CH426885A - Bladed intermediate floor for turbines and processes for their manufacture - Google Patents

Bladed intermediate floor for turbines and processes for their manufacture

Info

Publication number
CH426885A
CH426885A CH1616364A CH1616364A CH426885A CH 426885 A CH426885 A CH 426885A CH 1616364 A CH1616364 A CH 1616364A CH 1616364 A CH1616364 A CH 1616364A CH 426885 A CH426885 A CH 426885A
Authority
CH
Switzerland
Prior art keywords
disc
ring
assembly
spokes
blades
Prior art date
Application number
CH1616364A
Other languages
German (de)
Inventor
Adolf Dr Frankel
Original Assignee
Ass Elect Ind
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 Ass Elect Ind filed Critical Ass Elect Ind
Publication of CH426885A publication Critical patent/CH426885A/en

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

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).
CH1616364A 1963-12-24 1964-12-15 Bladed intermediate floor for turbines and processes for their manufacture CH426885A (en)

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
CH426885A true CH426885A (en) 1966-12-31

Family

ID=10457718

Family Applications (1)

Application Number Title Priority Date Filing Date
CH1616364A CH426885A (en) 1963-12-24 1964-12-15 Bladed intermediate floor for turbines and processes for their manufacture

Country Status (2)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140010643A1 (en) * 2011-03-11 2014-01-09 Alstom Technology Ltd. Method of fabricating a steam turbine deflector

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
GB2250782B (en) * 1990-12-11 1994-04-27 Rolls Royce Plc Stator vane assembly
US20120121395A1 (en) * 2009-04-23 2012-05-17 Volvo Aero Corporation Method for fabricating a gas turbine engine component and a gas turbine engine component
US10221707B2 (en) * 2013-03-07 2019-03-05 Pratt & Whitney Canada Corp. Integrated strut-vane
US9835038B2 (en) 2013-08-07 2017-12-05 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
US9556746B2 (en) * 2013-10-08 2017-01-31 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
US10443451B2 (en) 2016-07-18 2019-10-15 Pratt & Whitney Canada Corp. Shroud housing supported by vane segments
DE102017212311A1 (en) 2017-07-19 2019-01-24 MTU Aero Engines AG Umströmungsanordung for arranging in the hot gas duct of a turbomachine
FR3077329B1 (en) 2018-01-29 2022-06-24 Safran Aircraft Engines INTER-TURBINE CASING COMPRISING ATTACHED SEPARATOR VANE

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140010643A1 (en) * 2011-03-11 2014-01-09 Alstom Technology Ltd. Method of fabricating a steam turbine deflector
US9604323B2 (en) * 2011-03-11 2017-03-28 General Electric Technology Gmbh Method of fabricating a steam turbine deflector

Also Published As

Publication number Publication date
GB1058759A (en) 1967-02-15

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