WO2000028096A1 - Nozzle for device to inject oxygen and technological gases and inverse dimensioning method - Google Patents
Nozzle for device to inject oxygen and technological gases and inverse dimensioning method Download PDFInfo
- Publication number
- WO2000028096A1 WO2000028096A1 PCT/IB1999/001793 IB9901793W WO0028096A1 WO 2000028096 A1 WO2000028096 A1 WO 2000028096A1 IB 9901793 W IB9901793 W IB 9901793W WO 0028096 A1 WO0028096 A1 WO 0028096A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- nozzle
- outlet
- development
- throat
- flow
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07021—Details of lances
Definitions
- This invention concerns a nozzle for a device to inject oxygen and technological gases, and also the relative dimensioning method, as set forth in the respective main claims.
- the device is used to inject at supersonic velocity a gassy flow of oxygen or other technological gases used in metallurgical processes of metal melting.
- the nozzle according to the invention can be used advantageously, though not exclusively, in an integrated injection device suitable to emit, with the supersonic gassy flow, another flow, at subsonic velocity, either gassy, liquid or consisting of solid fuels in powder form or in little particles.
- the optimum solution would suggest mounting the injection device on the walls of the furnace, putting the end, or emission nozzle, far from the bath of metal, in such a way as to preserve it from such damaging elements as the extremely high temperature, the splashes of molten metal, corrosion and impacts with the scra .
- the present Applicant in the light of the shortcomings of the state of the art, and taking into account the technological requirements of preparing injection devices with high performance and high functionality, has developed an algorithm of dimensioning and calculation which allows to design nozzles suitable to satisfy all the operational and technological requirements .
- the principle of the invention is based on the concept of optimising the conversion of potential energy into kinetic energy, so that the potential energy varies with respect to the axial coordinate of the nozzle following a law of the type with a hyperbolic tangent.
- This invention is therefore achieved in a method of dimensioning and calculation which exploits the algorithm mentioned above and allows to obtain many advantages, overcoming the shortcomings of the state of the art.
- the purpose of the invention is to define an inverse method of three-dimensional axi-symmetric dimensioning for nozzles with a convergent/divergent development applied on supersonic injection devices, hereinafter called simply lances, which allows to obtain a plurality of advantages with respect to traditional methods adopted until now.
- a first advantage is that it is possible to achieve a nozzle with a geometry which develops in such a way as to adapt to the natural profile of the fall in pressure of the flow delivered.
- a second advantage is that the method according to the invention allows to obtain the profile of the whole nozzle without dividing it into a supersonic zone, a subsonic zone and a transit zone between the two .
- Another advantage is that it is possible to obtain a great homogeneity of the profile of velocity and pressure along the nozzle, and particularly in correspondence with the outlet of the relative lance; this allows to obtain greater distances from the outlet along which the density of the jet can be maintained. Moreover, a further advantage is that the operation to dimension the nozzle is considerably simplified.
- the method according to the invention allows to achieve a nozzle with a convergent/divergent development, obtaining velocity and pressure profiles which are highly stable inside the nozzle itself in its different transverse sections; it also obtains a very limited sublayer, and extremely uniform values of pressure/temperature/velocity at the outlet, throughout the field of application of the technology.
- the characteristics as above are obtained by optimising the fall in pressure along the convergent/divergent nozzle (Laval nozzle) in. such a way that the fall in pressure follows a hyperbolic tangent development .
- the approach adopted to obtain the dimensioning of the nozzle is an inverse approach, in the sense that the geometric development of the nozzle adapts to the natural profile of the fall in pressure of the gas, instead of imposing it arbitrarily with its geometric configuration.
- the geometry of the nozzle is adapted to the natural fall in pressure of the gassy flow which travels through the nozzle and therefore we obtain an optimum variation of the thermodynamic parameters, according to the natural laws of expansion.
- the method according to the invention allows to establish a substantially univocal relationship between velocity, static pressure and delivery of the flow in relation to the geometry of the nozzle.
- This relationship allows to correlate the individual sizes analytically and to achieve the dimensioning of the nozzle according to the required performance based on the specific operating technological requirements .
- the outlet velocities of the flow from the nozzle are in the range of 1.5 ⁇ 2.5 Mach, but the dimensioning method can be applied for the three- dimensional axi-symmetric dimensioning for different ranges of velocity.
- the optimum length of the nozzle is such as to ensure that the ratio is in the range of 8-25.
- the optimum value of the ratio between inlet temperature and temperature at outlet of the nozzle is in the range of 1.2 ⁇ 2.5 while the ratio between pressure at inlet and pressure at outlet of the nozzle is in the range of 2-40.
- Fig. 1 is a partial diagram of a section of a nozzle for a device to inject technological gases to which the method according to the invention is applied;
- Figs. 2a and 2b show two graphs in which the velocity of the flow is shown on the y axis and on the x axis the position, respectively, of a nozzle dimensioned according to the state of the art and a nozzle dimensioned according to the invention;
- Figs. 3a and 3b show two graphs in which the static pressure of the flow is shown on the y axis and on the x axis the position, respectively, of a nozzle dimensioned according to the state of the art and a nozzle dimensioned according to the invention;
- Fig. 4 shows the development of the radial coordinate r of the nozzle according to the axial co-ordinate x in relation to different constant values of the normalised function of flow ⁇ ;
- TABLES I-XV show the ratios of the axial coordinate and the respective radial coordinate of the wall of the nozzle with respect to the radial coordinate in correspondence with the throat of the nozzle in the optimum range of the outlet velocities, calculated according to the dimensioning method of the invention.
- DETAILED DESCRIPTION OF PREFERRED EMBODIMENT With reference to the attached Figures, a nozzle 10 according to the invention is associated with a lance suitable to be mounted on the walls of a furnace for melting metals, or a vessel in general to perform metallurgical transformations .
- the nozzle 10 has an outlet mouth 11 which is located at a defined distance from the upper level of the liquid bath and above the overlying layer of slag.
- the lance is suitable to be inserted in a suitable aperture made on the wall of the furnace and to cooperate with appropriate equipment, of a type known to the state of the art, to manipulate and possibly to insert, remove and orient etc. the lance.
- the nozzle 10 (Fig. 1) has a convergent/divergent (or
- Laval Laval conformation defined by a throat 12 made at a position upstream of the outlet mouth 11; the throat 12 defines a convergent part upstream and a divergent part downstream.
- the geometry of the nozzle 10 can be defined according to an axial dimension (axis x) , which coincides with the axis of symmetry of the nozzle 10, and a radial dimension (axis y).
- the construction of the system is based on the fundamental equations of fluid dynamics and particularly, respectively, the continuity equation, the momentum preservation equation and the energy preservation equation.
- w is the velocity vector
- p is the density of the fluid
- p is the static pressure
- h is the enthalpy.
- R is the universal constant of the gas
- T is the temperature on the absolute scale
- ⁇ is the molecular mass of the means. Since the analysis refers to the stationary case, the derivative with respect to the time of the state variables is nil.
- the axis of symmetry is necessarily reduced to a rectilinear line of flow due to the axi-symmetrical nature of the problem considered.
- auxiliary function or flow function ⁇ , defined as that function according to which the scalar product of the velocity vector w and the gradient of the function ⁇ is equal to zero.
- w-V ⁇ o (1.2.6.a) Having defined u and v, respectively, as the components on the axis of symmetry x and in the radial direction r of the 1.0
- the problem is solved by applying the iterative algorithm of calculation on the variable ⁇ , which requires an initial condition for ⁇ .
- the pressures p ⁇ n and Pou t re the real pressures, respectively, at inlet and outlet.
- a coefficient b>0 can be chosen as desired.
- f(x, ⁇ ) X ( ⁇ ) ⁇ " + ⁇ ⁇ f ( ) ⁇ n
- the geometry calculated with the method according to the invention can therefore be calculated according to the delivery desired but, in the optimum field of the outlet velocities (1,5 ⁇ 2,5 Mach), the ratios of the axial coordinate and the corresponding radial coordinate of the wall of the nozzle with respect to the radial coordinate in correspondence with the throat 12 of the nozzle 10 are those indicated in the Tables from I to XV.
- the nozzle 10 preferentially has a dimensionless length L/r * of between
- the ratio r/r * of the radial coordinate of the wall of the nozzle 10 with respect to the radial coordinate in correspondence with the throat 12, taken at the entrance to the nozzle 10, according to the invention is between about 2.38 and about 2.46 for all the values of outlet velocity of the flow.
- the same ratio r/r * taken at the outlet of the nozzle 10 varies from a minimum value of about 1.084, for the lowest velocities of 1.5 Mach, to a maximum value of about 1.618 for the highest velocities of 2.5 Mach, with intermediate values for the corresponding intermediate velocities .
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU63624/99A AU6362499A (en) | 1998-11-10 | 1999-11-08 | Nozzle for device to inject oxygen and technological gases and inverse dimensioning method |
EP99951051A EP1129222A1 (en) | 1998-11-10 | 1999-11-08 | Nozzle for device to inject oxygen and technological gases and inverse dimensioning method |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ITUD98A000195 | 1998-11-10 | ||
IT1998UD000195A IT1302799B1 (en) | 1998-11-10 | 1998-11-10 | NOZZLE FOR OXYGEN AND GASTECNOLOGICAL INJECTION DEVICE AND RELATED SIZING METHOD |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2000028096A1 true WO2000028096A1 (en) | 2000-05-18 |
Family
ID=11422779
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/IB1999/001793 WO2000028096A1 (en) | 1998-11-10 | 1999-11-08 | Nozzle for device to inject oxygen and technological gases and inverse dimensioning method |
Country Status (5)
Country | Link |
---|---|
US (1) | US6284189B1 (en) |
EP (1) | EP1129222A1 (en) |
AU (1) | AU6362499A (en) |
IT (1) | IT1302799B1 (en) |
WO (1) | WO2000028096A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011120976A1 (en) | 2010-03-31 | 2011-10-06 | Sms Siemag Ag | Ultrasonic nozzle for use in metallurgical installations and method for dimensioning an ultrasonic nozzle |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7476352B2 (en) * | 2004-05-21 | 2009-01-13 | 3M Innovative Properties Company | Lubricated flow fiber extrusion |
US20050288516A1 (en) * | 2004-06-28 | 2005-12-29 | Warren Jack S | Use of a device or devices, such as a convergent divergent funnel mixer, to optimize the available reaction volume, the raw material feed ratios and the weight hourly space velocity in a tube reactor |
WO2007054957A1 (en) * | 2005-11-10 | 2007-05-18 | Tata Steel Limited | An improved lance for ld steelmaking |
DE102010047969A1 (en) | 2010-03-31 | 2011-10-06 | Sms Siemag Aktiengesellschaft | Device for injecting gas into a metallurgical vessel |
US10589246B2 (en) * | 2015-02-26 | 2020-03-17 | Kellogg Brown & Root Llc | High temperature inlet distributor |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5579999A (en) * | 1993-07-19 | 1996-12-03 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Shock-free supersonic elliptic nozzles and method of forming same |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3938743A (en) * | 1974-06-26 | 1976-02-17 | Koppers Company, Inc. | Adjustably positionable supersonic nozzle means |
US4057421A (en) | 1974-10-22 | 1977-11-08 | Sumitomo Metal Industries Limited | Process for vacuum decarburization of steel |
EP0234077A1 (en) * | 1986-02-25 | 1987-09-02 | Council of Scientific and Industrial Research | Improved burner for furnaces employing acoustic energy |
LU87353A1 (en) * | 1988-09-28 | 1990-04-06 | Arbed | OXYGEN BLOWING LANCE |
US5782414A (en) * | 1995-06-26 | 1998-07-21 | Nathenson; Richard D. | Contoured supersonic nozzle |
-
1998
- 1998-11-10 IT IT1998UD000195A patent/IT1302799B1/en active IP Right Grant
-
1999
- 1999-11-08 EP EP99951051A patent/EP1129222A1/en not_active Withdrawn
- 1999-11-08 WO PCT/IB1999/001793 patent/WO2000028096A1/en not_active Application Discontinuation
- 1999-11-08 AU AU63624/99A patent/AU6362499A/en not_active Abandoned
- 1999-11-09 US US09/436,256 patent/US6284189B1/en not_active Expired - Lifetime
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5579999A (en) * | 1993-07-19 | 1996-12-03 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Shock-free supersonic elliptic nozzles and method of forming same |
Non-Patent Citations (3)
Title |
---|
BROWN E.F. E.A.: "Survey of Methods for Exhaust-Nozzle flow analysis", JOURNAL OF AIRCRAFT, vol. 13, no. 1, January 1976 (1976-01-01), pages 4 - 11, XP000867650 * |
PRASANTH,R.K.;WHITAKER,K.W.: "Neuromorphic approach to inverse problems in aerodynamics", AIAA JOURNAL, vol. 33, no. 6, June 1995 (1995-06-01), pages 1150 - 1152, XP002098645 * |
SETTLES,G.S.; GEPPERT,S.T.: "Redesigning blasting nozzles to improve productivity", JOURNAL OF PROTECTIVE COATINGS AND LININGS, vol. 13, no. 10, October 1996 (1996-10-01), pages 64 - 72, XP002098644 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011120976A1 (en) | 2010-03-31 | 2011-10-06 | Sms Siemag Ag | Ultrasonic nozzle for use in metallurgical installations and method for dimensioning an ultrasonic nozzle |
DE102011002616A1 (en) | 2010-03-31 | 2011-12-15 | Sms Siemag Ag | Supersonic nozzle for use in metallurgical plants and method for dimensioning a supersonic nozzle |
Also Published As
Publication number | Publication date |
---|---|
EP1129222A1 (en) | 2001-09-05 |
ITUD980195A1 (en) | 2000-05-10 |
IT1302799B1 (en) | 2000-09-29 |
AU6362499A (en) | 2000-05-29 |
US6284189B1 (en) | 2001-09-04 |
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