U.S. patent number 3,695,820 [Application Number 05/030,030] was granted by the patent office on 1972-10-03 for gas burners.
Invention is credited to Ivor Hawkes, Joshua Swithenbank.
United States Patent |
3,695,820 |
Hawkes , et al. |
October 3, 1972 |
GAS BURNERS
Abstract
A gas burner comprises an annular chamber surrounding the fuel
and air inlet end of a throated nozzle, with a circular slit
orifice opening from the chamber into the nozzle upstream of the
throat, and a flame stabilizer at one end of the nozzle, fuel gas
passing through the slit expanding to form a Coanda wall jet around
the inlet peripheral converging wall of the nozzle and inducing a
flow of air down the center of the nozzle, the radial pressure
gradient created by the jet sheet following the converging wall of
the nozzle to its throat bringing about a high degree of air
entrainment, whereby stable combustion results, at a point
determined by the flame stabilizer.
Inventors: |
Hawkes; Ivor (Lyme, NH),
Swithenbank; Joshua (Hathersage, EN) |
Family
ID: |
10140551 |
Appl.
No.: |
05/030,030 |
Filed: |
April 20, 1970 |
Foreign Application Priority Data
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Apr 19, 1969 [GB] |
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20,110/69 |
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Current U.S.
Class: |
431/354; 239/403;
431/350; 239/401; 239/417 |
Current CPC
Class: |
F23D
14/64 (20130101); F23D 14/74 (20130101) |
Current International
Class: |
F23D
14/72 (20060101); F23D 14/46 (20060101); F23D
14/74 (20060101); F23D 14/64 (20060101); F23d
013/40 () |
Field of
Search: |
;431/350,353,354
;60/39.49 ;239/DIG.7,403,401,39C,417 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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948,350 |
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Aug 1956 |
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DT |
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845,676 |
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Aug 1960 |
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GB |
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857,780 |
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Apr 1939 |
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FR |
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Primary Examiner: Dority, Jr.; Carroll B.
Claims
What we claim is:
1. A gas burner comprising:
a source of fuel gas,
an annular chamber for receiving a supply of fuel gas under
pressure from said source,
a convergent-divergent throated nozzle surrounded near its inlet
end by said annular chamber,
said burner including a circular slit orifice opening from the
chamber into the nozzle upstream of the throat, said nozzle and
said slit being arranged to produce a Coanda effect entraining air
as an oxidizer as a result of fuel gas under pressure issuing from
said slit,
a flame stabilizer mounted at one end of the nozzle, said flame
stabilizer being mounted at the inlet end of the nozzle and is in
the form of a vortex chamber with non-radial air inlet slots,
whereby expansion of gas through the slit forms a Coanda wall jet
around the inner peripheral converging wall of the nozzle for the
induction of air down the center of the nozzle.
2. A gas burner comprising:
a source of fuel gas, an annular chamber for receiving a supply of
fuel gas under pressure from said source,
a convergent-divergent throated nozzle surrounded near its inlet
end by said annular chamber,
said burner including a circular slit orifice opening from the
chamber into the nozzle upstream of the throat, said nozzle and
said slit being arranged to produce a Coanda effect entraining air
as an oxidizer as a result of fuel gas under pressure issuing from
said slit,
means for adjusting the gap where the slit opens into the
nozzle,
a flame stabilizer mounted at one end of the nozzle,
whereby expansion of gas through the slit forms a Coanda wall jet
around the inner peripheral converging wall of the nozzle for the
induction of air down the center of the nozzle.
3. A gas burner as in claim 2, wherein the flame stabilizer is
mounted at the exit end of the nozzle.
4. A gas burner as in claim 3, wherein the end stabilizer is a
tunnel stabilizer of larger diameter than the exit end, to provide
return eddy currents by the helical vortex created by the gas and
air immediately on leaving the exit.
5. A gas burner comprising:
an annular chamber,
a throated nozzle surrounded near its inlet end by the chamber, a
circular slit orifice opening from the chamber into the nozzle
upstream of the throat,
a flexible annular diaphragm forming one wall of the annular
orifice,
a flame stabilizer mounted at one end of the nozzle, and
a fuel gas inlet to the annular chamber, whereby expansion of gas
through the slit will form a Coanda wall jet around the inner
peripheral converging wall of the nozzle, for the induction of air
down the center of the nozzle.
6. A gas burner as in claim 5, wherein the inlet end of the nozzle
is axially adjustable with respect to an outer sleeve that forms
one wall of the annular orifice.
7. A gas burner as in claim 6, wherein the adjustment is manual, as
by a screwthreaded connection between the nozzle and the
sleeve.
8. A gas burner as in claim 6, wherein said nozzle and said chamber
are movable axially thereof and include piston means for displacing
said chamber selectively relative to said nozzle, whereby the
adjustment of the gap is made by said piston means.
Description
This invention relates to gas burners of the injector type in which
air for combustion is entrained by the flow of the fuel gas under
pressure.
In the usual injector type burner, the gas is fed through one or
more nozzles directed in the desired direction of gas/air flow, and
air is entrained around the peripheral surface of the expanding gas
jet issuing from a nozzle, and mixed with the gas by the turbulence
there created. Such burners may operate using primary air only,
induced in the manner described, or they may use both primary and
secondary air, the latter being entrained into the flame already
produced by the combustion with the primary air.
The word gas as used throughout this specification is intended to
embrace any artificially produced or natural gas, or any vapor that
is suitable for combustion with air.
The principle object of the invention is to provide a burner of
simple design in which there is a greater rate of air entrainment
than is possible with a conventional injector burner, so that for a
given duty a smaller burner may be used than is possible with a
conventional burner.
A further object is to provide a burner in which the air/gas
mixture boundary velocity gradients at the nozzle exit are higher
than in a conventional injector burner so that a higher turndown
ratio and a higher combustion intensity can be achieved.
Yet another object is to provide a burner with a gas inlet orifice
that is readily adjustable, so that a wide variety of gases can be
burned efficiently by the same burner, with the possibility of
remote control of the adjustment.
Arising from the simple design of the burner, the invention also
permits easy removal from the burner of grit or particles present
in dirty gases.
According to the present invention a gas burner comprises an
annular chamber, a throated nozzle surrounded near its inlet end by
the chamber, a circular slit orifice opening from the chamber into
the nozzle upstream of the throat, for the expansion of gas through
the slit to form a Coanda wall jet around the inner peripheral
converging wall of the nozzle, for the induction of air down the
center of the nozzle, and a flame stabilizer mounted at one end of
the nozzle. By the Coanda effect, the jet sheet follows the
converging wall and the radial pressure gradient created by the
curvature of the wall to its throat brings about a high degree of
air entrainment. Stable combustion then results, at a point
determined by the flame stabilizer.
The flame stabilizer may be mounted at the next exit end of the
nozzle. Thus, it may be a tunnel stabilizer of larger diameter than
the exit end, to provide return eddy currents by the toroidal
vortex created by the gas and air immediately on leaving the exit.
Alternatively, the exit stabilizer may be formed of an array of
angled blades.
The flame stabilizer may however be mounted at the inlet end of the
nozzle in the form of a vortex chamber with non-radial air inlet
slots. This enables a highly turbulent helical vortex to be formed
at the nozzle exit, for the stabilizing of the flame.
By suitable proportioning of the relative dimensions of the
circular slit diameter and gap, and the diameter of the nozzle
throat, the whole of the air for stoichiometric combustion can be
induced down the center of the nozzle or the air as induced may be
primary air, secondary air being entrained into the flame region
itself by the flame turbulence. For any given gas and burner
configuration there is an optimum slit gap width for maximum flame
intensity, and preferably the burner has means for adjusting the
gap, for tuning to this optimum during operation. Once the gap has
been set, the gas/air entrainment ratio is comparatively
insensitive to gas pressure over a wide range, and down to
comparatively low pressures. At very low gas pressures approaching
pilot light operation, the pressure drop across the gap from the
annular chamber into the nozzle may be insufficient to produce an
effective Coanda wall jet and therefore the burner tends to burn
over-rich as insufficient air is entrained. To overcome this, a
further feature of the invention consists in the provision of a
flexible annular diaphragm forming one wall of the annular orifice.
At low gas pressure, the diaphragm limits the effective gap width
appropriately, but at higher gas pressures the diaphragm is forced
towards one side of the orifice to increase the gap width, until
eventually it abuts one side of the orifice, so that the effective
gap width remains fixed, appropriate to the normal working pressure
of the gas. AT lower pressures than this, the diaphragm flexes to
reduce the gap width and increase the pressure drop necessary to
maintain the necessary entrainment.
Whether or not such a flexible diaphragm is provided, the gap width
may be adjustable, manually or remotely. Thus, the inlet end of the
nozzle may be axially adjustable with respect to an outer sleeve
that forms one wall of the annular slit. The adjustment may be
manual, as by a screwthreaded connection between the nozzle and the
sleeve or it may be controlled by fluid pressure, as by providing a
chamber within the outlet sleeve, this making it possible for the
adjustment -- of one burner or a plurality of burners
simultaneously -- to be remotely controlled.
The invention will now be further described with reference to
several embodiments shown in the accompanying diagrams, in
which:
FIG. 1 is a longitudinal section of a burner, showing its annular
orifice and other essential features of construction in
diagrammatic manner;
FIG. 2 is an end view taken in the direction of arrow A in FIG.
1;
FIG. 3 is a longitudinal section of the inlet end of a burner
provided with means for manually controlling the width of its
annular orifice;
FIG. 4 is a longitudinal section through the inlet end of a burner
provided with fluid-pressure operated means for controlling the
width of its annular orifice, the burner, also being fitted with an
inlet vortex chamber;
FIG. 5 is a section taken to a smaller scale, on the line 5--5 of
FIG. 4, and
FIG. 6 is a fragmentary longitudinal section through the inlet end
of another burner provided with means for automatically controlling
the width of its annular orifice.
In FIG. 1, a fuel gas inlet 1 leads to an annular chamber 2
provided with an annular orifice 3 (see also FIG. 2) from which the
gas flows into a converging inlet 4 of a nozzle 5, to form a Coanda
wall jet in the nozzle the jet flowing through a throat 6 and along
a diverging length 7 of the nozzle to an exit 8. Primary air for
combustion is induced by the wall jet from the atmosphere into the
inlet 4. The inlet may be fitted with a vortex chamber 9, to
provide for stabilization of the flame burning at the nozzle exit
8. Such a vortex chamber is also shown in FIG. 4. Alternatively, a
tunnel type stabilizer 10, or a swirl type stabilizer, may be
fitted on the nozzle exit 8 to stabilize the flame.
The gas and air flowing into the stabilizer 10 form return eddy
currents beyond the shoulder formed by the larger diameter of the
stabilizer as compared with the exit end of the nozzle 5.
The efficient burning of different gases necessitates an
appropriate gap width for the orifice 3. The burner is therefore
preferably adjustable as to gap width. One adjustable construction
is shown in FIG. 3. The annular orifice 3 is formed between an
outer sleeve and an inner nozzle plug 12, these being axially
movable one relative to the other by means of screw threads 13, so
that rotation of the sleeve 11 alters the gap proportionally to the
pitch of the threads. To take up thread backlash and provide a
resistance to the rotary motion, a spring 14 is compressed between
the ends of the two components 11, 12. An O-ring seal 15 prevents
gas leakage. A pointer 16 carried by the plug 12 protrudes from a
slot 17 in the sleeve 11 and enables the gap width to be set in
relation to scale markings (not shown) on the outside of the
sleeve.
In FIG. 4, a pressure chamber 18 is formed by a sleeve 11A and a
nozzle plug 12A. O-ring seals 15A, 15B prevent leakage from the
chamber 18. Pressure fluid admitted to the chamber 18 by an inlet
19 acts against the spring 14 and controls the width of the orifice
gap 3 to an amount proportional to the force generated by the fluid
pressure in overcoming the spring. The pressure of the fluid in the
chamber 18 should be such that the net axial force caused by
changes in fuel gas pressure in the chamber 2 is negligible
compared to that generated by the control pressure, thus rendering
the gap width insensitive to changes in fuel gas pressure.
The construction of FIG. 4 has the advantage that the orifice gaps
on a large number of burners can be rapidly and similarly altered
from a location remote from the burners, by inter-coupling the
fluid chambers 16 to a common control source of pressure fluid.
FIG. 4 also shows the vortex chamber 9, for inducing into the
primary air, formed integrally with the sleeve 11A. Air approaches
the vortex chamber as shown by the arrows B, and is then sucked
into the chamber by the Coanda wall jet of the nozzle. It enters
the chamber 9 through oblique slots 20 (see FIG. 5), and is caused
to produce a vortex, which continues to and beyond the nozzle exit
(FIG. 1).
The construction of FIG. 6 provides for automatically increasing
the air entrainment ratio, at very low fuel gas pressures. A
flexible annular diaphragm 21 is clamped between an outer sleeve
11B and an end cover 11C (providing the nozzle inlet 4), so as to
form one wall of the annular orifice 3. At zero pressure difference
between the annular chamber 2 and the atmosphere, the width of the
orifice gap is the distance between the end 22 of a plug 12B
providing the nozzle proper, and the inner edge 23 of the
undistorted diaphragm. As the fuel gas pressure increases, the
diaphragm distorts towards the end cover 11C until it eventually
contacts a point 24 on the latter, to leave between the diaphragm
and the point 22 the maximum gap width required for the efficient
operation of the burner at the normal working pressure of the gas
supplied to the chamber 2.
Where the flame stabilizer 10 is mounted at the exit end, the
annular slit 3 is readily accessible for cleaning. For cleaning
purposes, a flame stabilizer 9 mounted at the inlet end may be made
dismountable, e.g., separate from the sleeve 11A of FIG. 4.
* * * * *