GB833638A - Improvements in or relating to a method of securing turbine or compressor blades to supporting parts - Google Patents

Improvements in or relating to a method of securing turbine or compressor blades to supporting parts

Info

Publication number
GB833638A
GB833638A GB60356A GB60356A GB833638A GB 833638 A GB833638 A GB 833638A GB 60356 A GB60356 A GB 60356A GB 60356 A GB60356 A GB 60356A GB 833638 A GB833638 A GB 833638A
Authority
GB
United Kingdom
Prior art keywords
turbine
lands
blade
rotor
leading
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
GB60356A
Inventor
Kennard William Tyson
Frederick Danesbury Raper
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 GB60356A priority Critical patent/GB833638A/en
Priority to FR70933D priority patent/FR70933E/en
Publication of GB833638A publication Critical patent/GB833638A/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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K11/00—Resistance welding; Severing by resistance heating
    • B23K11/002—Resistance welding; Severing by resistance heating specially adapted for particular articles or work
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • D—TEXTILES; PAPER
    • D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
    • D06B—TREATING TEXTILE MATERIALS USING LIQUIDS, GASES OR VAPOURS
    • D06B23/00—Component parts, details, or accessories of apparatus or machines, specially adapted for the treating of textile materials, not restricted to a particular kind of apparatus, provided for in groups D06B1/00 - D06B21/00
    • 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
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
    • D—TEXTILES; PAPER
    • D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
    • D06B—TREATING TEXTILE MATERIALS USING LIQUIDS, GASES OR VAPOURS
    • D06B2700/00—Treating of textile materials, e.g. bleaching, dyeing, mercerising, impregnating, washing; Fulling of fabrics
    • D06B2700/36—Devices or methods for dyeing, washing or bleaching not otherwise provided for

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

833,638. Fixing turbine blades. ROLLSROYCE Ltd. Dec. 20, 1956 [Jan. 6, 1956], No. 603/56. Addition to 702,390. Class 110 (3). [Also in Group XXII] In a method of producing in the manufacture of turbo machines and the like a simple pressure butt-resistance welded joint between one part grooved to provide spaced lands and another part, as claimed in the parent Specification, the lands 12 are formed on a turbine or compressor rotor or stator 10, and the said other part is a turbine or compressor blade 11 of aerofoil section having greater thickness adjacent the mid-chord position than at the leading and trailing edges and the butting end of the blade is chamfered adjacent its leading and trailing edges 11a, 11b so that initially only the mid-section 11c of the butting end contacts the rotor, but during welding the whole section penetrates the lands. The leading edge chamfer 11a is at a greater angle but of less chordwise extent than the trailing edge chamfer. The grooving may be continuous annular grooves or a spiral groove but preferably parallel lenticular grooves tapering in depth and width are formed locally by milling or pressing. The parts may be welded in apparatus described in the parent Specification, or by the method claimed in Specification 806,201 in the apparatus described in that Specification. The sheet metal band or tube with slots permitting a blade to extend therethrough may be attached to the rotor or stator and the blades fed through the slots as described in the parent Specification.
GB60356A 1956-01-06 1956-01-06 Improvements in or relating to a method of securing turbine or compressor blades to supporting parts Expired GB833638A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB60356A GB833638A (en) 1956-01-06 1956-01-06 Improvements in or relating to a method of securing turbine or compressor blades to supporting parts
FR70933D FR70933E (en) 1956-01-06 1957-01-03 Improvements to turbo-machines or similar machines and to the manufacture of their parts

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB60356A GB833638A (en) 1956-01-06 1956-01-06 Improvements in or relating to a method of securing turbine or compressor blades to supporting parts

Publications (1)

Publication Number Publication Date
GB833638A true GB833638A (en) 1960-04-27

Family

ID=9707291

Family Applications (1)

Application Number Title Priority Date Filing Date
GB60356A Expired GB833638A (en) 1956-01-06 1956-01-06 Improvements in or relating to a method of securing turbine or compressor blades to supporting parts

Country Status (2)

Country Link
FR (1) FR70933E (en)
GB (1) GB833638A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10352253A1 (en) * 2003-11-08 2005-06-09 Alstom Technology Ltd Compressor blade
US20160238021A1 (en) * 2015-02-16 2016-08-18 United Technologies Corporation Compressor Airfoil

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10352253A1 (en) * 2003-11-08 2005-06-09 Alstom Technology Ltd Compressor blade
US7351039B2 (en) 2003-11-08 2008-04-01 Alstom Technology Ltd. Compressor rotor blade
US20160238021A1 (en) * 2015-02-16 2016-08-18 United Technologies Corporation Compressor Airfoil

Also Published As

Publication number Publication date
FR70933E (en) 1959-09-30

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