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GB1058759A - Improvements in or relating to the bladed diaphragms of turbines - Google Patents

Improvements in or relating to the bladed diaphragms of turbines

Info

Publication number
GB1058759A
GB1058759A GB5087163A GB5087163A GB1058759A GB 1058759 A GB1058759 A GB 1058759A GB 5087163 A GB5087163 A GB 5087163A GB 5087163 A GB5087163 A GB 5087163A GB 1058759 A GB1058759 A GB 1058759A
Authority
GB
United Kingdom
Prior art keywords
disc
ring
assembly
spokes
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
Application number
GB5087163A
Inventor
Adolf Frankel
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.)
Associated Electrical Industries Ltd
Original Assignee
Associated Electrical Industries 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 Associated Electrical Industries Ltd filed Critical Associated Electrical Industries Ltd
Priority to GB5087163A priority Critical patent/GB1058759A/en
Priority to CH1616364A priority patent/CH426885A/en
Publication of GB1058759A publication Critical patent/GB1058759A/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,058,759. Making turbines. ASSOCIATED ELECTRICAL INDUSTRIES Ltd. Nov. 11, 1964 [Dec. 24, 1963], No. 60871/63. Heading B3A. [Also in Division F1] A bladed diaphragm of a turbine includes a central disc 1 secured to a peripheral ring 5 by radial spokes 9, and an assembly of guide blades 13 fitted into an annular recess 11 machined into one face of the assembly of disc and ring with the spokes spaced at angles corresponding to multiples of the spacing of the guide blades and with each spoke aligned with and forming an aerodynamic continuation of one of the blades. The disc 1 is formed integrally with the spokes 9 and the radially outer ends of the spokes are secured to the ring 5 by welding at 28. The downstream face of the disc and ring assembly is formed with further annular recesses 21, 23 which define thin tongues. The guide blade assembly 13 is formed by inner and outer rings 17, 15 which are formed with slots 19 which receive the ends of the guide blades. The upstream portion of every third guide blade 7A is removed so that the face of this blade lies flush with the adjacent edges of the rings 17, 15. The blade assembly 13 is then engaged within the annular recess 11 of the disc and ring assembly so that the " third " blades 7A align with the spokes 9 and form aerodynamic continuations thereof. The blade assembly is secured by welding between the rings 17 and 15 and disc 1 and ring 5 respectively as indicated at 27A and 25A (Fig. 4, not shown).
GB5087163A 1963-12-24 1963-12-24 Improvements in or relating to the bladed diaphragms of turbines Expired GB1058759A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB5087163A GB1058759A (en) 1963-12-24 1963-12-24 Improvements in or relating to the bladed diaphragms of turbines
CH1616364A CH426885A (en) 1963-12-24 1964-12-15 Bladed intermediate floor for turbines and processes for their manufacture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5087163A GB1058759A (en) 1963-12-24 1963-12-24 Improvements in or relating to the bladed diaphragms of turbines

Publications (1)

Publication Number Publication Date
GB1058759A true GB1058759A (en) 1967-02-15

Family

ID=10457718

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5087163A Expired GB1058759A (en) 1963-12-24 1963-12-24 Improvements in or relating to the bladed diaphragms of turbines

Country Status (2)

Country Link
CH (1) CH426885A (en)
GB (1) GB1058759A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2250782A (en) * 1990-12-11 1992-06-17 Rolls Royce Plc Stator vane assembly
DE3942203C2 (en) * 1988-12-29 2001-04-26 Gen Electric Turbine frame arrangement
EP2422052A1 (en) * 2009-04-23 2012-02-29 Volvo Aero Corporation A method for fabricating a gas turbine engine component and a gas turbine engine component
US20140255159A1 (en) * 2013-03-07 2014-09-11 Pratt & Whitney Canada Corp. Integrated strut-vane
EP2835503A1 (en) * 2013-08-07 2015-02-11 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
EP2860354A1 (en) * 2013-10-08 2015-04-15 Pratt & Whitney Canada Corp. Integrated strut and turbine vane nozzle arrangement
EP3232067A1 (en) * 2016-03-15 2017-10-18 General Electric Company Gas turbine engine ring or circular row, corresponding assembly and designing method
US9909434B2 (en) 2015-07-24 2018-03-06 Pratt & Whitney Canada Corp. Integrated strut-vane nozzle (ISV) with uneven vane axial chords
WO2019145648A1 (en) 2018-01-29 2019-08-01 Safran Aircraft Engines Inter-turbine casing comprising mounted splitter blades
US10443451B2 (en) 2016-07-18 2019-10-15 Pratt & Whitney Canada Corp. Shroud housing supported by vane segments
US11371370B2 (en) 2017-07-19 2022-06-28 MTU Aero Engines AG Flow arrangement for placing in a hot gas duct of a turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2972380A1 (en) * 2011-03-11 2012-09-14 Alstom Technology Ltd METHOD FOR MANUFACTURING STEAM TURBINE DIAPHRAGM
CN115889687B (en) * 2022-11-09 2024-05-17 中国航发沈阳黎明航空发动机有限责任公司 Wax mould combination method for single crystal conjuncted guide vane air inlet edge seeding

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3942203C2 (en) * 1988-12-29 2001-04-26 Gen Electric Turbine frame arrangement
GB2250782A (en) * 1990-12-11 1992-06-17 Rolls Royce Plc Stator vane assembly
GB2250782B (en) * 1990-12-11 1994-04-27 Rolls Royce Plc Stator vane assembly
EP2422052A4 (en) * 2009-04-23 2013-01-02 Volvo Aero Corp A method for fabricating a gas turbine engine component and a gas turbine engine component
EP2422052A1 (en) * 2009-04-23 2012-02-29 Volvo Aero Corporation A method for fabricating a gas turbine engine component and a gas turbine engine component
US20200024985A1 (en) * 2013-03-07 2020-01-23 Pratt & Whitney Canada Corp. Integrated strut-vane
US20140255159A1 (en) * 2013-03-07 2014-09-11 Pratt & Whitney Canada Corp. Integrated strut-vane
EP2775098A3 (en) * 2013-03-07 2014-09-24 Pratt & Whitney Canada Corp. Integrated strut-vane
US11193380B2 (en) 2013-03-07 2021-12-07 Pratt & Whitney Canada Corp. Integrated strut-vane
US10221707B2 (en) * 2013-03-07 2019-03-05 Pratt & Whitney Canada Corp. Integrated strut-vane
EP2835503A1 (en) * 2013-08-07 2015-02-11 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
US9835038B2 (en) 2013-08-07 2017-12-05 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
US10221711B2 (en) 2013-08-07 2019-03-05 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
EP2860354A1 (en) * 2013-10-08 2015-04-15 Pratt & Whitney Canada Corp. Integrated strut and turbine vane nozzle arrangement
US9556746B2 (en) 2013-10-08 2017-01-31 Pratt & Whitney Canada Corp. Integrated strut and turbine vane nozzle arrangement
US10662815B2 (en) 2013-10-08 2020-05-26 Pratt & Whitney Canada Corp. Integrated strut and turbine vane nozzle arrangement
US9909434B2 (en) 2015-07-24 2018-03-06 Pratt & Whitney Canada Corp. Integrated strut-vane nozzle (ISV) with uneven vane axial chords
US10443626B2 (en) 2016-03-15 2019-10-15 General Electric Company Non uniform vane spacing
EP3232067A1 (en) * 2016-03-15 2017-10-18 General Electric Company Gas turbine engine ring or circular row, corresponding assembly and designing method
US10443451B2 (en) 2016-07-18 2019-10-15 Pratt & Whitney Canada Corp. Shroud housing supported by vane segments
US11371370B2 (en) 2017-07-19 2022-06-28 MTU Aero Engines AG Flow arrangement for placing in a hot gas duct of a turbomachine
FR3077329A1 (en) * 2018-01-29 2019-08-02 Safran Aircraft Engines INTER-TURBINE HOUSING COMPRISING SEPARATORY REPORTED BLADES
WO2019145648A1 (en) 2018-01-29 2019-08-01 Safran Aircraft Engines Inter-turbine casing comprising mounted splitter blades
CN111655974A (en) * 2018-01-29 2020-09-11 赛峰飞机发动机公司 Inter-turbine casing including installed splitter blades
US11143044B2 (en) 2018-01-29 2021-10-12 Safran Aircraft Engines Inter-turbine casing comprising mounted splitter blades
CN111655974B (en) * 2018-01-29 2022-05-13 赛峰飞机发动机公司 Inter-turbine casing including installed splitter blades

Also Published As

Publication number Publication date
CH426885A (en) 1966-12-31

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