US3918842A - Blade assembly for a fluid flow machine - Google Patents

Blade assembly for a fluid flow machine Download PDF

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Publication number
US3918842A
US3918842A US475916A US47591674A US3918842A US 3918842 A US3918842 A US 3918842A US 475916 A US475916 A US 475916A US 47591674 A US47591674 A US 47591674A US 3918842 A US3918842 A US 3918842A
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US
United States
Prior art keywords
groove
rotor assembly
face
blades
platforms
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
US475916A
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English (en)
Inventor
Peter John Longley
Anthony George Gale
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 1971 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 Rolls Royce 1971 Ltd filed Critical Rolls Royce 1971 Ltd
Application granted granted Critical
Publication of US3918842A publication Critical patent/US3918842A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • ABSTRACT 1 1 Foreign Application Priority Data
  • a bladed rotor for a gas turbine engine the shrouds June 26. 1973 United Kingdom 30252/73 or platforms of the blades each have a face which c0- operates with a corresponding face on the next adja- [52] US. Cl 416/219; 416/193 cent blade to form a radially tapering groove whose [51] Int. Cl. F01D 5/18; FOlD 5/24 width decreases as the radial distance from the rotor [58] Field of Search 416/191, 193, 219, 221 axis increases. and a sealing member such as a wire is mounted in the groove to seal between the adjacent [56] References Cited platforms or shrouds.
  • At least one projection from said face or faces adapted to prevent said sealing member falling radially inward to disengage from the groove.
  • the groove may be formed between a radial surface on one face and an inclined surface on the corresponding face, or between an inclined surface on one face and an oppositely inclined surface on the corresponding face.
  • the sealing member comprises a wire which is curved longitudinally to match the curve of said tapered groove.
  • FIG. 1 shows a diagrammatic view of a gas turbine engine showing an embodiment of the present invention
  • FIG. 2 shows an enlarged pictorial view of the embodiment shown at FIG. 1,
  • FIG. 3 shows a section taken between two respective blades shown at FIG. 2,
  • FIG. 4 shows an end elevation of two adjacent blade roots taken in direction of arrow 4 at FIG. 3,
  • FIG. 5 shows an enlarged pictorial view of the sealing member
  • I FIG. 6 is a view similar to FIG. 2 but of a second embodiment of the invention.
  • a gas turbine engine shown generally at 10 comprises an intake 12, compressor section 13, combustion section 14 and turbine section 15 terminating in exhaust nozzle 16.
  • a brokenaway portion of the casing round the turbine section 15 shows diagrammatically the turbine rotor in accordance with the invention.
  • FIG. 2 is an enlarged pictorial view of the broken away section shown at FIG. 1 and shows individual aerofoil shaped turbine blade members a, 20b, 20c and 20d terminating in blade root portions 21a, 21b, 21c and 21d only three of which are wholly or partially exposed in the drawings, the blade roots in turn are secured in the rotor disc (not shown) by means of fir tree root members.
  • the outer tips of the blades 20a, b, c, d, etc. are in turn bounded by a shroud portion 22 which it will be appreciated may also be provided with a similar sealing system as that shown at the blade roots.
  • the surface 25 is provided with a recessed portion 25', the recess terminating in an inclined arcuate surface 27 against which the arcuate wire sealing member 28 rests.
  • the inclined surface 27 and flat surface 26 together form a tapered groove whose width decreases as the radial distance from the rotor axis increases, and the wire 28 is of the same length as the root portion of the blade.
  • This construction can also be seen at FIG. 4.
  • the sealing members 28 are prevented from moving radially inwardly by means of a projecting portion 29 being provided upon the substantially flat surface 26, the projection 29 being spaced radially inward of that part of the flat surface 26 which corresponds with the inclined surface 27.
  • the sealing members and blades are prevented from moving axially from the disc by means of lock plates 30 and 31 shown in more detail at FIG. 3.
  • FIG. 6 shows a further embodiment of the invention, in this case the sealing member 28 is arranged to nestle in the tapered arcuate groove formed between two inclined arcuate step portions 32 provided upon the radially outermost surfaces of two recessed portions one of which is provided on each side of the blade root portion; again cooperating projections 33 radially inward of the surfaces 32 prevent the member 28 falling radially inwardly.
  • sealing members 28 are interposed between the platforms, they prevent these platforms fretting against one another, and their position at the inner end of the aerofoil enables them to provide damping of this area; clearly the faster the rotor rotates, the more centrifugal load acts on the sealing members and the greater will be the damping. It will also be understood that expansion or contraction occurring in the turbine may be accommodated by the above mentioned sealing arrangements.
  • seal members 28 in arcuate form the curved shape gives angular location to enable the ends of the seal member to be shaped by machining to conform with the surface of the blade front and rear faces 21a and 21b etc.
  • the arcuate shape also prevents twisting of the seal member 28 and ensures friction damping.
  • a bladed rotor assembly for a gas turbine engine comprising a rotor and a plurality of angularly spaced apart aerofoil blades supported from the rotor, each blade having a platform member, said platform member having a face which cooperates with a corresponding face on the next adjacent blade to form a radially tapering groove whose width decreases as its distance from the rotor axis increases, said radially tapering groove being curved longitudinally relative said rotor assembly, and a sealing member mounted in the tapered and longitudinally curved groove so as to seal between the adjacent platforms, said sealing member comprising a wire curved longitudinally relative said rotor assembly and being substantially complementary to the longitudinal curve of said groove.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US475916A 1973-06-26 1974-06-03 Blade assembly for a fluid flow machine Expired - Lifetime US3918842A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3025273A GB1460714A (en) 1973-06-26 1973-06-26 Bladed rotor for a gas turbine engine

Publications (1)

Publication Number Publication Date
US3918842A true US3918842A (en) 1975-11-11

Family

ID=10304699

Family Applications (1)

Application Number Title Priority Date Filing Date
US475916A Expired - Lifetime US3918842A (en) 1973-06-26 1974-06-03 Blade assembly for a fluid flow machine

Country Status (5)

Country Link
US (1) US3918842A (enrdf_load_stackoverflow)
JP (1) JPS5548166B2 (enrdf_load_stackoverflow)
FR (1) FR2235272B1 (enrdf_load_stackoverflow)
GB (1) GB1460714A (enrdf_load_stackoverflow)
IT (1) IT1012974B (enrdf_load_stackoverflow)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4326835A (en) * 1979-10-29 1982-04-27 General Motors Corporation Blade platform seal for ceramic/metal rotor assembly
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US4936749A (en) * 1988-12-21 1990-06-26 General Electric Company Blade-to-blade vibration damper
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
EP1167691A3 (en) * 2000-06-30 2003-10-15 General Electric Company Blade damper and method for making same
US20040149163A1 (en) * 2003-02-03 2004-08-05 Taylor Fred J. Manual railroad hopper car door actuating mechanism
US20050047917A1 (en) * 2003-09-02 2005-03-03 Hans-Egon Brock Rotor of a steam or gas turbine
EP2053285A1 (en) * 2007-10-25 2009-04-29 Siemens Aktiengesellschaft Turbine blade assembly
WO2009053169A1 (en) * 2007-10-25 2009-04-30 Siemens Aktiengesellschaft Turbine blade assembly and seal strip
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
US20110027088A1 (en) * 2009-07-31 2011-02-03 General Electric Company Rotor blades for turbine engines
US20120121384A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor and method for manufacturing a rotor for a turbo machine
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
US20130323031A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
EP2679770A1 (en) 2012-06-26 2014-01-01 Siemens Aktiengesellschaft Platform seal strip for a gas turbine
US9840920B2 (en) * 2012-06-15 2017-12-12 General Electric Company Methods and apparatus for sealing a gas turbine engine rotor assembly
US10385706B2 (en) * 2014-06-26 2019-08-20 Safran Aircraft Engines Rotary assembly for a turbomachine
US11352892B2 (en) 2020-04-17 2022-06-07 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk
FR3120903A1 (fr) * 2021-03-16 2022-09-23 Safran Aircraft Engines Roue à aubes pour une turbine
US11512602B2 (en) 2020-01-20 2022-11-29 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8819133D0 (en) * 1988-08-11 1988-09-14 Rolls Royce Plc Bladed rotor assembly & sealing wire therefor
US6851932B2 (en) * 2003-05-13 2005-02-08 General Electric Company Vibration damper assembly for the buckets of a turbine
EP2098687A1 (de) * 2008-03-07 2009-09-09 Siemens Aktiengesellschaft Rotor für eine Strömungsmaschine
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2445154A (en) * 1944-03-04 1948-07-13 Ingersoll Rand Co Blade mounting
US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
US3752598A (en) * 1971-11-17 1973-08-14 United Aircraft Corp Segmented duct seal
US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4417361Y1 (enrdf_load_stackoverflow) * 1965-12-24 1969-07-28

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2445154A (en) * 1944-03-04 1948-07-13 Ingersoll Rand Co Blade mounting
US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
US3752598A (en) * 1971-11-17 1973-08-14 United Aircraft Corp Segmented duct seal
US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement

Cited By (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4326835A (en) * 1979-10-29 1982-04-27 General Motors Corporation Blade platform seal for ceramic/metal rotor assembly
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US4936749A (en) * 1988-12-21 1990-06-26 General Electric Company Blade-to-blade vibration damper
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
EP1167691A3 (en) * 2000-06-30 2003-10-15 General Electric Company Blade damper and method for making same
US20040149163A1 (en) * 2003-02-03 2004-08-05 Taylor Fred J. Manual railroad hopper car door actuating mechanism
US6955127B2 (en) 2003-02-03 2005-10-18 Taylor Fred J Manual railroad hopper car door actuating mechanism
US20050047917A1 (en) * 2003-09-02 2005-03-03 Hans-Egon Brock Rotor of a steam or gas turbine
US7104758B2 (en) * 2003-09-02 2006-09-12 Man Turbo Ag Rotor of a steam or gas turbine
RU2347913C2 (ru) * 2003-09-02 2009-02-27 Ман Турбо Аг Ротор паровой или газовой турбины
US8613599B2 (en) 2007-10-25 2013-12-24 Siemens Aktiengesellschaft Turbine blade assembly and seal strip
EP2053285A1 (en) * 2007-10-25 2009-04-29 Siemens Aktiengesellschaft Turbine blade assembly
US20110014050A1 (en) * 2007-10-25 2011-01-20 Peter Lake Turbine blade assembly and seal strip
WO2009053169A1 (en) * 2007-10-25 2009-04-30 Siemens Aktiengesellschaft Turbine blade assembly and seal strip
CN101836018B (zh) * 2007-10-25 2014-06-25 西门子公司 涡轮叶片组件和密封条
RU2486349C2 (ru) * 2007-10-25 2013-06-27 Сименс Акциенгезелльшафт Уплотнительный гребень, узел лопаток турбины и газовая турбина, содержащая такой узел лопаток
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
CN102227545A (zh) * 2008-10-31 2011-10-26 索拉透平公司 包括密封件凹座的涡轮叶片
US8137072B2 (en) 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
US8596983B2 (en) 2008-12-19 2013-12-03 Solar Turbines Inc. Turbine blade assembly including a damper
US20110027088A1 (en) * 2009-07-31 2011-02-03 General Electric Company Rotor blades for turbine engines
US8371816B2 (en) 2009-07-31 2013-02-12 General Electric Company Rotor blades for turbine engines
US9022727B2 (en) * 2010-11-15 2015-05-05 Mtu Aero Engines Gmbh Rotor for a turbo machine
US20120121436A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor for a turbo machine
US8888456B2 (en) * 2010-11-15 2014-11-18 Mtu Aero Engines Gmbh Rotor and method for manufacturing a rotor for a turbo machine
US20120121384A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor and method for manufacturing a rotor for a turbo machine
US20130323031A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
US9650901B2 (en) * 2012-05-31 2017-05-16 Solar Turbines Incorporated Turbine damper
US9840920B2 (en) * 2012-06-15 2017-12-12 General Electric Company Methods and apparatus for sealing a gas turbine engine rotor assembly
EP2679770A1 (en) 2012-06-26 2014-01-01 Siemens Aktiengesellschaft Platform seal strip for a gas turbine
WO2014001084A1 (en) 2012-06-26 2014-01-03 Siemens Aktiengesellschaft Platform seal strip, turbine blade assembly and method for assembling it
US10385706B2 (en) * 2014-06-26 2019-08-20 Safran Aircraft Engines Rotary assembly for a turbomachine
US11512602B2 (en) 2020-01-20 2022-11-29 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk
US11352892B2 (en) 2020-04-17 2022-06-07 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk
FR3120903A1 (fr) * 2021-03-16 2022-09-23 Safran Aircraft Engines Roue à aubes pour une turbine

Also Published As

Publication number Publication date
FR2235272A1 (enrdf_load_stackoverflow) 1975-01-24
JPS5069412A (enrdf_load_stackoverflow) 1975-06-10
FR2235272B1 (enrdf_load_stackoverflow) 1980-08-01
JPS5548166B2 (enrdf_load_stackoverflow) 1980-12-04
DE2430181A1 (de) 1975-01-16
DE2430181B2 (de) 1976-06-10
GB1460714A (en) 1977-01-06
IT1012974B (it) 1977-03-10

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