US2090468A - Turbine blade - Google Patents

Turbine blade Download PDF

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Publication number
US2090468A
US2090468A US62741A US6274136A US2090468A US 2090468 A US2090468 A US 2090468A US 62741 A US62741 A US 62741A US 6274136 A US6274136 A US 6274136A US 2090468 A US2090468 A US 2090468A
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US
United States
Prior art keywords
blades
packing
blade
turbine
sections
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
US62741A
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English (en)
Inventor
Brown David Somers
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.)
PARSONS MACHINE STEAM TURBINE
PARSONS MACHINE STEAM TURBINE COMPANY Ltd
Original Assignee
PARSONS MACHINE STEAM TURBINE
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 PARSONS MACHINE STEAM TURBINE filed Critical PARSONS MACHINE STEAM TURBINE
Application granted granted Critical
Publication of US2090468A publication Critical patent/US2090468A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers

Definitions

  • the invention relates to turbine blades and more particularly to assemblies of such blades into unit groups, such as sectors, for mounting on their carrier members;
  • blades andpacking sections are arrangedalternately in a'former to build up a sector of the required size and are held in place temporarily, e. .g., by' a root-wire threaded through them, by a shroud, or by tack-welding,
  • a suitable flux e-. g., a solution of borax
  • an appropriate molten metal e. g., a brazing mixture
  • the main object of the invention is to overcome these diflficulties.
  • the invention consists in the improved blade assemblies, blades and packing pieces hereinafter described and particularly pointed out in the claims appendant hereto.
  • Figure 1 shows a side view of one form of assembly of blades and intermediate distance pieces, held in place by a root wire;
  • Figure 2 being an elevation of one blade and distance piece
  • Figure 3 shows an elevation of one blade and distance piece having a longitudinal ridge on each face
  • Figure 4 being a corresponding end view of two blades and three distance pieces
  • Figures 5 and 6 are views similar to Figures 3 and 4 in which the distance pieces each have three longitudinal ridges on one face and two on the other; 1 Figures '7, 8, 9 and 10 show modified forms in which the projections take the form of isolated patches arranged at the angles of a triangle;
  • each packing section (see Figures 3 and 4) each packing section
  • b,- is provided with a slightly raised ridge, d, running across its two faces associated with the 20 adjacent blades, the ridge being very readily produced at the time a length of metal is rolled, drawn, extruded or otherwise brought to shape before'being'cut into short lengths to form the packing sections. 5
  • the blades and packing so assembled may be temporarilyheld in place by a wire, e, threaded through the packing sections and adjacent roots of the -blades,-(see Figures 1 and 2) by tackwelding or as heretofore proposed by a binding 30 wire or by a shroud.
  • the appropriate part of the assembly is then dipped into a cleaning bath, preferably in a boil-. ing condition, and immediately afterwards immersed in molten metal, e. g., .a brazing mixture, 35 which on cooling effects the permanent attachment between the blades and packing sections.
  • molten metal e. g., .a brazing mixture
  • each packing section, b is provided with five projecting ridges, d, parallel to the length of the blade, three on the one face 45 and two on the other.
  • two ridges may be provided on each face or any other number of ridges may be provided in any desired combination.
  • the temporary connection is pref- 5O erably made by a threaded wire, e, since tack-welding on the lower surfaces of blades and packing sections may close entirely access of the flux or the like to the space between the two parallel ridges and the blade in contact therewith. 5
  • the slight projections may be of many different shapes and if isolated patches, 1, (see Figures '7 and 8, where the patches are circular and Figures 9 and 10 where they are square) are preferably arranged at the angles of a triangle with the apex either up-or down as shown so as to provide three projections per pair of surfaces to be attached, it may be two on one surface and one on the other,
  • the projections are made on the blades and either take the form of ridges or patches as above or are provided by corrugating the'knife edge of the blade to a sinusoidal form in way of the packing sections as shown at h, Figure 12, the hollows and troughsof the corrugations being made, by pinching areas such as 1', Figure II, a1- ternately in opposite directions.
  • the corrugations diagrammatically shown in Figures 13 and 14 project from the untreated edge of the blade and hold the packing sectional), a slight distance apart,
  • the desired spacing of blades and packing sections may in some cases be secured by introducing a'length of wire of suitable gauge, e. g., a staple straddling the assembling wire, e, before completing the union.
  • a'length of wire of suitable gauge e. g., a staple straddling the assembling wire, e, before completing the union.
  • turbine blade as used above is broad enough to include the blades of turbo-compressors and the like.
  • a unit group of assembled turbine blades of the character described comprising a series of blades with knife edges sinusoidal at least at their root ends, intermediate root pieces with surfaces juxtaposed adjacent to said sinusoidal parts of said blades, together with joining material filling the space between said root pieces and said juxtaposed sinusoidal parts.
  • a unit group of assembled turbine blades of the character described comprising in combination a seris of turbine blades each having a root; associated packing pieces disposed in the neighborhood of said roots with surfaces of said roots and of said packing-pieces juxtaposed and spacing projections locatedbetween said juxtaposed surfaces and individually integral with one of them, said spacing devices comprising isolated patches of small thickness in triangular configuration, with joining material in the free spaces left between said juxtaposed surfaces.
  • a root packing piece forspaced turbine blades in which at least one operative face has integral therewith a plurality of isolated spacing projections of small thickness, said projections being arranged in triangular configuration.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US62741A 1935-02-15 1936-02-07 Turbine blade Expired - Lifetime US2090468A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4887/35A GB452027A (en) 1935-02-15 1935-02-15 Improvements in and relating to turbine blades

Publications (1)

Publication Number Publication Date
US2090468A true US2090468A (en) 1937-08-17

Family

ID=9785716

Family Applications (1)

Application Number Title Priority Date Filing Date
US62741A Expired - Lifetime US2090468A (en) 1935-02-15 1936-02-07 Turbine blade

Country Status (3)

Country Link
US (1) US2090468A (xx)
GB (1) GB452027A (xx)
NL (1) NL40782C (xx)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2654143A (en) * 1949-08-24 1953-10-06 Allis Chalmers Mfg Co Method of making welded blade structures
US2807435A (en) * 1951-06-12 1957-09-24 Fairchild Engine & Airplane Turbine stator blade
US2808228A (en) * 1950-08-01 1957-10-01 Rolls Royce Turbo-machines
US2894318A (en) * 1952-10-08 1959-07-14 Gen Electric Turbomachine bucket-wheel fabricated by casting

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2654143A (en) * 1949-08-24 1953-10-06 Allis Chalmers Mfg Co Method of making welded blade structures
US2808228A (en) * 1950-08-01 1957-10-01 Rolls Royce Turbo-machines
US2807435A (en) * 1951-06-12 1957-09-24 Fairchild Engine & Airplane Turbine stator blade
US2894318A (en) * 1952-10-08 1959-07-14 Gen Electric Turbomachine bucket-wheel fabricated by casting

Also Published As

Publication number Publication date
GB452027A (en) 1936-08-17
NL40782C (xx)

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