GB667979A - Improvements in or relating to axial flow compressors and turbines - Google Patents

Improvements in or relating to axial flow compressors and turbines

Info

Publication number
GB667979A
GB667979A GB1986548A GB1986548A GB667979A GB 667979 A GB667979 A GB 667979A GB 1986548 A GB1986548 A GB 1986548A GB 1986548 A GB1986548 A GB 1986548A GB 667979 A GB667979 A GB 667979A
Authority
GB
United Kingdom
Prior art keywords
blade
turbines
july
projection
flow compressors
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
GB1986548A
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 GB1986548A priority Critical patent/GB667979A/en
Publication of GB667979A publication Critical patent/GB667979A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials

Landscapes

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

Abstract

667,979. Axial-flow compressors and turbines. ROLLS-ROYCE, LTD. July 12,1950. [July 28, 1949] No. 19865/48. Classes 110(i) and 110(iii). Each rotor blade 11a is formed with a platform 11b having a radially inwardly facing pocket 15 into which extends a projection 16 on the periphery of the rotor disc or drum 10, the space between the projection and the pocket containing a damping element 17, as of rubber, to damp blade vibration. Each blade is pivotally attached at its root to three flanges 13 by a pin 14 and has an elongated flexible stem 11c. Adjacent platforms 11b are slightly spaced from one another. The projections 16 are formed on extensions 13a of the two outer flanges 13. If the pin mountings can be relied upon to provide sufficient pivotal freedom of the blades under working conditions, the stems 11c may be shortened or eliminated. The root fixing may be of the fir-tree type, or the blades may be integral with the rotor disc.
GB1986548A 1949-07-28 1949-07-28 Improvements in or relating to axial flow compressors and turbines Expired GB667979A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1986548A GB667979A (en) 1949-07-28 1949-07-28 Improvements in or relating to axial flow compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1986548A GB667979A (en) 1949-07-28 1949-07-28 Improvements in or relating to axial flow compressors and turbines

Publications (1)

Publication Number Publication Date
GB667979A true GB667979A (en) 1952-03-12

Family

ID=10136475

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1986548A Expired GB667979A (en) 1949-07-28 1949-07-28 Improvements in or relating to axial flow compressors and turbines

Country Status (1)

Country Link
GB (1) GB667979A (en)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2795393A (en) * 1952-07-10 1957-06-11 Havilland Engine Co Ltd Rotors of multi-stage axial flow compressors or turbines
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
US2914297A (en) * 1955-05-03 1959-11-24 Gen Electric Rotor construction
US2925997A (en) * 1953-05-27 1960-02-23 Rolls Royce Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means
US2928652A (en) * 1955-10-12 1960-03-15 Gen Electric Roll-pin support for turbomachine blades
US2944787A (en) * 1957-03-20 1960-07-12 United Aircraft Corp Compressor blade limit stops
US2956774A (en) * 1954-09-28 1960-10-18 Stalker Corp Vibration dampers for bladed wheels
US2969952A (en) * 1956-10-05 1961-01-31 Edward A Stalker Rotary fluid machines with damped blades
US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US3129921A (en) * 1962-07-06 1964-04-21 United Aircraft Corp Blade damping device
US4135849A (en) * 1977-01-21 1979-01-23 Westinghouse Electric Corp. Pinned root turbine blade providing maximum friction damping
US4460316A (en) * 1982-12-29 1984-07-17 Westinghouse Electric Corp. Blade group with pinned root
FR2544381A1 (en) * 1983-04-14 1984-10-19 Gen Electric ROTATING COMPONENT COMPRISING AUBES WITH MODIFIED TAVE D'ARONDE
US4494909A (en) * 1981-12-03 1985-01-22 S.N.E.C.M.A. Damping device for turbojet engine fan blades
US4541778A (en) * 1984-05-18 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Pin rooted blade biaxial air seal
EP0214875A1 (en) * 1985-07-16 1987-03-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping element limiting the angular deflection of turbo machine rotor vanes

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2795393A (en) * 1952-07-10 1957-06-11 Havilland Engine Co Ltd Rotors of multi-stage axial flow compressors or turbines
US2912222A (en) * 1952-08-02 1959-11-10 Gen Electric Turbomachine blading and method of manufacture thereof
US2925997A (en) * 1953-05-27 1960-02-23 Rolls Royce Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US2956774A (en) * 1954-09-28 1960-10-18 Stalker Corp Vibration dampers for bladed wheels
US2914297A (en) * 1955-05-03 1959-11-24 Gen Electric Rotor construction
US2928652A (en) * 1955-10-12 1960-03-15 Gen Electric Roll-pin support for turbomachine blades
US2969952A (en) * 1956-10-05 1961-01-31 Edward A Stalker Rotary fluid machines with damped blades
US2944787A (en) * 1957-03-20 1960-07-12 United Aircraft Corp Compressor blade limit stops
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US3129921A (en) * 1962-07-06 1964-04-21 United Aircraft Corp Blade damping device
US4135849A (en) * 1977-01-21 1979-01-23 Westinghouse Electric Corp. Pinned root turbine blade providing maximum friction damping
US4494909A (en) * 1981-12-03 1985-01-22 S.N.E.C.M.A. Damping device for turbojet engine fan blades
US4460316A (en) * 1982-12-29 1984-07-17 Westinghouse Electric Corp. Blade group with pinned root
USRE37900E1 (en) 1982-12-29 2002-11-05 Siemens Westinghouse Power Corporation Blade group with pinned root
FR2544381A1 (en) * 1983-04-14 1984-10-19 Gen Electric ROTATING COMPONENT COMPRISING AUBES WITH MODIFIED TAVE D'ARONDE
US4541778A (en) * 1984-05-18 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Pin rooted blade biaxial air seal
EP0214875A1 (en) * 1985-07-16 1987-03-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping element limiting the angular deflection of turbo machine rotor vanes

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