US3746468A - Device for attaching turbine blades to a rotor - Google Patents

Device for attaching turbine blades to a rotor Download PDF

Info

Publication number
US3746468A
US3746468A US00186611A US3746468DA US3746468A US 3746468 A US3746468 A US 3746468A US 00186611 A US00186611 A US 00186611A US 3746468D A US3746468D A US 3746468DA US 3746468 A US3746468 A US 3746468A
Authority
US
United States
Prior art keywords
rotor
blades
grooves
pins
fluid machine
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
US00186611A
Other languages
English (en)
Inventor
P Saunders
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.)
CBS Corp
Original Assignee
Westinghouse Electric 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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Application granted granted Critical
Publication of US3746468A publication Critical patent/US3746468A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • ABSTRACT An annular array of circumferentially spaced rotatable turbine blades is securely fastened to a rotor by a plurality of pins having an hourglass shaped cross section; the pins fit into a plurality of axially disposed, registering grooves in the blades and rotor and provide multiple blade roots and reduce the probability of a blade flying off the rotor as fatigue cracks must initiate and propagate through a plurality of the roots to have such a failure.
  • an elastic fluid machine having a rotor and an annular array of circumferentially spaced blades disposed on said rotor, when made in accordance with this invention, comprises a plurality of pins disposed axially with respect to said rotor and having a cross section shaped to securely fasten the blades to the rotor.
  • FIG. I is a partial perspective view of an annular array of circumferentially spaced, rotatable blades fastened to a rotor in accordance with the teachings of this invention
  • FIG. 2 is a partial perspective view similar to FIG. 1 showing a modification
  • FIG. 3 is a partial perspective view similar to FIG. 1 showing another embodiment of this invention.
  • FIG. 4 is a partial perspective view similar to FIG. 1 showing a different embodiment
  • FIG. 5 is a partial sectional view taken on line V-V of FIG. 4.
  • FIG. 1 shows a portion of an annular array of circumferentially spaced rotatable blades I disposed on a rotor 3 of a steam turbine or other elastic fluid machine.
  • the blades I have a base portion 5, which forms segments of a ring which tightly encircles the rotor 3.
  • the base portions 5 have a plurality of axially extending grooves 7, which register with axially extending grooves 9 in the rotor.
  • the grooves 7 and 9 widen as they extend radially into the blades and rotor, and are properly shaped to receive a plurality of pins 11 having a cross section in the shape of an hourglass or a pair of radially disposed symmetrical lobes.
  • the grooves 7 and 9 and pins 11 are generally rounded and have no abrupt changes in direction so that as the mating surfaces thereof engage there are no stress concentrations normally associated with rapid changes in direction of a stressed member.
  • the rounded grooves also advantageously provide a plurality of terminating surfaces for fatigue cracks, which may develop in the base portion of the blade or in the rotor.
  • each base portion or in the rotor allows a fatigue crack to develop and progress across a segment of the base portion of the blade or the rotor without the blade flying off the rotor as the grooves 7 and 9 act as holes drilled at the end of the crack to stop its progress through the remainder of the structure.
  • a plurality of short pins II can be utilized to provide even greater protection against a blade flying off the rotor; since each short pin 11 is distinct, a fatigue crack initiated in one pin will not progress to adjacent pins and several pins must develop fatigue cracks and fail before a blade will fly off the rotor.
  • FIG. 3 shows an arrangement, wherein the base portions 5 of the blades 1 have abutting sides 13, which cooperate to form a groove 7, which registers with the groove 9 in the rotor to receive the pins 11.
  • the grooves 7 along the edges I3 of the base portion 5 are inexpensive to manufacture and. provide additional flexibility to the overall turbine design by allowing the same number of grooves in the rotor to be utilized with a different number of blades.
  • abutting surfaces 13' of the base portion 5' are arcuate shaped and generally conform to the shape of the cupped blade and thus extend over a greater number of pins 11 providing a more uniform distribution of stresses by supporting the blade from its leading to its trailing edge.
  • the fastening arrangements hereinbefore described advantageously supply a root portion with a large moment of inertia and section modulus to support vibration stresses; provide a stiff base increasing the speed at which the blade becomes resident; allow the grooves to be a standard size, reducing the machine cost; and permit the use of high strength material for forming the pins II.
  • Utilizing high strength pins 11 reduces the size of the grooves and the amount of material, which must be machined away to form the grooves. Providing a plurality of pins maintains a high section modulus.
  • An elastic fluid machine comprising a rotor havng an outer peripheral surface, an annular array of blades having an arcuate-shaped root portion, the inner surface of which forms a ring tightly encircling said outer peripheral surface of said rotor, at least one axially disposed groove in each of said root portions of said blades, said rotor having a plurality of axially disposed grooves which register with the grooves in the root portions of said blades and are generally symmetrical thereto, said grooves widening as they extend radially into said blade root portions and into said rotor, and a plurality of pins having a cross section which fits securely into said grooves to fasten said blades to said rotor.
  • An elastic fluid machine as set forth in claim 2 pair of registering grooves. wherein the arcuate abutting surfaces are such that 5.
  • An elastic fluid machine asset forth in claim 2 each pin engages the root portion of two blades. wherein there are a plurality of pins disposed in each 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00186611A 1971-10-05 1971-10-05 Device for attaching turbine blades to a rotor Expired - Lifetime US3746468A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US18661171A 1971-10-05 1971-10-05

Publications (1)

Publication Number Publication Date
US3746468A true US3746468A (en) 1973-07-17

Family

ID=22685609

Family Applications (1)

Application Number Title Priority Date Filing Date
US00186611A Expired - Lifetime US3746468A (en) 1971-10-05 1971-10-05 Device for attaching turbine blades to a rotor

Country Status (6)

Country Link
US (1) US3746468A (it)
JP (1) JPS538004B2 (it)
DE (1) DE2247970A1 (it)
GB (1) GB1339100A (it)
IT (1) IT968595B (it)
SE (1) SE382341B (it)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4904160A (en) * 1989-04-03 1990-02-27 Westinghouse Electric Corp. Mounting of integral platform turbine blades with skewed side entry roots
US5129786A (en) * 1990-11-08 1992-07-14 United Technologies Corporation Variable pitch pan blade retention arrangement
WO2001057365A1 (en) * 1998-09-14 2001-08-09 General Electric Company Means for securing a bucket to a turbine wheel and methods of installation
WO2007031408A1 (de) * 2005-09-15 2007-03-22 Alstom Technology Ltd Deckband mit lösbarer verankerung für eine schaufelreihe einer strömungsmaschine
WO2007031383A1 (de) * 2005-09-15 2007-03-22 Alstom Technology Ltd Schaufel einer strömungsmaschine mit lösbarer verankerung für separate deckplatte
KR100785544B1 (ko) * 2000-02-03 2007-12-12 제너럴 일렉트릭 캄파니 터빈 및 버킷 설치 방법
FR2990462A1 (fr) * 2012-05-14 2013-11-15 Snecma Dispositif d'attache d'aubes sur un disque de rotor de turbomachine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2139295A (en) * 1983-05-05 1984-11-07 Tuomo Kaivola Thermal joint e.g. for a turbine
US4767274A (en) * 1986-12-29 1988-08-30 United Technologies Corporation Multiple lug blade to disk attachment
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1423466A (en) * 1920-10-02 1922-07-18 Westinghouse Electric & Mfg Co Interlocking blade shroud
US1831104A (en) * 1927-10-15 1931-11-10 Ljungstroms Angturbin Ab Blade ring for radial flow elastic fluid turbines
US2430185A (en) * 1946-07-25 1947-11-04 Continental Aviat & Engineerin Turbine rotor
GB798613A (en) * 1955-05-06 1958-07-23 Ite Circuit Breaker Ltd Improvements in or relating to the securing of an element such as turbine blade to abody such as a rotor
US2873947A (en) * 1953-11-26 1959-02-17 Power Jets Res & Dev Ltd Blade mounting for compressors, turbines and like fluid flow machines
US3313519A (en) * 1965-06-22 1967-04-11 Ass Elect Ind Turbine rotors

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1423466A (en) * 1920-10-02 1922-07-18 Westinghouse Electric & Mfg Co Interlocking blade shroud
US1831104A (en) * 1927-10-15 1931-11-10 Ljungstroms Angturbin Ab Blade ring for radial flow elastic fluid turbines
US2430185A (en) * 1946-07-25 1947-11-04 Continental Aviat & Engineerin Turbine rotor
US2873947A (en) * 1953-11-26 1959-02-17 Power Jets Res & Dev Ltd Blade mounting for compressors, turbines and like fluid flow machines
GB798613A (en) * 1955-05-06 1958-07-23 Ite Circuit Breaker Ltd Improvements in or relating to the securing of an element such as turbine blade to abody such as a rotor
US3313519A (en) * 1965-06-22 1967-04-11 Ass Elect Ind Turbine rotors

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4904160A (en) * 1989-04-03 1990-02-27 Westinghouse Electric Corp. Mounting of integral platform turbine blades with skewed side entry roots
US5129786A (en) * 1990-11-08 1992-07-14 United Technologies Corporation Variable pitch pan blade retention arrangement
WO2001057365A1 (en) * 1998-09-14 2001-08-09 General Electric Company Means for securing a bucket to a turbine wheel and methods of installation
KR100785544B1 (ko) * 2000-02-03 2007-12-12 제너럴 일렉트릭 캄파니 터빈 및 버킷 설치 방법
WO2007031408A1 (de) * 2005-09-15 2007-03-22 Alstom Technology Ltd Deckband mit lösbarer verankerung für eine schaufelreihe einer strömungsmaschine
WO2007031383A1 (de) * 2005-09-15 2007-03-22 Alstom Technology Ltd Schaufel einer strömungsmaschine mit lösbarer verankerung für separate deckplatte
FR2990462A1 (fr) * 2012-05-14 2013-11-15 Snecma Dispositif d'attache d'aubes sur un disque de rotor de turbomachine
US9518470B2 (en) 2012-05-14 2016-12-13 Snecma Device for attaching blades to a turbine engine rotor disk

Also Published As

Publication number Publication date
SE382341B (sv) 1976-01-26
GB1339100A (en) 1973-11-28
IT968595B (it) 1974-03-20
JPS4844606A (it) 1973-06-27
JPS538004B2 (it) 1978-03-24
DE2247970A1 (de) 1973-04-12

Similar Documents

Publication Publication Date Title
US4130379A (en) Multiple side entry root for multiple blade group
US3746468A (en) Device for attaching turbine blades to a rotor
US3326523A (en) Stator vane assembly having composite sectors
US3752599A (en) Bucket vibration damping device
US3377050A (en) Shrouded rotor blades
US3014695A (en) Turbine bucket retaining means
US2714499A (en) Blading for turbomachines
KR820000756B1 (ko) 로우터블레이드
US2391623A (en) Bladed rotor
US5474421A (en) Turbomachine rotor
US3554668A (en) Turbomachine rotor
JPS5813759B2 (ja) ガスタ−ビンエンジンのロ−タ−段
US3756745A (en) Composite blade root configuration
JPH03182603A (ja) タービンロータディスクへのガスタービンエンジンブレードの改良型アタッチメント
RU2433275C2 (ru) Весовой балансир, диск ротора с весовым балансиром, ротор и двигатель летательного аппарата, содержащие указанный диск
US3588278A (en) Blade structure for an axial flow elastic fluid utilizing machine
US2510734A (en) Turbine or compressor rotor
US4602412A (en) Method for assembling in a circular array turbine blades each with an integral shroud
US5540551A (en) Method and apparatus for reducing vibration in a turbo-machine blade
US6174129B1 (en) Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism
EP0633976A1 (en) Mounting of axial turbo-machinery
US20220034229A1 (en) Bladed rotor system and corresponding method of servicing
US3758232A (en) Blade assembly for gas turbine engines
US3728044A (en) Turbine rotor
JP6554482B2 (ja) タービンエンジンロータ用の回転対称部品、ならびに関連するタービンエンジンロータ、タービンエンジンモジュール、およびタービンエンジン