GB634583A - Method of making airfoils - Google Patents

Method of making airfoils

Info

Publication number
GB634583A
GB634583A GB13211/47A GB1321147A GB634583A GB 634583 A GB634583 A GB 634583A GB 13211/47 A GB13211/47 A GB 13211/47A GB 1321147 A GB1321147 A GB 1321147A GB 634583 A GB634583 A GB 634583A
Authority
GB
United Kingdom
Prior art keywords
blank
bent
tension
jaws
bend
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
GB13211/47A
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.)
Goodyear Aircraft Corp
Original Assignee
Goodyear Aircraft Corp
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 Goodyear Aircraft Corp filed Critical Goodyear Aircraft Corp
Publication of GB634583A publication Critical patent/GB634583A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21DWORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00Making other particular articles
    • B21D53/78Making other particular articles propeller blades; turbine blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Clamps And Clips (AREA)
  • Bending Of Plates, Rods, And Pipes (AREA)

Abstract

634,583. Making parts of aircraft. GOODYEAR AIRCRAFT CORPORATION. May 16, 1947, No. 13211. Convention date, Nov. 26, 1946. [Classes 83 (ii) and 83 (iv)] Angular bending; stretching; stamping.- A step in a process for making an airfoil and more particularly a leading edge for a helicopter blade comprises applying a longitudinal tension to a blank so as to tension it strongly, but below its elastic limit and then gripping the tensioned blank at closelyspaced areas and applying additional stress to permanently bend the blank therebetween. A blank 1 of sheet stainless steel, formed with holes 2 and slits 3 is bent longitudinally to U-shape in cross-section and placed in a tensioning and bending device. This comprises a pair of heavy members pivoted at 7, connected on one side of the pivot by a pressure cylinder 6 and at the other side formed as jaws with portions 8 adapted to be tightly clamped on to the blank, suitable filler blocks being placed within the blank. From each jaw extends an elongated channel-member 9 having at its outer end a plate 11 secured by bolts 12 to a clamp 13 or 14 adapted to grip the ends of the blank. The blank is placed in the device in the position shown in dotted lines in Fig. 3, the clamps 13 and 14 are tightened and the bolts 12 turned so as to put the blank under a tension which never exceeds and is preferably ten to twenty per cent below the elastic limit. The clamps 8 are then tightened on to the work and the jaws move apart so as to stretch a short length of the blank to beyond the yield point and give it a permanent bend as indicated in full lines in the Fig. 3. By turning the jaws over and arranging the pivot at the end as shown in Fig. 4, the blank is given another bend in the reverse direction near its other end. The bent blank is then trimmed as indicated by the full lines 16 in Fig. 5, so that the curved bottom part is shorter than the top, formed by straight upper edges 15 which are then bent at right angles along the line 15a to form a flange by which the blank is clamped by a member 18 within a channelled member 17. By supporting the member 17 by a number of clamping frames 21, a former 20 may be slowly forced down into the blank so as to draw it to the required final form, after which the ends are cut square and the flange removed.
GB13211/47A 1946-11-26 1947-05-16 Method of making airfoils Expired GB634583A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US634583XA 1946-11-26 1946-11-26

Publications (1)

Publication Number Publication Date
GB634583A true GB634583A (en) 1950-03-22

Family

ID=22049327

Family Applications (1)

Application Number Title Priority Date Filing Date
GB13211/47A Expired GB634583A (en) 1946-11-26 1947-05-16 Method of making airfoils

Country Status (1)

Country Link
GB (1) GB634583A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10005348A1 (en) * 2000-02-08 2001-08-16 Eads Airbus Gmbh Aerodynamic surface edge structure manufacturing method uses screw movement between left and right mold parts for applying pressure to parallel metal stringers at rear of sheet metal outer skin
WO2013037999A1 (en) * 2011-09-16 2013-03-21 Siemens Aktiengesellschaft Compressor blade and method for the production thereof

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10005348A1 (en) * 2000-02-08 2001-08-16 Eads Airbus Gmbh Aerodynamic surface edge structure manufacturing method uses screw movement between left and right mold parts for applying pressure to parallel metal stringers at rear of sheet metal outer skin
US6415510B2 (en) 2000-02-08 2002-07-09 Airbus Deutschland Gmbh Method of fabricating leading edge nose structures of aerodynamic surfaces
DE10005348B4 (en) * 2000-02-08 2004-05-06 Airbus Deutschland Gmbh Process for the manufacture of nose structures for aerodynamic surfaces
WO2013037999A1 (en) * 2011-09-16 2013-03-21 Siemens Aktiengesellschaft Compressor blade and method for the production thereof
US9234429B2 (en) 2011-09-16 2016-01-12 Siemens Aktiengesellschaft Method for producing a compressor blade by forging and uniaxially stretching

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