US2430185A - Turbine rotor - Google Patents

Turbine rotor Download PDF

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Publication number
US2430185A
US2430185A US686240A US68624046A US2430185A US 2430185 A US2430185 A US 2430185A US 686240 A US686240 A US 686240A US 68624046 A US68624046 A US 68624046A US 2430185 A US2430185 A US 2430185A
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United States
Prior art keywords
rotor
turbine rotor
turbine
haft
hole
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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
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US686240A
Inventor
Ford L Prescott
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Continental Aviation and Engineering Corp
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Continental Aviation and Engineering Corp
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Publication date
Application filed by Continental Aviation and Engineering Corp filed Critical Continental Aviation and Engineering Corp
Priority to US686240A priority Critical patent/US2430185A/en
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Publication of US2430185A publication Critical patent/US2430185A/en
Anticipated expiration legal-status Critical
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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/70—Interfitted members
    • Y10T403/7075—Interfitted members including discrete retainer

Definitions

  • This invention relates to turbine blades and to methods of manufacturing turbines, particularly to the method of securing turbine buckets to a rotor.
  • the velocity of rotation of turbine rotors is so high that blade tip velocities often reach the speed of sound.
  • the centrifugal forces set up by such high rotational velocities present rather diificult designproblems, one of which is an effective and economical method for securing the turbine buckets or blades to the rotor.
  • the joint proposed by this invention is one that is easily and economically manufactured, and yet distributes the stresses so as to provide great strength.
  • Fig. 1 is an end elevation view of a portion of method of mounting
  • Fig. 2 is a developed plan view of the periphery of the rotor.
  • FIG. 1 shows a portion of a turbine rotor 2 on which are mountedblades 4 according to the invention.
  • the invention is efl'ected by machining a plurality of V-slots 6 in the periphery of the rotor such that the slots diverge outwardly toward the periphery.
  • Each blade 4 is provided with a haft 8 which is formed to fit into slot 6.
  • a number of holes Ill At the surface of contact between haft 8 and rotor 2, there are drilled a number of holes Ill.
  • the axis of each hole will preferably lie substantially'in the contact surface so that approximately half of each hole will be in the haft and half will be in the rotor itself.
  • the holes may be formed with blade 4 and haft 8 held in place, or they may be formed before assembly. Wire pins or keys I! are then driven tightly into the holes to hold the haft securely in the V-notch.
  • each haft and the support having a plurality of holes drilled in the contact surfaces such that approximately half of a hole is in the support and the other half in the haft, and a wire tightly driven into each hole to key the blades to the support, the wirebeing held in place solely by the friction of the driving fit.
  • the turbine rotor showing the blade and its FORD L. PRESCOTT.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Nov. 4, 1947. I PRESCOTT 2,430,185
TURBINE ROTOR Filed July 25, 1946 ATTORNEY! Patented Nov. 4, 1947 UNETED STATES PATENT OFFlCE TURBINE ROTOR I Ford L. Prescott, Gainesville, Fla., assignor to Continental Aviation & Engineering Corporation, Detroit, Mich., a corporation of Virginia Application July 25, 1946, Serial No. 686,240
1 Claim. 1
This invention relates to turbine blades and to methods of manufacturing turbines, particularly to the method of securing turbine buckets to a rotor.
The velocity of rotation of turbine rotors is so high that blade tip velocities often reach the speed of sound. The centrifugal forces set up by such high rotational velocities present rather diificult designproblems, one of which is an effective and economical method for securing the turbine buckets or blades to the rotor.
It is the object of this invention to provide a strong and economical joint for securing turbine blades, or buckets, as theyare often called, to the rotor. The joint proposed by this invention is one that is easily and economically manufactured, and yet distributes the stresses so as to provide great strength.
In the drawings:
Fig. 1 is an end elevation view of a portion of method of mounting, and
Fig. 2 is a developed plan view of the periphery of the rotor.
The drawings show a portion of a turbine rotor 2 on which are mountedblades 4 according to the invention.
The invention is efl'ected by machining a plurality of V-slots 6 in the periphery of the rotor such that the slots diverge outwardly toward the periphery. Each blade 4 is provided with a haft 8 which is formed to fit into slot 6. At the surface of contact between haft 8 and rotor 2, there are drilled a number of holes Ill. The axis of each hole will preferably lie substantially'in the contact surface so that approximately half of each hole will be in the haft and half will be in the rotor itself. The holes may be formed with blade 4 and haft 8 held in place, or they may be formed before assembly. Wire pins or keys I! are then driven tightly into the holes to hold the haft securely in the V-notch.
notches, each haft and the support having a plurality of holes drilled in the contact surfaces such that approximately half of a hole is in the support and the other half in the haft, and a wire tightly driven into each hole to key the blades to the support, the wirebeing held in place solely by the friction of the driving fit. the turbine rotor showing the blade and its FORD L. PRESCOTT.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS
US686240A 1946-07-25 1946-07-25 Turbine rotor Expired - Lifetime US2430185A (en)

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US686240A US2430185A (en) 1946-07-25 1946-07-25 Turbine rotor

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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2743080A (en) * 1949-04-29 1956-04-24 Ruston & Hornsby Ltd Turbine rotors
US2953348A (en) * 1952-12-30 1960-09-20 Gen Motors Corp Blade fastenings
US3014695A (en) * 1960-02-03 1961-12-26 Gen Electric Turbine bucket retaining means
US3282561A (en) * 1964-12-14 1966-11-01 Associated Electric Ind Ltd Turbine rotors
US3746468A (en) * 1971-10-05 1973-07-17 Westinghouse Electric Corp Device for attaching turbine blades to a rotor
US4334827A (en) * 1979-04-04 1982-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for attaching blades to a compressor rotor for a turbojet
US5129786A (en) * 1990-11-08 1992-07-14 United Technologies Corporation Variable pitch pan blade retention arrangement
US5368444A (en) * 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US5372481A (en) * 1993-11-29 1994-12-13 Solar Turbine Incorporated Ceramic blade attachment system
DE10346263A1 (en) * 2003-10-06 2005-04-28 Alstom Technology Ltd Baden Turbine blade root fastening has form-locking component constructed as separate component with regard to blade root and blade carrier and engages simultaneously in longitudinal slots in first and second anchoring contours
US7661931B1 (en) 2007-02-20 2010-02-16 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US20100068063A1 (en) * 2007-05-31 2010-03-18 Richard Hiram Berg Methods and apparatus for assembling gas turbine engines
US7686571B1 (en) 2007-04-09 2010-03-30 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US7704044B1 (en) 2006-11-28 2010-04-27 Florida Turbine Technologies, Inc. Turbine blade with attachment shear inserts
US20180135414A1 (en) * 2015-08-21 2018-05-17 Mitsubishi Heavy Industries Compressor Corporation Steam turbine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102397C (en) *
US726624A (en) * 1902-09-02 1903-04-28 Mark Bodley Tappet for use in stamp-batteries or the like.
US845901A (en) * 1906-01-26 1907-03-05 Richard Schulz Fastening of blades in turbines.
US961328A (en) * 1910-03-17 1910-06-14 Henry H Wait Turbine-blade.
US965131A (en) * 1908-02-29 1910-07-19 Donald M Bliss Shaft-coupling.
US1347031A (en) * 1917-01-31 1920-07-20 British Westinghouse Electric Attachment of moving blades of elastic-fluid turbines
US1719415A (en) * 1927-09-14 1929-07-02 Westinghouse Electric & Mfg Co Turbine-blade attachment
US1793468A (en) * 1929-05-28 1931-02-24 Westinghouse Electric & Mfg Co Turbine blade

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102397C (en) *
US726624A (en) * 1902-09-02 1903-04-28 Mark Bodley Tappet for use in stamp-batteries or the like.
US845901A (en) * 1906-01-26 1907-03-05 Richard Schulz Fastening of blades in turbines.
US965131A (en) * 1908-02-29 1910-07-19 Donald M Bliss Shaft-coupling.
US961328A (en) * 1910-03-17 1910-06-14 Henry H Wait Turbine-blade.
US1347031A (en) * 1917-01-31 1920-07-20 British Westinghouse Electric Attachment of moving blades of elastic-fluid turbines
US1719415A (en) * 1927-09-14 1929-07-02 Westinghouse Electric & Mfg Co Turbine-blade attachment
US1793468A (en) * 1929-05-28 1931-02-24 Westinghouse Electric & Mfg Co Turbine blade

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2743080A (en) * 1949-04-29 1956-04-24 Ruston & Hornsby Ltd Turbine rotors
US2953348A (en) * 1952-12-30 1960-09-20 Gen Motors Corp Blade fastenings
US3014695A (en) * 1960-02-03 1961-12-26 Gen Electric Turbine bucket retaining means
US3282561A (en) * 1964-12-14 1966-11-01 Associated Electric Ind Ltd Turbine rotors
US3746468A (en) * 1971-10-05 1973-07-17 Westinghouse Electric Corp Device for attaching turbine blades to a rotor
US4334827A (en) * 1979-04-04 1982-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for attaching blades to a compressor rotor for a turbojet
US5129786A (en) * 1990-11-08 1992-07-14 United Technologies Corporation Variable pitch pan blade retention arrangement
US5368444A (en) * 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US5372481A (en) * 1993-11-29 1994-12-13 Solar Turbine Incorporated Ceramic blade attachment system
DE10346263A1 (en) * 2003-10-06 2005-04-28 Alstom Technology Ltd Baden Turbine blade root fastening has form-locking component constructed as separate component with regard to blade root and blade carrier and engages simultaneously in longitudinal slots in first and second anchoring contours
US7704044B1 (en) 2006-11-28 2010-04-27 Florida Turbine Technologies, Inc. Turbine blade with attachment shear inserts
US7661931B1 (en) 2007-02-20 2010-02-16 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US7686571B1 (en) 2007-04-09 2010-03-30 Florida Turbine Technologies, Inc. Bladed rotor with shear pin attachment
US20100068063A1 (en) * 2007-05-31 2010-03-18 Richard Hiram Berg Methods and apparatus for assembling gas turbine engines
US8016565B2 (en) * 2007-05-31 2011-09-13 General Electric Company Methods and apparatus for assembling gas turbine engines
US20180135414A1 (en) * 2015-08-21 2018-05-17 Mitsubishi Heavy Industries Compressor Corporation Steam turbine
US10550697B2 (en) * 2015-08-21 2020-02-04 Mitsubishi Heavy Industries Compressor Corporation Steam turbine

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