US3693875A

US3693875A - Rocket burner with flame pattern control

Info

Publication number: US3693875A
Application number: US203072A
Authority: US
Inventors: Thomas L Shepard
Original assignee: Individual
Current assignee: Individual
Priority date: 1971-11-29
Filing date: 1971-11-29
Publication date: 1972-09-26
Anticipated expiration: 1989-09-26

Abstract

An oxygen-fuel burner of the rocket burner type comprising a cylindrical combustion chamber having an open discharge end and a burner plate with separate oxygen and fuel ports constituting the opposite end of the chamber; the projected longitudinal axes of the oxygen ports extending in converging directions towards the longitudinal axis of the chamber but in off-set, non-intersecting relation thereto, so that points on the respective axes that most closely approach the chamber axis define a transversely positioned plane between the burner plate and the chamber exhaust; the projected longitudinal axes of the fuel ports being substantially parallel to the chamber axis for mixing of oxygen and fuel at and beyond the plane of closest approach, and means for adjusting the longitudinal position of the burner plate on the chamber axis and thereby locating the plane of closest approach in relation to the chamber exhaust for determining the pattern of the burner discharge flames.

Description

[451 Sept. 26, 1972 United States Patent Shepard ABSTRACT [54] ROCKET BURNER WITH FLAME a H9 93 32 2m MWL ma S n mh r he MSG .101.. 577 999 lll 860 Primary Examiner- Lloyd L. King 5 Claims, 8 Drawing Figures Attorney-H. Hume Mathews and Emund W." Bopp PATENTEUsEPes Isra SHEET 3 UF 4 FIG-7 ROCKET BURNER WITH FLAME PATTERN CONTROL This is a division of application Ser. No. 872,171, filed Oct. 29, 1969.

BACKGROUND OF THE INVENTION u The invention concerns burners for space heating, heat working, and the like, and especially burners of the oxygen-fuel type wherein oxygen and fuel respectively are fed as required to the burner for combustion and projection of heating flames. Control of the physical size and shape, i.e. pattern or configuration, of the burner flames is essential for many applications, such as for example where short, bushy or spreading flames best serve the heating purpose; in other applications, a long slender, needle-type flame may be indicated.

Although flame pattern control for oxygen-fuel burners has heretofore been proposed and practiced, it has not been satisfactorily achieved insofar as known, in modern acceptable burner equipment. For example, a prior art device known as the shelltype burner utilized the needle valveprinciple for changing the flame pattern. In this burner the oxygen is fed through a cylindrical housing or shell and mixed with fuel gas from a feeder that is axially adjustable in the shell for defining an annular nozzle type opening, constituting the adjustable burner passage. The burner also includes a socalled bluff body flame stabilizer and spreader that is in direct contact with the oxygen-fuel flame at the point of mixing. Asindicated above, control of the flame pattern of the shell burner is accomplished by axial movement of the central fuel feeder for varying in the manner of needle valv'e control, the annular passage for directing an oxygen-fuel mixture into the combustion region at the bluffbody. Serious difficulties and disadvantages were encountered in the operation of the shell burner. Premature ignition of thehighly combustible oxygen-fuel mixtures within the burner itself created a dangerous explosion hazard; also excessive maintenance was involved due to the difficulty of properly cooling'the burner parts in direct contact with the hot oxygen-fuel flames. For these reasons general use of the shell type oxygen-fuel burner has greatly declined.

A more acceptable oxygen-fuel burner now in common use is known as the rocket burner, a typical example being shown by U.S. Pat No. 3,135,626 granted June 2, 1964 to Moen and Shepherd. Briefly, the rocket burner comprises a cylindrical combustion chamber open at the discharge end and having a multiport burner plate forming the opposite end of the chamber. Fuel gas and oxygen are separately fed in closely grouped parallel streams through respective ports in the burner plate for mixing and burning in the combustion chamber. Initially, this is accompanied by establishment of low velocity anchoring flames as gases `along the peripheries of adjacent fuel and oxygen streams mingle after passing through the burner platel ports.

ln the rocket burner, a limited degree of flame pattern control can of course, be achieved .by valve regulation of the amounts, pressures and ratios of the oxygen and fuel fed to the burner; also by locating the burner plate selected distances from the burner exhaust, an elongated stiff flame or a comparatively short, fat flame can be produced. However, regulation of the oxoutput.

ygen and fuel burner input does not provide for flexibility in varying the flame pattern for a given BTU burner output. Location of the burner plate at different distances from the burner exhaust also does not achieve the desired control of flame pattern as the closely grouped parallel gas streams from the conventional bumer plate ordinarily start mixing and burning well within the combustion chamber near the burner plate and tend to diverge downstream. Where the burner plate is comparatively close to the exhaust of the combustion chamber, bushy type flames naturally result; however, a widespreading umbrella-shaped flame is not possible with -the .conventional rocket burner. A n' The invention therefore is concerned with providing an improved 'rocket burner having flexible flame pattern control over a wide range for a given BTU burner SUMMARY oF THE INVENTION ln accordance with the invention in its broader aspects, a rocket type oxygen-fuel burner is provided with a specially designed multiple-port burner plate for so directing respectivestreams of fuel gas and oxygen into the cylindrical combustion chamber of the burner, that initial mixing of the gases for combustion occurs within a region spaced from the burner plate; furthermore for a given BTU output of the burner, this region can be shifted toward or away from the exhaust end of the combustion chamber by corresponding relative longitudinal movement of the burner plate with respect to the combustion chamber for changing throughout a wide range the pattern of the discharge flames.

ln a preferred form of the invention, the region of initial gas mixing is determined by interaction of a plurality of the fuel gas streams that yflow from the burner plate generally parallel to the longitudinal or central axis of the chamber, with a plurality of oxygen streams that flow angularly from the burner plate so as to converge toward the chamber axis, but in off-set or tangential, non-intersecting relation thereto. Accordingly, the

points on the respective converging axes that `are closest to the chamber axis define a plane that is transverse to this axis. The plane,\herein called the plane of closest approach, is the general locator of the region of gas mixing and primary combustion.

y Since the projected longitudinal axes of the oxygen ports start to ldiverge beyond the plane of closest approach, the momentum of high velocity oxygen streams tends to produce bushy, wide-spreading flames where the burner is adjusted for axes divergence beyond the chamber exhaust; conversely where the adjustment is such that the diverging streams are confined by the chamber walls, an elongated sharp and jet-like high velocity flame is produced. Variation of the flame discharge pattern within the limits indicated above is achieved in accordance with the invention by relative longitudinal movement between the burner plate and the combustion chamber, and hence variation of the position of the plane of closest approach with respect to the chamber exhaust for controlling divergence of the mixed combustion gases.

A principal object of the invention therefore is to provide an improved oxygen-fuel burner of the rocket burner type with flame pattern control wherein the chamber exhaust is made variable for varying within a wide range the pattern of the chamber exhaust flames.

A further and related object is to provide an improved burner of the character described above wherein the projected longitudinal axes of the oxygen and fuel ports ofthe burner plate are angularly related for defining the remotely spaced gas mixing region, and the burner plate is movable relative to the chamber exhaustfor varying the location of the mixing region and so controlling the pattern of the exhaust flames.

A further object of the invention is to provide an improved bumer of the type described above that achieves efficient use of heat output for variable flame pattern control, that is easily adjustable for a given BTU- burner outputwithin a wide range of flame pattern control, and that has low maintenance cost and is free of preignition hazard. I

. Other objects, featuresand advantages will appear from `the following description .with reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view, partly in section, of a rocket type oxygen-fuel burner embodying the invention;

FIG. 2 is a plan view of the multi-port burner element of the rocket burner shown in FIG. l;

FIG. 3 is a sectional view taken along the line 3-3 of FIG. 2;

FIG. 4 is a diagrammatic view of the burner element and combustion chamber indicating convergence of two oxygen streams toward the chamber axis;

FIG. 5 is a diagrammatic plan view indicating the relation of the oxygen streams to the chamber axis at the plane of closest approach along line 5 5 of FIG. 4; and

FIGS. 6, 7 and 8 are diagrammatic views illustrating respectively, different positions ofthe burner plate with respect to the combustion chamber exhaust for'achieving different patterns of the exhaust flames.

DESCRIPTION OF PREFERRED EMBODIMENT The oxygen-fuel rocket burner 10 shown by way of example in FIG. l, comprises a tubular or cylindrical housing l2 within which a burner element 14 defines one end of a combustion chamber 16. The open end of the housing at 18 defines the opposite or discharge end of the chamberfrom which heating flames are projected for heat working, space heating, etc. As the combustion chamber is subject to the high temperatures encountered in the'operation of oxygen-fuel burners, the lhousing l2 includes a water-cooled jacket 20 that extends throughout the length of the combustion chamber and most of the housing for effective heat dissipation.

The burner element 14, herein for convenience termed burner plate, constitutes in effect a flow divider for separately feeding a plurality of oxygen and fuel-gas streams respectively into the combustion chamber. In the present example, the burner plate is formed as an apertured disc-like cylinder that is concentrically mounted within the combustion chamber and serves as a partition between the combustion chamber and an elongated plenum chamber 22 for the fuel gas. The plenum chamber extends from the burner plate to the opposite end of the housing where it is connected to a fuel gas supply conduit at 23, that conveniently may be utility natural gas.

Certain of the burner plate apertures or ports are centered as at 24 for example, and extend through the burner plate for directly communicating with the fuel gas plenum chamber 22. A plurality of other ports 26 for supplying oxygen to the combustion chamber are arranged in a circle, preferably concentric with the longitudinal axis of the combustion chamber (and burner plate), around the smaller centrally grouped fuel ports 24. Additionalfuel ports 28 in the burner plate, also communicating with the fuel chamber 22, are disposed in a circlearound the outer peripheral area of the ox ygen ports 26. The central fuel ports 24, shown as 6 in number, and the outer fuel lports 28, also 6 in number, extend transversely through the burner plate; i.e. the axes of the respective ports extend generally parallel to the longitudinal axis of the combustion chamber. The oxygen ports 26, however, are angularly disposed with respect to the chamber axis, the projected longitudinal axes of which converge toward the chamber exhaust in off-set, tangential relation to the chamber axis so as to be in non-intersecting relation therewith. That is, the longitudinal axes of the oxygen `ports are inclined toward and skewed somewhat with respect to the chamber axis as indicated in FIG. 2 for establishing the geometric relation described above.

The oxygen ports 26 are connected to an oxygen supply through a manifold arrangement that comprises a plurality of tubes 30 interconnecting the corresponding oxygen ports and a header 32. The header in turn, is fed by a conduit 34 that extends longitudinally through the chamber 22 and the housing to the exterior for connection as indicated with a source of pressurized oxygen.

It will be apparent that in the apparatus so far described, separate supplies of oxygen and fuel-gas are fed to the corresponding ports in the burner plate, the oxygen from the conduit 34 and manifold to the ports 24, and the fuel-gas from the supply line at 23 and plenum chamber 22 directly to the

burner plate ports

24 and 28. Accordingly, the burner plate ports direct as indicated above, separate streams of oxygen and fuelgas respectively into the combustion chamber 16 for mixture beyond the burner plate and subsequent burning as more fully described below.

The combustion chamber walls as mentioned above are protected from overheating by a water-cooled jacket 20 constituting part of the housing 12 and consisting of concentric

tubular walls

36, 38 and 40 that are spaced in the usual manner for defining annular, reverse-flow cooling paths. As shown, the cooling path extends from the cooling water inlet 42 through the annular passage 44 defined by wallsl 38 and 40 to the burner exhaust end, where the flow reverses into the annular passage 46 formed between the

walls

36 and 38, and thence to the cooling water outlet 48.

The materials of construction for the present burner may conform in general to those used in previous rocket burners; i;e. the burner plate may be made of copper or tellurium copper, and the cylinders of the the length of the combustion chamber, and thereby the pattern of the exhaust flames. To this end, the burner plate 14, manifold 30-32, and conduit 34 are integrated as a structural unit for relative movement with respect to the housing l2. The burner plate has a sliding fit with the inner cylinder wall 40 constituting the combustion chamber wall, and the conduit 34 is guided for longitudinal movement by a sealing bushing 50 through the end wall 52 of thehousing. Relative movernent between the burner plate assembly and the housing can be achieved in any suitable manner; for example', a gear rack 54 thatis connected to the conduit, is engaged by a coacting` pinion 56 that in turn is manuallyoperated at 58 for moving the conduit (and the burner plate) longitudinally in either direction.

` Reference is now made to FIGS. 2 and 3 for illustrating the specific arrangement of the burner plate ports for directing interactingy streams of oxygen and fuel-gas respectively into the combustion chamber. Taking for example the oxygen port 26a, it will be noted that the longitudinal axis 26' thereof is skewed with respect to the center of the burner plate, i.e. the longitudinal axis of the combustion chamber, so that intersection ofthe port axis 26' with the chamber axis 16 is not possible. It will also be noted that the oxygen port axis 26' intersects withthe longitudinal-axis of one of the centrally located small fuel ports'24b, hereinafter referred to as primary fuel ports, for insuring mixingof these two y streams. Moving clockwise, it will also be seen that the other oxygen ports 26b, 26e, etc., are similarly skewed with respect to the chamber axis kand have their respective longitudinal axes oriented for intersecting with corresponding axes of primary fuel ports 24C, 24d, etc.

FIG. 3 illustrates the angular direction of the

oxygen ports

26a and 26d for directing oxygen streams in converging direction toward the chamber axis 16', but in tangential offset, non-intersecting relation thereto as best illustrated in FIG. 2. The oxygen streams from the 6 ports shown in FIG. 2 therefore tend to form a clockwise vortex around the chamber axis at a region remote from the burner plate.

FIGS. 4 and 5 which diagrammatically supplement FIGS` 2 and 3, indicate the relationship between the projected longitudinal axes of the oxygen ports and the extension of the chamber axis 16'. In the partly sectional view of the combustion chamber and burner plate shown by FIG. 4, the burner plate is in a similar position to that shown in FIG. 3. The oxygen streams from the

ports

26a and 26d are represented for convenience in illustration, as straight high velocity jets or stream cores0-l and 0-4, disregarding for the moment any modifying elects of the fuel-gas streams (not shown) fromA the

primary fuel ports

24a and 24d, etc. Although the axes of the two skewed streams appear in FIG. 4 to intersect each other and the chamber axis 16' at some point beyond the section line 5-5, their closest approach to the axis actually occurs at the section line. Accordingly, the transverse plane or region determined by the section line 5-5 is referred to herein as the plane of closest approach." FIG. 5 taken along this section line shows the skewing angle a of the oxygen streams 0-1 and 0-4 as about 60 in clockwise direction from the initial positions of FIG. 3 as represented by the horizontal or transverse burner plate axis 14'. The other oxygen streams 0L2 and 0-3, etc. are assumed to be skewed uniformly in the same direction as best shown in FIG. 2.

Between the plane of closest approach and the chamber exhaust, the oxygen streams begin to diverge toward the combustion chamber wall. FIG. 6 illustrates schematically this divergence for a given advanced position of the burner plate wherein the combustion chamber is comparatively short. In this example, divergence of the oxygen port axes extends beyond the chamber exhaust.

Returning briefly to FIG. 2, it will be seen thatvthe additional or secondary fuel gasv ports 28 along the peripheral area of'thejbumer vplate are designed to supply the main volume of comparatively low velocity fuel to the combustion chamber. As the axes of these ports, as in the case of the central or primary fuel-

gas ports

24a, 24b, etc., extend generally parallel tothe chamber axis, the secondary fuel gas streams form in effect a low velocity gas envelope at the `chamber periphery surrounding the oxygen and the primary fuel streams.

In FIG. 6, the sectional view is intended to indicate the interaction of the oxygen and fuel streams in and beyond the combustion chamber, rather than the precise scalar relationship of the axes in FIGS. 2, 3 and 4. It was found in developing the present invention that a wide spreading, bushy or umbrella type flame for the rocket burner as represented by FIG. 6 is best achieved by using the momentum of high velocity oxygen streams directed in both converging and tangential (or skewed) directions with respect to the combustionchamber axis for locating the plane of closest approach sufficiently near the chamber exhaust that the divergence of the high velocity stream yis not confined by the chamber walls. By avoiding convergence carried to actual intersection of the oxygen stream axes, as at some common point on the chamber axis, serious problems involving limitation of flame length, combustion chamber cooling, etc., are avoided and the advantages of free gas and flame divergence beyond the plane of closest approach for producing the desired umbrella-type flame are retained` Referring more specifically to the burner operation, the primary combustion mechanism in the present invention, while somewhat similar to that described in the Moen and Shepherd Patent above, wherein holding flames for stabilizing the main combustion chamber flames are established in a low velocity region near the discharge side of the burner plate, actually differs materially therefrom by establishing primary combustion for the stabilizing flames in a chamber-centered region a material distance from the burner plate. This is achieved by feeding the comparatively small primary supply of fuel gas from the

burner ports

24a, 24b, etc., directly into the converging oxygen streams entering the region of closest approach, FIGS. 2 and 6. As the oxygen and primary fuel streams gradually converge,

the respective streams mix and provide as schematically indicated at 25 low velocity holding flames.

This introduction of a comparatively small amount of fuel into the oxygen streams at the plane of closest approach, produces a transversely extending region for the primary and stabilizing combustion. This region is in a gas mixture zone of relatively low velocity, extending to the enveloping fuel streams F, Secondary combustion is therefore effectively stabilized by direct communication with the primary combustion zone. The size and spread of this zone, referring to FIG. 5, is readily controlled in the design, according to the convergence and skewing angles of the oxygen port axes. As the diverging oxygen streams from the region of closest approach continue to diverge toward the chamber exhaust and mix with the enveloping main supply of secondary fuel gas from the ports 28, combustion of the mixed gases is ensured by the primary combustion or holding flames at the lregion of closest approach as indicated in FIG. 6.

The secondary combustion region, i.e. where Vcombustion of the spreading mixed oxygen and fuel gases is completed, extends beyond the chamber exhaust as indicated and is determined generally by the velocity and divergence of the oxygen streams with respect to the chamber exhaust andthe amount of fuel gas from the ports 28. It will be seenfrom FIG. 6 that the main or secondary fuel supply envelope from the ports 28 is traversed by and mixed with the stronger high velocity diverging oxygen streams -1 and 0-4, etc., with consequent spreading or mushrooming of the mixed burning gases beyond the chamber exhaust. Accordingly, a secondary combustion or flame region having the desired wide-spreading umbrella type" pattern is established.

The degree of flame spread for a given burner plate adjustment can of course be further varied by empirical adjustment of the supply pressures for the oxygen and fuel gas streams. Variation of the oxygemfuel ratio af fects flame spread to the extent that a ratio giving an optimum fuel supply for producing combustible mixtures for the main combustion-flame system, results in a larger secondary combustion region. Although the term oxygen as used herein generally refers to the preferred use of commercially pure oxygen, it is also intended to include oxygen enriched gases in applications where the higher combustion temperatures obtainable by pure oxygen are not required.

Where the burner plate and plane of closest approach are located as illustrated in FIG. 7, so that the projected diverging axes 26' of the oxygen. stream cores intersect the combustion chamber wall, as distinguished from FIG. 6 wherein divergence of the axes beyond the plane of closest approach is not restricted by the chamber wall, mixing and initial secondary combustion of the enveloping fuel streams F, and the oxygen streams 0-1 and 0-4, etc., are confined to a greater extent within the now elongated combustion chamber 16. That is, as the chamber wall is now effective to deflect the oxygen streams generally along and into the enveloping fuel streams, mixing of the oxygen and secondary fuel tends to take place mainly within the combustion chamber. The momentum of the oxygen streams, combined with the chamber pressure incident to secondary combustion, produces a stiff, sharp and elongated flame at the combustion chamber exhaust. lt is believed that this effect is due in part to the energy of the deflected oxygen cores, that tend to reconverge, somewhat as a tapering cone, on the chamber axis. Secondary fuel is during this process mixed with the oxygen and carried along toward the central axis of the chamber, where secondary cornbustion continues as the mixed gases and combustion flames are discharged at high velocity from the burner exhaust to form a long, needle-type flame.

FIG. 8 illustrates an intermediate adjustment of the burner plate for obtaining a flame pattern that represents a moderately bushy flame, materially longer than the umbrella type flame of FIG. 6. In this flame pattern adjustment the projected longitudinal axes 26' of the oxygen stream cores barely clear the chamber exhaust so that part of the oxygen stream is deflected inwardly by the chamber wall. Accordingly, but part of the oxygen stream energy is available to spread the mixed gases and flame in divergent directions at the exhaust so that a modified bushy flame of moderate length is produced. It will be apparent from the descriptions of FIGS. 6-8, that a wide range of graduated flame pattern control can be achieved by corresponding adjustment of the burner plate (and plane of closest approach) with respect to the chamber exhaust.

Summarizing briefly, it will be seen that the invention avoids certain prior art difficulties by the use of aerodynamic flame-holding for establishing an oxygenfuel mixing region remote from any part of the burner plate, thereby isolating the movable burner plate from any contact with flame or combustible oxygen-fuel mixtures.

In practice, the rocket burner of the invention is flexible in scope of operation; all gaseous, atomizable or vaporizable fuels can be burned at high efficiency without major design changes, and optimum conditions for a given fuel can be obtained by adjustment of design parameters. Basic variable factors of the burner include the burner BTU output that is determined by the amounts of oxygen and fuel supplied, the angle of exhaust flame divergence determined by the position of the burner plate (and the diverging and skewing angles of the oxygen stream cores), and the turn-down ratio. The latter is defined in terms of the full range of burner operation for a stable flame situation. This can be quantitatively expressed as a ratio (BTU/hr. (max.)/BTU/hr. (min.).)

Conventional commercial burners have in general a narrow range within which stable flame operation can be obtained, whereas rocket burners of the present invention may have, for example, a turn-down ratio of about 1,000: 1 that is determined by the burner dimensions, principally the diameters of the respective oxygen and fuel ports, and the angular relation of the port axes to the chamber axis.

Practical advantages of the invention also include improved flame stability by reason of the low velocity, centered primary combustion region, improved turndown ratio, simplicity of design wherein a flame stabilizing bluff body or the like, in the flame is not needed, and greatly improved safety with practical elimination of preignition and explosion hazard.

Having set forth the invention in what is considered to be the best embodiment thereof, it will be understood that changes may be made in the system and apparatus as above set forth without departing from the spirit of the invention or exceeding the scope thereof as defined in the following claims.

l claim: 1. In an oxygen-fuel burner having a com` bustion chamber of generally tubular configuration and means for feeding separate streams of oxygen and fuel respectively, into the chamber, the method of controlling the pattern of the flames discharged from the chamber which comprises:

a. directing the fuel streams at low velocity in generally parallel flow toward the discharge end of the chamber,

b. directing oxygen flow at comparatively high velocity in streams radially spaced from the longitudinal axis of the chamber in generally converging, non-intersecting relation to the chamber axis for defining a transverse zone at the respective points of closest approach to the axis,

for mixing with converging oxygen flow and establishing a primary stabilizing combustion reglon,

. directing the main fuel supply along the peripheral region of the chamber for defining a secondary fuel envelope for the oxygen streams, so that the diverging high velocity oxygen streams beyond the defined zone traverse and mix with the secondary fuel envelope for establishing a secondary combustion region,

e. and changing the location of oxygen traverse of the secondary fuel envelope with respect to the discharge end of the chamber for varying the confining effect of the chamber on the secondary combustion discharge flame pattern.

2. The method of flame pattern control as specified in claim 1 wherein the flow of primary and secondary fuel constitutes a plurality of streams in generally parallel relation to the axis.

3. The method of flame pattern control as specified l in claim l wherein the location of the defined zone is directing a portion of the fuel into the dened zone variable with respect to the discharge end of the combustion chamber for changing the location of the oxygen-fuel envelope traverse.

4. The method of flame pattern control as specified in claim 3 wherein the defined zone is so located within the chamber that the divergent oxygen streams impinge on the chamber wall and the mixed oxygen and fuel gases are confined to axial flow for producing a long, needle-type secondary combustion flame.

5. The method of flame pattern control as specified in claim 3 wherein the defined zone is so located near the chamber discharge end, that the divergent oxygen streams with mixed secondary fuel expand laterally beyond the chamber for producing a spreading, cornparatively short umbrella-type secondary combustion flame.

Claims

2. The method of flame pattern control as specified in claim 1 wherein the flow of primary and secondary fuel constitutes a plurality of streams in generally parallel relation to the axis.
3. The method of flame pattern control as specified in claim 1 wherein the location of the defined zone is variable with respect to the discharge end of the combustion chamber for changing the location of the oxygen-fuel envelope traverse.
4. The method of flame pattern control as specified in claim 3 wherein the defined zone is so located within the chamber that the divergent oxygen streams impinge on the chamber wall and the mixed oxygen and fuel gases are confined to axial flow for producing a long, needle-type secondary combustion flame.
5. The method of flame pattern control as specified in claim 3 wherein the defined zone is so located near the chamber discharge end, that the divergent oxygen streams with mixed secondary fuel expand laterally beyond the chamber for producing a spreading, comparatively short umbrella-type secondary combustion flame.