GB2508038A - Structural beam - Google Patents

Structural beam Download PDF

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Publication number
GB2508038A
GB2508038A GB1301846.0A GB201301846A GB2508038A GB 2508038 A GB2508038 A GB 2508038A GB 201301846 A GB201301846 A GB 201301846A GB 2508038 A GB2508038 A GB 2508038A
Authority
GB
United Kingdom
Prior art keywords
support element
beam according
support
ribs
clement
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.)
Granted
Application number
GB1301846.0A
Other versions
GB201301846D0 (en
GB2508038B (en
Inventor
Timothy John Evans
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.)
ESTRESS Ltd
Original Assignee
ESTRESS Ltd
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 ESTRESS Ltd filed Critical ESTRESS Ltd
Publication of GB201301846D0 publication Critical patent/GB201301846D0/en
Publication of GB2508038A publication Critical patent/GB2508038A/en
Application granted granted Critical
Publication of GB2508038B publication Critical patent/GB2508038B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C3/00—Structural elongated elements designed for load-supporting
    • E04C3/30—Columns; Pillars; Struts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/065—Rotors characterised by their construction elements
    • F03D1/0675—Rotors characterised by their construction elements of the blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/185—Spars
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C3/00—Structural elongated elements designed for load-supporting
    • E04C3/02—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces
    • E04C3/04—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C3/00—Structural elongated elements designed for load-supporting
    • E04C3/30—Columns; Pillars; Struts
    • E04C3/32—Columns; Pillars; Struts of metal
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C3/00—Structural elongated elements designed for load-supporting
    • E04C3/02—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces
    • E04C3/04—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal
    • E04C2003/0404—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal beams, girders, or joists characterised by cross-sectional aspects
    • E04C2003/0426—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal beams, girders, or joists characterised by cross-sectional aspects characterised by material distribution in cross section
    • E04C2003/043—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal beams, girders, or joists characterised by cross-sectional aspects characterised by material distribution in cross section the hollow cross-section comprising at least one enclosed cavity
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C3/00—Structural elongated elements designed for load-supporting
    • E04C3/02—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces
    • E04C3/04—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal
    • E04C2003/0404—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal beams, girders, or joists characterised by cross-sectional aspects
    • E04C2003/0443—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal beams, girders, or joists characterised by cross-sectional aspects characterised by substantial shape of the cross-section
    • E04C2003/0447—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of metal beams, girders, or joists characterised by cross-sectional aspects characterised by substantial shape of the cross-section circular- or oval-shaped
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Landscapes

  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Mechanical Engineering (AREA)
  • Structural Engineering (AREA)
  • Civil Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)
  • Laser Beam Processing (AREA)

Abstract

A beam comprising a first support element 1 being operative to resist applied longitudinal compressive or tensioning force and a second support element 2, free to move longitudinally with respect to the first support element. The first support element is located within the second support element and may inter-engage laterally via discrete ribs 4 positioned along the length of the second support element so as to resist lateral bending forces. The ribs may be made of a composite material or a metal such as aluminium or titanium adhesively bonded to the second support element. Preferably the second support member is an aerofoil profile and may be used as a wind turbine blade or as an aircraft wing.

Description

Structural Beam The present invention relates to a beam for use as a structural engineering element.
Tt is known from British Patent 0B22991038 to provide a strut comprising a first support element and a second support element extending longitudinally alongside one another, the first support element being operative to resist applied longitudinal compressive or tensioning force, the second support element being interconnected with the first support element so as to resist buckling of the first support element. In GB22991033 the second support element is fl-cc to movc longitudinally along thc first support clcn1ent. The first and sccond support elements inter-engage laterally by radial contact along the complete longitudinal length of the second support element.
A beam according to the present invention comprises a first support element and a second support element extending longitudinally alongside one another, the first support element being operative to resist applied longitudinal compressive or tensioning force, and the first and second elements being operative to resist lateral bending forces. The second support element is interconnected with the first support element at discrete positions so as to resist buckling and bending of the first support element. The second support element is free to move longitudinally with respect to the first support element.
It is prefened that the first and second support elements are arranged one within the other so as to inter-engage laterally by ribs positioned along the length of the second support element.
The second support element preferably makes a radial mechanical contact fit with the first support elemcnt via the ribs so as to be longitudinally slidable thereon. The second support element preferably acts as a female tubular sleeve with respect to the first element.
The first element is preferably a metallic tube or rod. The metal can be a steel or an aluminium or titanium alloy.
The second support element is composed of a material less dense than that of the first element. This has the advantage of adding bending stiffness to the beam without a great increase in weight. The second support element is preferably composed of an advanced or composite material, such as carbon, aphite, Keviar (trade mark), glass, ceramic, metal matrix, or composite materials including at least one or a combination of these materials.
Altcrnativcly thc sccond clcmcnt could bc of\vood.
The ribs are preferably diaphragms made of a composite such as Tufnol (trade mark).
Alternatively thc ribs could bc metallic. The first clement passes through an aperture in the nb. The first element inter-engages laterally with the rib at the rib's aperture contact surface, and the second element inter-engages laterally with the rib at the rib's peripheral contact surface. A rib may additionally be connected to tile first element or to the second element or to both.
The second support element is longitudinally located to the first support element at one position oniy such that from this position the second support element is free to move longitudinally with respect to the first support element. Any longitudinal load developed in the second support clement is transmitted to the first support clement at this position.
The second support element is torsionally located to the first support element at one position only. If this position is different to the longitudinal location position thc means of torsion transmission will ensure that the second support element is free to move longitudinally with respect to the first support element. Any torsional load developed in the second support elenicnt is transmitted to the first support element at this position.
The longitudinal and torsional location of the second support clement to the first element may be provided by means of an interference fit between the two elements, which may or may not involve a rib.
The first and second support elements, and ribs, may be split into two or more connected elements. Connection may be through jigsaw contact or direct fastening.
Preferred embodiments of thc prcscnt invention will now be described by way of examplc to Figure 1. The figure contains cross sectional views through a preferred beam according to the present invention.
The beam illustrated comprises an inner metallic tube (1) and an outer composite tubular sleeve (2). The inner tube(1) is circular and the outer sleeve (2) is of an aerofoil profile and their cross sections vary longitudinally. The outer composite sleeve (2) is composed of two half shells (2a, 2b)joined together by adhesive bonds (3). The inner tube (1) and outer sleeve (2) are iii intimate lateral contact with discrete ribs (4). Ends of the inner tube (1) extend beyond the ends of the outer tubular sleeve (2) terminating at end joints (5) capable of transmitting and reacting longitudinal, lateral and moment forces. The outer periphery of each discrete rib (4) is connected to the outer composite sleeve (2) by an adhesive bond (6).
A single rib is connected longitudinally to the inner metallic tube by means of cirelips (7). A single rib is connected torsionally to the inner metallic tube by means of a keyed joint (8).
The remaining ribs (4) make a mechanical contact fit with the inner metallic tube (I) such that the nbs (4) and outer composite tube (2) are free to move longitudinally with respect to the inner metallic tube (1) from the circlips connection (7). The inner metallic tube (1) acts to resist longitudinally applied tensile or compressive loads, lateral loads and moments applied to the end joints (5). The outer composite sleeve (2) acts to strengthen the inner tube (1) in its resistance to lateral bending and buckling. The outer composite sleeve (2) acts to resist and transmit lateral loading applied along its length. The lateral loading on the sleeve (2) is transmitted by means of the ribs (4) to the inner metallic tube (1). Any longitudinal or torsional load developed in the outer composite sleeve (2) is transmitted to the inner tube at the circlips connection (7) or keyed joint (8) respectively.
Figure 2 shows another embodiment of the invention, in which a friction-reducing or lubricating element (9) is introduced between the aperture contact surface of a rib (4) and the inner metallic tube (1) at one or more ribs.
Figure 3 shows another embodiment of the invention, in which an interference fit (10) between the first and second support elements (1) (2) provides the means of the longitudinal and torsional location and connection of the two support elements (1) (2). The interference fit connection between elements (1) (2) may or may not involve a rib (4).
The preferred embodiments of the beam according to the present invention could be employed as a blade aerofoil, such as a wind turbine blade or an aircraft wing, where one end joint (5) is connected to a wind turbinc hub or aircraft fuselage respectively, and the other end joint (5) at the other end of the first support element (1) is connected to a \vingtip or wringlet device.

Claims (33)

  1. CLAIMS1. A beam comprising a first support element and a second support element extending longitudinally alongside one another, the first support element being operative to resist applied longitudinal comprcssive or tensioning force, and the first and second elements being operative to resist lateral bending forces, the second support element being free to move longitudinally with respect to the first support element.
  2. 2. A beam according to claim 1, in which the first and second support elements are arranged so that the first support clement can be loaded longitudinally in tension or compression without any substantial longitudinal loading of the second support ci em ent.
  3. 3. A beam according to claim 1 or claim 2 in which the first and second support elements are arranged one within the other so as to inter-engage laterally via discrete ribs positioned along the tength of the second support element so as to resist lateral bending forces.
  4. 4. A beam according to any preceding claim in which the second support element makes a mechanical contact fit with the first support element via ribs so as to bc slidable thereon.
  5. 5. A beam according to any preceding claim in which the second support element is a tubular sleeve.
  6. 6. A beam according to any preceding claim in which the second support element is shorter in length than the first support element.
  7. 7. A beam according to any preceding claim in which the cross section of the second support element varies along the length of the element.
  8. S. A beam according to any preceding claim in which the first support element is a tube or rod.
  9. 9. A beam according to any preceding claim in which the cross section of the first support clement varies along the length of the clement.
  10. 10. A beam according to any preceding claim in which the first support element is of metal.
  11. 11. A beam according to claim 10 in which the metal is steel or an aluminium or titanium alloy.
  12. 12. A beam according to any preceding claim in which the second support clement is composed of a material less dense than the first support element such as an advanced or composite material.
  13. 13. A beam according to claim 12 in which the advanced or composite material comprises carbon, Kevlar (trade mark), glass, ceramic, metal matrix, wood or composite materials including at least one or a combination of these materials.
  14. 14. A beam according to any preceding claim in which the ribs are diaphragms containing an aperture.
  15. IS. A beam according to any preceding claim in which the ribs are of a composite material.
  16. 16. A beam according to claim 15 in which the composite material is Tufnol (trade mark).
  17. 17. A beam according to any preceding claim in which the ribs are metallic.
  18. 1 S. A beam according to claim 17 in which the metal is steel or an aluminium or titanium alloy.
  19. 19. A beam according to any preceding claim in which the ribs are adhesively bonded to the second support element around their peripheral contact surfaces.
  20. 20. A beam according to any preceding claim in which the second support element is longitudinally located to the first support element at one position only, such that from this position the second support element is free to move longitudinally with respect to the first support clement.
  21. 21. A beam according to any preceding claim in which the second support element is torsionally located to the first support element at one position only, and that if this position is different to the longitudinal location position in claim 20 the means of torsion transmission will ensure that the second support element is free to move longitudinally with respect to the first support element.
  22. 22. A beam according to claims 20 and 21 in which thc longitudinal and torsional location means is provided by an interference fit between the first and second support elements.
  23. 23. A beam according to any preceding claim in which thc first or sccond support elements or rib elements may each be split into two or morc elements connected byjigsa\v contact, or by mechanically fastened, adhesively bonded or welded joints.
  24. 24. A beam according to any preceding claim in which a friction-reducing or lubricating element is provided between the aperture contact surface of a rib and the first support element.
  25. 25. A beam according to claim 24 in which the friction-reducing or lubricating clement is PTFE.
  26. 26. A beam according to any preceding claim in which the first support element possesses longitudinally adjustable end joints.
  27. 27. A beam according to any preceding claim in which cross section of the first support element is circular.
  28. 28. A beam according to any preceding claim in which the cross section of the second support element is of an aerofoil profile.
  29. 29. A beam according to any preceding claim which is employed as a blade.
  30. 30. A beam according to claim 29 in which the blade is a wind turbine blade.
  31. 31. A beam according to any preceding claim which is employed as a wing.
  32. 32. A beam according to daim 31 in which the wing is an aircraft wing.
  33. 33. A beam substantially as hereinbefore described with reference to Figure 1, Figure 2 or Figure 3.
GB1301846.0A 2012-11-17 2013-02-01 Structural beam Active GB2508038B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1220725.4A GB201220725D0 (en) 2012-11-17 2012-11-17 Structural beam

Publications (3)

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GB201301846D0 GB201301846D0 (en) 2013-03-20
GB2508038A true GB2508038A (en) 2014-05-21
GB2508038B GB2508038B (en) 2016-06-29

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GB1301846.0A Active GB2508038B (en) 2012-11-17 2013-02-01 Structural beam

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2299103A (en) * 1995-03-24 1996-09-25 Euro Stress Ltd Strut
DE19614393A1 (en) * 1996-04-12 1996-11-28 Wilhelm Dipl Ing Konrad Wind power generator design
US20030222188A1 (en) * 2002-05-29 2003-12-04 Smelser James M. Bearing brace apparatus
FR2920407A1 (en) * 2007-08-29 2009-03-06 Michel Kieffer Wing forming device for e.g. flying apparatus, has ribs including orifice to section of spar, so that spar traverses ribs in level of orifices, and wing fixed at fixation point on fuselage or spar, where ribs are freely mounted on spar

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2299103A (en) * 1995-03-24 1996-09-25 Euro Stress Ltd Strut
DE19614393A1 (en) * 1996-04-12 1996-11-28 Wilhelm Dipl Ing Konrad Wind power generator design
US20030222188A1 (en) * 2002-05-29 2003-12-04 Smelser James M. Bearing brace apparatus
FR2920407A1 (en) * 2007-08-29 2009-03-06 Michel Kieffer Wing forming device for e.g. flying apparatus, has ribs including orifice to section of spar, so that spar traverses ribs in level of orifices, and wing fixed at fixation point on fuselage or spar, where ribs are freely mounted on spar

Also Published As

Publication number Publication date
GB201301846D0 (en) 2013-03-20
GB2508038B (en) 2016-06-29
GB201220725D0 (en) 2013-01-02

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