US3576377A - Blades for fluid flow machines - Google Patents

Blades for fluid flow machines Download PDF

Info

Publication number
US3576377A
US3576377A US783632A US3576377DA US3576377A US 3576377 A US3576377 A US 3576377A US 783632 A US783632 A US 783632A US 3576377D A US3576377D A US 3576377DA US 3576377 A US3576377 A US 3576377A
Authority
US
United States
Prior art keywords
blade
bridgepiece
shroud
end faces
blades
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
US783632A
Other languages
English (en)
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
Application granted granted Critical
Publication of US3576377A publication Critical patent/US3576377A/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
    • F01D5/12—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

Definitions

  • each blade in a turbine blade ring has a shroud portion which is adapted to abut the next adjacent shroud portions of blades in the blade ring.
  • the abutting surfaces are provided by the wear-resistant ends of a bridgepiece which fits over the shroud and is brazed into position.
  • the present invention relates to blades for fluid flow machines and has particular but not exclusive reference to rotor blades for a compressor or turbine of a gas turbine engine.
  • a blade for a fluid flow machine which blade has a shroud portion at its tip, said shroud portion being adapted to extend circumferentially when the blade is positioned in a ring of blades and terminating in circumferentially opposite end faces, a bridgepiece connected to the shroud portion and extending between said end faces, the bridgepiece having end portions which are made of material having greater wear resistance than the blade, which end portions are positioned over the end faces of the shroud portion, so that the end portions of the bridgepiece provide abutment surfaces for abutment with corresponding surfaces provided on the shroud portions of adjacent blades of said ring of blades.
  • the areas of the abunnent surfaces of the bridgepiece may be greater than the areas of the end faces of the shroud portion over which they fit.
  • the abutment surfaces of the bridgepieces on two adjacent shroud portions also preferably provide an interference fit between the shroud portions and are inclined at an angle to the engine axis thereby providing a twist on blade.
  • the invention also includes a blade rotor comprising a ring of blades, as described above, mounted on a rotor member.
  • a method of making a blade for use in a bladed rotor of a fluid flow machine comprises the steps of forming a blade with a shroud portion at its tip, the shroud portion being adapted to extend circumferentially when the blade is positioned in a ring of blades, and terminating in circumferentially opposite end faces, making a bridgepiece having end portions, at least the end portions of which are made of a material which has greater wear resistance than the material of the blade, locating the bridgepiece on the shroud portion so that it extends between said end faces of the shroud portion and the end portions overlie said end faces of the shroud portion, and
  • FIG. 1 shows a gas turbine engine with the turbine casing broken away.
  • FIG. 2 shows part of a ring of rotor blades of the turbine of the engine of FIG. 1.
  • FIG. 3 is an enlarged pictorial view of one of the turbine blades of FIG. 2.
  • FIG. 4 is an exploded view of the blade of FIG. 3 illustrating the position of the bridge piece.
  • FIG. 1 there is shown a gas turbine engine 1 having compressor means 2 combustion equipment 3, turbine means 4 and a propulsion nozzle 5 all in flow series.
  • the turbine means 4 consists of a plurality of rotor stages 6 and stator stages 7.
  • FIG. 2 shows one of the rotor stages 6 which comprises a plurality of aerofoil-shaped blades 8 mounted by means of root portions 9 on the periphery of a rotor disc 10.
  • Each blade has a shroud portion 11 at its tip, each shroud portion extending circumferentially and cooperating with the shroud portion of the next adjacent blades to form a shroud ring.
  • Each shroud portion has abutment surfaces 15 for abutment with the next adjacent shroud portions of the ring to form an interference joint which puts a slight twist on each blade and assists in damping out vibration of the blades.
  • the abutment surfaces 15, seen more clearly in FIG. 3 are inclined to the longitudinal axis of the engine in order to provide a reaction on the blade which provides the twist.
  • the abutment surfaces 15 form part of a bridgepiece 16 which is fitted over the top of the shroud portion 11 and the abutment surfaces 15 are provided by the end faces of end portions 18 of the bridgepiece, which overlie the circumferentially opposite end faces 17 of the shroud portion 11.
  • the bridge piece 16 is shown both in position on the blade shroud portion 11 and displaced thereabove, as in an exploded view. 1
  • the bridgepiece 16 is made of a material which is more wear resistant than the material of the blade, for example the material sold under the trade name of Stellite, the blades being made of a material sold under the trade name of Nimonic 115.
  • the bridgepiece 16 is shown both in position on the blade shroud portion 11 and displaced thereabove, as in an exploded view.
  • the use of a bridgepiece of hard material has simply and effectively solved this problem and at the same time enables the surface areas of the end faces to be increased.
  • the bridgepiece is simply and accurately located circumferentially on the blade by the end portion 18 and axial location is made between two projections 19 on the shroud portion 11.
  • the bridgepieces are brazed in position and hence may be utilized in the case of blades which are made of nonweldable material.
  • the bridgepiece has the further advantage that in the event of excessive wear it may be machined off and replaced without detriment to the blade.
  • the bridgepiece itself may be fabricated from two Stellite end portions 18 the intermediate portion 20 being made of a different material.
  • the intermediate portion 20 of the bridgepiece may be reduced in thickness by machining after attachment to the shroud portion to reduce the weight of the assembly.
  • a blade for a fluid flow machine a shroud portion at the tip of the blade, said shroud being adapted to extend circumferentially when the blade is positioned in a ring of blades and terminating in circumferentially opposite end faces, a bridgepiece connected to the shroud portion and extending between said end faces, the bridgepiece having end portions which are made of material having greater wear resistance than the blade, which end portions are positioned over the end faces of the shroud portion, so that the end portions of the bridgepiece provide abutment surfaces for abutment with corresponding surfaces provided on he shroud portions of adjacent blades of said ring blades, said bridgepiece being replaceable without detriment to the blade.
  • a bladed rotor comprising a rotor member, a plurality of blades mounted on the rotor member, each blade having a shroud portion at its tip which extends circumferentially of the rotor, and terminates in circumferentially opposite end faces, a bridgepiece connected to the shroud portion and extending circumferentially of the rotor, the bridgepiece having end portions which are made of a material having greater wear resistance than the blade, which end portions are positioned over the end faces of the shroud portion and provide abutment surfaces which abut corresponding surfaces provided on the shroud portions of adjacent blades of the rotor, said bridgepiece and end portions being replaceable to provide new abutment surfaces.
  • a blade for a fluid flow machine a shroud portion at the tip of the blade, said shroud being adapted to extend circumferentially when the blade is positioned in a ring of blades and terminating in circumferentially opposite end faces, a bridgepiece connected to the shroud portion and extending between said end faces, the bridgepiece having end portions which are made of material having greater wear resistance than the blade, which end portions are positioned over the end faces of the shroud portion, so that the end portions of the bridgepiece provide abutment surfaces for abutment with corresponding surfaces provided on the shroud portions of adjacent blades of said ring of blades, the areas of the abutment surfaces of the bridgepiece being greater than the areas of the end faces of the shroud portion over which they fit.
  • a method of making a blade for use in a bladed rotor of a fluid flow machine comprising the steps of:

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)
US783632A 1967-12-22 1968-12-13 Blades for fluid flow machines Expired - Lifetime US3576377A (en)

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
US3576377A true US3576377A (en) 1971-04-27

Family

ID=10481718

Family Applications (1)

Application Number Title Priority Date Filing Date
US783632A Expired - Lifetime US3576377A (en) 1967-12-22 1968-12-13 Blades for fluid flow machines

Country Status (4)

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

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3871791A (en) * 1972-03-09 1975-03-18 Rolls Royce 1971 Ltd Blade for fluid flow machines
US4257741A (en) * 1978-11-02 1981-03-24 General Electric Company Turbine engine blade with airfoil projection
US4460316A (en) * 1982-12-29 1984-07-17 Westinghouse Electric Corp. Blade group with pinned root
US4722668A (en) * 1985-08-31 1988-02-02 Bbc Brown, Boveri & Company, Limited Device for damping blade vibrations in turbo-machines
US4815938A (en) * 1987-12-24 1989-03-28 Westinghouse Electric Corp. Shroud gap control for integral shrouded blades
US4948338A (en) * 1988-09-30 1990-08-14 Rolls-Royce Plc Turbine blade with cooled shroud abutment surface
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
US20040120823A1 (en) * 2002-12-19 2004-06-24 Warner Craig M. Steam turbine bucket flowpath
US20050079058A1 (en) * 2003-10-09 2005-04-14 Pratt & Whitney Canada Corp. Shrouded turbine blades with locally increased contact faces
EP1767744A1 (de) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Turbinenschaufeln mit Deckplatten, die mit einer aufgeschweissten Hartschicht versehen sind sowie Herstellungsverfahren
US20080019835A1 (en) * 2004-04-30 2008-01-24 Alstom Technology Ltd. Gas turbine blade shroud
US20090047132A1 (en) * 2007-08-16 2009-02-19 General Electric Company Durable blade
WO2012076591A1 (en) * 2010-12-09 2012-06-14 Alstom Technology Ltd Shroud of a rotor blade
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
US20130028741A1 (en) * 2011-07-28 2013-01-31 Chad Daniel Kleinow Cap for ceramic blade tip shroud
CN103089322A (zh) * 2013-01-29 2013-05-08 杭州汽轮机股份有限公司 工业汽轮机高负荷短叶片的阻尼围带结构
US20130170994A1 (en) * 2012-01-04 2013-07-04 General Electric Company Device and method for aligning tip shrouds
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
FR3086692A1 (fr) * 2018-09-28 2020-04-03 Safran Aircraft Engines Aube de turbomachine equipee d'une piece rapportee anti-usure
US10895159B2 (en) * 2017-05-24 2021-01-19 Safran Aircraft Engines Removable anti-wear part for blade tip
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4576551A (en) * 1982-06-17 1986-03-18 The Garrett Corporation Turbo machine blading
DE3413628C2 (de) * 1983-04-25 1996-09-19 Gen Electric Spaltdichtung für eine Dampfturbine
FR2552159B1 (fr) * 1983-09-21 1987-07-10 Snecma Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
FR3111158B1 (fr) * 2020-06-04 2022-06-03 Safran Aircraft Engines Pièce amovible anti-usure pour talon d’aube

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3185441A (en) * 1961-08-10 1965-05-25 Bbc Brown Boveri & Cie Shroud-blading for turbines or compressors
US3304056A (en) * 1965-03-19 1967-02-14 Hitachi Ltd Turbine blades

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3185441A (en) * 1961-08-10 1965-05-25 Bbc Brown Boveri & Cie Shroud-blading for turbines or compressors
US3304056A (en) * 1965-03-19 1967-02-14 Hitachi Ltd Turbine blades

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3871791A (en) * 1972-03-09 1975-03-18 Rolls Royce 1971 Ltd Blade for fluid flow machines
US4257741A (en) * 1978-11-02 1981-03-24 General Electric Company Turbine engine blade with airfoil projection
USRE37900E1 (en) 1982-12-29 2002-11-05 Siemens Westinghouse Power Corporation Blade group with pinned root
US4460316A (en) * 1982-12-29 1984-07-17 Westinghouse Electric Corp. Blade group with pinned root
US4722668A (en) * 1985-08-31 1988-02-02 Bbc Brown, Boveri & Company, Limited Device for damping blade vibrations in turbo-machines
US4815938A (en) * 1987-12-24 1989-03-28 Westinghouse Electric Corp. Shroud gap control for integral shrouded blades
US4948338A (en) * 1988-09-30 1990-08-14 Rolls-Royce Plc Turbine blade with cooled shroud abutment surface
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
US20040120823A1 (en) * 2002-12-19 2004-06-24 Warner Craig M. Steam turbine bucket flowpath
US6786698B2 (en) * 2002-12-19 2004-09-07 General Electric Company Steam turbine bucket flowpath
US20050079058A1 (en) * 2003-10-09 2005-04-14 Pratt & Whitney Canada Corp. Shrouded turbine blades with locally increased contact faces
US7001152B2 (en) 2003-10-09 2006-02-21 Pratt & Wiley Canada Corp. Shrouded turbine blades with locally increased contact faces
US20080019835A1 (en) * 2004-04-30 2008-01-24 Alstom Technology Ltd. Gas turbine blade shroud
US7628587B2 (en) * 2004-04-30 2009-12-08 Alstom Technology Ltd Gas turbine blade shroud
EP1767744A1 (de) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Turbinenschaufeln mit Deckplatten, die mit einer aufgeschweissten Hartschicht versehen sind sowie Herstellungsverfahren
US8182228B2 (en) * 2007-08-16 2012-05-22 General Electric Company Turbine blade having midspan shroud with recessed wear pad and methods for manufacture
US20090047132A1 (en) * 2007-08-16 2009-02-19 General Electric Company Durable blade
CN101382149B (zh) * 2007-08-16 2015-07-01 通用电气公司 一种制造叶片的方法
WO2012076591A1 (en) * 2010-12-09 2012-06-14 Alstom Technology Ltd Shroud of a rotor blade
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
US20130028741A1 (en) * 2011-07-28 2013-01-31 Chad Daniel Kleinow Cap for ceramic blade tip shroud
JP2013029104A (ja) * 2011-07-28 2013-02-07 General Electric Co <Ge> セラミックブレード先端シュラウド用のキャップ
EP2551459A3 (en) * 2011-07-28 2017-07-26 General Electric Company Cap for ceramic blade tip shroud
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
CN103195505A (zh) * 2012-01-04 2013-07-10 通用电气公司 用于对准顶端围带的装置和方法
US20130170994A1 (en) * 2012-01-04 2013-07-04 General Electric Company Device and method for aligning tip shrouds
CN103195505B (zh) * 2012-01-04 2016-04-27 通用电气公司 用于对准顶端围带的装置和方法
CN103089322A (zh) * 2013-01-29 2013-05-08 杭州汽轮机股份有限公司 工业汽轮机高负荷短叶片的阻尼围带结构
US9683446B2 (en) 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
US10895159B2 (en) * 2017-05-24 2021-01-19 Safran Aircraft Engines Removable anti-wear part for blade tip
US10294801B2 (en) * 2017-07-25 2019-05-21 United Technologies Corporation Rotor blade having anti-wear surface
FR3086692A1 (fr) * 2018-09-28 2020-04-03 Safran Aircraft Engines Aube de turbomachine equipee d'une piece rapportee anti-usure
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements

Also Published As

Publication number Publication date
DE1816066A1 (de) 1969-08-07
FR1598028A (enrdf_load_stackoverflow) 1970-06-29
GB1186240A (en) 1970-04-02
DE1816066B2 (de) 1970-11-05

Similar Documents

Publication Publication Date Title
US3576377A (en) Blades for fluid flow machines
US3199836A (en) Axial flow turbo-machine blade with abrasive tip
US3801222A (en) Platform for compressor or fan blade
US2755063A (en) Rotor constructions for gas-turbine engines
US4824328A (en) Turbine blade attachment
CA1039198A (en) Trubomachine with removable stator vane
US3628890A (en) Compressor blades
US4659289A (en) Turbine side plate assembly
US4339229A (en) Rotor wheel for axial-flow turbomachinery
EP0112092A1 (en) Turbine blade with integral shroud and method of assembling the blades in a circular array
JPS60159398A (ja) 軸流圧縮機の羽根車
EP1451446A1 (en) Turbine blade pocket shroud
US4602412A (en) Method for assembling in a circular array turbine blades each with an integral shroud
SE8503614D0 (sv) Gas turbine bladed disk assembly
EP0274978B1 (en) Multiple lug blade to disk attachment
GB2043796A (en) Bladed rotor for gas turbine engine
US3572968A (en) Turbine bucket cover
GB996729A (en) Improvements relating to turbines and compressors
US5445498A (en) Bucket for next-to-the-last stage of a turbine
US3339833A (en) Axial fluid flow machine such as a compressor or turbine
GB1408491A (en) Composite turbomachinery blade root configuration
US2394124A (en) Bladed body
JPH0772485B2 (ja) ロータへの羽根の装着方法並びにロータ及び羽根組立体
US3867069A (en) Alternate root turbine blading
US2483610A (en) Bladed impeller for turboblowers