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GB670665A - Improvements in or relating to compressors and turbines - Google Patents

Improvements in or relating to compressors and turbines

Info

Publication number
GB670665A
GB670665A GB1991349A GB1991349A GB670665A GB 670665 A GB670665 A GB 670665A GB 1991349 A GB1991349 A GB 1991349A GB 1991349 A GB1991349 A GB 1991349A GB 670665 A GB670665 A GB 670665A
Authority
GB
United Kingdom
Prior art keywords
platforms
blades
july
engagement
platform
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
Application number
GB1991349A
Inventor
Denis Arthur Drew
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB1991349A priority Critical patent/GB670665A/en
Publication of GB670665A publication Critical patent/GB670665A/en
Expired legal-status Critical Current

Links

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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Landscapes

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

Abstract

670,665. Axial-flow compressors and turbines. ROLLS-ROYCE, Ltd., July 12, 1950. [July 28, 1949] No. 19913/49. Classes 110(i) and 110(iii). Each rotor blade 10 has, towards its root end, a platform 10b which forms, together with the platforms of the other blades, a substantially continuous annular wall, relative vibration between the platforms being frictionally damped by metal pads 14, each of which is pressed by centrifugal force against adjacent platforms. Each pad 14 is retained axially by the engagement of a flange 14a between the associated platforms 10b and an interstage spacer ring 12, and retained radially by engagement with an annular shoulder 15, but with sufficient freedom of movement to allow it to bear against the platforms under the action of centrifugal force. To permit relative movement, adjacent platforms 10b are slightly spaced apart, and each platform is joined to a fir-tree root 10c by a flexible stem 10d. If, however, the blades are pivotally attached to the rotor disc 11, as by means of a pin, the flexible stems may be shortened or eliminated. To prevent adjacent blades from vibrating in unison their flexible stems may be of differing crosssection. According to the Provisional Specification, platforms may be provided at the blade tips or between the tips and the roots, in which case the pads 14 can be formed with retaining tags which are bent over to engage the radially outer side.
GB1991349A 1949-07-28 1949-07-28 Improvements in or relating to compressors and turbines Expired GB670665A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1991349A GB670665A (en) 1949-07-28 1949-07-28 Improvements in or relating to compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1991349A GB670665A (en) 1949-07-28 1949-07-28 Improvements in or relating to compressors and turbines

Publications (1)

Publication Number Publication Date
GB670665A true GB670665A (en) 1952-04-23

Family

ID=10137229

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1991349A Expired GB670665A (en) 1949-07-28 1949-07-28 Improvements in or relating to compressors and turbines

Country Status (1)

Country Link
GB (1) GB670665A (en)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2912222A (en) * 1952-08-02 1959-11-10 Gen Electric Turbomachine blading and method of manufacture thereof
US2916257A (en) * 1953-12-30 1959-12-08 Gen Electric Damping turbine buckets
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor
US2957675A (en) * 1956-05-07 1960-10-25 Gen Electric Damping means
US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US2997274A (en) * 1953-04-13 1961-08-22 Morgan P Hanson Turbo-machine blade vibration damper
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
US3047268A (en) * 1960-03-14 1962-07-31 Stanley L Leavitt Blade retention device
US3396905A (en) * 1966-09-28 1968-08-13 Gen Motors Corp Ducted fan
FR2376958A1 (en) * 1977-01-11 1978-08-04 Rolls Royce MOBILE COMPRESSOR STAGE
FR2527260A1 (en) * 1982-05-18 1983-11-25 Snecma RETRACTABLE DAMPING DEVICE FOR AUBES OF A TURBOMACHINE
US4455122A (en) * 1981-12-14 1984-06-19 United Technologies Corporation Blade to blade vibration damper
US4723889A (en) * 1985-07-16 1988-02-09 Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." Fan or compressor angular clearance limiting device
EP0297120A1 (en) * 1986-12-29 1989-01-04 United Technologies Corp Interblade seal for turbomachine rotor.
GB2227192A (en) * 1988-12-29 1990-07-25 Gen Electric Damped gas turbine engine airfoil row
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
WO1994012773A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade damper
EP2418356A1 (en) * 2010-08-10 2012-02-15 Siemens Aktiengesellschaft Turbine inter-platform damper and corresponding turbine blade
US10196896B2 (en) 2015-04-13 2019-02-05 Rolls-Royce Plc Rotor damper
FR3075284A1 (en) * 2017-12-18 2019-06-21 Safran Aircraft Engines SHOCK ABSORBER DEVICE
US11536157B2 (en) 2017-12-18 2022-12-27 Safran Aircraft Engines Damping device

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2912222A (en) * 1952-08-02 1959-11-10 Gen Electric Turbomachine blading and method of manufacture thereof
US2997274A (en) * 1953-04-13 1961-08-22 Morgan P Hanson Turbo-machine blade vibration damper
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2916257A (en) * 1953-12-30 1959-12-08 Gen Electric Damping turbine buckets
US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US2957675A (en) * 1956-05-07 1960-10-25 Gen Electric Damping means
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
US3047268A (en) * 1960-03-14 1962-07-31 Stanley L Leavitt Blade retention device
US3396905A (en) * 1966-09-28 1968-08-13 Gen Motors Corp Ducted fan
FR2376958A1 (en) * 1977-01-11 1978-08-04 Rolls Royce MOBILE COMPRESSOR STAGE
US4455122A (en) * 1981-12-14 1984-06-19 United Technologies Corporation Blade to blade vibration damper
US4516910A (en) * 1982-05-18 1985-05-14 S.N.E.C.M.A. Retractable damping device for blades of a turbojet
EP0095409A1 (en) * 1982-05-18 1983-11-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping device for the vanes in the rotor of a turbo machine
FR2527260A1 (en) * 1982-05-18 1983-11-25 Snecma RETRACTABLE DAMPING DEVICE FOR AUBES OF A TURBOMACHINE
US4723889A (en) * 1985-07-16 1988-02-09 Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." Fan or compressor angular clearance limiting device
EP0297120A1 (en) * 1986-12-29 1989-01-04 United Technologies Corp Interblade seal for turbomachine rotor.
EP0297120A4 (en) * 1986-12-29 1990-09-05 United Technologies Corporation Interblade seal for turbomachine rotor
GB2227192A (en) * 1988-12-29 1990-07-25 Gen Electric Damped gas turbine engine airfoil row
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
WO1994012773A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade damper
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
EP2418356A1 (en) * 2010-08-10 2012-02-15 Siemens Aktiengesellschaft Turbine inter-platform damper and corresponding turbine blade
US10196896B2 (en) 2015-04-13 2019-02-05 Rolls-Royce Plc Rotor damper
US10385696B2 (en) 2015-04-13 2019-08-20 Rolls-Royce Plc Rotor damper
FR3075284A1 (en) * 2017-12-18 2019-06-21 Safran Aircraft Engines SHOCK ABSORBER DEVICE
US11421534B2 (en) 2017-12-18 2022-08-23 Safran Aircraft Engines Damping device
US11536157B2 (en) 2017-12-18 2022-12-27 Safran Aircraft Engines Damping device

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