious, holds the key in position. Continuing around the wheel, the key is inserted in each blade and the next blade is inserted to retain the key until the last blade is put in, which cannot be retained in this manner. The final blade is retained by any other suitable means, the simplest and preferred being a radial pin. extending through a hole in the blade platform into the wheel rim between the blade root grooves, and secured in position by staking the metal of the blade platform (not illustrated). While the scale of the structure will vary with the size of turbine, it will be apparent that the key 20 is relatively small compared to the blades. In the particular installation shown on the patent drawings, the overall length of the key is only of an inch and its thickness about inch.
The detailed description of the preferred embodiment of the invention for the purpose of explaining the principles thereof is not to be construed as limiting or restricting the invention, since many modifications may be made by the exercise of skill in the art within the scope of the invention.
I claim: l A bladed rotor wheel assembly for a turbine or the like comprising, in combination, a wheel having a rim with blade slots extending transversely of the rim, the rim portion bounding the slots having multiple serrations,
blades having roots with multiple serrations slidably insertable into the slots and having the blade root serrations interlock with the serrations on the wheel rim,
each blade having a portion radially outwardly of the rim overlying the blade root,
at kerf in said portion and in the radially outer portion of one lateral face of the blade root extending radially and circumferentially of the wheel,
a notch in the wheel extending circumferentially and intersecting two serrations of the rim portion bounding the blade slots,
3 4 the said kerfs being aligned with the notch when the References tilted by the Examiner 313C165 are installed, and UNITED STATES PATENTS a blade retalnlng key having a stem adapted to he in 2,867,408 1/59 Kolb et a1. 253 77 the said kerf and a lug extending from the stern into the said notch,
FOREIGN PATENTS the lug having two projections conforming to and ex- 671 960 5/52 Great Britain tending under two of the serrations of the root of 779059 7/57 Great Britain: the adjacent blade, 313,027 4/56 Switzerland.
so that the adjacent blade root holds the key in place 10 radially of the wheel and the key holds the fil'st- KARL ALBRECHT, Primary Ex mentioned blade in place axially of the Wheel. JOSEPH H. BRANSON, JR., Examiner.
US311865A 1963-09-26 1963-09-26 Turbine blade lock Expired - Lifetime US3198485A (en)

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US311865A US3198485A (en) 1963-09-26 1963-09-26 Turbine blade lock
GB38511/64A GB1011713A (en) 1963-09-26 1964-09-21 Bladed turbine or compressor rotors

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3575522A (en) * 1968-08-30 1971-04-20 Gen Motors Corp Turbine cooling
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
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
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
US6416286B1 (en) * 2000-12-28 2002-07-09 General Electric Company System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets
US6431836B2 (en) * 2000-03-14 2002-08-13 Man Turbomaschinen Ag Ghh Borsig Blade lock and process for manufacturing a blade lock
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US20130177429A1 (en) * 2012-01-05 2013-07-11 General Electric Company System for axial retention of rotating segments of a turbine
US9127563B2 (en) 2011-04-05 2015-09-08 General Electric Company Locking device arrangement for a rotating bladed stage

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB671960A (en) * 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
CH313027A (en) * 1953-07-28 1956-03-15 Tech Studien Ag Device for securing against axial displacement of blades and spacers of turbo machines
GB779059A (en) * 1954-07-15 1957-07-17 Rolls Royce Improvements in or relating to axial-flow fluid machines, for example compressors orturbines of gas-turbine engines
US2867408A (en) * 1953-04-10 1959-01-06 Parsons C A & Co Ltd Axial locking of rotor blades for turbines and the like

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB671960A (en) * 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
US2867408A (en) * 1953-04-10 1959-01-06 Parsons C A & Co Ltd Axial locking of rotor blades for turbines and the like
CH313027A (en) * 1953-07-28 1956-03-15 Tech Studien Ag Device for securing against axial displacement of blades and spacers of turbo machines
GB779059A (en) * 1954-07-15 1957-07-17 Rolls Royce Improvements in or relating to axial-flow fluid machines, for example compressors orturbines of gas-turbine engines

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3575522A (en) * 1968-08-30 1971-04-20 Gen Motors Corp Turbine cooling
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
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
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
CZ297759B6 (en) * 2000-03-14 2007-03-21 Man Turbo Ag Blade lock and process for producing thereof
US6431836B2 (en) * 2000-03-14 2002-08-13 Man Turbomaschinen Ag Ghh Borsig Blade lock and process for manufacturing a blade lock
US6416286B1 (en) * 2000-12-28 2002-07-09 General Electric Company System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets
US6929453B2 (en) 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US9127563B2 (en) 2011-04-05 2015-09-08 General Electric Company Locking device arrangement for a rotating bladed stage
US20130177429A1 (en) * 2012-01-05 2013-07-11 General Electric Company System for axial retention of rotating segments of a turbine
US9051845B2 (en) * 2012-01-05 2015-06-09 General Electric Company System for axial retention of rotating segments of a turbine

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