GB1186240A - Improvements in Blades for Fluid Flow Machines. - Google Patents

Improvements in Blades for Fluid Flow Machines.

Info

Publication number
GB1186240A
GB1186240A GB58478/67A GB5847867A GB1186240A GB 1186240 A GB1186240 A GB 1186240A GB 58478/67 A GB58478/67 A GB 58478/67A GB 5847867 A GB5847867 A GB 5847867A GB 1186240 A GB1186240 A GB 1186240A
Authority
GB
United Kingdom
Prior art keywords
bridge
blade
blades
shroud
chromium
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
GB58478/67A
Inventor
Michael Hargreaves Beanland
Michael Anthony Wilson
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 GB58478/67A priority Critical patent/GB1186240A/en
Priority to US783632A priority patent/US3576377A/en
Priority to DE19681816066 priority patent/DE1816066B2/en
Priority to FR1598028D priority patent/FR1598028A/fr
Publication of GB1186240A publication Critical patent/GB1186240A/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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

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)

Abstract

1,186,240. Turbine and compressor blades. ROLLS-ROYCE Ltd. Dec. 19, 1968 [Dec.22, 1967], No. 58478/67. Heading F1T. A blade, such as a turbine or compressor rotor blade in a gas turbine engine, has a tip shroud 11 with a bridge piece 16 fitted over the top of the shroud 11 and having end portions 18 of a material having greater wear resistance than the blade. The portions 18 have inclined abutment surfaces 15 which co-operate in the assembled condition with the surfaces 15 on adjacent rotor blades to provide an interference fit which puts a slight twist on the blades to assist vibration damping. Axial location of each bridge piece 16 is provided by ribs 19 on the shroud 11, the bridge 16 then being brazed in position. Each blade may be made from a nickel-chromium alloy whilst the bridge 16, or only the end portions 18 thereof, is/ are made from a wear resistant alloy containing tungsten and chromium carbides, cobalt and chromium. To reduce weight, the intermediate portion of the bridge 16 may be reduced in thickness by machining after brazing.
GB58478/67A 1967-12-22 1967-12-22 Improvements in Blades for Fluid Flow Machines. Expired GB1186240A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB58478/67A GB1186240A (en) 1967-12-22 1967-12-22 Improvements in Blades for Fluid Flow Machines.
US783632A US3576377A (en) 1967-12-22 1968-12-13 Blades for fluid flow machines
DE19681816066 DE1816066B2 (en) 1967-12-22 1968-12-20 Blade for turbo machines
FR1598028D FR1598028A (en) 1967-12-22 1968-12-23

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB58478/67A GB1186240A (en) 1967-12-22 1967-12-22 Improvements in Blades for Fluid Flow Machines.

Publications (1)

Publication Number Publication Date
GB1186240A true GB1186240A (en) 1970-04-02

Family

ID=10481718

Family Applications (1)

Application Number Title Priority Date Filing Date
GB58478/67A Expired GB1186240A (en) 1967-12-22 1967-12-22 Improvements in Blades for Fluid Flow Machines.

Country Status (4)

Country Link
US (1) US3576377A (en)
DE (1) DE1816066B2 (en)
FR (1) FR1598028A (en)
GB (1) GB1186240A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2564006A (en) * 2017-05-24 2019-01-02 Safran Aircraft Engines Removable anti-wear part for blade root

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1419381A (en) * 1972-03-09 1975-12-31 Rolls Royce Fan for gas turbine engines
US4257741A (en) * 1978-11-02 1981-03-24 General Electric Company Turbine engine blade with airfoil projection
US4576551A (en) * 1982-06-17 1986-03-18 The Garrett Corporation Turbo machine blading
US4460316A (en) 1982-12-29 1984-07-17 Westinghouse Electric Corp. Blade group with pinned root
DE3413628C2 (en) * 1983-04-25 1996-09-19 Gen Electric Gap seal for a steam turbine
FR2552159B1 (en) * 1983-09-21 1987-07-10 Snecma DEVICE FOR CONNECTING AND SEALING TURBINE STATOR BLADE SECTIONS
EP0214393B1 (en) * 1985-08-31 1989-12-13 BBC Brown Boveri AG Antivibration device for turbo machine blades
US4815938A (en) * 1987-12-24 1989-03-28 Westinghouse Electric Corp. Shroud gap control for integral shrouded blades
GB2223276B (en) * 1988-09-30 1992-09-02 Rolls Royce Plc Turbine aerofoil blade
US5083903A (en) * 1990-07-31 1992-01-28 General Electric Company Shroud insert for turbomachinery blade
US5137426A (en) * 1990-08-06 1992-08-11 General Electric Company Blade shroud deformable protective coating
US5324168A (en) * 1993-05-13 1994-06-28 Eastman Kodak Company Use of stellite to prevent silver plateout
US6786698B2 (en) * 2002-12-19 2004-09-07 General Electric Company Steam turbine bucket flowpath
US7001152B2 (en) * 2003-10-09 2006-02-21 Pratt & Wiley Canada Corp. Shrouded turbine blades with locally increased contact faces
EP1591625A1 (en) * 2004-04-30 2005-11-02 ALSTOM Technology Ltd Gas turbine blade shroud
EP1767744A1 (en) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Shrouded turbine blades comprising a welded hardface cladding and process of manufacture
US8182228B2 (en) * 2007-08-16 2012-05-22 General Electric Company Turbine blade having midspan shroud with recessed wear pad and methods for manufacture
RU2010150602A (en) * 2010-12-09 2012-06-20 Альстом Текнолоджи Лтд (Ch) ROTOR BLADE BANDAGE
US20120195742A1 (en) * 2011-01-28 2012-08-02 Jain Sanjeev Kumar Turbine bucket for use in gas turbine engines and methods for fabricating the same
US9163519B2 (en) * 2011-07-28 2015-10-20 General Electric Company Cap for ceramic blade tip shroud
US8894368B2 (en) * 2012-01-04 2014-11-25 General Electric Company Device and method for aligning tip shrouds
CN103089322B (en) * 2013-01-29 2015-04-22 杭州汽轮机股份有限公司 Damp lashing strip structure of industrial steam turbine high load short vane
US9683446B2 (en) 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
US10294801B2 (en) * 2017-07-25 2019-05-21 United Technologies Corporation Rotor blade having anti-wear surface
FR3086692B1 (en) * 2018-09-28 2022-07-29 Safran Aircraft Engines TURBOMACHINE BLADE EQUIPPED WITH AN ANTI-WEAR INSERT
FR3111158B1 (en) * 2020-06-04 2022-06-03 Safran Aircraft Engines Removable anti-wear piece for blade heel
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1159965B (en) * 1961-08-10 1963-12-27 Bbc Brown Boveri & Cie Device for vibration damping on a turbine or compressor blade ring
US3304056A (en) * 1965-03-19 1967-02-14 Hitachi Ltd Turbine blades

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2564006A (en) * 2017-05-24 2019-01-02 Safran Aircraft Engines Removable anti-wear part for blade root
GB2564006B (en) * 2017-05-24 2022-02-16 Safran Aircraft Engines Removable anti-wear part for blade tip

Also Published As

Publication number Publication date
DE1816066A1 (en) 1969-08-07
FR1598028A (en) 1970-06-29
DE1816066B2 (en) 1970-11-05
US3576377A (en) 1971-04-27

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLE Entries relating assignments, transmissions, licences in the register of patents
PLE Entries relating assignments, transmissions, licences in the register of patents