GB656634A - Improvements in or relating to blades for turbines or compressors - Google Patents

Improvements in or relating to blades for turbines or compressors

Info

Publication number
GB656634A
GB656634A GB12649A GB12649A GB656634A GB 656634 A GB656634 A GB 656634A GB 12649 A GB12649 A GB 12649A GB 12649 A GB12649 A GB 12649A GB 656634 A GB656634 A GB 656634A
Authority
GB
United Kingdom
Prior art keywords
portions
blade
machined
recesses
turbine
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
GB12649A
Inventor
James Alexander Petrie
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 GB12649A priority Critical patent/GB656634A/en
Publication of GB656634A publication Critical patent/GB656634A/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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

656,634. Turbine and compressor blades. ROLLS-ROYCE, Ltd. Jan. 3, 1949, No. 126. [Class 110(iii)] [Also in Group XXII] A hollow compressor or turbine blade is made by forming the leading portion 10a with an integral root part 10c and the trailing portion 11a with an integral root part 11c the two portions being shaped so as to abut over surfaces extending lengthwise of the blade, machining a longitudinal recess 13, 14 in at least one of the portions 10 or 11 and then permanently securing the portions together over their abutment surfaces Each portion is formed from a cast or forged blank and the abutment surfaces 16 and 17 are co - planar. Recesses 13 are machined in each part with a cutter of V-section and meet up with recesses 14 machined in the root portions. The blade tip may have a shroud 10b, 11b of parallelogram form. The two parts of the blade are joined by welding or brazing along the abutting surfaces.
GB12649A 1949-01-03 1949-01-03 Improvements in or relating to blades for turbines or compressors Expired GB656634A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB12649A GB656634A (en) 1949-01-03 1949-01-03 Improvements in or relating to blades for turbines or compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB12649A GB656634A (en) 1949-01-03 1949-01-03 Improvements in or relating to blades for turbines or compressors

Publications (1)

Publication Number Publication Date
GB656634A true GB656634A (en) 1951-08-29

Family

ID=9698866

Family Applications (1)

Application Number Title Priority Date Filing Date
GB12649A Expired GB656634A (en) 1949-01-03 1949-01-03 Improvements in or relating to blades for turbines or compressors

Country Status (1)

Country Link
GB (1) GB656634A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
WO2006108764A1 (en) * 2005-04-14 2006-10-19 Alstom Technology Ltd Convectively cooled gas turbine blade
CN103586647A (en) * 2013-10-14 2014-02-19 西安航空动力股份有限公司 Forming method of aeroengine hollow guide vane

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
WO2006108764A1 (en) * 2005-04-14 2006-10-19 Alstom Technology Ltd Convectively cooled gas turbine blade
US7766619B2 (en) 2005-04-14 2010-08-03 Alstom Technology Ltd Convectively cooled gas turbine blade
CN103586647A (en) * 2013-10-14 2014-02-19 西安航空动力股份有限公司 Forming method of aeroengine hollow guide vane
CN103586647B (en) * 2013-10-14 2015-12-02 西安航空动力股份有限公司 A kind of forming method of aeroengine hollow guide vane

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