HIGH VELOCITY OXY AIR FUEL THERMAL SPRAY APPARATUS

Abstract

The apparatus comprises a labyrinth mixing device designed to mix a first oxidizer gas and a fuel under pressure, and to inject the mixture produced in a combustion chamber, a torch's main body (1) housing the labyrinth mixing device (2) and connectors (7) for fuel and oxidizer gases, a torch's front part (3) defining, with the labyrinth mixing device (2), the internal geometry of the combustion chamber (4) comprising several second oxidizer gas injectors (32,33) for injecting separately a second oxidizer gas upstream in the combustion chamber to promote the combustion process and connecting down-stream to a gas expanding nozzle (50) designed to receive products of combustion of said mixture and form a high-velocity gaseous jet, an ignition device (30) to start combustion of said mixture, a material delivery device (6) designed to inject an spray material axially into said high-velocity gaseous jet. The labyrinth mixing device (2) comprises one or more flanges (23,24) which define one or more mixing volumes (21,22) and holes (25,26,27), concentrically placed both on the flanges (23,24) and passing through the mixing device (2) and opening at the downstream end of the mixing device (2) for connecting a feeding section (20) of the labyrinth mixing device (2) with the combustion chamber (4). The labyrinth mixing device (2) comprises a crossing axial bore (28) to inject the spray material into the combustion chamber (4).

Claims

1. A high-velocity thermal spray apparatus for depositing a material on a substrate as a surface coating or for building up a bulk material as additive manufacturing comprising: a labyrinth mixing device (2) designed to mix a first oxidizer gas and a fuel under pressure, and to inject the mixture produced in a combustion chamber (4), a torch's main body (1) housing the labyrinth mixing device (2) and connectors (7) for fuel and oxidizer gases, a torch's front part (3) defining, with the labyrinth mixing device (2), the internal geometry of the combustion chamber (4), and connecting down-stream to a gas expanding nozzle (50) designed to receive products of combustion of said mixture and form a high-velocity gaseous jet, an ignition device (30) to start combustion of said mixture, a material delivery device (6) designed to inject a spray material axially into said high-velocity gaseous jet; characterized by comprising several second oxidizer gas injectors (32,33) for injecting separately a second oxidizer gas upstream in the combustion chamber to promote the combustion process and wherein the labyrinth mixing device (2) comprises one or more flanges (23,24) which define one or more mixing volumes (21,22), between the main body (1) and the own labyrinth mixing device (2), and holes (25,26,27), concentrically placed both on the flanges (23,24) and passing through the mixing device (2) and opening at the downstream end of the mixing device (2) for connecting a fuel-first oxidizer feeding section (20) of the labyrinth mixing device (2) with the combustion chamber (4), and wherein the labyrinth mixing device (2) further comprises a crossing axial bore (28) to inject the spray material into the combustion chamber (4).

2. A high-velocity thermal spray apparatus as in claim 1 wherein said secondary oxidizer gas injectors comprises one or more sequential and closely spaced arrays of narrow continuous slots and/or series of orifices (32,33) to allow the independent injection of the second oxidizer in one or more sequential and closely spaced injection points of the combustion chamber (4).

3. A high-velocity thermal spray apparatus according to claim 1, wherein the combustion chamber is designed to generate different combustion conditions inside the geometry of such combustion chamber, as result of a distribution of locally different mixtures of the first oxidizer and fuel, and the separated up-stream addition of a second oxidizer,

4. A high-velocity thermal spray apparatus according to claim 1, wherein the first oxidizer used is compressed air.

5. A high-velocity thermal spray apparatus according to claim 1, wherein the second oxidizer is oxygen gas.

6. A high-velocity thermal spray apparatus according to claim 1, where a low temperature diluted combustion mixture is created near the labyrinth mixing device (40) in the combustion chamber.

7. A high-velocity thermal spray apparatus according to claim 1, wherein an oxygen rich, high temperature flame area (42) is created near the second oxidizer injector in the combustion chamber.

8. A high-velocity thermal spray apparatus as in claim 1, wherein the labyrinth mixing device (2) is housed partially inside the torch's main body (1) such that the mixing device (2) is closed up at its upstream end by a material delivery device (6) while its downstream end is located inside the combustion chamber (4), and wherein the torch's main body (1) comprises one or more connectors (7) feeding fuel and first oxidizer gas stream to the feeding section (20) of the labyrinth mixing device (2).

9. A high-velocity thermal spray apparatus as in claim 1, wherein the geometry of the combustion chamber is defined between the labyrinth mixing device (2) and the convergent shape of the front part (3) of the torch, wherein such front part opens to a gas expanding nozzle (50).

10. A high-velocity thermal spray apparatus as in claim 1, wherein said material delivery device (6) comprises at least two inlets (60, 61) and one outlet ending inside the axial bore of the labyrinth mixing device (2), a first inlet (61) for a first carrier gas stream at a first pressure, used to carry the selected spray material, and a second inlet (60) for an injection gas stream with a second pressure higher that the first pressure and close to the pressure inside the combustion chamber (4), thus suctioning the first carrier gas stream with the coating material into said labyrinth mixing device (2) and subsequently into the combustion chamber (4) and expanding nozzle (50).

11. A high-velocity thermal spray apparatus as in claim 103 wherein the nature of the gases of the injection gas stream flowing through inlet 60 are selected for additional functionality as oxidizing, fuelling, dilution, chemical reaction enhancement, or others.

12. A high-velocity thermal spray apparatus as in previous claims wherein the gas expanding nozzle (50) is provided with an axial nozzle bore, comprising the first inlet cylindrical bore (52) followed by a second outlet diverging bore (51) that opens downstream.

13. A high-velocity thermal spray apparatus as in claim 12 wherein the radial dimension of an inlet bore (52) of the nozzle (50) is slightly larger than the outlet bore (51) of the convergent outlet section (31) of the combustion chamber (4) to prevent spray powder stream from getting in contact with the walls of the inlet bore (52).

14. A high-velocity thermal spray apparatus as in claim 12, wherein the length of the gas expanding nozzle (50) is chosen between 20 and 250 mm.

15. A high-velocity thermal spray apparatus as in claim 12, wherein the gas expanding nozzle (50) has a gas collimator device (53) at the output to control the supersonic gas expansion in the ambient.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0034] To complete the description and in order to provide for a better understanding of the invention, a set of drawings is provided. Said drawings form an integral part of the description and illustrate embodiments of the invention, which should not be interpreted as restricting the scope of the invention, but just as examples of how the invention can be carried out. The drawings comprise the following figures:

[0035] FIG. 1a shows a longitudinal sectional view of the preferred embodiment of the invention, which is a high velocity oxy/air fuel (HVOAF) torch used to spray with supersonic velocity a stream of spray particles to build up a coating of such heated particle on a surface down-stream of the discharge end of the apparatus illustrated.

[0036] FIG. 2a shows an enlarged partial view of the labyrinth mixing device and combustion chamber of FIG. 1.

[0037] FIG. 2b shows an enlarged partial view of the labyrinth mixing device and combustion chamber like FIG. 2a, showing the high-velocity gaseous gas and different temperature regions generated inside the combustion chamber.

[0038] FIG. 3 shows the second oxidizer injectors as a rear-view A-A′ of the combustion chamber case illustrating the inlet channels and orifices through which the second oxidant gas is injected into the combustion chamber.

[0039] FIG. 4 shows a frontal view of the labyrinth mixing device illustrating the circular series of closely spaced orifices through which the fuel and first oxidant mixture is fed into the combustion chamber.

[0040] FIG. 5 shows an enlarged sectional view of a nozzle illustrating their main parts as the first inlet cylindrical bore, the second divergent bore and the collimator output.

[0041] FIG. 6 shows an enlarged, sectional view of the embodiment with an additional material delivery device (for example a powder injector) illustrating the nature of the venturi type design that allows injecting the powder axially into the gas expanding jet.

[0042] FIG. 7 shows the microstructure of a cermet type coating (WCCoCr sintered powder) obtained with the apparatus of the invention as example of very hard coatings that can be produced. Shows WC-CoCr cermet-microhardness indentations 1728HV0,3.

[0043] FIG. 8a shows the microstructure of a first aluminium type coating (AlSi16Sc0.4Zr0.2 powder) obtained with the apparatus of the invention as example of processing of aluminium alloys without experiencing the sticking of particles into barrel. Shows AlSi16Sc0.4Zr0.2 coating as sprayed metallographic cross section.

[0044] FIG. 8b shows the etched microstructure of a first aluminium type coating (AlSi16Sc0.4Zr0.2 powder) obtained with the apparatus of the invention. Shows AlSi16Sc0.4Zr0.2 coating metallographic cross section etched.

[0045] FIG. 9 shows the microstructure of a second aluminium (99,9% powder) type coating obtained with the apparatus of the invention as example of processing aluminium alloys. Shows aluminum coating as sprayed metallographic cross section.

[0046] FIG. 10 shows the microstructure of a bronze type coating obtained with the apparatus of the invention as example of processing cupper base alloys. Shows bronze coating as sprayed metallographic cross section.

[0047] FIG. 11 shows the microstructure of a hot work tool steel type of coating (Heatvar Uddelhom) obtained with the apparatus of the invention as example of processing steel and metallic alloys. Shows tool steel (Heatvar) as sprayed metallographic cross section

DESCRIPTION OF WAYS OF CARRYING OUT THE INVENTION

[0048] Referring to the drawings, a better understanding of the present invention may be obtained by reference to FIG. 1a, which is a longitudinal sectional view of a high-velocity oxy/air-fuel (HVOAF) torch constructed in accordance to the preferred embodiment of the present invention. However, the disclosed embodiment is merely exemplary, and it should be understood that the invention may be embodied in many various and alternative forms.

[0049] As can be seen in FIG. 1a, the HVOAF torch comprises a main body 1, which houses a labyrinth mixing device 2, comprising two flanges 23 and 24 in the middle section. The labyrinth mixing device 2 comprises an axial crossing bore 28 that is closed up at its upstream end by a material delivery device such as an axial powder injector 6, which receives the end of a gas injection supply tube 60 and the end of a coating material carrier gas supply tube 61. The gas injection supply tube 60 being at a higher pressure than the material carrier gas supply 61.

[0050] The main body 1 is fixed to a torch's front part 3, thus forming a combustion chamber 4. The combustion chamber 4 is closed off at its downstream end by a gas expanding nozzle 50, which is provided with an axial nozzle bore, comprising an inlet bore 52 followed by an outlet diverging bore 51 that opens downstream. The radial dimension of an inlet bore 52 should be slightly larger than the outlet bore of the convergent outlet section 31 of the combustion chamber 4 to prevent spray powder stream from getting in contact with the walls of the inlet bore 52.

[0051] The labyrinth mixing device 2 is provided with holes 25, 26 and 27, which connect the fuel-air feeding section 20 with the combustion chamber 4. Such holes are concentrically placed both on the flanges 23 and 24 and at the downstream end of the mixing device 2, thus creating two interconnected intermediate mixing volumes 21 and 22.

[0052] The fuel and air stream could be pre-mixed outside the torch and injected into the main body through the connectors 7. After entering the fuel-air feeding section 20 of the mixing device 2, the fuel-air pre-mixture is pressed through the orifices of the first flange 23, thus expanding into the first intermediate mixing volume 21 in the following step. The same compression and expansion processes are repeated through the second flange 24 of the mixing device 2 and second intermediate mixing volume 22, after which the fuel-air mixture is injected into the combustion chamber 4.

[0053] Inside the combustion chamber 4, the oxygen gas stream is fed at two sequential locations, firstly through an array of narrow continuous slots 33 and lately though a circular series of orifices 32, both closely spaced along circumferential rings at the up-stream end of the front part 3, as schematically shown in FIG. 3. The combustion mixture is then ignited with the help of a sparkplug 30, which is placed in a radial orifice at the downstream of the front part 3. Such a radial orifice ends in the combustion chamber 4. This sequential array of fuel-air and oxygen injection points lead to the creation of several combustion regions featuring substantially different temperatures from different dilution degrees and oxidant to fuel ratios, as schematically shown in FIG. 2b. In the proximity of the cylindrical section wall at most up-stream end, the fuel-air mixture generates a zone in the combustion chamber with usually high level of dilution, thus building a low-temperature region 40, which evolves forming a sort of boundary that surrounds the mixing device 2 wall until it embeds the particle jet stream 44. At the junction zone between the labyrinth mixing device 2 and the front part 3, the first array of oxygen injectors 33 provides for a sudden increase of oxygen saturation and thus to an equivalent increase in the temperature of the gaseous combustion mixture in this combustion region 41. Few millimetres downstream, in the walls of the combustion chamber, the second array of oxygen injectors 32 provides for an additional supply of oxygen, thus newly increasing the oxidant to fuel ratio and, in consequence, the gas temperature in this combustion region labelled as 42 in FIG. 2b. Upon reaching the proximity of the low temperature region 40, both flow streams mix together, embed the particle stream 44 and build a fourth combustion region 43 with an intermediate temperature around it. In this way, the feedstock material is injected into the coldest region of the combustion chamber and is gradually heated up along its way throughout the gun nozzle 50.

[0054] In the preferred embodiment of the present invention, the powder injector 6 allows the implementation of low-pressure carrier-gas streams to carrier the feedstock powder material into the torch (inlet tube 61), since a high-pressure gas-injection stream (inlet tube 60) provides a suction of the low-pressure gas stream into the injector 6 and lately into the mixing device 2, crossing it through the axial bore (28) to the combustion chamber 4.

REFERENCES

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