US3758258A - A method for combusting fuels in a substantially conically shaped curtain - Google Patents

A method for combusting fuels in a substantially conically shaped curtain Download PDF

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Publication number
US3758258A
US3758258A US00127228A US3758258DA US3758258A US 3758258 A US3758258 A US 3758258A US 00127228 A US00127228 A US 00127228A US 3758258D A US3758258D A US 3758258DA US 3758258 A US3758258 A US 3758258A
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fuel
combustion
air
axis
flow
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US00127228A
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English (en)
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M Kolhi
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COLLIN CONSULT AB
COLLIN CONSULTING R AB
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COLLIN CONSULT AB
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space

Definitions

  • ABSTRACT A device and method for improving the combustion of fuels which emerge from the orifice of a burner nozzle in the form of a conically shaped fuel curtain, around which and coaxial with is a connecting envelope of combustion air.
  • Extending coaxially with the main burner tube are further tubes which form air passages.
  • the further tubes are provided at the ends thereof adjacent the fuel nozzle with air nozzle means which give the air a determined direction of flow relative to the radial plane, thereby creating a subpressure externally of the fuel and air cones, whereupon the cones are drawn rearwardly and outwardly with respect to the burner nozzle tip.
  • the present invention relates to a method for combusting fuels which are ejected from an orifice in a manner to form a substantially conically shaped curtain of fuel which is mixed with an envelope of combustion air located substantially coaxial with the fuel curtain.
  • the invention also relates to a device for carrying out the method and is substantially characterized in that arranged in a ring around the axis of the burner cone and externally of the fuel curtain and the combustion air envelope are members adapted to cause the atmosphere externally of the combustion air envelope and the fuel curtain to move outwardly from the cone axis to maintain a condition of subpressure which holds the combustion zone rearwardly displaced and concentrates said combustion zone around the cone axis.
  • FIG. 1 illustrates in perspective and in partially broken away view a basic condition of a substantially coneshaped curtain of fuel issuing from the nozzle orifice of a burner and the cone of combustion air located coaxial with the fuel curtain.
  • FIG. 2 illustrates separately and in perspective how the outer surface of the fuel cone is influenced by a subpressure, resulting in an increased cone angle.
  • FIG. 3 illustrates, also in perspective, a fuel cone and a connecting cone of combustion air subjected to a subpressure on the outer surfaces thereof.
  • FIG. 4 shows in perspective and partly in longitudinal section an embodiment of a burner constructed in. ac-
  • cordance with the invention and provided with means which cause the atmosphere outside the cones to move to create and maintain the necessary subpressure.
  • FIG. 5 illustrates how air is directed by positively guiding the same at suitable preferred and critical angles to the radial plane of the burner.
  • FIG. 6 illustrates the possibility of causing the positively guided air to rotate around the burner axis of a burner of the type illustrated in FIG. 4 for example.
  • FIG. 7 illustrates in longitudinal section a modified burner in which the desired subpressure is created by means of an ejector action.
  • FIG. 8 is an axial partial sectional view of a further modified burner construction with which the combustion zone is displaced rearwardly to extreme limits.
  • FIG. 9 illustrates a modified embodiment of the structure illustrated in FIG. 6.
  • FIG. 10 is an axial section of a further embodiment of the invention.
  • FIG. 1 illustrates the basic condition of a fuel spray issuing from a fuel orifice 10 of a conventional fuel nozzle 11.
  • the emerging fuel forms a conical film 12 which is atomized into fine droplets.
  • the fuel cone 12 is surrounded by a conical envelope 13 of combustion air which emerges through a constriction 14 in a casing or the like 15 surrounding the fuel nozzle ll.
  • the cones act upon each other and the surrounding atmosphere, but for the sake of simplicity the cones are shown in a theoretical condition and their influence on each other and the surroundings has been ignored.
  • the fuel cone and/or the air cone are capable of rotating around their respective cone axes, either in the same direction or in opposite directions and at the same or different speeds.
  • the atomized fuel is mixed with the air of combustion, and the subpressure created within the cones, as a result of the flow, tends to draw the fuel and the air of combustion rogether.
  • ignition means not shown
  • a relatively long, yellow flame is obtained, which indicates that free carbon is present, because the temperature increase of the fuel air mixture is too slow.
  • the final products obtained during the process of combustion consist of, inter alia, S S0 elemental carbon, i.e., soot and nitrogen oxides, which are deleterious to the environment, as indicated in the aforegoing.
  • FIG. 2 illustrates the same fuel nozzle 1i. as that illustrated in FIG. 1, the casing having been removed and the conical air envelope 13 excluded.
  • the Figure also illustrates in chain lines the initial position of the fuel cone.
  • the Figure illustrates diagrammatically an example of how, in accordance with the invention, the atmosphere outside the fuel cone 12 is caused to move outwardly from the burner axis in the direction of arrows 16.
  • a source of subpressure e.g. the illustrated suction fan 17 whose suction inlet opening is identified with the reference numeral 18 and the ejection outlet opening with the reference numeral 119.
  • the air drawn into the fan is discharged through the opening 19 externally of the burner.
  • the resulting movement of the atmosphere in the direction of arrows 16 in the zone externally of the fuel cone 12 creates a subpressure which results in the widening of the fuel cone, which thus takes the shape of a bowl 20, as illustrated in the Figure, and the cone angle of which is also considerably increased.
  • the helical arrow Zll indicates a flow line, which shows that in this instance the fuel bowl 20 rotates around its axis, although it is not always necessary for the fuel bowl to rotate. Movement of the fuel bowl can be accomplished in a known manner, for example by arranging tengentially directed grooves inside the nozzle.
  • FIG. 3 illustrates diagrammatically how the fuel cone and the air cone are actuated in the manner described with reference to FIG. 2.
  • FIG. 3 thus shows the nozzle orifice 10, the nozzle 11, the casing 15, the restriction 14, the initial fuel cone and air cone i2 and 13 respectively and the fuel bowl 20.
  • a bowl-shaped envelope of combustion air 22 which is located around the fuel bowl 20 coaxialiy therewith.
  • flow lines which show how the bowls may rotate.
  • the arrows 16 shown in FIG. 2 are also shown in FIG. 3 and represent appropriate directions of movement for the atmosphere present during removal by suction of the atmosphere from the zone located substantially within the base of the arrows and which is of particular interest in connection with the invention.
  • the Figure also illustrates how the fuel cone 12 and the combustion air cone 13 have been substantially widened. This'widening of the two cones is caused by the subpressure created in the zone nearest the fuel opening as a result of air flowing out through the restriction l4 and of the subpressure which in turn is created around the cylindrical surface of the envelope of combustion air in the region radially outside the restriction 14.
  • the bowsl 2% and 22 are caused to coincide, whereupon a concentrated mixture of air and fuel is obtained which when ignited gives a relatively stable combustion zone.
  • the subpressure is increased, the combustion zone is moved rearwardly towards the burner nozzle and is concentrated radially inwardly. Combustion is effected more rapidly in this combustion zone than with the example described with reference to FIG. 1. In this way, a more rapid increase in temperature is obtained, resulting in the suppression of soot formation and the formation of other final products harmful to the environment.
  • FIGS. 1-3 are intended to illustrate the principle of the method according to the invention
  • FIGS. 4-10 illustrate more concrete devices for putting the method of the invention into effect, further developments of the method being described with reference to these Figures.
  • the method according to the invention for creating a region of subpressure outside the respective fuel and combustion air cones has, in the aforegoing, only been described and illustrated in principle, with reference to FIGS. 1-3.
  • the source or means for causing the atmosphere in the zones in question to move outwardly from the common cone axis has been exemplified in the form of a suction fan or the like, which, as will be understood, only represents an extremely elementary embodiment of the method according to the invention. Furthermore, mention has been made of a method by which the air flow paths are given a specific direction without the means for carrying out the method having been described in detail.
  • combustion air and/or the fuel mist can be caused to rotate. Such rotation contributes to a more effective mixture of the fuel mist with the combustion air.
  • FIG. 4 One example of a burner by means of which this development of the method according to the invention can be carried out is illustrated in FIG. 4, in
  • the reference numeral 24 indicates a body surrounding the fuel nozzle 25 and widening in a direction towards the discharge end of the burner.
  • the body 24 is extended with a tubular portion 26, which simultaneously forms a passage for the fuel and an attachment means for a number of helically arranged guide vanes 27.
  • the body 24 and its stem 26 are encircled by two co-axial tubes, of which the inner is identified with the reference numeral 28 and the outer with the reference numeral 29.
  • the tubes 28 and 29 are provided attheir ends located around the nozzle 25 with flanges 30 and 31.
  • the flow passage has a restriction 34, provided by the embodiment of the body 24.
  • the combustion air is subjected to an ejector action.
  • formed between the tubes 28 and 29 is a relatively narrow, angular passage through which air is forced to flow in the direction of arrows 36 out through an annular gap 37 located between the two flanges 3b and 31.
  • the fuel issues from the nozzle opening 35 to form a bowl-shaped curtain of fuel identified in FIG. 3 with the reference numeral 20.
  • FIG. 4 illustrates amethod of causing such recirculation by eddying the atmosphere around the zone of combustion.
  • the positively directed air emerging through the annular gap 37 in the direction of arrows 36 causes, by ejector action, the air nearest the gap 37 to rotate and form eddies 38, which lie in the form of a ring around the flange 30.
  • the eddy movement together with the gas movement in the zone of combustion induces a very intensive eddy movement, identified by the arrow 3!, whereby hot smoke gases are recirculated back to the beginning of the combustion zone.
  • the recirculated hot smoke gases will further increase the temperature in the combustion zone, so that combustion becomes extremely intensive and is therewith also concentrated to a relatively narrow region around the burner axis, simulatneously as the combustion zone is moved closer to the burner orifice.
  • a particularly important factor correlated with the withdrawal of the combustion zone is the flow of air through the restriction 34 around the body 24, this flowcausing, by ejector action, a region of subpressure to be created in front of the body 24 around the fuel nozzle 35.
  • the angle to the radial plane for the positively directed air flow from the gap between the flanges 30 and 31 is critical or should at least be maintained within certain suitable angle regions in order for a reasonable combustion result to be obtained.
  • the two tubes 28 and 29 are shown with their flanges 31 and 30 directed at a negative angle of 20 to the radial plane, which is represented by the line 40.
  • This angle of 20 is applied in the embodiment illustrated in FIG. 4.
  • Particularly suitable angular areas are those which extend at +5 to 30" to the radial plane and whichextend outwardly from the nozzle axis in accordance with the invention.
  • the gap 30 and 31 in the gap 37 can be provided with vane like members or the gap can be replaced with a ring of openings 63 which have a determined direction of orientation and which positively guide the air to flow at the desired angle to the lines extending perpendicularly to the axis of the burner nozzle, as shown in FIG. 9.
  • FIG. 7 illustrates diagrammatically a further embodiment of a burner in which the flow passage for the combustion air is incorporated in an ejector means arranged to lower the pressure in the area around the burner tip externally of the fuel air bowl.
  • the reference numeral 42 identifies the fuel nozzle proper, which is surrounded by a body 43, past the edge surface 44 of which combustion air flows in the direction of the arrows 45 through an encircling tube 46, which terminates approximately level with the edge surface 44 of the body 43.
  • an outer tube 47 Arranged coaxially with the tube 46 is an outer tube 47, an annular flow gap being formed in which air flows in the direction of arrows 48.
  • a ring of combined support and distance means Positioned at the end of the tube 47 is a ring of combined support and distance means which support an annular, outlet member, generally indicated at 49, at such a distance from the end of the tube 47 that an annular opening 50 is formed between the end of the tube 47 and the outlet member 49.
  • the eddies substantially comprise recirculated smoke gas entrained from the contact zone between the eddies 51 and the cylindrical surface of the bowlshaped envelope of the combustion zone represented by the arrows 52.
  • a central recirculation is also obtained within the combustion zone, as illustrated by the looped arrows 53.
  • the Figure also shows by way of example the two terminals X and Y of an arbitrarily selected fuel igntion means.
  • FIG. 8 illustrated one half of a further modified burner construction according to the invention, in which the central body 43 illustrated in FIG. 7 is shown.
  • an inner tube 54 terminates at a certain distance behind the edge surface 44 of the body 43.
  • An outer tube 55 having an annular or ring-shaped ejector 56 surrounds the tube 54 with an intermediate annular gap 57 and terminates at a certain distance in front of the end surface of the body 43.
  • Combustion air flows in the direction of arrow 59 between the body 43 and the inner tube 54 through a constriction S8 and past the end of the tube 54, where the air is entrained raidally outwardly by the air emerging at a higher velocity from the gap 57.
  • the two air flows together then give rise to an ejector action when passing the ejector 56, so that a recirculation eddy, indicated by the arrow 60, is created similarly to the eddy 51 in FIG. 7 with the same effect.
  • H6 illustrates another embodiment of the invention in which is embodied a number of gaps or passages for positively directing the air flows at different angles to the aforementioned lines extending perpendicularly to the axis of the nozzle.
  • the reference numeral 64 identifies a central tube which bears at one end thereof a fuel nozzle 65. Extending coaxially with the tube 64 are two tubes 66 and 67, these being defined between the tubes air through flow passages 68 and 69.
  • the tube 64 is provided in the vicinity of the burner nozzle 65 with guide surfaces 70 which together with guide surfaces 71 on the tube 66 give the flow of air a direction determined by the gap.
  • the tube 66 is also provided with guide surfaces which together with guide surfaces 73 on the tube 67 direct the air flow in a direction different to the first mentioned air flow.
  • gaps may be arranged and that their configuration may be so selected that the air passing therethrough may be made to flow in any desired direction relative to the radial plane.
  • a method of combusting fuel comprises forcing said fuel through an orifice adapted to produce a conically shaped fuel curtain; forcing combustion air through a substantially annular flow-through area located coaxially with said orifice, directing said combustion air away from the axis of the fuel cone to form a substantially conical or bowl shaped curtain concentric with and exterior to said fuel cone; maintaining the pressure used to force said combustion air at a sufficiently high level to create a sub-atmospheric pressure zone between said combustion air curtain and said fuel cone whereby said fuel cone angle is increased and said fuel is admixed with said combustion air in a combustion zone; igniting said admixture and mainting said combustion zone during combustion.
  • a method according to claim 1 including continuously withdrawing the atmosphere by suction to influence the pressure conditions at the air curtain.
  • a method according to claim 1 including causing the atmosphere adjacent the air curtain to move in a substantially toroidal shaped pattern of eddy current to influene the pressure conditions at the air curtain.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
US00127228A 1970-03-24 1971-03-23 A method for combusting fuels in a substantially conically shaped curtain Expired - Lifetime US3758258A (en)

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SE7004010A SE410218B (sv) 1970-03-24 1970-03-24 Brennare

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US (1) US3758258A (es)
JP (1) JPS5544281B1 (es)
AT (1) AT319451B (es)
BE (1) BE764767A (es)
CA (1) CA934286A (es)
CH (1) CH558501A (es)
DE (1) DE2113659C2 (es)
DK (1) DK141827B (es)
ES (1) ES196846Y (es)
FI (1) FI52769C (es)
FR (1) FR2085029A5 (es)
GB (1) GB1351212A (es)
NL (1) NL7103900A (es)
NO (1) NO130202B (es)
SE (1) SE410218B (es)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3876362A (en) * 1973-04-23 1975-04-08 Yasuo Hirose Method of combustion
US3880354A (en) * 1971-12-23 1975-04-29 Chemetron Corp Method and apparatus for controlling heat effect in metal cutting operations
US3918834A (en) * 1973-08-09 1975-11-11 Isaak Yakovlevich Sigal Method of reducing the concentration of nitrogen oxides in a gaseous effluent from a thermal plant
FR2369418A1 (fr) * 1976-10-27 1978-05-26 Gen Electric Injecteur de combustible pour turbine a gaz
US4361285A (en) * 1980-06-03 1982-11-30 Fluid Kinetics, Inc. Mixing nozzle
US4410140A (en) * 1981-04-30 1983-10-18 Hauck Manufacturing Company Atomizer and method
US4473185A (en) * 1979-10-25 1984-09-25 Peterson Folke K Method and device for producing microdroplets of fluid
US4618323A (en) * 1980-02-19 1986-10-21 Southers California Edison Method and burner tip for suppressing emissions of nitrogen oxides
US20040007056A1 (en) * 2001-08-06 2004-01-15 Webb Cynthia C. Method for testing catalytic converter durability
US20060234174A1 (en) * 2005-03-17 2006-10-19 Southwest Research Institute. Use of recirculated exhaust gas in a burner-based exhaust generation system for reduced fuel consumption and for cooling
US20070039381A1 (en) * 2005-08-05 2007-02-22 Timmons Suzanne A Secondary Air Injector For Use With Exhaust Gas Simulation System
US20070283749A1 (en) * 2001-08-06 2007-12-13 Southwest Research Institute System and method for burner-based accelerated aging of emissions control device, with engine cycle having cold start and warm up modes
US7412335B2 (en) 2002-08-06 2008-08-12 Southwest Research Institute Component evaluations using non-engine based test system
US20100062384A1 (en) * 2008-09-05 2010-03-11 Eric Lavoie Oil burning system
CN101886812A (zh) * 2009-05-12 2010-11-17 约翰津克公司 空气火炬装置和方法
US8425224B2 (en) 2005-03-17 2013-04-23 Southwest Research Institute Mass air flow compensation for burner-based exhaust gas generation system
US10697639B2 (en) 2017-03-16 2020-06-30 General Electric Compamy Dual-fuel fuel nozzle with liquid fuel tip

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US836219A (en) * 1903-01-26 1906-11-20 Charles G Hawley Process of burning fuel.
US2515845A (en) * 1946-06-25 1950-07-18 Shell Dev Flame pocket fluid fuel burner
US2986206A (en) * 1957-02-28 1961-05-30 Shell Oil Co Combustion device for liquid fuel
US3030773A (en) * 1959-01-22 1962-04-24 Gen Electric Vortex type combustion with means for supplying secondary air
FR1297465A (fr) * 1961-08-10 1962-06-29 Procédé et appareil de pulvérisation pour la réalisation de revêtements de vernis, de peinture ou de métal
US3163202A (en) * 1960-07-19 1964-12-29 Indugas Ges Fur Ind Gasverwend Burner for industrial furnaces and the like
US3275057A (en) * 1964-07-01 1966-09-27 Hotwork Ltd Tunnel burners
US3576384A (en) * 1968-11-29 1971-04-27 British American Oil Co Multinozzle system for vortex burners

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB892151A (en) * 1960-10-05 1962-03-21 Bengt Rudolf Holtback Apparatus for burning liquid or gaseous fuels on the recirculation principle

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US836219A (en) * 1903-01-26 1906-11-20 Charles G Hawley Process of burning fuel.
US2515845A (en) * 1946-06-25 1950-07-18 Shell Dev Flame pocket fluid fuel burner
US2986206A (en) * 1957-02-28 1961-05-30 Shell Oil Co Combustion device for liquid fuel
US3030773A (en) * 1959-01-22 1962-04-24 Gen Electric Vortex type combustion with means for supplying secondary air
US3163202A (en) * 1960-07-19 1964-12-29 Indugas Ges Fur Ind Gasverwend Burner for industrial furnaces and the like
FR1297465A (fr) * 1961-08-10 1962-06-29 Procédé et appareil de pulvérisation pour la réalisation de revêtements de vernis, de peinture ou de métal
US3275057A (en) * 1964-07-01 1966-09-27 Hotwork Ltd Tunnel burners
US3576384A (en) * 1968-11-29 1971-04-27 British American Oil Co Multinozzle system for vortex burners

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3880354A (en) * 1971-12-23 1975-04-29 Chemetron Corp Method and apparatus for controlling heat effect in metal cutting operations
US3876362A (en) * 1973-04-23 1975-04-08 Yasuo Hirose Method of combustion
US3918834A (en) * 1973-08-09 1975-11-11 Isaak Yakovlevich Sigal Method of reducing the concentration of nitrogen oxides in a gaseous effluent from a thermal plant
FR2369418A1 (fr) * 1976-10-27 1978-05-26 Gen Electric Injecteur de combustible pour turbine a gaz
US4105163A (en) * 1976-10-27 1978-08-08 General Electric Company Fuel nozzle for gas turbines
US4473185A (en) * 1979-10-25 1984-09-25 Peterson Folke K Method and device for producing microdroplets of fluid
US4618323A (en) * 1980-02-19 1986-10-21 Southers California Edison Method and burner tip for suppressing emissions of nitrogen oxides
US4361285A (en) * 1980-06-03 1982-11-30 Fluid Kinetics, Inc. Mixing nozzle
US4410140A (en) * 1981-04-30 1983-10-18 Hauck Manufacturing Company Atomizer and method
US20040007056A1 (en) * 2001-08-06 2004-01-15 Webb Cynthia C. Method for testing catalytic converter durability
US20060201239A1 (en) * 2001-08-06 2006-09-14 Webb Cynthia C Method for Testing Catalytic Converter Durability
US7347086B2 (en) 2001-08-06 2008-03-25 Southwest Research Institute System and method for burner-based accelerated aging of emissions control device, with engine cycle having cold start and warm up modes
US7277801B2 (en) 2001-08-06 2007-10-02 Southwest Research Institute Method for testing catalytic converter durability
US20070283749A1 (en) * 2001-08-06 2007-12-13 Southwest Research Institute System and method for burner-based accelerated aging of emissions control device, with engine cycle having cold start and warm up modes
US7412335B2 (en) 2002-08-06 2008-08-12 Southwest Research Institute Component evaluations using non-engine based test system
US7748976B2 (en) 2005-03-17 2010-07-06 Southwest Research Institute Use of recirculated exhaust gas in a burner-based exhaust generation system for reduced fuel consumption and for cooling
US20060234174A1 (en) * 2005-03-17 2006-10-19 Southwest Research Institute. Use of recirculated exhaust gas in a burner-based exhaust generation system for reduced fuel consumption and for cooling
US8425224B2 (en) 2005-03-17 2013-04-23 Southwest Research Institute Mass air flow compensation for burner-based exhaust gas generation system
US20070039381A1 (en) * 2005-08-05 2007-02-22 Timmons Suzanne A Secondary Air Injector For Use With Exhaust Gas Simulation System
US20100062384A1 (en) * 2008-09-05 2010-03-11 Eric Lavoie Oil burning system
US8052418B2 (en) 2008-09-05 2011-11-08 Energy Efficiency Solutions, Llc Oil burning system
US8672672B2 (en) 2008-09-05 2014-03-18 Energy Efficiency Solutions, Llc Oil burning system
CN101886812A (zh) * 2009-05-12 2010-11-17 约翰津克公司 空气火炬装置和方法
US10697639B2 (en) 2017-03-16 2020-06-30 General Electric Compamy Dual-fuel fuel nozzle with liquid fuel tip

Also Published As

Publication number Publication date
FI52769C (fi) 1977-11-10
DK141827C (es) 1980-11-10
CH558501A (de) 1975-01-31
FI52769B (es) 1977-08-01
FR2085029A5 (es) 1971-12-17
SE410218B (sv) 1979-10-01
DE2113659C2 (de) 1984-07-05
AT319451B (de) 1974-12-27
NL7103900A (es) 1971-09-28
GB1351212A (en) 1974-04-24
ES196846U (es) 1975-04-16
NO130202B (es) 1974-07-22
DE2113659A1 (de) 1971-10-14
BE764767A (fr) 1971-08-16
JPS5544281B1 (es) 1980-11-11
CA934286A (en) 1973-09-25
ES196846Y (es) 1975-08-16
DK141827B (da) 1980-06-23

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