US2617179A - Method of manufacturing tapered beams - Google Patents

Method of manufacturing tapered beams Download PDF

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Publication number
US2617179A
US2617179A US161152A US16115250A US2617179A US 2617179 A US2617179 A US 2617179A US 161152 A US161152 A US 161152A US 16115250 A US16115250 A US 16115250A US 2617179 A US2617179 A US 2617179A
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Prior art keywords
web
tapered
section
bulbous
forging
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Expired - Lifetime
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US161152A
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Walter F Burke
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McDonnell Aircraft Corp
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McDonnell Aircraft Corp
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Publication date
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Priority to US161152A priority Critical patent/US2617179A/en
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Publication of US2617179A publication Critical patent/US2617179A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C25/00—Profiling tools for metal extruding
    • B21C25/08—Dies or mandrels with section variable during extruding, e.g. for making tapered work; Controlling variation
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S29/00—Metal working
    • Y10S29/047—Extruding with other step
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49616—Structural member making
    • Y10T29/49623—Static structure, e.g., a building component
    • Y10T29/49634—Beam or girder

Definitions

  • This invention relates to the manufacture of structural elements for aircraft and is particularly directed to the manufacture of tapered beams or spars therefor.
  • the primary object of the invention is to produce a tapered I-beam or spar from a uniform section I-beam having an enlarged web portion.
  • Another object of the invention is to produce a tapered I-beam or spar requiring only a minimum of metal working or machining.
  • a further object of the invention is to produce a flanged tapered beam whose parts have a desired thickness and formed from a uniform section flanged beam provided with a bulbous web.
  • a still further object of the invention is to produce a tapered beam from a uniform section I-beam having a bulbous Web in which the flanges of the I-beam retain their original size as the bulbous web is forged for tapering the beam.
  • the invention consists in forming an I-beam by extruding, rolling, or forging so that the web thereof is enlarged, after which a suitable length is cut therefrom and the web forged to reduce its section at one end of the beam for tapering thereof, and then machining the web to the desired thickness and also machining the flanges of the beam to the proportions desired, should the latter be necessary.
  • Fig. 1 is a side elevational view of an I-beam made in accordance with the invention
  • Fig. 2 is a sectional view taken along the line 2-2 of Fig. 1,
  • Fig. 3 is a side elevational view of the beam after a metal forming operation
  • Fig. 4 is a sectional view taken substantially along the line 4-4 of Fig. 3,
  • Fig. 5 is a sectional view taken substantially along the line 5-5 of Fig. 3,
  • Fig. 6 is a side elevational view of the I-beam after it has been machined
  • Fig. 7 is a sectional view taken along the line 17 of Fig. 6;
  • Fig. 8 is a sectional view taken substantially along the line 88 of Fig. 6.
  • FIG. l of the drawings in which the numeral I indicates an I-beam having a comparatively large flange 2 on one edge thereof and a smaller flange 3 on the opposite edge.
  • the web 4 of the I-beam is made bulbous, as particularly shown in Fig. 2.
  • the I-beam is preferably made of soft, ductile metal and the 2 Claims. 01129-155) 2 shape illustrated may be extruded, rolled, or forged as desired.
  • a suitable length is out from a stock beam and the bulbous Web 4 then subjected to a forging or pressing operation for the purpose of changing the section thereof in order to form a tapered I-beam which is particularly useful in aircraft construction.
  • the foregoing of the bulbous web is continued until the beam is made substantially the desired size.
  • the amount of forging done on the web varies from one end of the beam to the other in order that the web section may taper, thereby tapering the beam in direct proportion.
  • the forging operation causes the flanges 2 and 3 to be spread apart, the bulbous section of the beam gradually increasing toward the smaller end thereof so that it will be substantially the same as that illustrated in Figs. 2 and 5.
  • the partially completed tapered I-beam is then subjected to .a machining operation.
  • the web of the beam is reduced to its desired section, which may be either uniform or variable, as the load requirements to be imposed on the beam may dictate.
  • the forging operation on the web may have a tendency to distort flanges 2 and 3, and they may also be machined in order to present a clean, smooth surface to the cooperating structure of the aircraft.
  • the machining may be done by a planer, a miller, a shaper, or any other suitable machining tool, which machining will remove any unevenness in the surfaces of the web section or flanges resulting from the forging or pressing operation.
  • the method of producing a tapered I-beam as described is a material advance in the art over the methods of manufacture previously practiced.
  • One of these methods was to cut a tapered I-beam from a solid extruded or rolled section as large as the maximum size of the tapered beam, and therafter machining the excess material for forming the flanges and the web.
  • the above described method eliminates the use of costly die work that would be necessary in a rolling or forging operation for forming a tapered I-beam. Applicant's method has also reduced the amount of material wasted, as well as the time necessary for manufacturing a tapered I-beam. The over-all economy in material and labor very materially reduces the unit cost of the completed tapered I-beam.
  • the method of manufacturing a tapered beam member from a beam having parallel 3 flanges connected by a bulbous web section which comprises forging the bulbous section progressively and in varying amounts from one end toward the opposite end while allowing the opposite margins to move laterally and freely into a tapering relation varying from one end to the opposite end and proportionately with the forging of the bulbous section, and machine finish ing the web section to final desired dimensions.
  • the method of manufacturing a tapered beam member from a beam having parallel flanges connected by a bulbous web section which comprises forging the bulbous section progressively and in varying amounts from one end toward the opposite end while allowing the opposite margins to move laterally and freely into a tapering relation varying from one end to the opposite end proportionately with the forging of the bulbous section, and machine finishing the flanges to final desired dimensions.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Forging (AREA)

Description

METHOD OF MANUFACTURING TAPERED BEAMS Filed May 10, 1950 2 FIG. l.
INVENTOR. WALTER F. BURKE CM/WCW ATTORNEYS.
Patented Nov. 11, 1952 METHOD OF MANUFACTURING TAPERED' BEAMS Walter F. Burke, St. Louis, Mo., assignor to Mc- Donnell Aircraft Corporation, St. Louis, Mo., a
corporation of Maryland Application May 10, 1950, Serial No. 161,152
This invention relates to the manufacture of structural elements for aircraft and is particularly directed to the manufacture of tapered beams or spars therefor.
The primary object of the invention is to produce a tapered I-beam or spar from a uniform section I-beam having an enlarged web portion.
Another object of the invention is to produce a tapered I-beam or spar requiring only a minimum of metal working or machining.
A further object of the invention is to produce a flanged tapered beam whose parts have a desired thickness and formed from a uniform section flanged beam provided with a bulbous web.
A still further object of the invention is to produce a tapered beam from a uniform section I-beam having a bulbous Web in which the flanges of the I-beam retain their original size as the bulbous web is forged for tapering the beam.
The invention consists in forming an I-beam by extruding, rolling, or forging so that the web thereof is enlarged, after which a suitable length is cut therefrom and the web forged to reduce its section at one end of the beam for tapering thereof, and then machining the web to the desired thickness and also machining the flanges of the beam to the proportions desired, should the latter be necessary.
In the drawings:
Fig. 1 is a side elevational view of an I-beam made in accordance with the invention,
Fig. 2 is a sectional view taken along the line 2-2 of Fig. 1,
Fig. 3 is a side elevational view of the beam after a metal forming operation,
Fig. 4 is a sectional view taken substantially along the line 4-4 of Fig. 3,
Fig. 5 is a sectional view taken substantially along the line 5-5 of Fig. 3,
Fig. 6 is a side elevational view of the I-beam after it has been machined,
Fig. 7 is a sectional view taken along the line 17 of Fig. 6; and
Fig. 8 is a sectional view taken substantially along the line 88 of Fig. 6.
This invention is practiced on the structural member illustrated in Fig. l of the drawings in which the numeral I indicates an I-beam having a comparatively large flange 2 on one edge thereof and a smaller flange 3 on the opposite edge. The web 4 of the I-beam is made bulbous, as particularly shown in Fig. 2. The I-beam is preferably made of soft, ductile metal and the 2 Claims. 01129-155) 2 shape illustrated may be extruded, rolled, or forged as desired.
A suitable length is out from a stock beam and the bulbous Web 4 then subjected to a forging or pressing operation for the purpose of changing the section thereof in order to form a tapered I-beam which is particularly useful in aircraft construction. The foregoing of the bulbous web is continued until the beam is made substantially the desired size. The amount of forging done on the web varies from one end of the beam to the other in order that the web section may taper, thereby tapering the beam in direct proportion. The forging operation causes the flanges 2 and 3 to be spread apart, the bulbous section of the beam gradually increasing toward the smaller end thereof so that it will be substantially the same as that illustrated in Figs. 2 and 5. When the forging or pressing operation has been completed on the bulbous web, the partially completed tapered I-beam is then subjected to .a machining operation. During this operation the web of the beam is reduced to its desired section, which may be either uniform or variable, as the load requirements to be imposed on the beam may dictate. The forging operation on the web may have a tendency to distort flanges 2 and 3, and they may also be machined in order to present a clean, smooth surface to the cooperating structure of the aircraft. The machining may be done by a planer, a miller, a shaper, or any other suitable machining tool, which machining will remove any unevenness in the surfaces of the web section or flanges resulting from the forging or pressing operation.
The method of producing a tapered I-beam as described, is a material advance in the art over the methods of manufacture previously practiced. One of these methods was to cut a tapered I-beam from a solid extruded or rolled section as large as the maximum size of the tapered beam, and therafter machining the excess material for forming the flanges and the web.
The above described method eliminates the use of costly die work that would be necessary in a rolling or forging operation for forming a tapered I-beam. Applicant's method has also reduced the amount of material wasted, as well as the time necessary for manufacturing a tapered I-beam. The over-all economy in material and labor very materially reduces the unit cost of the completed tapered I-beam.
What I claim is:
1. The method of manufacturing a tapered beam member from a beam having parallel 3 flanges connected by a bulbous web section, which comprises forging the bulbous section progressively and in varying amounts from one end toward the opposite end while allowing the opposite margins to move laterally and freely into a tapering relation varying from one end to the opposite end and proportionately with the forging of the bulbous section, and machine finish ing the web section to final desired dimensions.
2. The method of manufacturing a tapered beam member from a beam having parallel flanges connected by a bulbous web section, which comprises forging the bulbous section progressively and in varying amounts from one end toward the opposite end while allowing the opposite margins to move laterally and freely into a tapering relation varying from one end to the opposite end proportionately with the forging of the bulbous section, and machine finishing the flanges to final desired dimensions.
WABTER F. BURKE.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 679,759 Lanz Aug. 6, 1901 1,656,846 Witherow 'Jan. 17, 1928 1,746,520 Brody Feb. 11, 1930 1,814,593 Gersman July 14, 1931 1,857,582 Bender May 10, 1932 FOREIGN PATENTS Number Country Date 673,211 Germany Mar. 17, 1939
US161152A 1950-05-10 1950-05-10 Method of manufacturing tapered beams Expired - Lifetime US2617179A (en)

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2716806A (en) * 1952-07-08 1955-09-06 Macdonald S Reed Milling and stretching integral panels
US2716805A (en) * 1952-07-08 1955-09-06 Macdonald S Reed Extruding integrally stiffened panels
US2748460A (en) * 1951-01-18 1956-06-05 Conmar Prod Corp Method of manufacturing sliders for slide fasteners
US2756491A (en) * 1952-09-16 1956-07-31 Conmar Prod Corp Manufacture of sliders for slide fasteners
US2909061A (en) * 1955-11-17 1959-10-20 Boeing Co Drag sensitive wind tunnel model support
US3164898A (en) * 1960-08-09 1965-01-12 Guy F Kotrbaty Method of producing extruded shapes
US3282017A (en) * 1963-05-14 1966-11-01 Frank C Rothermel Method of providing increased strength to composite beam construction
US3672038A (en) * 1970-05-05 1972-06-27 Lombard Corp Method and apparatus for producing extruded steel shapes
US5465487A (en) * 1993-08-23 1995-11-14 Dean; Charles W. Method of making a rigid frame construction
US5787559A (en) * 1993-08-23 1998-08-04 Dean; Charles W. Rigid frame construction apparatus
US5875905A (en) * 1997-06-11 1999-03-02 United Fixtures Company Tapered cantilevered support arm for storage rack systems
US20090095413A1 (en) * 2005-06-17 2009-04-16 The Boeing Company Composite reinforcement of metallic structural elements
US20100135818A1 (en) * 2009-12-01 2010-06-03 Achuthan Babu Systems and methods of assembling a rotor blade for use in a wind turbine
US20110142662A1 (en) * 2010-10-28 2011-06-16 General Electric Company Spar Cap Assembly for a Wind Turbine Rotor Blade
WO2013162671A3 (en) * 2012-02-14 2014-02-20 Gulfstream Aerospace Corporation Reinforced composite structures for aircrafts and methods for making the same
US9109352B1 (en) * 2014-03-14 2015-08-18 Gary A. Knudson Metal building system
US20150375843A1 (en) * 2014-06-26 2015-12-31 The Boeing Company Elongated Structures and Related Assemblies
US11312468B2 (en) * 2018-08-08 2022-04-26 The Boeing Company Elongate structures, structural assemblies with elongate structures, and methods for supporting a structural load

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US679759A (en) * 1901-05-03 1901-08-06 John Lanz Method of forming plates or blanks of varying widths.
US1656846A (en) * 1921-12-30 1928-01-17 Colonial Trust Co Method of making axle blanks
US1746520A (en) * 1927-04-12 1930-02-11 Kalman Steel Company Inc Production of expanded load-bearing members
US1814593A (en) * 1926-06-21 1931-07-14 Harvey M Gersman Process for widening rolled metal products
US1857582A (en) * 1927-05-05 1932-05-10 Ramapo Ajax Corp Method of making forged compromise bars
DE673211C (en) * 1932-11-06 1939-03-17 Bamag Meguin Akt Ges Die for re-forging thick-web rail profiles in such greater heights

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US679759A (en) * 1901-05-03 1901-08-06 John Lanz Method of forming plates or blanks of varying widths.
US1656846A (en) * 1921-12-30 1928-01-17 Colonial Trust Co Method of making axle blanks
US1814593A (en) * 1926-06-21 1931-07-14 Harvey M Gersman Process for widening rolled metal products
US1746520A (en) * 1927-04-12 1930-02-11 Kalman Steel Company Inc Production of expanded load-bearing members
US1857582A (en) * 1927-05-05 1932-05-10 Ramapo Ajax Corp Method of making forged compromise bars
DE673211C (en) * 1932-11-06 1939-03-17 Bamag Meguin Akt Ges Die for re-forging thick-web rail profiles in such greater heights

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2748460A (en) * 1951-01-18 1956-06-05 Conmar Prod Corp Method of manufacturing sliders for slide fasteners
US2716806A (en) * 1952-07-08 1955-09-06 Macdonald S Reed Milling and stretching integral panels
US2716805A (en) * 1952-07-08 1955-09-06 Macdonald S Reed Extruding integrally stiffened panels
US2756491A (en) * 1952-09-16 1956-07-31 Conmar Prod Corp Manufacture of sliders for slide fasteners
US2909061A (en) * 1955-11-17 1959-10-20 Boeing Co Drag sensitive wind tunnel model support
US3164898A (en) * 1960-08-09 1965-01-12 Guy F Kotrbaty Method of producing extruded shapes
US3282017A (en) * 1963-05-14 1966-11-01 Frank C Rothermel Method of providing increased strength to composite beam construction
US3672038A (en) * 1970-05-05 1972-06-27 Lombard Corp Method and apparatus for producing extruded steel shapes
US5465487A (en) * 1993-08-23 1995-11-14 Dean; Charles W. Method of making a rigid frame construction
US5787559A (en) * 1993-08-23 1998-08-04 Dean; Charles W. Rigid frame construction apparatus
US5875905A (en) * 1997-06-11 1999-03-02 United Fixtures Company Tapered cantilevered support arm for storage rack systems
US20090095413A1 (en) * 2005-06-17 2009-04-16 The Boeing Company Composite reinforcement of metallic structural elements
US20100135818A1 (en) * 2009-12-01 2010-06-03 Achuthan Babu Systems and methods of assembling a rotor blade for use in a wind turbine
US8702397B2 (en) * 2009-12-01 2014-04-22 General Electric Company Systems and methods of assembling a rotor blade for use in a wind turbine
US20110142662A1 (en) * 2010-10-28 2011-06-16 General Electric Company Spar Cap Assembly for a Wind Turbine Rotor Blade
WO2013162671A3 (en) * 2012-02-14 2014-02-20 Gulfstream Aerospace Corporation Reinforced composite structures for aircrafts and methods for making the same
US8703269B2 (en) 2012-02-14 2014-04-22 Gulfstream Aerospace Corporation Reinforced composite structures for aircrafts and methods for making the same
US9109352B1 (en) * 2014-03-14 2015-08-18 Gary A. Knudson Metal building system
US20150375843A1 (en) * 2014-06-26 2015-12-31 The Boeing Company Elongated Structures and Related Assemblies
US9527572B2 (en) * 2014-06-26 2016-12-27 The Boeing Company Elongated structures and related assemblies
US9950779B2 (en) 2014-06-26 2018-04-24 The Boeing Company Elongated structures and related assemblies
US10207786B2 (en) 2014-06-26 2019-02-19 The Boeing Company Elongated structures and related assemblies
US11312468B2 (en) * 2018-08-08 2022-04-26 The Boeing Company Elongate structures, structural assemblies with elongate structures, and methods for supporting a structural load

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