EP1155781A1 - Thermoabrasive blast gun - Google Patents

Thermoabrasive blast gun Download PDF

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Publication number
EP1155781A1
EP1155781A1 EP01450009A EP01450009A EP1155781A1 EP 1155781 A1 EP1155781 A1 EP 1155781A1 EP 01450009 A EP01450009 A EP 01450009A EP 01450009 A EP01450009 A EP 01450009A EP 1155781 A1 EP1155781 A1 EP 1155781A1
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EP
European Patent Office
Prior art keywords
chamber
abrasive
fuel
lance
annular
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.)
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Application number
EP01450009A
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German (de)
French (fr)
Inventor
Philippe Cluchague
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.)
Thermo Blast International SA
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Thermo Blast International SA
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Publication date
Application filed by Thermo Blast International SA filed Critical Thermo Blast International SA
Publication of EP1155781A1 publication Critical patent/EP1155781A1/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C5/00—Devices or accessories for generating abrasive blasts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B7/00—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas
    • B05B7/16—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed
    • B05B7/20—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed by flame or combustion
    • B05B7/201—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed by flame or combustion downstream of the nozzle
    • B05B7/205—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed by flame or combustion downstream of the nozzle the material to be sprayed being originally a particulate material

Definitions

  • the present invention relates to thermo-mechanical pickling by projection using an lance or pistol with an abrasive using gases from combustion of fuel and compressed air.
  • This pickling principle is well known and implements devices which all use liquid fuel which is sprayed and mixed with compressed air, the assembly being introduced and burned in a combustion chamber. This generates a flow of combustion products gaseous at a high temperature, and which flows out of the combustion results in abrasive particles transported using a gas suitable carrier.
  • the object of the present invention is precisely to overcome the drawbacks known thermo-mechanical projection devices by proposing a lance simpler, faster and more practical, more reliable, more efficient and capable of using both gaseous fuels and liquid fuels.
  • the invention relates generally to any pickling involving an abrasive agent or the like, the latter expression designating any agent solid or liquid such as water for example, the solid agent being in the state particulate or granular carried by a suitable gaseous or liquid fluid.
  • the lance of the invention is capable of accepting as fuel a liquid as well as gas while offering very good flame stability, good performance, easy start-up and increased efficiency due to high ejection temperatures which can be reached, of the order of 700 ° C at ejection and high agent ejection velocities abrasive or the like, these speeds possibly reaching values of the order of 800 to 850 m / s.
  • said second routing path of the combustion air in the combustion chamber consists of grooves helical formed at the periphery of the injector between the latter and said internal envelope delimiting the combustion chamber, the outlets in the latter of the helical grooves being aligned in a circle parallel to the alignment circle of the outlets of the intake channels of the fuel, the angle formed between the outlet jet of said helical grooves and the plane of the first aforementioned circle being within a range of the order of 5 degrees to 20 degrees, and more particularly 9 to 10 degrees, while the angle formed between the axis of the lance and said fuel inlet channels is in the range of about 30 degrees to 90 degrees.
  • the first chamber upstream of the injector is an annular chamber surrounding said abrasive agent conduit or the like, said annular chamber being connected to an external source of fuel, gaseous or liquid, via a fitting fitted with a flow adjustment nozzle allowing the admission of combustion air into said flow annular chamber parallel to the fuel.
  • the second chamber in upstream of the injector is an annular chamber surrounding the agent conduit abrasive or the like and said first upstream chamber, said chamber ring communicating with the combustion air intake inlet via a baffle formed by an intermediate tubular casing coaxial with said external and internal envelopes and arranged at a distance from the latter so to constrain the flow of combustion air at the entrance to lick the internal wall of the outer envelope to its distal end then the outer wall of the internal envelope to finally open into said annular chamber.
  • the combustion air is supplied in a hollow part a handle which is provided with the lance and is distributed in a prechamber annular formed in the proximal part of the lance, which prechamber communicates with the annular space between said outer envelopes and intermediate.
  • the distal end of the abrasive or similar conduit is spaced the neck of the ejection nozzle, so as to constitute in particular an acceleration zone contributing to the generation of an output flow at high speed.
  • FIG. 1 there is shown an embodiment of a lance thermo-abrasive according to the invention comprising an outer metal tube 1, cylindrical, integral at its proximal end with a metal handle hollow cylinder 2 and provided, at its distal end, with a sandblasting nozzle 3 fixed by a ferrule 4 screwed onto the threaded end of said tube 1.
  • the hollow handle 2 is open at both ends and communicates by one of them with the inside of the tube 1 by a passage orifice 5 and by the other end with a flexible supply pipe (not shown) combustion air under pressure from an appropriate source, for example via a quick coupling capable of being screwed onto a thread 6 formed on said end of the handle 2.
  • the proximal end of the tube 1 is closed by a piece in the form of diabolo 7 defining an annular chamber 8 internal to the tube 1 and communicating with the inside of the handle 2.
  • the diabolo 7 is pierced with a passage 9 coaxial with the tube 1 and in which a connection tube 10 is introduced, the external part 11 of which has a diameter enlarged with a frustoconical part 12 pressed against a frustoconical part diabolo 7 antagonist with interposition of an O-ring 13.
  • the outer end of the part 11 has a thread 14 for the connection of an agent intake pipe (not shown) abrasive or the like inside the lance, via the connection tube 10.
  • this fitting 17 can be connected a line (not shown) for supplying a fuel, gaseous or liquid, from an appropriate source.
  • a nozzle 18 Inside the fitting 17 is arranged a nozzle 18 (FIG. 5) of which the frustoconical distal end 19 is loaded by pressing against the edge of the passage 15 for sealing against the annular chamber 8.
  • the nozzle 18 is axially adjustable by screwing thanks to an external thread 18a cooperating with an internal thread of the connector 17.
  • the nozzle 18 is provided with an axial passage 18b which passes through it from one end to the other.
  • a injector 20 coaxial with tube 1 and having a central cylindrical passage 20a in which the connecting tube 10 extends, an annular space 21 remaining between the two parts 20 and 10.
  • the annular space 21 is closed at the end internal of the injector 20 by the foot of a tube 22 coaxial with the tube 1 and loaded conveying the abrasive agent or the like downstream of the injector 20.
  • the foot of the tube 22 is screwed onto a thread formed at the end of the tube-connector 10, pressing the injector 20 against the diabolo 7, now thus in place said injector.
  • the injector 20 is shown enlarged in Figure 2. It includes a part of enlarged diameter defining a cylindrical wall 23 coaxial with passage 20a and in which several helical grooves are dug identical 24 with rectangular section.
  • 2 grooves are provided, the pitch of which is of the order of 18 mm for a diameter of the wall 23 of the order of 36 mm.
  • the upstream orifices of the two grooves 24 are diametrically opposite and each groove has for example a section of 2 x 4 mm.
  • the total cross-section of the combustion air in the two grooves 24 is advantageously 16 mm 2 for a diameter of the ejection nozzle 3 of the order of 13 mm.
  • This total section can vary within a range of 10 to 30 mm 2 with a number of grooves equal to or greater than two.
  • the grooves 24 are closed at the height of the wall 23 by a tube sleeve 25 said inner tube, coaxial with tube 1 and extending to the nozzle 3 on the inner end of which it is screwed.
  • the inner tube 25 is provided with perforations 26 approximately in its central part, the perforated area extending beyond the end distal of the tube 22 which end is at a significant distance in particular from the neck 27 of the nozzle 3.
  • the intermediate tube 28 is provided externally with projections 29 forming spacers vis-à-vis the outer tube 1, the tube 28 being threaded at its proximal end on a shoulder of the diabolo 7.
  • annular spaces between the tubes 1, 25 and 28 communicate, at their distal end, by an annular chamber 30 formed between the nozzle 3 and tube 1.
  • the annular space between tubes 1 and 28 communicates at their end proximal with the inside of the handle 2, however at this same end the annular space between the tubes 25 and 28 communicates with a annular chamber 31 delimited between the internal face hollowed out along a channel circular 32 of semi-circular section of the diabolo 7 and an inclined face 33 of the injector 20.
  • the helical grooves 24 of the injector 20 open at their ends upstream, in the annular chamber 31 and, at their downstream end, in the space annular 34 between the tubes 25 and 22, which space constitutes the combustion of the lance.
  • combustion chamber 34 also open out radial channels 35 passing through the injector 20 by communicating the space annular 21 with the chamber 34, the inclination of said channels 35 being of around 30 to 90 ° and more particularly 45 ° relative to the axis of the launch.
  • abrasive agent or the like is introduced into the lance via the connection tube. 10 and the tube 22.
  • abrasive agent or the like is meant any agent granular or powdery solid for example, or liquid such as water, this last or the vehicle (gaseous or liquid) of the particulate agent being conveyed under an appropriate pressure, adjustable so as to obtain the flow rate to feed the appropriate lance.
  • Fuel in gaseous form for example, is sent to the appropriate pressure via fitting 17, annular chamber 9, space annular 21 then the radial channels 35, towards the combustion chamber 34.
  • Combustion air is supplied, at the appropriate pressure, via handle 2, the annular space 8, the space between the tubes 1 and 28, the annular chamber 30, the space between the tubes 25 and 28, the annular chamber 31 and the grooves helical 24, to combustion chamber 34.
  • Gas injection is direct without premixing with the combustion air before entering the combustion chamber 34.
  • the injection is carried out by several orifices arranged in an arc coaxial with the lance and supplying the primary zone of said chamber.
  • the lance is started in the known manner using a spark plug (not shown) arranged in the combustion chamber 34, substantially a third of its length from the injector 20.
  • Such a feeding also makes it possible to create pockets rich in gases upstream of the injector 20 which provide better flame stability, which makes starting easier.
  • the combustible gas is transported thanks to its natural trigger pressure.
  • the stabilization of the flame is also obtained thanks to the aerodynamic trajectory of the combustion air generated by the grooves helical 24 machined at the periphery of the injector 20.
  • the groove section is used to calibrate the combustion air flow and the no propeller generates an aerodynamic recirculation vortex in the combustion chamber 34.
  • the angle of inclination of the channels 35 is chosen so as to supply combustible gas to the vortex of the mixture fuel-oxidant without disturbing its establishment.
  • the baffled trajectory of cold combustion air in the double space annular between the tubes 1, 25 and 28 allows to cool the lance and to increase thus its lifespan. Note also the cooling of the sonic neck from the nozzle 3 by the circulation in the chamber 30 of the combustion air.
  • Abrasive particles or the like are thus effectively warmed up, and accelerated to the point of reaching speed lance output of the order of 800 to 850m / s, with combustion temperatures in the chamber 34 which can reach 2000 ° C. with an ejection temperature of around 700 ° C.
  • the lance of the invention it is possible to replace the gaseous fuel with a liquid fuel supplied by the same way, the fitting 17.
  • This pre-mixing is done simply by slightly unscrewing the nozzle 18 so that spaces 8 and 9 communicate via passage 15 and calibrating the combustion air passage section from space 8 to space 9 by an appropriate positioning of the nozzle 18.
  • the lance according to the invention can be used possibly to spray an abrasive when cold, at subsonic speed, to project a heat flux for thermal stripping or to project a coating media.
  • the invention is obviously not limited to the embodiment represented and described above but on the contrary covers all the variants thereof, especially with regard to the number, shape, dimensions and arrangement fuel and fuel air lines in the injector 20.

Abstract

The gun has an envelope (1) housing a combustion chamber (34) and terminating in a nozzle (3). A conduit (10) inside the housing is supplied with abrasive. An annular injector (20) delivers fuel radially (35) between the conduit and the inside of a tubular sleeve (25) with air holes (26) along its length. Air is delivered (24) through a spiral passage to the outside of the tubular sleeve.

Description

La présente invention a trait au décapage thermo-mécanique par projection à l'aide d'une lance ou pistolet d'un abrasif à l'aide de gaz issus de la combustion d'un carburant et d'air comprimé.The present invention relates to thermo-mechanical pickling by projection using an lance or pistol with an abrasive using gases from combustion of fuel and compressed air.

Ce principe de décapage est bien connu et met en oeuvre des dispositifs de projection qui tous utilisent un carburant liquide qui est pulvérisé et mélangé à de l'air comprimé, l'ensemble étant introduit et brûlé dans une chambre de combustion. On génère ainsi un flux de produits de combustion gazeux d'une température élevée, et qui en s'écoulant hors de la chambre de combustion entraíne des particules abrasives acheminées à l'aide d'un gaz porteur approprié.This pickling principle is well known and implements devices which all use liquid fuel which is sprayed and mixed with compressed air, the assembly being introduced and burned in a combustion chamber. This generates a flow of combustion products gaseous at a high temperature, and which flows out of the combustion results in abrasive particles transported using a gas suitable carrier.

Les dispositifs connus présentent divers inconvénients, notamment des problèmes de démarrage, de stabilité de la combustion, de rendement, de longévité et ne permettent pas par ailleurs l'utilisation de carburants gazeux. Or, sur ce dernier aspect, il serait avantageux de pouvoir utiliser un carburant gazeux, car ce dernier a un rendement énergétique et un pouvoir calorifique supérieurs à ceux d'un carburant liquide et, de surcroít, le mélange d'un carburant avec un comburant tous les deux gazeux est meilleur car plus homogène et beaucoup plus propre et donc écologique car ne générant pas de particules lourdes imbrûlées.Known devices have various drawbacks, including problems with starting, combustion stability, efficiency, longevity and do not otherwise allow the use of gaseous fuels. However, on this last aspect, it would be advantageous to be able to use a fuel gaseous because the latter has an energy efficiency and a calorific value superior to that of a liquid fuel and, moreover, the mixture of a fuel with an oxidizer both gaseous is better because more homogeneous and much cleaner and therefore ecological because it does not generate heavy unburnt particles.

La présente invention a précisément pour but de pallier les inconvénients des dispositifs de projection thermo-mécanique connus en proposant une lance thermo-abrasive à démarrage plus simple, rapide et pratique, plus fiable, plus efficace et susceptible d'utiliser aussi bien des carburants gazeux que des carburants liquides.The object of the present invention is precisely to overcome the drawbacks known thermo-mechanical projection devices by proposing a lance simpler, faster and more practical, more reliable, more efficient and capable of using both gaseous fuels and liquid fuels.

A cet effet, l'invention a pour objet une lance thermo-abrasive comprenant :

  • une enveloppe tubulaire métallique externe munie à une extrémité d'une buse d'éjection et définissant une chambre de combustion ;
  • un conduit central disposé dans ladite chambre de combustion, raccordable à une source externe d'agent abrasif ou analogue, et
  • un système d'injection disposé entre l'enveloppe externe et le conduit d'introduction d'agent abrasif ou analogue, agencé pour acheminer dans ladite chambre de combustion un carburant et de l'air comburant ;
caractérisée en ce que ledit système d'injection est constitué :
  • d'un injecteur annulaire interposé entre ledit conduit central et une enveloppe tubulaire interne coaxiale à l'enveloppe tubulaire externe et reliée à son extrémité distale à ladite buse d'éjection, ladite enveloppe interne étant percée de passages d'air comburant et délimitant ladite chambre de combustion,
  • d'un premier trajet d'acheminement dudit carburant dans la chambre de combustion comprenant un jeu de canaux rayonnants dont les axes définissent une surface conique coaxiale à la lance, lesdits canaux reliant la chambre de combustion à une première chambre en amont de l'injecteur, communiquant avec une entrée d'admission de carburant sous pression,
  • et d'un second trajet d'acheminement de l'air comburant dans la chambre de combustion comprenant un jeu de canaux hélicoïdaux ménagés dans l'injecteur et reliant la chambre de combustion à une seconde chambre en amont de l'injecteur, communiquant, via l'espace annulaire entre ladite enveloppe externe et ladite enveloppe interne, avec une entrée d'admission d'air comburant sous pression.
To this end, the subject of the invention is a thermo-abrasive lance comprising:
  • an external metallic tubular casing provided at one end with an ejection nozzle and defining a combustion chamber;
  • a central duct disposed in said combustion chamber, connectable to an external source of abrasive agent or the like, and
  • an injection system arranged between the outer casing and the conduit for introducing an abrasive agent or the like, arranged to convey fuel and combustion air into said combustion chamber;
characterized in that said injection system consists of:
  • an annular injector interposed between said central duct and an internal tubular casing coaxial with the external tubular casing and connected at its distal end to said ejection nozzle, said internal casing being pierced with combustion air passages and delimiting said chamber combustion,
  • a first path for conveying said fuel into the combustion chamber comprising a set of radiating channels, the axes of which define a conical surface coaxial with the lance, said channels connecting the combustion chamber to a first chamber upstream of the injector , communicating with a pressure fuel inlet,
  • and a second path for conveying the combustion air into the combustion chamber comprising a set of helical channels formed in the injector and connecting the combustion chamber to a second chamber upstream of the injector, communicating via the annular space between said external envelope and said internal envelope, with an inlet for admission of pressurized combustion air.

L'invention vise d'une manière générale tout décapage faisant intervenir un agent abrasif ou analogue, cette dernière expression désignant tout agent solide ou liquide tel que de l'eau par exemple, l'agent solide étant à l'état particulaire ou granulaire véhiculé par un fluide gazeux ou liquide approprié.The invention relates generally to any pickling involving an abrasive agent or the like, the latter expression designating any agent solid or liquid such as water for example, the solid agent being in the state particulate or granular carried by a suitable gaseous or liquid fluid.

La lance de l'invention est susceptible d'accepter comme carburant un liquide aussi bien qu'un gaz tout en offrant une très bonne stabilité de flamme, un bon rendement, une mise en marche facile et une efficacité accrue du fait des hautes températures d'éjection pouvant être atteintes, de l'ordre de 700°C à l'éjection et des hautes vitesses d'éjection de flux chargé de l'agent abrasif ou analogue, ces vitesses pouvant atteindre des valeurs de l'ordre de 800 à 850 m/s.The lance of the invention is capable of accepting as fuel a liquid as well as gas while offering very good flame stability, good performance, easy start-up and increased efficiency due to high ejection temperatures which can be reached, of the order of 700 ° C at ejection and high agent ejection velocities abrasive or the like, these speeds possibly reaching values of the order of 800 to 850 m / s.

Suivant un mode de réalisation, ledit second trajet d'acheminement de l'air comburant dans la chambre de combustion est constitué de gorges hélicoïdales ménagées à la périphérie de l'injecteur entre ce dernier et ladite enveloppe interne délimitant la chambre de combustion, les débouchés dans cette dernière destites gorges hélicoïdales étant alignés suivant un cercle parallèle au cercle d'alignement des débouchés des canaux d'admission du carburant, l'angle formé entre le jet de sortie desdites gorges hélicoïdales et le plan du premier cercle susnommé étant compris dans une plage de l'ordre de 5 degrés à 20 degrés, et plus particulièrement 9 à 10 degrés, cependant que l'angle formé entre l'axe de la lance et lesdits canaux d'admission du carburant est compris dans une plage de l'ordre de 30 degrés à 90 degrés.According to one embodiment, said second routing path of the combustion air in the combustion chamber consists of grooves helical formed at the periphery of the injector between the latter and said internal envelope delimiting the combustion chamber, the outlets in the latter of the helical grooves being aligned in a circle parallel to the alignment circle of the outlets of the intake channels of the fuel, the angle formed between the outlet jet of said helical grooves and the plane of the first aforementioned circle being within a range of the order of 5 degrees to 20 degrees, and more particularly 9 to 10 degrees, while the angle formed between the axis of the lance and said fuel inlet channels is in the range of about 30 degrees to 90 degrees.

Suivant une autre caractéristique de la lance selon l'invention la première chambre en amont de l'injecteur est une chambre annulaire entourant ledit conduit d'agent abrasif ou analogue, ladite chambre annulaire étant reliée à une source externe de carburant, gazeux ou liquide, via un raccord muni d'un gicleur de réglage de débit autorisant l'admission d'air comburant dans ladite chambre annulaire parallèlement au carburant.According to another characteristic of the lance according to the invention the first chamber upstream of the injector is an annular chamber surrounding said abrasive agent conduit or the like, said annular chamber being connected to an external source of fuel, gaseous or liquid, via a fitting fitted with a flow adjustment nozzle allowing the admission of combustion air into said flow annular chamber parallel to the fuel.

Suivant une autre caractéristique de la lance la seconde chambre en amont de l'injecteur est une chambre annulaire entourant le conduit d'agent abrasif ou analogue ainsi que ladite première chambre d'amont, ladite chambre annulaire communiquant avec l'entrée d'admission d'air comburant via une chicane constituée par une enveloppe tubulaire intermédiaire coaxiale auxdites enveloppes externe et interne et disposée à distance de ces dernières en sorte de contraindre le flux d'air comburant d'entrée à lécher la paroi interne de l'enveloppe externe jusqu'à son extrémité distale puis la paroi externe de l'enveloppe interne pour déboucher enfin dans ladite chambre annulaire.According to another characteristic of the lance, the second chamber in upstream of the injector is an annular chamber surrounding the agent conduit abrasive or the like and said first upstream chamber, said chamber ring communicating with the combustion air intake inlet via a baffle formed by an intermediate tubular casing coaxial with said external and internal envelopes and arranged at a distance from the latter so to constrain the flow of combustion air at the entrance to lick the internal wall of the outer envelope to its distal end then the outer wall of the internal envelope to finally open into said annular chamber.

Avantageusement, l'air comburant est acheminé dans une partie creuse d'une poignée dont est munie la lance et est distribué dans une préchambre annulaire ménagée dans la partie proximale de la lance, laquelle préchambre communique avec l'espace annulaire entre lesdites enveloppes externe et intermédiaire.Advantageously, the combustion air is supplied in a hollow part a handle which is provided with the lance and is distributed in a prechamber annular formed in the proximal part of the lance, which prechamber communicates with the annular space between said outer envelopes and intermediate.

Suivant encore une autre caractéristique de la lance suivant l'invention l'extrémité distale du conduit d'agent abrasif ou analogue est à distance substantielle du col de la buse d'éjection, en sorte de constituer notamment une zone d'accélération contribuant à la génération d'un flux de sortie à vitesse élevée.According to yet another characteristic of the lance according to the invention the distal end of the abrasive or similar conduit is spaced the neck of the ejection nozzle, so as to constitute in particular an acceleration zone contributing to the generation of an output flow at high speed.

D'autres caractéristiques et avantages ressortiront de la description qui va suivre d'un mode de réalisation de la lance selon l'invention, description donnée à titre d'exemple uniquement et en regard des dessins annexés sur lesquels :

  • Figure 1 représente en coupe axiale une lance conforme à l'invention ;
  • Figure 2 est une coupe axiale agrandie de l'injecteur de la lance de la figure 1 ;
  • Figure 3 est une vue en élévation latérale de l'enveloppe intermédiaire de la lance de la figure 1 ;
  • Figure 4 est une vue en bout de l'enveloppe de la figure 3, et
  • Figure 5 est une vue en élévation agrandie du gicleur d'admission de carburant de la lance.
Other characteristics and advantages will emerge from the description which follows of an embodiment of the lance according to the invention, description given by way of example only and with reference to the appended drawings in which:
  • Figure 1 shows in axial section a lance according to the invention;
  • Figure 2 is an enlarged axial section of the injector of the lance of Figure 1;
  • Figure 3 is a side elevational view of the intermediate casing of the lance of Figure 1;
  • Figure 4 is an end view of the envelope of Figure 3, and
  • Figure 5 is an enlarged elevational view of the fuel inlet nozzle of the lance.

Sur la figure 1 on a représenté un mode de réalisation d'une lance thermo-abrasive selon l'invention comprenant un tube extérieur 1, métallique, cylindrique, solidaire à son extrémité proximale d'une poignée métallique cylindre creuse 2 et pourvu, à son extrémité distale, d'une buse de sablage 3 fixée par une virole 4 vissée sur l'extrémité filetée dudit tube 1.In Figure 1 there is shown an embodiment of a lance thermo-abrasive according to the invention comprising an outer metal tube 1, cylindrical, integral at its proximal end with a metal handle hollow cylinder 2 and provided, at its distal end, with a sandblasting nozzle 3 fixed by a ferrule 4 screwed onto the threaded end of said tube 1.

La poignée creuse 2 est ouverte à ses deux extrémités et communique par l'une d'elles avec l'intérieur du tube 1 par un orifice de passage 5 et par l'autre extrémités avec une canalisation souple (non représentée) d'amenée d'air comburant sous pression provenant d'une source appropriée, par l'intermédiaire d'un raccord rapide susceptible d'être vissé sur un filetage 6 ménagé sur ladite extrémité de la poignée 2.The hollow handle 2 is open at both ends and communicates by one of them with the inside of the tube 1 by a passage orifice 5 and by the other end with a flexible supply pipe (not shown) combustion air under pressure from an appropriate source, for example via a quick coupling capable of being screwed onto a thread 6 formed on said end of the handle 2.

L'extrémité proximale du tube 1 est fermée par une pièce en forme de diabolo 7 définissant une chambre annulaire 8 interne au tube 1 et communiquant avec l'intérieur de la poignée 2.The proximal end of the tube 1 is closed by a piece in the form of diabolo 7 defining an annular chamber 8 internal to the tube 1 and communicating with the inside of the handle 2.

Le diabolo 7 est percé d'un passage 9 coaxiale au tube 1 et dans lequel est introduit un tube-raccord 10 dont la partie externe 11 présente un diamètre élargi avec une partie tronconique 12 pressée contre une partie tronconique antagoniste du diabolo 7 avec interposition d'un joint d'étanchéité torique 13.The diabolo 7 is pierced with a passage 9 coaxial with the tube 1 and in which a connection tube 10 is introduced, the external part 11 of which has a diameter enlarged with a frustoconical part 12 pressed against a frustoconical part diabolo 7 antagonist with interposition of an O-ring 13.

L'extrémité externe de la partie 11 comporte un filetage 14 pour le branchement d'une canalisation (non représentée) d'admission d'un agent abrasif ou analogue à l'intérieur de la lance, via le tube-raccord 10.The outer end of the part 11 has a thread 14 for the connection of an agent intake pipe (not shown) abrasive or the like inside the lance, via the connection tube 10.

L'espace annulaire défini par le passage 9, entre le diabolo 7 et le tube 10, communique avec l'espace annulaire 8 par un perçage 15 en regard d'un orifice de passage 16 ménagé dans le tube extérieur 1 et dans lequel est rapporté et fixé par soudage un raccord 17. Sur ce raccord 17 peut être branchée une conduite (non représentée) d'amenée d'un carburant, gazeux ou liquide, provenant d'une source appropriée.The annular space defined by passage 9, between the diabolo 7 and the tube 10, communicates with the annular space 8 by a hole 15 opposite a passage orifice 16 formed in the outer tube 1 and in which is attached and fixed by welding a fitting 17. On this fitting 17 can be connected a line (not shown) for supplying a fuel, gaseous or liquid, from an appropriate source.

A l'intérieur du raccord 17 est disposé un gicleur 18 (figure 5) dont l'extrémité distale tronconique 19 est chargée par appui contre le bord du passage 15 d'assurer l'étanchéité vis-à-vis de la chambre annulaire 8. Le gicleur 18 est réglable axialement par vissage grâce à un filetage externe 18a coopérant avec un filetage interne du raccord 17.Inside the fitting 17 is arranged a nozzle 18 (FIG. 5) of which the frustoconical distal end 19 is loaded by pressing against the edge of the passage 15 for sealing against the annular chamber 8. The nozzle 18 is axially adjustable by screwing thanks to an external thread 18a cooperating with an internal thread of the connector 17.

En outre, le gicleur 18 est muni d'un passage axial 18b qui le traverse d'une extrémité à l'autre.In addition, the nozzle 18 is provided with an axial passage 18b which passes through it from one end to the other.

Dans le passage 9, à l'extrémité interne du diabolo 7, est engagé un injecteur 20 coaxial au tube 1 et présentant un passage central cylindrique 20a dans lequel s'étend le tube-raccord 10, un espace annulaire 21 subsistant entre les deux pièces 20 et 10. L'espace annulaire 21 est fermé à l'extrémité interne de l'injecteur 20 par le pied d'un tube 22 coaxial au tube 1 et chargé d'acheminer l'agent abrasif ou analogue en aval de l'injecteur 20.In passage 9, at the inner end of the diabolo 7, is engaged a injector 20 coaxial with tube 1 and having a central cylindrical passage 20a in which the connecting tube 10 extends, an annular space 21 remaining between the two parts 20 and 10. The annular space 21 is closed at the end internal of the injector 20 by the foot of a tube 22 coaxial with the tube 1 and loaded conveying the abrasive agent or the like downstream of the injector 20.

Le pied du tube 22 est vissé sur un filetage ménagé à l'extrémité du tube-raccord 10, en pressant l'injecteur 20 contre le diabolo 7, maintenant ainsi en place ledit injecteur.The foot of the tube 22 is screwed onto a thread formed at the end of the tube-connector 10, pressing the injector 20 against the diabolo 7, now thus in place said injector.

L'injecteur 20 est représenté agrandi sur la figure 2. Il comporte une partie de diamètre élargie définissant une paroi cylindrique 23 coaxiale au passage 20a et dans laquelle sont creusées plusieurs gorges hélicoïdales identiques 24 à section rectangulaire.The injector 20 is shown enlarged in Figure 2. It includes a part of enlarged diameter defining a cylindrical wall 23 coaxial with passage 20a and in which several helical grooves are dug identical 24 with rectangular section.

A titre d'exemple, il est prévu 2 gorges dont le pas est de l'ordre de 18 mm pour un diamètre de la paroi 23 de l'ordre de 36 mm.For example, 2 grooves are provided, the pitch of which is of the order of 18 mm for a diameter of the wall 23 of the order of 36 mm.

Les orifices amont des deux gorges 24 sont diamétralement opposés et chaque gorge présente par exemple une section de 2 x 4 mm.The upstream orifices of the two grooves 24 are diametrically opposite and each groove has for example a section of 2 x 4 mm.

La section totale de passage de l'air comburant dans les deux gorges 24 est avantageusement de 16 mm2 pour un diamètre de la buse d'éjection 3 de l'ordre de 13 mm. Cette section totale peut varier dans une plage de 10 à 30 mm2 avec un nombre de gorges égal ou supérieur à deux.The total cross-section of the combustion air in the two grooves 24 is advantageously 16 mm 2 for a diameter of the ejection nozzle 3 of the order of 13 mm. This total section can vary within a range of 10 to 30 mm 2 with a number of grooves equal to or greater than two.

Les gorges 24 sont fermées à hauteur de la paroi 23 par un tube manchon 25 dit tube intérieur, coaxial au tube 1 et s'étendant jusqu'à la buse 3 sur l'extrémité interne de laquelle il est vissé.The grooves 24 are closed at the height of the wall 23 by a tube sleeve 25 said inner tube, coaxial with tube 1 and extending to the nozzle 3 on the inner end of which it is screwed.

Le tube intérieur 25 est muni de perforations 26 approximativement dans sa partie centrale, la zone perforée s'étendant au delà de l'extrémité distale du tube 22 laquelle extrémité se trouve à une distance importante notamment du col 27 de la buse 3.The inner tube 25 is provided with perforations 26 approximately in its central part, the perforated area extending beyond the end distal of the tube 22 which end is at a significant distance in particular from the neck 27 of the nozzle 3.

Entre les tubes intérieur 25 et extérieur 1 est disposé un tube dit intermédiaire 28 coaxial aux deux autres tubes et représenté plus clairement sur les figures 3 et 4.Between the inner 25 and outer 1 tubes is disposed a so-called tube intermediate 28 coaxial with the other two tubes and shown more clearly in Figures 3 and 4.

A chaque extrémité le tube intermédiaire 28 est muni extérieurement de saillies 29 formant entretoises d'écartement vis-à-vis du tube extérieur 1, le tube 28 étant enfilé à son extrémité proximale sur un épaulement du diabolo 7. At each end the intermediate tube 28 is provided externally with projections 29 forming spacers vis-à-vis the outer tube 1, the tube 28 being threaded at its proximal end on a shoulder of the diabolo 7.

Les espaces annulaires entre les tubes 1, 25 et 28 communiquent, à leur extrémité distale, par une chambre annulaire 30 ménagée entre la buse 3 et le tube 1.The annular spaces between the tubes 1, 25 and 28 communicate, at their distal end, by an annular chamber 30 formed between the nozzle 3 and tube 1.

L'espace annulaire entre les tubes 1 et 28 communique à leur extrémité proximale avec l'intérieur de la poignée 2 cependant qu'à cette même extrémité l'espace annulaire entre les tubes 25 et 28 communique avec une chambre annulaire 31 délimitée entre la face interne évidée suivant un canal circulaire 32 de section semi-circulaire du diabolo 7 et une face inclinée 33 de l'injecteur 20.The annular space between tubes 1 and 28 communicates at their end proximal with the inside of the handle 2, however at this same end the annular space between the tubes 25 and 28 communicates with a annular chamber 31 delimited between the internal face hollowed out along a channel circular 32 of semi-circular section of the diabolo 7 and an inclined face 33 of the injector 20.

Les gorges hélicoïdales 24 de l'injecteur 20 débouchent, à leur extrémité amont, dans la chambre annulaire 31 et, à leur extrémité aval, dans l'espace annulaire 34 entre les tubes 25 et 22, lequel espace constitue la chambre de combustion de la lance.The helical grooves 24 of the injector 20 open at their ends upstream, in the annular chamber 31 and, at their downstream end, in the space annular 34 between the tubes 25 and 22, which space constitutes the combustion of the lance.

Dans cette chambre de combustion 34 débouchent également des canaux radiaux 35 traversant l'injecteur 20 en faisant communiquer l'espace annulaire 21 avec la chambre 34, l'inclinaison desdits canaux 35 étant de l'ordre de 30 à 90° et plus particulièrement 45° par rapport à l'axe de la lance.In this combustion chamber 34 also open out radial channels 35 passing through the injector 20 by communicating the space annular 21 with the chamber 34, the inclination of said channels 35 being of around 30 to 90 ° and more particularly 45 ° relative to the axis of the launch.

Le fonctionnement de la lance ci-dessus décrite est le suivant.The operation of the lance described above is as follows.

L'agent abrasif ou analogue est introduit dans la lance via le tube-raccord 10 et le tube 22. Par agent abrasif ou analogue on entend tout agent solide granulaire ou pulvérulent par exemple, ou liquide tel que de l'eau, ce dernier ou le véhicule (gazeux ou liquide) de l'agent particulaire étant acheminé sous une pression appropriée, réglable en sorte d'obtenir le débit d'alimentation de la lance approprié.The abrasive agent or the like is introduced into the lance via the connection tube. 10 and the tube 22. By abrasive agent or the like is meant any agent granular or powdery solid for example, or liquid such as water, this last or the vehicle (gaseous or liquid) of the particulate agent being conveyed under an appropriate pressure, adjustable so as to obtain the flow rate to feed the appropriate lance.

Le carburant, sous forme gazeuse par exemple, est acheminé à la pression appropriée via le raccord 17, la chambre annulaire 9, l'espace annulaire 21 puis les canaux radiaux 35, vers la chambre de combustion 34.Fuel, in gaseous form for example, is sent to the appropriate pressure via fitting 17, annular chamber 9, space annular 21 then the radial channels 35, towards the combustion chamber 34.

L'air comburant est acheminé, à la pression appropriée, via la poignée 2, l'espace annulaire 8, l'espace entre les tubes 1 et 28, la chambre annulaire 30, l'espace entre les tubes 25 et 28, la chambre annulaire 31 et les gorges hélicoïdales 24, vers la chambre de combustion 34. Combustion air is supplied, at the appropriate pressure, via handle 2, the annular space 8, the space between the tubes 1 and 28, the annular chamber 30, the space between the tubes 25 and 28, the annular chamber 31 and the grooves helical 24, to combustion chamber 34.

L'injection du gaz est directe sans pré-mélange avec l'air comburant avant de pénétrer dans la chambre de combustion 34. L'injection est réalisée par plusieurs orifices disposés en arc de cercle coaxial à la lance et alimentant la zone primaire de ladite chambre.Gas injection is direct without premixing with the combustion air before entering the combustion chamber 34. The injection is carried out by several orifices arranged in an arc coaxial with the lance and supplying the primary zone of said chamber.

On obtient ainsi une répartition plus uniforme des températures de combustion et on améliore sensiblement la longévité des matériaux composant la chambre.A more uniform distribution of temperatures is thus obtained. combustion and significantly improves the longevity of the component materials bedroom.

Le démarrage de la lance est réalisé à la manière connue à l'aide d'une bougie d'allumage (non représentée) disposée dans la chambre de combustion 34, sensiblement au tiers de sa longueur à partir de l'injecteur 20.The lance is started in the known manner using a spark plug (not shown) arranged in the combustion chamber 34, substantially a third of its length from the injector 20.

Une telle alimentation permet en outre de créer des poches riches en gaz en amont de l'injecteur 20 qui assurent une meilleure stabilité de flamme, ce qui facilite le démarrage. Le gaz combustible est véhiculé grâce à sa pression de détente naturelle.Such a feeding also makes it possible to create pockets rich in gases upstream of the injector 20 which provide better flame stability, which makes starting easier. The combustible gas is transported thanks to its natural trigger pressure.

Il ne nécessite donc aucune autre énergie ou néanmoins supplémentaire pour assurer son acheminement dans la chambre de combustion.It therefore requires no other or additional energy to ensure its routing in the combustion chamber.

Ceci simplifie le système et le rend fiable et économique.This simplifies the system and makes it reliable and economical.

La stabilisation de la flamme est également obtenue grâce à la trajectoire aérodynamique de l'air comburant générée par les gorges hélicoïdales 24 usinées à la périphérie de l'injecteur 20.The stabilization of the flame is also obtained thanks to the aerodynamic trajectory of the combustion air generated by the grooves helical 24 machined at the periphery of the injector 20.

La section des gorges permet de calibrer le débit d'air comburant et le pas de l'hélice permet de générer un tourbillon aérodynamique de recirculation dans la chambre de combustion 34. L'angle d'inclinaison des canaux 35 est choisi de façon à alimenter en gaz combustible le tourbillon du mélange combustible-comburant sans perturber son établissement.The groove section is used to calibrate the combustion air flow and the no propeller generates an aerodynamic recirculation vortex in the combustion chamber 34. The angle of inclination of the channels 35 is chosen so as to supply combustible gas to the vortex of the mixture fuel-oxidant without disturbing its establishment.

La trajectoire en chicane de l'air comburant froid dans le double espace annulaire entre les tubes 1, 25 et 28 permet de refroidir la lance et d'accroítre ainsi sa durée de vie. Il est à noter également le refroidissement du col sonique de la buse 3 par la circulation dans la chambre 30 de l'air frais comburant.The baffled trajectory of cold combustion air in the double space annular between the tubes 1, 25 and 28 allows to cool the lance and to increase thus its lifespan. Note also the cooling of the sonic neck from the nozzle 3 by the circulation in the chamber 30 of the combustion air.

Le fait de disposer le nez du tube 22 très en retrait de la buse 3 et à hauteur de la zone perforée 26 du tube 25 assure un meilleur mélange des gaz de combustion et du flux abrasif acheminé par le tube 22. Having the nose of the tube 22 very far back from the nozzle 3 and at height of the perforated zone 26 of the tube 25 ensures better mixing of the gases of combustion and of the abrasive flow conveyed by the tube 22.

Les particules abrasives ou analogues sont ainsi efficacement réchauffées, et accélérées au point d'atteindre en sortie de lance des vitesses de l'ordre de 800 à 850m/s, avec des températures de combustion dans la chambre 34 pouvant atteindre 2000°C avec une température d'éjection de l'ordre de 700°C.Abrasive particles or the like are thus effectively warmed up, and accelerated to the point of reaching speed lance output of the order of 800 to 850m / s, with combustion temperatures in the chamber 34 which can reach 2000 ° C. with an ejection temperature of around 700 ° C.

Selon une caractéristique très avantageuse de la lance de l'invention il est possible de substituer au carburant gazeux un carburant liquide acheminé par la même voie, le raccord 17.According to a very advantageous characteristic of the lance of the invention it it is possible to replace the gaseous fuel with a liquid fuel supplied by the same way, the fitting 17.

Le fonctionnement de la lance est similaire avec cette seule différence qu'un pré-mélange carburant-air comburant est réalisé avant introduction dans la chambre de combustion 34 via les canaux 35.The functioning of the lance is similar with this only difference that a fuel-air oxidizer pre-mixture is produced before introduction into the combustion chamber 34 via the channels 35.

Ce pré-mélange est opéré simplement en dévissant légèrement le gicleur 18 en sorte de faire communiquer les espaces 8 et 9 via le passage 15 et en calibrant la section de passage de l'air comburant de l'espace 8 vers l'espace 9 par un positionnement approprié du gicleur 18.This pre-mixing is done simply by slightly unscrewing the nozzle 18 so that spaces 8 and 9 communicate via passage 15 and calibrating the combustion air passage section from space 8 to space 9 by an appropriate positioning of the nozzle 18.

Il est à noter par ailleurs que la lance selon l'invention peut être utilisée éventuellement pour projeter un abrasif à froid, à vitesse subsonique, pour projeter un flux thermique pour un décapage thermique ou pour projeter un média de revêtement.It should also be noted that the lance according to the invention can be used possibly to spray an abrasive when cold, at subsonic speed, to project a heat flux for thermal stripping or to project a coating media.

Enfin, l'invention n'est évidemment pas limitée au mode de réalisation représenté et décrit ci-dessus mais en couvre au contraire toutes les variantes, notamment en ce qui concerne les nombre, forme, dimensions et disposition des conduits d'acheminement du combustible et d'air carburant dans l'injecteur 20.Finally, the invention is obviously not limited to the embodiment represented and described above but on the contrary covers all the variants thereof, especially with regard to the number, shape, dimensions and arrangement fuel and fuel air lines in the injector 20.

Claims (9)

Lance thermo-abrasive comprenant : une enveloppe tubulaire métallique externe (1) munie à une extrémité d'une buse d'éjection (3) et définissant une chambre de combustion (34) ; un conduit central (10) disposé dans ladite chambre de combustion, raccordable à une source externe d'agent abrasif ou analogue, et un système d'injection (20) disposé entre l'enveloppe externe (1) et le conduit (10) d'introduction d'agent abrasif ou analogue, agencé pour acheminer dans ladite chambre de combustion (34) un carburant et de l'air comburant ; caractérisée en ce que ledit système d'injection est constitué : d'un injecteur annulaire (20) interposé entre ledit conduit central (10) et une enveloppe tubulaire interne (25) coaxiale à l'enveloppe tubulaire externe (1) et reliée à son extrémité distale à ladite buse d'éjection (3), ladite enveloppe interne (25) étant percée de passages (26) d'air comburant et délimitant ladite chambre de combustion (34), d'un premier trajet d'acheminement dudit carburant dans la chambre de combustion (34) comprenant un jeu de canaux rayonnants (35) dont les axes définissent une surface conique coaxiale à la lance, lesdits canaux (35) reliant la chambre de combustion (34) à une première chambre (9,21) en amont de l'injecteur (20), communiquant avec une entrée (9) d'admission de carburant sous pression, et d'un second trajet d'acheminement de l'air comburant dans la chambre de combustion (34) comprenant un jeu de canaux hélicoïdaux (24) ménagés dans l'injecteur (20) et reliant la chambre de combustion à une seconde chambre (31) en amont de l'injecteur, communiquant, via l'espace annulaire entre ladite enveloppe externe (1) et ladite enveloppe interne (25), avec une entrée (5) d'admission d'air comburant sous pression. Thermo-abrasive lance comprising: an external metallic tubular casing (1) provided at one end with an ejection nozzle (3) and defining a combustion chamber (34); a central duct (10) disposed in said combustion chamber, connectable to an external source of abrasive agent or the like, and an injection system (20) disposed between the outer casing (1) and the conduit (10) for introducing abrasive agent or the like, arranged to convey fuel and fuel into said combustion chamber (34) combustion air; characterized in that said injection system consists of: an annular injector (20) interposed between said central duct (10) and an internal tubular casing (25) coaxial with the external tubular casing (1) and connected at its distal end to said ejection nozzle (3), said internal envelope (25) being pierced with passages (26) for combustion air and delimiting said combustion chamber (34), a first path for conveying said fuel into the combustion chamber (34) comprising a set of radiating channels (35) whose axes define a conical surface coaxial with the lance, said channels (35) connecting the combustion chamber ( 34) to a first chamber (9,21) upstream of the injector (20), communicating with an inlet (9) for admission of pressurized fuel, and a second path for conveying the combustion air into the combustion chamber (34) comprising a set of helical channels (24) formed in the injector (20) and connecting the combustion chamber to a second chamber ( 31) upstream of the injector, communicating, via the annular space between said external envelope (1) and said internal envelope (25), with an inlet (5) for admitting pressurized combustion air. Lance thermo-abrasive suivant la revendication 1, plus particulièrement destinée à fonctionner avec un carburant liquide, caractérisée en ce que ladite entrée (9) d'admission de carburant assure en parallèle l'admission d'air comburant.Heat-abrasive lance according to claim 1, more particularly intended to operate with a liquid fuel, characterized in that said fuel inlet inlet (9) ensures in parallel the intake of combustion air. Lance thermo-abrasive suivant la revendication 1 ou 2, caractérisée en ce que ledit second trajet d'acheminement de l'air comburant dans la chambre de combustion (34) est constitué de gorges hélicoïdales (24) ménagées à la périphérie de l'injecteur (20) entre ce dernier et ladite enveloppe interne (25) délimitant la chambre de combustion, les débouchés dans cette dernière destites gorges hélicoïdales (24) étant alignés suivant un cercle parallèle au cercle d'alignement des débouchés des canaux (35) d'admission du carburant, l'angle formé entre le jet de sortie desdites gorges hélicoïdales (24) et le plan du premier cercle susnommé étant compris dans une plage de l'ordre de 5 degrés à 20 degrés, typiquement 9 à 10 degrés, cependant que l'angle formé entre l'axe de la lance et lesdits canaux (35) d'admission du carburant est compris dans une plage de l'ordre de 30 degrés à 90 degrés.Thermo-abrasive lance according to claim 1 or 2, characterized in that said second path for the combustion air in the combustion chamber (34) consists of helical grooves (24) formed at the periphery of the injector (20) between the latter and said internal envelope (25) delimiting the combustion chamber, the outlets in the latter of the helical grooves (24) being aligned in a circle parallel to the alignment circle of the outlets of the channels (35) of fuel intake, the angle formed between the outlet jet of said helical grooves (24) and the plane of the first abovementioned circle being within a range of the order of 5 degrees to 20 degrees, typically 9 to 10 degrees, while the angle formed between the axis of the lance and said fuel intake channels (35) is within a range of the order of 30 degrees to 90 degrees. Lance thermo-abrasive suivant l'une des revendications 1 à 3, caractérisée en ce que la première chambre (9,21) en amont de l'injecteur (20) est une chambre annulaire entourant ledit conduit (10) d'agent abrasif ou analogue, ladite chambre annulaire (9,21) étant reliée à une source externe de carburant, gazeux ou liquide, via un raccord (17) muni d'un gicleur (18) de réglage de débit autorisant l'admission d'air comburant dans ladite chambre annulaire (9,21) parallèlement au carburant.Thermo-abrasive lance according to one of claims 1 to 3, characterized in that the first chamber (9,21) upstream of the injector (20) is an annular chamber surrounding said conduit (10) of abrasive agent or similar, said annular chamber (9,21) being connected to an external source of fuel, gaseous or liquid, via a connector (17) provided with a nozzle (18) for adjusting the flow allowing the admission of combustion air into said annular chamber (9,21) parallel to the fuel. Lance thermo-abrasive suivant l'une des revendications 1 à 4, caractérisée en ce que la seconde chambre (31) en amont de l'injecteur (20) est une chambre annulaire entourant le conduit (10) d'agent abrasif ou analogue ainsi que ladite première chambre d'amont (21), ladite chambre annulaire (31) communiquant avec l'entrée (5) d'admission d'air comburant via une chicane constituée par une enveloppe tubulaire intermédiaire (28) coaxiale auxdites enveloppes externe (1) et interne (25) et disposée à distance de ces dernières en sorte de contraindre le flux d'air comburant d'entrée à lécher la paroi interne de l'enveloppe externe (1) jusqu'à son extrémité distale puis la paroi externe de l'enveloppe interne (25) pour déboucher enfin dans ladite chambre annulaire (31).Thermo-abrasive lance according to one of claims 1 to 4, characterized in that the second chamber (31) upstream of the injector (20) is an annular chamber surrounding the conduit (10) of abrasive agent or the like that said first upstream chamber (21), said annular chamber (31) communicating with the combustion air intake inlet (5) via a baffle formed by an intermediate tubular casing (28) coaxial with said external casings (1 ) and internal (25) and disposed at a distance from the latter so as to constrain the flow of combustion air from the inlet to lick the internal wall of the external envelope (1) to its distal end and then the external wall of the internal envelope (25) to finally open into said annular chamber (31). Lance thermo-abrasive suivant l'une des revendications 1 à 5, caractérisée en ce que l'air comburant est acheminé dans une partie creuse d'une poignée (2) dont est munie la lance et est distribué dans une préchambre annulaire (8) ménagée dans la partie proximale de la lance, laquelle préchambre (8) communique avec l'espace annulaire entre lesdites enveloppes externe (1) et intermédiaire (28).Thermo-abrasive lance according to one of claims 1 to 5, characterized in that the combustion air is conveyed in a hollow part of a handle (2) with which the lance is provided and is distributed in an annular prechamber (8) formed in the proximal part of the lance, which prechamber (8) communicates with the annular space between said external (1) and intermediate (28) envelopes. Lance thermo-abrasive suivant les revendications 4 et 6, caractérisée en ce que ladite préchambre annulaire (8) communique par un passage (15) avec ladite première chambre annulaire (9,21) d'admission du carburant, ledit passage (15) étant susceptible d'être obturé par ledit gicleur (18,19) de réglage de débit.Heat-abrasive lance according to claims 4 and 6, characterized in that said annular prechamber (8) communicates by a passage (15) with said first annular fuel admission chamber (9,21), said passage (15) being capable of being closed by said nozzle (18, 19) for adjusting the flow rate. Lance thermo-abrasive suivant l'une des revendications 1 à 7, caractérisée en ce que l'extrémité distale du conduit (10,22) d'agent abrasif ou analogue est à distance substantielle du col (27) de la buse d'éjection (3), en sorte de constituer notamment une zone d'accélération contribuant à la génération d'un flux de sortie à vitesse élevée.Thermo-abrasive lance according to one of claims 1 to 7, characterized in that the distal end of the conduit (10, 22) of abrasive agent or the like is at a substantial distance from the neck (27) of the ejection nozzle (3), so as to constitute in particular an acceleration zone contributing to the generation of an output stream at high speed. Lance thermo-abrasive suivant l'une des revendications 3 à 8, caractérisé en ce que lesdites gorges hélicoïdales (24) sont au nombre de deux et la section totale de passage desdites gorges est comprise entre 10 et 30 mm2 et, de préférence, de l'ordre de 16 mm2 pour une buse d'éjection (3) d'un diamètre de l'ordre de 13 mm.Thermo-abrasive lance according to one of claims 3 to 8, characterized in that said helical grooves (24) are two in number and the total passage section of said grooves is between 10 and 30 mm 2 and, preferably, of the order of 16 mm 2 for an ejection nozzle (3) with a diameter of the order of 13 mm.
EP01450009A 2000-05-17 2001-05-15 Thermoabrasive blast gun Withdrawn EP1155781A1 (en)

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FR0006294A FR2809043B1 (en) 2000-05-17 2000-05-17 THERMO-ABRASIVE LANCE
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WO2003053601A1 (en) * 2001-12-21 2003-07-03 Piller Entgrattechnik Gmbh Method for cleaning, roughening and stripping surfaces
WO2010037548A1 (en) * 2008-10-01 2010-04-08 Technische Universität Chemnitz Method and device for thermally coating surfaces, particularly high-speed flame spraying

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FR2809043B1 (en) 2002-09-27

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