GB606151A - Improvements relating to blading of turbines, compressors and like machines - Google Patents

Improvements relating to blading of turbines, compressors and like machines

Info

Publication number
GB606151A
GB606151A GB34827/45A GB3482745A GB606151A GB 606151 A GB606151 A GB 606151A GB 34827/45 A GB34827/45 A GB 34827/45A GB 3482745 A GB3482745 A GB 3482745A GB 606151 A GB606151 A GB 606151A
Authority
GB
United Kingdom
Prior art keywords
blade
blades
tilt
rotor
adjacent
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
GB34827/45A
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.)
GEOFFREY BERTRAM ROBERT FIELDE
Power Jets Research and Development Ltd
Original Assignee
GEOFFREY BERTRAM ROBERT FIELDE
Power Jets Research and Development Ltd
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 GEOFFREY BERTRAM ROBERT FIELDE, Power Jets Research and Development Ltd filed Critical GEOFFREY BERTRAM ROBERT FIELDE
Publication of GB606151A publication Critical patent/GB606151A/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
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

606,151. Turbine blades. POWER JETS (RESEARCH & DEVELOPMENT), Ltd., FIELDEN, G. B. R., and OGSTON, W. M. Dec. 21, 1945, No. 34827. [Class 110 (iii)] An axial flow turbine blade of the kind in which the centre of gravity of the blade is offset from the radial direction so that the bending moment on the blade due to centrifugal force balances that due to the gases acting on the blade, is mounted individually and independently so that it can tilt under the influence of both these forces so as to accommodate any changes in the relation between the values of them. The turbine blade 3, Fig. 1, is pivotally mounted through needle roller bearings 5 on axially extending pins 6, the ends of which are held in recesses in the flanges 2 of a rotor disc 1 which are held together axially under tension. A peripheral clearance is left between adjacent blades to allow them to tilt. As the roller bearings 5 tend to bend under load, the centre portion of the bore may be relieved as at 7 to allow the pin to bend freely. The pins 6 may be skewed with reference to the axial plane. In a modification, the blade is attached to the rotor by flexible radial strips, the ends of which are bent around pins, one of which is within the body of the blade root and the other held between two adjacent rotor discs. In a further modification, Fig. 7, the blade is able to tilt in more than one plane. Attached to the root of the blade is a part-spherical head 11 which co-operates with members 14 to form a partspherical ball-race 15. This arrangement allows the blades to rotate, but by keeping the peripheral clearances low and the interengaging faces of the blades long in the axial direction, such rotation can be reduced to negligible proportions. In another modification, Fig. 10, the blade root has a channel 17 running around it in which is placed a pad 18 of yielding material shaped so that recesses are left in which engage correspondingly shaped projections 19 on the adjacent rotor discs 1. A yielding material with good damping characteristics is chosen to .dampen.out any vibration in the blades. The ball-race 15 may be replaced by a laminar element of this material. The clearances between adjacent blades and between the blades and the rotor are chosen so as to limit the amount of tilt. The blade mounting is stated to be suitable also for compressors and impellers.
GB34827/45A 1945-12-21 1945-12-21 Improvements relating to blading of turbines, compressors and like machines Expired GB606151A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB264413X 1945-12-21

Publications (1)

Publication Number Publication Date
GB606151A true GB606151A (en) 1948-08-06

Family

ID=10243653

Family Applications (1)

Application Number Title Priority Date Filing Date
GB34827/45A Expired GB606151A (en) 1945-12-21 1945-12-21 Improvements relating to blading of turbines, compressors and like machines

Country Status (6)

Country Link
US (1) US2727716A (en)
BE (1) BE470026A (en)
CH (1) CH264413A (en)
FR (1) FR937883A (en)
GB (1) GB606151A (en)
NL (1) NL70700C (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2660413A (en) * 1950-02-03 1953-11-24 Rolls Royce Locking arrangement for blading of axial-flow turbines and compressors
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
US2819869A (en) * 1950-05-02 1958-01-14 Jr Andre J Meyer Mounting arrangement for turbine or compressor blading
DE971286C (en) * 1951-08-31 1959-01-08 Power Jets Res & Dev Ltd Device for vibration damping on blades for turbines operated with elastic working fluid or for blowers
US2919889A (en) * 1955-03-03 1960-01-05 United Aircraft Corp Blade mounting
US3984194A (en) * 1974-04-12 1976-10-05 Aktiebolaget Svenska Flaktfabriken Axial flow fans

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
US2935297A (en) * 1954-06-09 1960-05-03 Stalker Corp Vibration dampers for rotor blades
US2819871A (en) * 1954-09-07 1958-01-14 John R Mcveigh Vane structure
BE543383A (en) * 1954-12-06
BE635976A (en) * 1962-08-10
US3687569A (en) * 1971-03-19 1972-08-29 Gen Electric Rotor with variable angle blades
US4022545A (en) * 1974-09-11 1977-05-10 Avco Corporation Rooted aerodynamic blade and elastic roll pin damper construction
EP2644834A1 (en) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Turbine blade and corresponding method for producing same turbine blade
EP2644828A1 (en) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Modular turbine blade having a platform
FR2996251B1 (en) * 2012-09-28 2018-07-27 Safran Aircraft Engines SELF-TENSIONING ATTACHMENT FOR TURBINE BLADE IN CMC
US11156111B2 (en) * 2018-08-31 2021-10-26 Rolls-Royce Corporation Pinned platform for blade with circumferential attachment
US11326474B2 (en) * 2019-12-04 2022-05-10 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with pinned attachment supplements for ceramic matrix composite component mounting

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1802648A (en) * 1925-12-31 1931-04-28 American Propeller Company Propeller
GB302953A (en) * 1927-09-21 1928-12-21 Neil Shaw Muir Improvements in or relating to centrifugal blowers, compressors and the like
US1921931A (en) * 1930-01-23 1933-08-08 Levasseur Pierre Screw propeller
US2219288A (en) * 1936-01-13 1940-10-29 Harold T Avery Rotative wing aircraft
DE713187C (en) * 1936-11-07 1941-11-03 Siemens Schuckertwerke Akt Ges Attachment for a fan wheel on its drive shaft
US2235605A (en) * 1937-03-10 1941-03-18 Bugatti Ettore Screw propeller
US2240873A (en) * 1937-11-11 1941-05-06 Dehavilland Aircraft Mounting of airscrew blades
US2394460A (en) * 1939-07-04 1946-02-05 Martinotti Pietro Aircraft propeller
US2344266A (en) * 1941-06-27 1944-03-14 Reissner Hans Aircraft propeller construction
US2317338A (en) * 1942-02-07 1943-04-20 Westinghouse Electric & Mfg Co Turbine blade fastening apparatus
US2354101A (en) * 1942-08-07 1944-07-18 United Aircraft Corp Fan construction
US2473899A (en) * 1943-12-11 1949-06-21 Curtiss Wright Corp Articulated and universal joint for propellers and other mechanisms
US2416178A (en) * 1944-09-19 1947-02-18 United Aircraft Corp Resiliently hinged blade mounting
US2436087A (en) * 1944-12-04 1948-02-17 Ernest H Benson Cooling fan for aircraft engines
US2595829A (en) * 1946-12-19 1952-05-06 Benson Mfg Company Axial flow fan and compressor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2660413A (en) * 1950-02-03 1953-11-24 Rolls Royce Locking arrangement for blading of axial-flow turbines and compressors
US2819869A (en) * 1950-05-02 1958-01-14 Jr Andre J Meyer Mounting arrangement for turbine or compressor blading
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
DE971286C (en) * 1951-08-31 1959-01-08 Power Jets Res & Dev Ltd Device for vibration damping on blades for turbines operated with elastic working fluid or for blowers
US2919889A (en) * 1955-03-03 1960-01-05 United Aircraft Corp Blade mounting
US3984194A (en) * 1974-04-12 1976-10-05 Aktiebolaget Svenska Flaktfabriken Axial flow fans

Also Published As

Publication number Publication date
CH264413A (en) 1949-10-15
NL70700C (en)
FR937883A (en) 1948-08-30
US2727716A (en) 1955-12-20
BE470026A (en)

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