WO2007054957A1 - An improved lance for ld steelmaking - Google Patents
An improved lance for ld steelmaking Download PDFInfo
- Publication number
- WO2007054957A1 WO2007054957A1 PCT/IN2006/000153 IN2006000153W WO2007054957A1 WO 2007054957 A1 WO2007054957 A1 WO 2007054957A1 IN 2006000153 W IN2006000153 W IN 2006000153W WO 2007054957 A1 WO2007054957 A1 WO 2007054957A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- nozzle
- central
- lance
- jet
- nozzles
- Prior art date
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
- C21C5/00—Manufacture of carbon-steel, e.g. plain mild steel, medium carbon steel or cast steel or stainless steel
- C21C5/28—Manufacture of steel in the converter
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F27—FURNACES; KILNS; OVENS; RETORTS
- F27B—FURNACES, KILNS, OVENS, OR RETORTS IN GENERAL; OPEN SINTERING OR LIKE APPARATUS
- F27B3/00—Hearth-type furnaces, e.g. of reverberatory type; Tank furnaces
- F27B3/10—Details, accessories, or equipment peculiar to hearth-type furnaces
- F27B3/22—Arrangements of air or gas supply devices
- F27B3/225—Oxygen blowing
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
- C21C5/00—Manufacture of carbon-steel, e.g. plain mild steel, medium carbon steel or cast steel or stainless steel
- C21C5/28—Manufacture of steel in the converter
- C21C5/42—Constructional features of converters
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
- C21C5/00—Manufacture of carbon-steel, e.g. plain mild steel, medium carbon steel or cast steel or stainless steel
- C21C5/28—Manufacture of steel in the converter
- C21C5/42—Constructional features of converters
- C21C5/46—Details or accessories
- C21C5/4606—Lances or injectors
Definitions
- the present invention generally relates to an improved lance for LD steelmaking.
- the invention relates to a multi-hole lance design with a central separately-controllable subsonic nozzle for varying the generation of liquid metal droplets according to the process requirement.
- LD steelmaking process is a purification process of liquid pig iron that contains, along with very high percentage of iron, carbon, phosphorus, magnesium, manganese, aluminium, etc as principal impurities. These impurities are removed by oxidation reactions using gaseous oxygen as the oxidizer.
- the oxygen gas is introduced into the LD vessel by means of multiple supersonic jets through a water-cooled lance with a copper head.
- argon gas is introduced through tuyres at the bottom of the vessel to stir the liquid metal thoroughly.
- This process of blowing oxygen gas from the top through the lance and injecting argon through the bottom is called combined blowing process.
- the refining process within the LD vessel can be summarized in the following way. Liquid pig iron is charged into the vessel along with metal scraps. These metal scraps can easily be melted because most of the reactions taking place in the LD vessel are exothermic reactions and the whole LD steelmaking process is an auto-generation process, i.e. it requires no external supply of heat.
- the impurities are oxidized and the oxides, other than the oxides of carbon, form the liquid slag that floats on top of the liquid metal.
- Carbon is oxidised as carbon mono-oxide (CO) gas that passes through the liquid slag. Due to this> the slag layer swells in volume and forms what in general, called as "slag foam".
- the slag foam comprises of liquid slag, gases evolving from the liquid metal and the liquid metal droplets thrown into the vessel due to the impact of the oxygen jets on the liquid metal surface.
- the foam thus formed, occupies a large volume of the vessel completely covering the lance head and partly the lance itself.
- the foam creates a large interfacial area between the liquid metal and the slag and thereby promotes interfacial reactions such as dephosphorization.
- the oxygen lance is operated at different lance heights to control the intensity of impingements of the supersonic jets.
- the lance height is defined as the distance of the lance tip at any instance to the flat liquid metal surface before the start of the blow.
- the prime interest of the steelmaker is to form the liquid slag quickly and dissolve the charged lime completely. It is felt that hard blow or lesser lance height will be disadvantagesous because the oxidation of the carbon is not preferred in this stage. So, the lance is operated at a higher height, say for example, the initial lance height is 2.2 m.
- the slag starts forming with the required chemical and physical properties.
- the lance height is reduced to give a hard blow. The reduced height can be around 1.5 m.
- the creation of metal droplets is also of great importance as far as the dephosphorization reaction is concerned.
- the lance is operated in this shorter height for most of the blow to promote the oxidation of carbon.
- the carbon percentage in the steel is very low and the generation of CO gas is reduced to a great extent.
- the slag is no longer foamy because of the absence of the generation of CO gas and it is understood that a thick liquid slag layer is formed on top of the metal surface.
- the hard blow and the creation of liquid metal droplets in this stage are not preferred due to similar reasons mentioned in the earlier" stages of the blow. So, the lance height is increased again to the initial lance height to give a softer blow.
- the lance is made up of copper and has a detachable head where the nozzles are fixed.
- the oxygen is blown into the vessel with supersonic velocities in the range of Mach number 2.0-2.4 through the nozzles.
- the number of supersonic nozzles in the lance is decided based on the size of the vessel, mass of the charge and the other operating conditions.
- a typical lance can have 6 supersonic nozzles with an angle or " inclination from the vertical axis of 17.5° to minimize jet coalescence.
- the nozzles are designed to produce the supersonic jets with the exit Mach number of 2.2. All the nozzles have a single supply of oxygen at the pressure of 13.5 bar.
- the employed lance is water-cooled to protect it from the hot temperature within the LD vessels.
- One object of the present invention is to improve the liquid metal droplet generation to increae the slag-metal interfacial area for improving the dephosphorization within the LD vessel. Since dephosphorization is essentially an interfacial reaction between the slag and metal, increasing the metal droplets would enhance the dephopshorization efficiency. In the present invention therefore, an effort has been made to improve the droplet generation in LD vessel.
- the metal droplets formation is essentially the function of the lance.
- the function of the oxygen jets have to be considered carefully under steelmaking conditions or very close to such conditions. It has been found that the provision of a central hole in the oxygen lance creates a lot of metal droplets and causes spitting. Spitting is disadvantageous because it might cause the blockage of the vessel mouth and further reduce the life of the lance and the vessel lining. So, though the central hole can produce a lot of droplets, it has disadvantages also.
- the central hole has a further advantage that was hitherto unknown in steel industry.
- the effect of high density slag foam on the supersonic jet characteristics in the LD vessel w$s considered. It has been found that the slag foam absorbs all the momentum supplied by the oxygen jets and the jets lose the momentum completely to the slag. Thus the existing knowledge on the supersonic oxygen jet characteristics within the LD vessel can be considered to be wrong.
- the droplet generation studies done using hydrodynamic models of LD vessels will not reveal the true mechanisms of droplet production within the LD vessel, they provide the basis for improved understanding of the droplet formation.
- peripheral jets Since the peripheral jets are exposed to the slag foam, they are expected to lose all the momentum to the slag layer through the jet-slag foam interface. Because the gas jets do not have sufficient momentum when they reach the molten metal surface, they cannot produce metal droplets as needed.
- the central jet will be covered by very little or no slag foam as compared to the peripheral jets.
- the peripheral jets will cover the central jet and make a protective cover to the central jet from the high density slag foam.
- the central jet will not lose its momentum to the slag layer and will reach the metal surface with concentrated momentum, i.e. with very high velocity that will tear the metal surface to produce the much needed metal droplets for improving the dephosphorization.
- shocks or strong discontinuities in pressure, velocity, temperature and density of the gas can occur within the diverging section of the nozzle itself.
- shocks formed at the diverging section can severely effect the performance of the supersonic nozzle and will reduce the life of the nozzle considerably.
- a shock formed inside with diverging section of the nozzle can suck the high temperature slag foam and metal droplets into the nozzle and severe erosion and failure of the lance can occur. It is clear that it is not possible to have a great degree of control of flow rates, as needed in the different phases of the LD steelmaking process, through the supersonic nozzle.
- the present invention provides an improved lance for LD steelmaking, comprising a plurality of peripheral supersonic nozzles provided with a single inlet high pressure gas supply line; and a central nozzle; wherein said central nozzle is a subsonic nozzle provided with a separate low pressure gas supply line; flow rate through said central s ⁇ bsonic nozzle being controllable for varying generation of liquid metal droplets during blow according to the process requirement.
- Figure 1 shows the schematic arrangement of a 6-hole lance design.
- Figure 2 shows a typical geometric arrangement of a supersonic nozzle.
- Figure 3 shows a schematic sketch of an LD vessel.
- Figure 4 shows a schematic sketch of the 7 hole lance with separate air supply line used in the hydrodyhamic model experiments
- Figures 5(a) are photographs showing extent of droplet generation in the and (b) case of an existing 6 nozzle lance and a 7 hole lance of the present invention
- Figure 6 shows a schematic representation of the droplet generation mechanism
- Figure 7 shows the droplet generation rates with 7-hole lance with different flow ratios
- Figure 8 shows the computational model and the mesh used for numerical simulation.
- Figure 9 gives a closer look of the nozzles
- Figure 10 shows the velocity contours for 7-hole lance with angle of inclination of 17.5° with the presence of vessel walls and metal surface
- Figure 11 shows the temperature contours with Shock at the nozzles with 17.5° angle.
- Figure 12 shows velocity contours showing the impact position on the metal surface
- Figure 14 shows schematic diagram of the domain with boundary conditions used for the high density ambient simualtion
- Figure 15 shows mixture density contours near the nozzle exit at an instant of time.
- Figure 16 shows momentum flux rates profiles at different axial locations(a) Nozzle exit;(b) 0.5 m;(c) 1.5 m and (d) 2.5 m
- Figure 17 shows schematic representation of a 7-hole lance design Since it has been found that the central hole will augment the droplet generation, the droplet generation mechanisms were studied through hydrodynamic model experiments on a 1:6 scale down model with the central hole as shown in the schematic sketch of figure 3. A 1:6 reduced scale model of the LD vessel made with plexiglas is used. The reduced scale models of the existing and the proposed lance designs were made in order to study the advantageous of the central hole in augmenting droplet generation.
- the top part of the vessel is made of stainless steel where the cylindrical and the vessel bottom portions are made of plexiglas to have required transparency for visualization of the experiments.
- the lance is made up of copper with the facility of putting different design of lance tips for investigation.
- the scaled down lance was designed having six peripheral nozzles with a central nozzle as shown in Figure 4. There are two separate air lines, line 1 is connected to all the six outer peripheral nozzles whereas line 2 is connected to the central nozzle.
- the flow rate through the central hole was controlled separately by means of a set of pressure regulator and air flow rotameter connected in series whereas the flow rate through the six peripheral nozzles was controlled through another set of pressure regulator and air flow rotameter.
- the inclination of the peripheral nozzles to the central axis were investigated at 17.5° (as existing in practice) and 22° as well, by using two different lance tips 3.
- the droplet generation mechanisms were investigated when all the 1- holes were in operation and comparisons were made with only the six peripheral nozzles in operation.
- a flow rate ratio, X is defined as the ratio flow rates through the central hole to that of one of the peripheral nozzles.
- the rate of droplet generation plotted against the flow rate ratio is shown in Figure 7.
- the flow rate through the central nozzle was varied from a flow rate ratio of as low as 25 % to as high as 125 %.
- the optimum flow rate through the central nozzle is obtained by maintaining the balance between an improved droplet generation and control of splashing and spitting due to bath spilling out of the mouth of the vessel. It was quite apparent that as the flow rate through the center hole was increased progressively, the rate of droplet generation was enhanced.
- Figure 7 shows that for a flow rate ratio, X of 1 (100%) given through the central nozzle, the droplet generation almost doubles and reaches a maximum value.
- the subsonic nozzle Since the optimum flow ratio obtained from hydrodynamic model experiments was unity, the subsonic nozzle has been designed with a larger exit diameter (54 mm) as compared to that of the peripheral supersonic nozzle (37.3 mm). This is needed to push the same mass flow rate through the central subsonic nozzle and one of the supersonic nozzle.
- the lance pipe diameter had to be increased by 100 mm compared to the existing lance dimensions.
- the volume flow rate through the central subsonic nozzle was kept almost the same as that of one of the peripheral supersonic jets. This means that mass flow rate through one of the supersonic nozzles in the periphery when compared to the central subsonic nozzle is different. This is due to the fact that because of the supersonic flow in the outer nozzles, the nozzle exit temperature falls down to 150 K. Due to this, the density of the gas at the exit of the supersonic nozzles becomes much higher, given that the pressure is almost uniform everywhere in the vessel. For the subsonic central jet, such low temperatures at the nozzle exit do not reach.
- the velocity contours are plotted at the symmetry plane to show the impact positions of the jets on the metal surface.
- the geometrical projections of th ⁇ jets are also shown on the liquid metal surface by dark circles. It can be seen that the jets almost follow the geometrical path and the coalescence is minimal due to the presence of the central jet and the bottom stagnation region.
- the velocity contours are shown only for the velocity magnitudes less than 150 m/s. It can be observed that the supersonic jets and the central subsonic jet reach the liquid metal bath with almost the same velocity magnitudes although the exit velocities at the respective nozzles were different. Since the subsonic nozzle exit diameter is hither (54 mm) than the supersonic nozzle exit diameter (37.3 mm), the velocities closer to the metal bath are matched.
- the gas in the central jet has to pass through the surrounding supersonic jets since it cannot pass through the metal surface (in the simulation). This kind of flow feature may not happen in the actual vessel because in the simulation, the metal surface is assumed to be a stress free flat wall. In LD vessel, the impact of the central jet will create a depression, which will change the flow characteristics completely.
- the likely range of ambient density (foam/emulsion) values are possible in the LD vessel has been calculated by assuming uniform decarburization rate throughout the blow. It turn is out that the average slag volume fraction in the foam inside the vessel will be in the range of 12-15%. This would result in an average ambient density range of 360-450 Kg/m 3 .
- the numerical domain and the boundary conditions used are shown in Figure 14.
- the vessel diameter required for a single axisymmetric nozzle has been calculated by using 1/6 of the original vessel cross-sectional area (because out of 6 nozzles, only one is being simulated).
- the liquid metal surface has been assumed to be a shear free flat wall.
- the lance height (distance between nozzle tip to the liquid metal surface) is taken to be 3.5 m, in order to study the behaviour of the jet over a long axial distance.
- the actual lance height in the vessel varies from 1.5-2.2 m.
- Th ⁇ simulations have been carried out using a 2D axisymmetric unsready RANS with volume of fluid (VOF) multiphase model to track the interface between the phases. No differentiation has been made between oxygen and carbon mono-oxide gas. Hence only one gas phase has been considered.
- the Realizable k- ⁇ turbulence model is used to close the system of equations.
- PISO algorithm has been used for pressure - velocity coupling.
- Second order upwind discretization scheme has been used for all the flow variables except temperature for which power law scheme is used.
- the average slag volume fraction (15%), computed from the steady decarburisation rate, is patched in the vessel domain as an initial guess.
- the slag is free to move throughout the domain depending on the local flow conditions unlike the earlier simulation,
- the surface tension forces have also not been included in this simulation when entering into a still ambient, the gas jet with high velocity invokes flow in the ambient also.
- Due to the momentum transferred to the ambient the ambient fluid adjacent to the jet boundary starts moving in the predominant flow direction of the jet fluid. So, the ambient fluid in the neighboring locations moves towards the jet because of this flow induced by the jet. Slag along with the ambient gas rushes towards the jet boundary owing to the flow induced by the jet.
- slag accumulates and the volume fraction/local density increases.
- the momentum transferred from the jet imposes movement to the slag and slowly, the slag covers the high-speed jet core.
- the slag foam density contours near the nozzle tip are plotted in Figure 15 in order to show the slag accumulation at the nozzle tip and its movement along the jet.
- momemtum flux rate (pV ) at different axial locations is shown in Figure 16 at a particular instant of time. It is worth noting that the maximum momentum flux rate does not occur at the axis of the jet but away from it in the radial direction as shown in Figure 16.
- the high speed core of the jet continuously pumps momentum to the jet shear layer, both convectively and diffusively. The velocity at the axis is still the maximum at any axial location.
- the diffusive transport of axial momentum in the radial direction ( ) will be towards the shear layer from the jet axis. Since the jet is spreading, the radial velocity, v will be towards the shear layer within the jet so the net convectjve transport of momentum in the radial direction (puv) is also towards the shear layer. Since the density of the shear layer fluid (slag + gas) is very high compared to the jet gas, the shear layer can store higher momentum fluxes without increasing the velocity enormously just like storage of thermal energy in a reservoir with higher specific heat/thermal capacitance without appreciable temperature differences. Moreover, the gravity is aiding the slag layer to gain momentum, i.e. the slag layer moves in the direction of the gravitational acceleration.
- the momentum transferred from the high speed jet core to the high density shear layer will be in addition to the momentum imparted by the gravitational acceleration. From the momentum flux rates Plots shown in Figure 16, the momentum flux rate at the high density shear layer is minimum 2 orders of magnitude higher than the high speed jet core. It is clear from the above discussions that the high density slag-gas foam present in the LD vessel poses some interesting flow features of the supersonic gas jets. The understanding of the depressions created during the blow might be changed completely.
- the multiple supersonic jets inside the LD steel vessel will also be subjected to such characteristics as shown above due to the presence of high density slag foam. It is clear from the above discussions that the peripheral supersonic jets will lose all their momentum to the slag layer adjacent to them. The slag layers will move towards the liquid metal pool with very high momentum and create complicated depression profiles. But due to the presence of the central jet in the new 7-hole design, the pressure inside the space amongst the supersonic jets will prevent the entrainment into this region. So, the central jet will not see or see minimally the slag foam and unlike the supersonic jets, it will not lose its momentum completely to the slag foam.
- FIG. 17 One embodiment of the present invention with a 7-hole design is schematically shown in Figure 17. It shows 6 peripheral supersonic jets with a central jet.
- the central jet is to be controlled separately with a separate gas supply line whereas the peripheral supersonic jets will have a single inlet gas supply line.
- the gas supply line for the 6 peripheral supersonic jets and the gas supply line for the central subsonic jets are provided with two separate control valves with actuators.
- the central jet can be put into operation during different stages of the blow and the flow rate can also be varied according to process requirement since it is a subsonic nozzle.
- the flow rate through the central subsonic nozzle is kept as a variable.
- the ratio of the volume flow rate through the central subsonic nozzle and that of one of the supersonic nozzles is kept as a variable.
- the maximum value of this ratio is kept as 1 in numerical simulation.
- the dimensions of the central nozzle are calculated by keeping this in mind.
- the outlet diameter of the subsonic nozzle is 54 mm and that of the supersonic nozzle is 37.3 mm (existing value).
- the angle of inclination of the peripheral jets is kept at 17.5% (the existing value).
- the angle of inclination of the peripheral supersonic nozzles can be equal or alternately varying.
- the alternately varying angle of inclination can have a distinct advantage.
- the covering of slag foam on the jet surface results in lower velocity of the gas jet and the slag layer covering the jet reaches the liquid metal surface with high momentum. This impact of slag layer onto the liquid metal will create a lot of slag droplets into the liquid metal and create interfacial area for slag-metal reactions.
- the surface area of the jet that is covered with slag layer can be increased and more slag can reach the liquid metal with high momentum, This is expected to improve the interfacial reactions such as dephosphorization.
- the angle of inclination of the peripheral jets is kept at 17.5°. This angle can be increased in the further modifications.
- the advantageous features of the present invention provides better on/off control of the central nozzle during the blow because of the separate gas supply line. This will give a strong control of the spitting of metal droplets off the vessel.
- the bigger subsonic nozzle at the centre of the lance head is useful to control the flow rate of oxygen through the central nozzle. This would mean more flexibility and control over the process.
- the system provides increased metal droplet generation, Since the central jet is protected from the slag foam by the peripheral jets, this would reach the metal bath with high velocities and promote increased droplet generation.
- the system provides improved effectiveness in dephosphorization. Improveed metal droplet generation will promote the interfacial reactions particularly dephosphorization.
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0618348A BRPI0618348B1 (en) | 2005-11-10 | 2006-05-04 | perfected spear for steelmaking ld |
EP06745217A EP1963541B1 (en) | 2005-11-10 | 2006-05-04 | An improved lance for ld steelmaking |
PL06745217T PL1963541T3 (en) | 2005-11-10 | 2006-05-04 | An improved lance for ld steelmaking |
KR1020087012642A KR101290639B1 (en) | 2005-11-10 | 2006-05-04 | An improved lance for ld steelmaking |
JP2008539618A JP5047185B2 (en) | 2005-11-10 | 2006-05-04 | Improved lance for LD steelmaking |
AT06745217T ATE546553T1 (en) | 2005-11-10 | 2006-05-04 | IMPROVED LANCE FOR LD STEEL PRODUCTION |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IN1023KO2005 | 2005-11-10 | ||
IN1023/KOL/05 | 2005-11-10 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2007054957A1 true WO2007054957A1 (en) | 2007-05-18 |
Family
ID=38023007
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/IN2006/000153 WO2007054957A1 (en) | 2005-11-10 | 2006-05-04 | An improved lance for ld steelmaking |
Country Status (8)
Country | Link |
---|---|
EP (1) | EP1963541B1 (en) |
JP (1) | JP5047185B2 (en) |
KR (1) | KR101290639B1 (en) |
AT (1) | ATE546553T1 (en) |
BR (1) | BRPI0618348B1 (en) |
PL (1) | PL1963541T3 (en) |
RU (1) | RU2414512C2 (en) |
WO (1) | WO2007054957A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8323558B2 (en) | 2009-11-30 | 2012-12-04 | L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Dynamic control of lance utilizing counterflow fluidic techniques |
US8377372B2 (en) | 2009-11-30 | 2013-02-19 | L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Dynamic lances utilizing fluidic techniques |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10781499B2 (en) * | 2018-01-17 | 2020-09-22 | Air Products And Chemicals, Inc. | Bottom stirring tuyere and method for a basic oxygen furnace |
Citations (5)
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US4432534A (en) * | 1982-02-10 | 1984-02-21 | Institut De Recherches De La Siderurgie Francaise | Oxygen lance for steel converter |
JPS6260807A (en) * | 1985-09-10 | 1987-03-17 | Nippon Kokan Kk <Nkk> | Converter operating method and oxygen blowing lance |
JPH07138632A (en) * | 1993-11-18 | 1995-05-30 | Nippon Steel Corp | Nozzle structure of lance for blowing oxygen into electric furnace |
US5681526A (en) * | 1996-04-23 | 1997-10-28 | Usx Corporation | Method and apparatus for post-combustion of gases during the refining of molten metal |
US6284189B1 (en) * | 1998-11-10 | 2001-09-04 | Danieli & C. Officine Meccaniche S.P.A. | Nozzle for device to inject oxygen and technological gases and relative dimensioning method |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5848758U (en) * | 1981-09-30 | 1983-04-01 | 新日本製鐵株式会社 | Top blowing lance nozzle shape in converter |
JPH06240329A (en) * | 1993-02-17 | 1994-08-30 | Nippon Steel Corp | Top blowing oxygen lance for refining molten metal and method for refining molten metal |
JP3655659B2 (en) * | 1995-03-03 | 2005-06-02 | 新日本製鐵株式会社 | Blow acid sending method on converter with good yield |
JPH10287909A (en) * | 1997-04-15 | 1998-10-27 | Sumitomo Metal Ind Ltd | Top-blown lance for blowing gas into converter and also melting skull stuck to nose |
-
2006
- 2006-05-04 RU RU2008123506/02A patent/RU2414512C2/en not_active IP Right Cessation
- 2006-05-04 KR KR1020087012642A patent/KR101290639B1/en active IP Right Grant
- 2006-05-04 AT AT06745217T patent/ATE546553T1/en active
- 2006-05-04 BR BRPI0618348A patent/BRPI0618348B1/en not_active IP Right Cessation
- 2006-05-04 WO PCT/IN2006/000153 patent/WO2007054957A1/en active Application Filing
- 2006-05-04 EP EP06745217A patent/EP1963541B1/en not_active Not-in-force
- 2006-05-04 PL PL06745217T patent/PL1963541T3/en unknown
- 2006-05-04 JP JP2008539618A patent/JP5047185B2/en not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4432534A (en) * | 1982-02-10 | 1984-02-21 | Institut De Recherches De La Siderurgie Francaise | Oxygen lance for steel converter |
JPS6260807A (en) * | 1985-09-10 | 1987-03-17 | Nippon Kokan Kk <Nkk> | Converter operating method and oxygen blowing lance |
JPH07138632A (en) * | 1993-11-18 | 1995-05-30 | Nippon Steel Corp | Nozzle structure of lance for blowing oxygen into electric furnace |
US5681526A (en) * | 1996-04-23 | 1997-10-28 | Usx Corporation | Method and apparatus for post-combustion of gases during the refining of molten metal |
US6284189B1 (en) * | 1998-11-10 | 2001-09-04 | Danieli & C. Officine Meccaniche S.P.A. | Nozzle for device to inject oxygen and technological gases and relative dimensioning method |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8323558B2 (en) | 2009-11-30 | 2012-12-04 | L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Dynamic control of lance utilizing counterflow fluidic techniques |
US8377372B2 (en) | 2009-11-30 | 2013-02-19 | L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Dynamic lances utilizing fluidic techniques |
Also Published As
Publication number | Publication date |
---|---|
RU2414512C2 (en) | 2011-03-20 |
BRPI0618348A2 (en) | 2013-01-08 |
JP2009516070A (en) | 2009-04-16 |
KR101290639B1 (en) | 2013-07-30 |
ATE546553T1 (en) | 2012-03-15 |
EP1963541B1 (en) | 2012-02-22 |
RU2008123506A (en) | 2009-12-27 |
PL1963541T3 (en) | 2012-07-31 |
BRPI0618348B1 (en) | 2018-11-21 |
JP5047185B2 (en) | 2012-10-10 |
KR20080077359A (en) | 2008-08-22 |
EP1963541A1 (en) | 2008-09-03 |
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