U.S. patent number 3,925,002 [Application Number 05/522,683] was granted by the patent office on 1975-12-09 for air preheating combustion apparatus.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Albert J. Verdouw.
United States Patent |
3,925,002 |
Verdouw |
December 9, 1975 |
Air preheating combustion apparatus
Abstract
A low emission combustion apparatus for a gas turbine engine
employs vaporization of liquid hydrocarbon fuel to produce a
mixture of vaporized fuel and primary or combustion air for a main
combustion apparatus. The primary air is brought to a high enough
temperature for vaporization of fuel by an air preheating combustor
in which a relatively small part of the total fuel is burned. The
preheating combustor operates at a relatively low temperature to
avoid production of nitrogen oxides, and thus may produce some
carbon monoxide. This, however, is burned in the main reaction
zone, which operates at a higher temperature. Prevaporization of
the fuel eliminates hot spots caused by fuel droplet combustion and
thus promotes clean combustion. The fuel vaporizer comprises
structure defining two concentric annular passages through which
the air flows with swirl and in which the fuel is laid on the outer
wall of each passage from a circumferential manifold. Fuel may be
supplied to one or both manifolds.
Inventors: |
Verdouw; Albert J.
(Indianapolis, IN) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
24081883 |
Appl.
No.: |
05/522,683 |
Filed: |
November 11, 1974 |
Current U.S.
Class: |
431/10; 60/746;
431/352; 60/737; 431/11 |
Current CPC
Class: |
F23R
3/30 (20130101); F23R 3/346 (20130101) |
Current International
Class: |
F23R
3/34 (20060101); F23R 3/30 (20060101); F23M
003/04 () |
Field of
Search: |
;431/10,352,353,215,11
;60/39.65,39.71 |
References Cited
[Referenced By]
U.S. Patent Documents
|
|
|
2621477 |
December 1952 |
Powter et al. |
3691762 |
September 1972 |
Ryberg et al. |
3859787 |
January 1975 |
Anderson et al. |
|
Primary Examiner: Favors; Edward G.
Attorney, Agent or Firm: Fitzpatrick; Paul
Claims
I claim:
1. A combustion apparatus for a gas turbine engine or the like
comprising, in combination, a housing adapted to receive air under
pressure and a combustion liner in the housing; the combustion
liner having an upstream end and a downstream outlet end and
defining, in flow sequence from the upstream end to the downstream
end, an air preheating combustor, a fuel vaporizer, a main reaction
zone, and a main dilution zone; the air preheating combustor
comprising a preheat reaction zone having means for admitting
preheat combustion air and fuel and a preheat dilution zone having
means for admitting dilution air and mixing the dilution air with
the combustion air from the preheat reaction zone to provide at
least substantially all combustion air for the main reaction zone,
in combination with means to proportion the fuel and air so as to
discharge a combustion products and air mixture from the preheating
combustor at approximately 600.degree. Celsius into the fuel
vaporizer; the fuel vaporizer comprising means defining a passage
leading from the preheating combustor to the main reaction zone,
and means for delivering fuel into the said passage for evaporation
and mixture with the gases flowing through the said passage; and
the main dilution zone defining entrances for dilution air
by-passing the preheating combustor.
2. A combustion apparatus for a gas turbine engine or the like
comprising, in combination, a housing adapted to receive air under
pressure and a combustion liner in the housing; the combustion
liner having an upstream end and a downstream outlet end and
defining, in flow sequence from the upstream end to the downstream
end, an air preheating combustor, a fuel vaporizer, a main reaction
zone, and a main dilution zone; the air preheating combustor
comprising a preheat reaction zone having means for admitting
preheat combustion air and fuel and a preheat dilution zone having
means for admitting dilution air and mixing the dilution air with
the combustion air from the preheat reaction zone to provide at
least substantially all combustion air for the main reaction zone,
in combination with means to proportion the fuel and air so as to
discharge a combustion products and air mixture from the preheating
combustor at approximately 600.degree. Celsius into the fuel
vaporizer; the fuel vaporizer comprising means defining a passage
leading from the preheating combustor to the main reaction zone and
means for delivering fuel into the said passage for evaporation and
mixture with the gases flowing through the said passage; the
preheat dilution zone diverging downstream and the fuel vaporizer
converging downstream to an outlet into the main reaction zone; the
main reaction zone diverging abruptly from the fuel vaporizer
outlet; and the main dilution zone defining entrances for dilution
air by-passing the preheating combustor.
3. A combustion apparatus for a gas turbine engine or the like
comprising, in combination, a housing adapted to receive air under
pressure and a combustion liner in the housing; the combustion
liner having an upstream end and a downstream outlet end and
defining, in flow sequence from the upstream end to the downstream
end, an air preheating combustor, a wall film fuel vaporizer, a
main reaction zone, and a main dilution zone; the air preheating
combustor comprising a preheat reaction zone having means for
admitting preheat combustion air and fuel and a preheat dilution
zone having means for admitting dilution air and mixing the
dilution air with the combustion air from the preheat reaction zone
to provide all combustion air for the main reaction zone, in
combination with means to proportion the fuel and air so as to
discharge a combustion products and air mixture from the preheating
combustor at approximately 600.degree. Celsius into the fuel
vaporizer; the fuel vaporizer comprising wall means defining an
annular passage leading from the preheating combustor to the main
reaction zone, means for imparting swirl to the gases flowing
through the said passage, means for delivering fuel to the outer
wall of the said passage for evaporation and mixture with the gases
flowing through the said passage.
4. A combustion apparatus for a gas turbine engine or the like
comprising, in combination, a housing adapted to receive air under
pressure and a combustion liner in the housing; the combustion
liner having an upstream end and a downstream outlet end and
defining, in flow sequence from the upstream end to the downstream
end, an air preheating combustor, a wall film fuel vaporizer, a
main reaction zone, and a main dilution zone; the air preheating
combustor comprising a preheat reaction zone having means for
admitting preheat combustion air and fuel and a preheat dilution
zone having means for admitting dilution air and mixing the
dilution air with the combustion air from the preheat reaction zone
to provide all combustion air for the main reaction zone, in
combination with means to proportion the fuel and air so as to
discharge a combustion products and air mixture from the preheating
combustor at approximately 600.degree. Celsius into the fuel
vaporizer; the fuel vaporizer comprising wall means defining an
annular passage leading from the preheating combustor to the main
reaction zone, means for imparting swirl to the gases flowing
through the said passage, means for delivering fuel to the outer
wall of the said passage for evaporation and mixture with the gases
flowing through the said passage, the preheat dilution zone
diverging downstream and the fuel vaporizer converging downstream
to an outlet into the main reaction zone; and the main reaction
zone diverging abruptly from the fuel vaporizer outlet.
5. A combustion apparatus for a gas turbine engine or the like
comprising, in combination, a housing adapted to receive air under
pressure and a combustion liner in the housing; the combustion
liner having an upstream end and a downstream outlet end and
defining, in flow sequence from the upstream end to the downstream
end, an air preheating combustor, a wall film fuel vaporizer, a
main reaction zone, and a main dilution zone; the air preheating
combustor comprising a preheat reaction zone having means for
admitting preheat combustion air and fuel and a preheat dilution
zone having means for admitting dilution air and mixing the
dilution air with the combustion air from the preheat reaction zone
to provide all combustion air for the main reaction zone, in
combination with means to proportion the fuel and air so as to
discharge a combustion products and air mixture from the preheating
combustor at approximately 600.degree. Celsius into the fuel
vaporizer; the fuel vaporizer comprising wall means defining outer
and inner annular passages leading in parallel from the preheating
combustor to the main reaction zone, means for imparting swirl to
the gases flowing through the said passages, means for delivering
fuel to the outer walls of the said passages for evaporation and
mixture with the gases flowing through the said passages, and means
for routing fuel alternatively to one or both of said passages.
6. A combustion apparatus for a gas turbine engine or the like
comprising, in combination, a housing adapted to receive air under
pressure and a combustion liner in the housing; the combustion
liner having an upstream end and a downstream outlet end and
defining, in flow sequence from the upstream end to the downstream
end, an air preheating combustor, a wall film fuel vaporizer, a
main reaction zone, and a main dilution zone; the air preheating
combustor comprising a preheat reaction zone having means for
admitting preheat combustion air and fuel and a preheat dilution
zone having means for admitting dilution air and mixing the
dilution air with the combustion air from the preheat reaction zone
to provide all combustion air for the main reaction zone, in
combination with means to proportion the fuel and air so as to
discharge a combustion products and air mixture from the preheating
combustor at approximately 600.degree. Celsius into the fuel
vaporizer; the fuel vaporizer comprising wall means defining outer
and inner annular passages leading in parallel from the preheating
combustor to the main reaction zone, means for imparting swirl to
the gases flowing through the said passages, means for delivering
fuel to the outer walls of the said passages for evaporation and
mixture with the gases flowing through the said passages, and means
for routing fuel alternatively to one or both of said passages; the
preheat dilution zone diverging downstream and the fuel vaporizer
converging downstream to an outlet into the main reaction zone; the
main reaction zone diverging abruptly from the fuel vaporizer
outlet.
7. A combustion apparatus for a gas turbine engine or the like
comprising, in combination, a housing adapted to receive air under
pressure and a combustion liner in the housing; the combustion
liner having an upstream end and a downstream outlet end and
defining, in flow sequence from the upstream end to the downstream
end, an air preheating combustor, a wall film fuel vaporizer, a
main reaction zone, and a main dilution zone; the air preheating
combustor comprising a preheat reaction zone having means for
admitting preheat combustion air and fuel and a preheat dilution
zone having means for admitting dilution air and mixing the
dilution air with the combustion air from the preheat reaction zone
to provide all combustion air for the main reaction zone, in
combination with means to proportion the fuel and air so as to
discharge a combustion products and air mixture from the preheating
combustor at approximately 600.degree. Celsius into the fuel
vaporizer; the fuel vaporizer comprising wall means defining outer
and inner annular passages leading in parallel from the preheating
combustor to the main reaction zone, means for imparting swirl to
the gases flowing through the said passages, means for delivering
fuel to the outer walls of the said passages for evaporation and
mixture with the gases flowing through the said passages, and means
for routing fuel alternatively to one or both of said passages; the
preheat dilution zone diverging downstream and the fuel vaporizer
converging downstream to an outlet into the main reaction zone; the
main reaction zone diverging abruptly from the fuel vaporizer
outlet; means for convectively cooling the liner wall portion
bounding the reaction zone by air flowing to the main dilution
zone; and the main dilution zone defining entrances for dilution
air by-passing the preheating combustor.
8. A method of burning liquid hydrocarbon fuel in compressed
combustion air comprising burning and mixing in the air a portion
of the fuel sufficient to produce a mixture of air and combustion
products at about 600.degree. Celsius in a first zone; flowing the
said mixture into a second zone and evaporating the remainder of
the fuel in the mixture in the second zone; flowing the resulting
mixture of air, combustion products, and fuel into a third zone;
and completing combustion of the fuel in the air in the said
resulting mixture in the third zone.
9. A method of burning liquid hydrocarbon fuel in compressed
combustion air to provide motive fluid for an engine comprising
burning and mixing in the air a portion of the fuel sufficient to
produce a mixture of air and combustion products at about
600.degree. Celsius in a first zone; flowing the said mixture into
a second zone and evaporating the remainder of the fuel in the
mixture in the second zone; flowing the resulting mixture of air,
combustion products, and fuel into a third zone; and completing
combustion of the fuel in the air in the said resulting mixture in
the third zone; flowing the resulting product into a fourth zone;
and mixing dilution air with the said resulting product in the
fourth zone to provide motive fluid for an engine.
Description
My invention is directed to combustion apparatus of a type suitable
for use in gas turbine engines and particularly to a combustion
apparatus employing combustion of a minor part of the fuel in a
precombustor which brings all of the primary or combustion air for
the main combustor to a temperature high enough for successful
vaporization of fuel delivered into it within a fuel vaporizer
through which the primary air proceeds to a main reaction zone
where the major part of the fuel is burned.
The combustion apparatus according to the invention is particularly
intended for use with engines of a non-regenerative type in which
the combustion air is at whatever temperature results from the
compression of the air, without additional heating in a regenerator
or recuperator by exhaust gases.
It is well known that a great deal of effort has been put into
devising combustion apparatus for power plants of all sorts to
produce exhaust gases with extremely low concentrations of products
considered to be inimical to public health such as smoke, unburned
hydrocarbons, carbon monoxide, and oxides of nitrogen. One
promising avenue toward such clean combustion lies in vaporization
of the liquid hydrocarbon fuel and mixture of the vapor with the
combustion air prior to the actual combustion of the fuel in the
air. This is relatively easy in an engine of a regenerative type in
which the air entering the combustion apparatus is ordinarily at
about 500.degree. to 600.degree.C. However, my invention is
directed to cleaning the exhaust of a known type of
non-regenerative single-shaft gas turbine engine, the Allison Model
501 engine. This engine, in various models, is used for aircraft
propulsion, in stationary power plants for gas pumping and
generation of electricity, and for propulsion of boats. A typical
Model 501 engine has a power output of 4680 shaft horsepower under
static sea level conditions and 1084.degree.C. turbine inlet
temperature. The engine has a compression ratio of 9.2 to 1.
Fuel is burned in six combustion liners arranged in parallel
relation in an annular combustion air space to which air is
delivered by the compressor. The general arrangement of combustion
liners in the engine is as shown in McDowall et al. U.S. Pat. No.
2,729,938, Jan. 10, 1956, and Tomlinson U.S. Pat. No. 3,064,424,
Nov. 20, 1962. Rated air flow is 14.65 kilograms per second or
about 2.45 kilograms per second through each combustion liner.
According to my invention, the relatively low temperature
compressor discharge air supplied to the combustion apparatus of
the engine is heated to about 500.degree. to 650.degree.C. in an
air preheating combustor associated with each main combustion
liner, the air so heated flows through fuel vaporization apparatus
in which fuel is vaporized and mixed with the combustion air so
supplied, and the resulting mixture is burned in a main combustion
zone of the apparatus. Thereafter, it flows through the dilution
zone of the combustion apparatus where additional unheated
compressed air is mixed with the combustion products to bring the
turbine motive fluid to the desired temperature.
While the invention is described here in terms of application to a
particular engine, it will be obvious that the principles of the
invention may be applied to engines of various sizes and pressure
ratios, and with other different parameters.
The principal objects of my invention are to provide a clean
burning combustion apparatus, to provide a combustion apparatus in
which air for fuel vaporization is preheated prior to vaporization
of the fuel and entry of the resulting mixture into a main reaction
zone; to provide improved fuel vaporization means for a combustion
apparatus; and to provide a combustion apparatus which is clean
burning over a relatively wide range of power outputs.
The nature of my invention and its advantages will be apparent to
those skilled in the art from the succeeding detailed description
of the preferred embodiment of the invention, the accompanying
drawings thereof, and the appended claims.
Referring to the drawings,
FIG. 1 is a schematic illustration of a combustion apparatus
incorporating a combustion liner according to my invention.
FIG. 2 is an enlarged fragmentary sectional view taken on the plane
indicated by the line 2--2 in FIG. 3.
FIG. 3 is a longitudinal sectional view of the combustion
liner.
FIG. 4 is an enlargement of a portion of FIG. 3.
Referring first to FIG. 1, a combustion liner 2 according to the
invention is mounted within a housing or combustion outer case 3. A
compressor 4 delivers air under pressure into a space 6 defined
between the housing 3 and the exterior of the combustion liner 2.
Fuel is supplied to the combustion liner through a fuel line 7
connected to a fuel nozzle 8 which delivers fuel into a preheating
combustor 10.
Additional fuel is supplied through lines 11 and 12 to a fuel
vaporizer 14. The combustion products from the preheating combustor
10 flow through the vaporizer 14 into main combustion apparatus 15
defined by the downstream portion of the liner 2. The combustion
products from the main combustion apparatus are discharged through
an outlet 16 and through suitable transition ducting (not
illustrated) into the turbine of the gas turbine engine, which
drives the compressor 4.
Referring now to FIG. 3, the fuel atomizing nozzle 8 enters the
upstream end of the preheating combustor 10 where it is surrounded
by an air inlet swirler 18 which preferably is a part of the fuel
nozzle assembly. The preheating combustor 10 is enclosed by a wall
of circular cross section defining a dome 19 at the upstream end, a
reaction zone side wall 20, and a diverging dilution and outlet
section 22. The fuel vaporizer 14 begins at the downstream end of
wall section 22. It is enclosed by a cylindrical wall portion 23
and a converging downstream wall portion 24 which ends at the
beginning of the main combustion apparatus 15. This combustion
apparatus is enclosed by an annular forward wall 26 and a side wall
portion 27 which provides the outer wall of the main reaction zone
28 in which combustion of the fuel is completed. The reaction zone
is connected through a slightly converging wall section 30 to a
liner wall section 31 which encloses the dilution zone 32 and
terminates at the outlet 16. The combustion liner may be supported
at nozzle 8 by an outer swirler 34 mounted on the swirler 18 and by
suitable supports at the discharge end of the liner, as is common.
Suitable ignition apparatus and cross connections between
combustion liners (not illustrated) may be provided generally as
shown in the McDowall et al patent cited above.
The preheating combustor 10 is generally similar to conventional
gas turbine combustion liners except for the fact that it is
proportioned to operate on a low overall fuel-air ratio so as to
discharge combustion products at about 600.degree.C., much below
the inlet temperature of a gas turbine. In addition to the
combustion air entering through swirlers 18 and 34, combustion air
enters through a ring of six ports 35 distributed around the
forward portion of wall 20. I prefer that about 40% of preheater
combustion air enter through the swirlers and 60% through ports 35.
Combustion takes place in the usual manner, and dilution air to mix
with the combustion products is admitted through six ports 36 near
the downstream end of wall section 20 and six ports 38 in the
upstream end of diverging wall section 22. Air entering radially
through dilution air ports 36 and 38 mixes with the combustion
products from burning of the fuel discharged by nozzle 8. The
combustion products then are discharged through an annular outlet
39 into the fuel vaporizer 14.
The fuel vaporizer includes a wall 40 defining with the outer wall
portions 23 and 24 an annular passage 42 of approximately constant
area. Wall 40 is supported from wall 23 by a ring of swirl vanes 43
which swirl the air flowing into the passage 42. Vanes 43 terminate
at a sheet metal ring 44 abutting the inner surface of wall 23. The
downstream end of wall 40 is welded to a wall 46 which defines the
outer boundary of a second annular passage 47 of approximately
constant area. A ring 48 is fixed to the upstream ends of walls 40
and 46. The inner boundary of passage 47 is defined by a converging
wall 51 supported from wall 46 by a swirler 52. Swirler 52 (see
also FIG. 2) comprises an annular cascade of vanes 54 extending
between an outer ring 55 abutting wall 46 and an inner ring 56
abutting wall 51.
Wall 51 forms part of a centerbody 58 which, in addition to the
side wall 51, has a forward wall 59 and a downstream end wall 60.
The structure providing the two passages 42 and 47 through the fuel
vaporizer has now been described.
Introduction of fuel is accomplished from a manifold 62 on the
outer surface of wall section 23 and a manifold 63 on the outer
surface of wall 46. These are connected to a source of fuel through
the fuel lines 11 and 12 already referred to. Each manifold
delivers fuel to the inner surface of the wall on which it is
mounted through a ring of small holes which discharge onto the
inner surface of the wall just downstream of the ring 44 or 55,
respectively. Eighteen approximately tangential fuel holes 64
evenly spaced around the axis of the apparatus are machined through
the wall 46 and 26 similar holes are machined through the wall 23.
Fuel thus discharged onto the inner surfaces of the walls is
contacted by the hot air coming through the swirler immediately
upstream from the fuel delivery point, evaporated, and mixed with
the air. It is then discharged through the downstream ends of the
coaxial passages 42 and 47. The two streams merge in the outlet
from the fuel vaporizer and discharge into the reaction zone 28
through the central opening 66 in wall 26. It should be noted that
this opening is slightly smaller than the diameter of the discharge
end of the vaporizer so that the innermost portion of the wall
serves as a flow dam to promote turbulence and mixing. Due to the
swirl around the liner axis, the fuel-air mixture tends to
recirculate in a generally toroidal pattern in the reaction zone,
and the fuel burns after being lit off by any suitable igniter.
No combustion air is added in the reaction zone. The reaction zone
wall 27 is cooled by convection by structure of a type previously
known. Air to cool the side wall 27 flows between the outer surface
of this wall and the inner surface of a sleeve 67 which is
supported adjacent the outer surface of wall 27 by axially
extending strips 68 spaced circumferentially around the wall. As
shown more clearly in FIG. 4, a passage 70 for convection cooling
air is defined between the walls 27 and 67. This is closed at the
downstream end by a ring 71 disposed between the walls, and the
cooling air is discharged into the combustion liner through a ring
of holes 72. A baffle 74 fixed to the wall 27 deflects this air
downstream along the inner surface of the wall portion 30 for film
cooling of this wall.
Dilution air is admitted to the dilution zone 32 through a ring of
eight secondary air ports 76. The resulting mixture with the
combustion products from the main combustion zone constitutes the
motive fluid developed by the combustor.
It may be desirable to indicate typical dimensions of a combustion
liner such as that shown. FIG. 3 is a drawing to scale of a liner
approximately 15 centimeters in diameter. Primary ports 35 are
approximately 13 millimeters in diameter, and ports 36 and 38 are
approximately 20 millimeters in diameter. Fuel inlet ports 64 and
the corresponding ports through wall 23 are about 4 millimeters in
diameter. The fuel ports should be large enough so that the fuel
may be admitted without any considerable pressure drop or without
going in at high velocity.
The fabrication of the combustion apparatus may follow usual
techniques with the parts being formed to shape and welded or
brazed together.
Considering now the preferred mode of operation of the combustion
apparatus and referring again to FIG. 1, we discuss specifically an
engine operating normally at constant speed and air flow, with fuel
flow varied to vary engine power output through variation of
turbine inlet temperature. Fuel for the pilot or preheater fuel
nozzle 8 and for the main fuel manifolds 62 and 63 may be drawn
from a fuel supply line 78 by a pump 79 which may be driven by the
engine. The pump delivers fuel through a fuel control 80 to an
engine metered fuel line 82. Fuel control 80 determines the rate of
supply of fuel to the engine and returns excess fuel through a
return line 83. Metered fuel line 82 branches into the lines 7, 11,
and 12 previously referred to. Division of flow between the several
lines is suitably controlled. As illustrated, a valve 84 controls
flow through line 7, a valve 85 controls flow through line 11, and
a valve 86 controls flow through line 12. Fuel is supplied
constantly to the pilot or preheat fuel nozzle 8. Valve 84 may be a
flow-limiting valve limiting flow to about 30% of maximum power
fuel flow. At idle (substantially zero shaft power) and power
levels above that, fuel is supplied to the fuel manifold 62 through
valve 85. This may be a valve responsive to the pressure ahead of
valve 84 which opens at a predetermined value of this pressure and
continues to open as flow increases through line 82 with increasing
engine power level. The manifold 63 is fueled only at higher power
levels of the engine. This flow may be controlled by a valve 86
which opens in response to increased fuel pressure level at higher
fuel flow levels.
Any other suitable arrangement for sequencing or controlling flow
to the manifolds may be used. Many such are known in connection
with duplex fuel nozzles or with zone burning arrangements in jet
engine afterburners, for example. My invention is not concerned
with the details of valving or fuel supply, which may be as
required to suit the operating environment of the engine. Valves
such as 84, 85, and 86 may control flow to a number of combustion
liners in parallel.
In the operation of the combustor, it is contemplated that about
20% of full power fuel will be injected through nozzle 8 so as to
preheat the air delivered to the vaporizer to about 600.degree.C.
Since a rather large amount of air is admitted through the ports
35, 36, and 38, the resulting combustion products are cool and
air-rich. The combustion zone in the preheating combustor is
conventional and will have hot spots, fuel droplets, and the usual
deficiencies of conventional combustors. However, the NO.sub.x
contribution from this zone is low due to the small amount of total
fuel (20%) admitted in the preheat zone. The low combustion
temperature and short residence time may cause some exhaust of
carbon monoxide or unburned hydrocarbons from the preheating
combustor, but these are duly oxidized in the main combustion zone
28 where temperature will rise to about 1400.degree. to
1650.degree.C. Because of combustion with a premixed mass may
vaporized fuel and air, there is clean combustion, avoiding hot
spots, in the main reaction zone, minimizing combination of oxygen
with nitrogen. The preheating combustor does not require any
variable geometry; that is, means for varying the air flow split.
If found desirable, means such as are well known maay be provided
to throttle flow through the main dilution air ports 76 to vary the
ratio of primary to secondary air in the main combustion
apparatus.
The structure, mode of operation, and advantages of combustion
apparatus according to the invention should be apparent to those
skilled in the art from the foregoing description.
The detailed description of the preferred embodiment of the
invention for the purpose of explaining the principles thereof is
not to be considered as limiting or restricting the invention,
since many modifications may be made by the exercise of skill in
the art.
* * * * *