CA2876470C

CA2876470C - Burner system

Info

Publication number: CA2876470C
Application number: CA2876470A
Authority: CA
Inventors: Darsell Karringten
Original assignee: ABSOLUTE COMBUSTION INTERNATIONAL Inc
Current assignee: ABSOLUTE COMBUSTION INTERNATIONAL Inc
Priority date: 2014-12-31
Filing date: 2014-12-31
Publication date: 2017-11-07
Anticipated expiration: 2034-12-31
Also published as: CA2876470A1

Abstract

A burner system comprises a main body having a fuel conveying passageway having in seriatim and in fluid communication one with the next, a fuel-receiving inlet, a main passageway, and a fuel-emitting outlet, and an air conveying passageway having in seriatim and in fluid communication one with the next, an air-receiving inlet, an intake air-flow chamber, at least one air-flow opening, turbulent air-flow chamber, and an air-emitting outlet. The air-emitting outlet and the fuel-emitting outlet are positioned and oriented to permit delivery of air and fuel, respectively, to a common destination for subsequent combustion. The ratio of the minimum cross-sectional area of the intake air-flow chamber to the minimum cross-sectional area of the turbulent air-flow chamber is between about 1:0.8 and 1:1.2.

Description

BURNER SYSTEM
FIELD OF THE INVENTION
[0001] The present invention relates to burners, and more particularly to burners that mix air or oxygen with a gaseous or evaporated fuel.
BACKGROUND OF THE INVENTION

[0002]
Many prior art burner systems react gaseous fuel or liquid fuel with air or oxygen to produce a heat output. It is highly desirable to maximize the heat output either in terms of a high temperature, maximized combustion efficiency, and minimized pollutants.

[0003] The closest know prior art is United States Patent 6,494,710, issued December 17, 2002, to Kim et al, which discloses a Method And Apparatus For Increasing Incineration Capacity Of The Ground Flares By Using Principle Of Tornado. The apparatus for incinerating waste gas comprises a plurality of combustion nozzles arranged in periphery of an inner tube for discharging the waste gas into the combustion chamber. The combustion nozzles are disposed within an incineration to for shielding the flare smoke, the flame light and the noise being generated. The incineration tube has a plurality of air inlets at its lower periphery. The plurality of air inlets are in fluid communication with an outer tube for introducing the swirled air into the flame generation side of a plurality of combustion nozzles, for providing the swirl force to be combusted gas which is elevated within the inner tube.
The outer tube is provided with several air inlet passages tangentially formed in communication with the incineration tube.

[0004] It is an object of the present invention to provide a burner system that produces a high temperature heat output.

[0005] It is an object of the present invention to provide a burner system that has a heat output realized by high combustion efficiency.

[0006] It is an object of the present invention to provide a burner system that has a heat output containing minimized pollutants.

SUMMARY OF THE INVENTION

[0007] In accordance with one aspect of the present invention there is disclosed a novel burner system comprising a main body having a fuel conveying passageway having in seriatim and in fluid communication one with the next, a fuel-receiving inlet, a main passageway, and a fuel-emitting outlet, and an air conveying passageway having in seriatim and in fluid communication one with the next, an air-receiving inlet, an intake air-flow chamber, at least one air-flow opening, turbulent air-flow chamber, and an air-emitting outlet. The air-emitting outlet and the fuel-emitting outlet are positioned and oriented to permit delivery of air and fuel, respectively, to a common destination for subsequent combustion. The ratio of the minimum cross-sectional area of the intake air-flow chamber to the minimum cross-sectional area of the turbulent air-flow chamber is between about 1:0.8 and 1:1.2.

[0008] In accordance with one aspect of the present invention there is disclosed a novel burner system comprising a fuel conveying structure having a fuel conveying passageway. The fuel conveying passageway has in seriatim and in fluid communication one with the next, a fuel-receiving inlet, a main passageway, and a fuel-emitting outlet. An air conveying structure has an air conveying passageway. The air conveying passageway has in seriatim and in fluid communication one with the next, an air-receiving inlet, an intake air-flow chamber, at least one air-flow opening, a turbulent air-flow chamber, and an air-emitting outlet.
The air-emitting outlet and the fuel-emitting outlet are positioned and oriented to permit delivery of air and fuel, respectively, to a common destination for subsequent combustion.
The ratio of the minimum cross-sectional area of the intake air-flow chamber to the minimum cross-sectional area of the turbulent air-flow chamber is between about 1:0.8 and 1:1.2.

[0009] In accordance with one aspect of the present invention there is disclosed a novel burner system comprising a fuel conveying structure having a fuel conveying passageway. The fuel conveying passageway has in seriatim and in fluid communication one with the next, a fuel-receiving inlet, a main passageway, and a fuel-emitting outlet. An air-flow disruption structure has in seriatim and in fluid communication one with the next, a first air-receiving inlet, an intake air-flow chamber, at least one air-flow opening, a turbulent air-flow chamber, and an air-transfer egress. An air-flow delivery structure has in seriatim and in fluid communication one with the next, an air-transfer ingress, and an air-emitting outlet, and wherein the air-transfer ingress is in fluid communication with the air-transfer egress of the air-flow disruption structure to receive air flow therefrom. The air-emitting outlet and the fuel-emitting outlet are positioned and oriented to permit delivery of air and fuel, respectively, to a common destination for subsequent combustion. The ratio of the minimum cross-sectional area of the intake air-flow chamber to the minimum cross-sectional area of the turbulent air-flow chamber is between about 1:0.8 and 1:1.2.

[00010] In accordance with one aspect of the present invention there is disclosed a novel air-flow disruption structure for use in a burner system. The air-flow disruption structure comprises in seriatim and in fluid communication one with the next, a first air-receiving inlet, an intake air-flow chamber, at least one air-flow opening, a turbulent air-flow chamber, and an air-transfer egress. The ratio of the minimum cross-sectional area of the intake air-flow chamber to the minimum cross-sectional area of the turbulent air-flow chamber is between about 1:0.8 and 1:1.2.

[00011] Other advantages, features and characteristics of the present invention, as well as methods of operation and functions of the related elements of the structure, and the combination of parts and economies of manufacture, will become more apparent upon consideration of the following detailed description and the appended claims with reference to the accompanying drawings, the latter of which is briefly described herein below.
BRIEF DESCRIPTION OF THE DRAWINGS

[00012] The novel features which are believed to be characteristic of the burner system according to the present invention, as to its structure, organization, use and method of operation, together with further objectives and advantages thereof, will be better understood from the following drawings in which a presently illustrated embodiment of the invention will now be illustrated by way of example. It is expressly understood, however, that the drawings are for the purpose of illustration and description only, and are not intended as a definition of the limits of the invention. In the accompanying drawings:

[00013] Figure 1 is a right side elevational view of the illustrated embodiment of the burner system according to the present invention;

[00014] Figure 2 is a front end view of the illustrated embodiment of the burner system of Figure 1;

[00015] Figure 3 is a back end view of the illustrated embodiment of the burner system of Figure 1;

[00016] Figure 4 is a cross-sectional view of the illustrated embodiment of the burner system of Figure 1, taken along section line 4-4 of Figure 1;

[00017] Figure 5A is a cross-sectional view of the illustrated embodiment of a back end portion of the burner system of Figure 1, taken along section line 5A-5A of Figure 2;

[00018] Figure 5B is a cross-sectional view of the illustrated embodiment of a back end portion of the burner system of Figure 1, taken along section line 5B-5B of Figure 2;

[00019] Figure 5C is a cross-sectional view of the illustrated embodiment of a back end portion of the burner system of Figure 1, taken along section line 5C-5C of Figure 2;

[00020] Figure 5D is a cross-sectional view of the illustrated embodiment of a back end portion of the burner system of Figure 1, taken along section line 5D-5D of Figure 2;

[00021] Figure 6 is a plan view of the rear housing of the illustrated embodiment of the burner system of Figure 1; and,

[00022] Figure 7 is a perspective view of the rear housing of the illustrated embodiment of the burner system of Figure 1.
DETAILED DESCRIPTION OF THE ILLUSTRATED EMBODIMENT

[00023] Reference will now be made to Figures 1 through 7, which show an illustrated embodiment of the burner system according to the present invention, as indicated by general reference numeral 100.

[00024] In brief, the illustrated embodiment of the burner system 100 comprises a main body 110 comprising a rear housing 120, a central housing 130, a front housing 140, an air conveying passageway 150 and a fuel conveying passageway 160. There is also a combustion chamber housing 170 having a narrower rearward combustion chamber housing 180 and a wider forward combustion chamber housing 190. The main body 110 generally houses the parts, and/or components, and/or elements of the present invention.

[00025] The main body 110 has a back end 111 and a front end 112, an outlet area 113 disposed immediately forwardly of the front end 112, and defines a longitudinal axis "L" extending between the front end 112 and the back end 111. It should be understood that although for some shapes of burner systems the determination of front end back end the back end might be somewhat arbitrary, the front end is generally defined as the flame is produced, and the back end is defined as the area where the air and the fuel have their inputs, and where the mixing of the air and the fuel possibly begins.

[00026] It should be understood that for the sake of convenience, the term air is used to describe air received from a pressurized or compressed source of air but that also oxygen from a pressurized or compressed source of oxygen could be used. If a source of air is used, the oxygen in the air is reacted with a fuel such as propane, natural gas, and so on. The nitrogen in the air is merely separated from the oxygen upon combustion. It is also contemplated that hydrogen could be used along with the oxygen.

[00027] As can be readily seen in Figure 4, the burner system 100 has the air conveying passageway 150. In the illustrated embodiment, the air conveying passageway 150 has, in seriatim and in fluid communication one with the next, a first air-receiving inlet 151a, an intake air-flow chamber 222, at least one air-flow opening 224, a turbulent air-flow chamber 230, a first air-flow channel 240a, and an air-emitting outlet 152. More specifically, the at least one air-flow opening 224 comprises a first air-flow opening 224a, a second air-flow opening 224b, a third air-flow opening 224c, and a fourth air-flow opening 224d, as will be described in greater deal subsequently.

[00028]
More specifically, there is at least one air-receiving inlet 151 in the main body 110, and in the illustrated embodiment, there is a first air-receiving inlet 151a and a second air-receiving inlet 151b in the main body 110, specifically in the rear housing 120 of the main body 110, provided in order to generally balance the air flow introduced into the intake air-flow chamber 222. The second air-receiving inlet 151b is similar to the first air-receiving inlet 151a in that it is in seriatim and in fluid communication with the intake air-flow chamber 222, the first air-flow opening 224a, the turbulent air-flow chamber 230, the first air-flow channel 240a, and the air-emitting outlet 152, in the same manner as described above for the first air-receiving inlet 151a.

[00029] The first air-receiving inlet 151a and the second air-receiving inlet 151b are each disposed at the back end 111 of the main body 110 of the burner system 100. The first air-receiving inlet 151a and the second air-receiving inlet 151b are spaced one hundred eighty degrees (180 ) apart around the longitudinal axis "L", in order to effectively maximize the subsequent mixing of air flow. The first air-receiving inlet 151a and the second air-receiving inlet 151b are each oriented generally along the longitudinal axis "L", as shown, but could alternatively be oriented at another angle. It is contemplated that there may also be additional air-receiving inlets appropriately located in the main body 110 to accommodate the need for additional air input.

[00030] It should also be noted that in an alternative embodiment, it is contemplated that there could be additional inlets for introducing a secondary type of fuel, such as hydrogen and even including the un-burnt emissions from other types of burner systems, and the like.

[00031] The main body 110 also has a fuel nozzle-receiving throughpassage 118 that is generally centrally disposed in the main body 110 and is oriented along longitudinal axis "L". The fuel nozzle-receiving throughpassage 118 is generally centrally disposed in the main body 110 and is oriented along the longitudinal axis "L".

[00032] As can be best seen in Figures 4 through 7, there is also a chamber-separating structure 226 that in the illustrated embodiment comprises a perforated metal wall that is preferably substantially annular in shape. As illustrated, the chamber-separating structure 226 is a unitary wall that is preferably substantially annular. The wall 226 acts as a chamber-separating structure that separates the intake air-flow chamber 222 and the turbulent air-flow chamber 230, and that separates the intake air-flow chamber 222 and the turbulent air-flow chamber 230 one from the other, and defines the first air-flow opening 224a, the second air-flow opening 224b, the third air-flow opening 224c, and the fourth air-flow opening 224d. The first air-flow opening 224a, the second air-flow opening 224b, the third air-flow opening 224c and the fourth air-flow opening 224d are disposed in substantially equally spaced relation around the substantially annular wall 226.

[00033] Preferably, the intake air-flow chamber 222 is substantially annular and the turbulent air-flow chamber 230 is substantially annular, and the intake air-flow chamber 222 is disposed in surrounding relation around the turbulent air-flow chamber 230. The intake air-flow chamber 222 and the turbulent air-flow chamber 230 are substantially concentric with each other.
Also, the fuel conveying passageway 160 extends through the substantially annular intake air-flow chamber 222 and the substantially annular turbulent air-flow chamber 230.

[00034]
Reference will now be made to Figures 5A through 7, which show the first air-flow opening 224a, the second air-flow opening 224b, the third air-flow opening 224c, and the fourth air-flow opening 224d.
Each of the first air-flow opening 224a, second air-flow opening 224b, the third air-flow opening 224c, and the fourth air-flow opening 224d is similar in nature one to the other in that each is in seriatim and in fluid communication with the first air-receiving inlet 151a, the intake air-flow chamber 222, the turbulent air-flow chamber 230, the first air-flow channel 240a, and the air-emitting outlet 152, in the same manner as described above for the first air-flow opening 224a.

[00035]
Preferably, each of the second air-flow opening 224b, the third air-flow opening 224c and the fourth air-flow opening 224d, has a smaller minimum cross-sectional area than the first air-flow opening 224a. More specifically, the ratio of the minimum cross-sectional area "B" of the first air-flow opening 224a to the minimum cross-sectional area "D" of the second air-flow opening 224b to the minimum cross-sectional area "E" of the third air-flow opening 224c to the minimum cross-sectional area "F" of the fourth air-flow opening 224d is about 1.4:0.6:1.0:0.4.

[00036] A
source of air flow 104 is connected in air delivery relation to the air-receiving inlet 151 of the air conveying passageway 150. More specifically, the source of air flow 104 is connected in air delivery relation to the first air-receiving inlet 151a via a first connecting hose 153a and is connected in air delivery relation to the second air-receiving inlet 151b via a second connecting hose 153b. It should be noted that in the illustrated embodiment, the source of air flow 104 is the only source of air flow. Alternatively, the source of air flow 104 could be the primary source of air flow along with a secondary source of air flow at a suitable pressure.

[00037] The fuel conveying passageway 160 has in seriatim and in fluid communication one with the next, a fuel-receiving inlet 161, a main passageway 164, and a fuel-emitting outlet 162 for delivering fuel to the outlet area 113 of the main body 110, by passing a flow of fuel from the fuel-receiving inlet 161 through the main passageway 164 to the fuel-emitting outlet 162. In the illustrated embodiment, the fuel conveying passageway 160 is disposed within a substantially straight fuel nozzle 200 that resides within the fuel nozzle-receiving throughpassage 118.

[00038] The fuel conveying passageway 160 extends from its fuel flow inlet 161 at the back end 201 of the fuel nozzle 200 to the fuel flow outlet 162 at the front end 202 of the fuel nozzle 200, and is substantially straight except for the forward portion at the front end 202 of the fuel nozzle 200 where the fuel conveying passageway 160 furcates into six separate passageways 161a, 161b, 161c, 161d, 161e, 161f each having its own fuel flow outlet 161a, 161b, 161c, 161d, 161e, 161f.

[00039] In the illustrated embodiment, the fuel-emitting outlet 162 actually comprises a first fuel-emitting outlet 162a, a second fuel-emitting outlet 162b, a third fuel-emitting outlet 162c, a fourth fuel-emitting outlet 162d, a fifth fuel-emitting outlet 162e, and a sixth fuel-emitting outlet 162f. The first fuel-emitting outlet 162a, the second fuel-emitting outlet 162b, the third fuel-emitting outlet 162c, the fourth fuel-emitting outlet 162d, the fifth fuel-emitting outlet 162e, and the sixth fuel-emitting outlet 162f are each oriented at an angle of about ten degrees (10 ) with respect to the longitudinal axis "L", which has been found to disperse the fuel fully for ready evaporation by the air. Any other suitable angle may alternatively be used.

[00040]
Further, a source of gaseous fuel flow 106 is connected in fuel delivery relation to the fuel flow inlet 161 of the fuel conveying passageway 160 via a connecting hose 163. It should be noted that in the illustrated embodiment, the source of gaseous fuel flow 106 is the only source of fuel flow. Alternatively, the source of fuel flow could be the primary source of fuel flow along with a secondary source of fuel flow at a suitable pressure.

[00041] The fuel nozzle 200 also comprises an external rear portion 203 disposed at the back end 201 of the fuel nozzle 200.

The external rear portion 203 projects rearwardly from the back end 111 of the main body 110 of the burner system 100.
Preferably, the external rear portion 203 of the fuel nozzle 200 is threaded to accept a co-operating nut 204 thereon, to thereby retain the fuel nozzle 200 in place in the main body 110.

[00042] As can be readily seen in Figure 4, a portion of the air conveying passageway 150 disposed immediately rearwardly of the combustion chamber housing 170 comprises a first air flow channel 240a disposed on the fuel nozzle 200, and more specifically comprises five substantially parallel air flow channels each disposed on the fuel nozzle 200, namely a first air flow channel 240a, a second air flow channel 240b, a third air flow channel 240c, a fourth air flow channel 240d, and a fifth air flow channel 240e. The first, second, third, fourth, and fifth air flow channels 240a-e are in fluid communication and in seriatim with the air flow inlet 151, the intake air flow chamber 222, the first air flow opening 224a, the turbulent air flow chamber 230, and the air transfer egress 232.
Further, the first air flow channel 240a, the second air flow channel 240b, the third air flow channel 240c, the fourth air flow channel 240d, and the fifth air flow channel 240e terminate in a first air flow outlet 152a, a second air flow outlet 152b, a third air flow outlet 152c, a fourth air flow outlet 152d, and a fifth air flow outlet 152e, respectively, which together form the overall air flow outlet 152 of the air conveying passageway 150. It has been found that it is preferable to have a purality of air-flow channels for the purpose of even air flow and distribution. Any suitable number of air-flow channels could be used depending on the specific application of the burner system 100, the size of the burner system 100 and the fuel nozzle 200, and so on. Various fuel nozzles according to the present invention have been tried, including from two air-flow channels on up. It has been found that each specific number of air-flow channels might have its own advantages and disadvantages.

[00043]
Each of the first, second, third, fourth and fifth air-flow channels 240a, 240b, 240c, 240d, 240e has an inlet 241, and an outlet 242 disposed adjacent the fuel-emitting outlet 162 for delivering air to the air-and-fuel combustion chamber 174 of the burner system 100. Substantially all of the first air-flow channel 240a, the second air-flow channel 240b, the third air-flow channel 240c, the fourth air-flow channel 240d, and the fifth air-flow channel 240e are oriented obliquely to the longitudinal axis "L".
Even more specifically, each of the first air-flow channel 240a, the second air-flow channel 240b, the third air-flow channel 240c, the fourth air-flow channel 240d, and the fifth air-flow channel 240e is helically shaped.
Each of the plurality of helically shaped air-flow channels 240 is substantially parallel to adjacent helically shaped air-flow channels 240. The helically shaped air-flow channels 240 are preferably disposed on the exterior of the fuel nozzle 200. As can be readily seen in the figures, due to the helical shape of the five air flow channels 240a-240e, the portion of each of the first air-flow channel 240a, the second air-flow channel 240b, the third air-flow channel 240c, the fourth air-flow channel 240d, and the fifth air-flow channel 240e adjacent the outlet 152 of each of the air-flow channels 240a-240d, at the outlet area 112, is oriented obliquely to the longitudinal axis "L".

[00044] The combustion chamber housing 170, which is best seen in Figure 4, is preferably elongate and substantially cylindrical, and defines a generally central longitudinal axis "L", extends between a back end 171 and a heat producing front end 172, defines a combustion chamber 174, and comprises a narrower rearward combustion chamber housing 180 with a back end 181 and a front end 182, and a wider forward combustion chamber housing 190 with a back end 191 and a front end 192. The combustion chamber housing 170 is connected at its back end 171 to the main body 110 of the burner system 100 at the outlet area 113 such that the destination for subsequent combustion 114 is at or adjacent the outlet area 113 and is disposed within the combustion chamber 174. The front end 192 of the wider forward combustion chamber housing 190 is disposed at the opposite other end of the main body 110, as are the first air-receiving inlet 151a and the second air-receiving inlet 151b.

[00045] Except for the air-emitting outlet 152 and the fuel-emitting outlet 162, the combustion chamber 174 is substantially closed at the back end 171.
Preferably, as in the illustrated embodiment described herein, the heat producing front end 172 is fully open to permit the egress of hot air therefrom. The air-emitting outlet 152 and the fuel-emitting outlet 162 are positioned and oriented to permit delivery of air from the air-emitting outlet 152 and delivery of fuel from the fuel-emitting outlet 162 each to a destination, namely the combustion chamber 174 at the outlet area 113, for subsequent combustion generally within the combustion chamber 174.

[00046] The combustion chamber 174 has a narrower rearward chamber portion 184 and a wider forward chamber portion 194, with the hot air outlet 176 disposed at the front end 192 of the wider forward chamber portion 194. The narrower rearward combustion chamber housing 180 generally defines the narrower rearward chamber portion 184 and the wider forward combustion chamber housing 190 defines the wider forward chamber portion 194.

[00047] In the illustrated embodiment, the narrower rearward combustion chamber housing 180 comprises a forwardly extending portion of the front housing 140 of the main body 110 and has an air and fuel ingress 185 and a combustion egress 186. The section of the narrower rearward chamber portion 184 immediately forward of the air and fuel ingress 185 is where the air from the five air flow outlets 152a-152e and the fuel from the six fuel flow outlets 162a-162f combine together one with the other and combust. As is well known in the art, a flame or spark, or the like, is initially used to start the combustion of the fuel and air.
Subsequently, the heat from the combustion of the fuel and air is sufficient to keep the combustion ongoing.

[00048] A
protective rearward insulative cover 188 is securely attached by means of welding in surrounding relation over the narrower rearward combustion chamber housing 180 by two annular end flanges 189, which are themselves securely attached by means of welding to the narrower rearward combustion chamber housing 180. Alternatively, any other suitable means of attachment could be used. The narrower rearward combustion chamber housing 180, the protective rearward insulative cover 188 and the two annular end flanges 189 are made from a suitable heat resistant material.

[00049] An annular flange 187 is welded to the protective rearward insulative cover 188 to extend perpendicularly outward therefrom, to receive the wider forward combustion chamber housing 190 in secure relation thereon.

[00050]
Similarly, the wider forward combustion chamber housing 190 comprises a forwardly extending tube and has a combustion ingress 195 and the hot air outlet 176.

[00051] A
protective forward insulative cover 198 is securely attached by means of welding in surrounding relation over the wider forward combustion chamber housing 190 by an annular end flange 199 and a back end plate 197. The annular end flange 199 and a back end plate 197 are themselves securely attached by means of welding to the wider forward combustion chamber housing 190.
Alternatively, any other suitable means of attachment could be used. Together, the protective forward insulative cover 198, the protective forward insulative cover 198, the back end plate 197 and the annular end flange 199 form a front assembly 195 that is mounted onto the annular flange 187 by means of threaded fasteners (not shown). The protective forward insulative cover 198, the protective forward insulative cover 198, the back end plate 197 and the annular end flange 199 are made from a suitable heat resistant material.

[00052] It should also be noted that the five air flow outlets 152a-e are aimed into the combustion chamber 174 in an oblique direction with respect to the longitudinal axis "L" of the combustion chamber 174, to thereby deliver the flow of air from the air conveying passageway 150 into the air and fuel ingress 185 of the combustion chamber 170, thereby inducing at least a peripheral flow of air in the combustion chamber 170.

[00053] After a significant amount of experimentation over a considerable amount of time, it has unexpectedly been found that the present invention, namely the burner system 100, operates fully and properly, and with complete combustion including no discernable or measureable NOx emissions, using a source of gaseous fuel flow 106 that delivers fuel to the fuel flow inlet 161 of the fuel conveying passageway 160 at a very low gauge pressure, and a source of air flow 104 that delivers air to the air flow inlet 151 of the air conveying passageway 150 at a very low gauge pressure. Further, it has unexpectedly been found that complete combustion including no discernable or measureable NOx emissions, can be achieved using a source of air flow 104 that delivers air to the air flow inlet 151 of the air conveying passageway 150 at a gauge pressure less than the pressure at which the source of gaseous fuel flow 106 delivers fuel to the fuel flow inlet 161 of the fuel conveying passageway 160.

[00054] It has been found that numerous relationships between the parameters of various portions, segments, parts, components, and the like of the burner system 100, such as the various sizes and ratios of sizes of the various portions, segments, parts, components, and the like of the burner system 100, are significant as related to the full and proper operation of the burner system 100. It has also been found that it is useful to have the pre-determined parameters of the burner system 100 are within ranges of ratios one with respect to another.
These various relationships between the parameters of the various portions, segments, parts, components, and the like of the burner system 100, are discussed below.

[00055] In the illustrated embodiment of the present invention, the following has been found.
Some of the ratios have been expressed in scientific notation, as deemed useful. The ratios represent measurements taken using the Imperial system of meaure.

[00056] Further, it has been found that various measurement ratios of the burner system 100 are useful in producing a burner system that produces a high temperature heat output, that has a heat output realized by high combustion efficiency, and that has a heat output containing minimized pollutants.

[00057] For instance, it has been found that the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the minimum cross-sectional area "B" of the first air-flow opening 224a should preferably be between about 1:0.7 and 1:1.1, and even more preferably be between about 1:0.8 and 1:1.0, and most preferably be about 1:0.9.

[00058]
Other ratios involving the minimum cross-sectional area "A" of the intake air-flow chamber 222 are also important. For instance, the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the circumferential length "C" of the intake air-flow chamber 222 should preferably be between about 1:530 and 1:810.
Also, the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d should preferably be between about 1:1.75 and 1:2.55. The ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the minimum cross-sectional area "G" of the turbulent air-flow chamber 230 should preferably be between about 1:0.8 and 1:1.2.
Also, the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the length "H" of the first air-flow channel 240a should preferably be between about 1:210 and 1:330 and the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the minimum cross-sectional area "I" of the first air-flow channel 240a should preferably be between about 1:0.09 and 1:0.17.

[00059]
Further, the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the airflow "J" through the burner system 100 should preferably be between about 1:80 and 1:120, and the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the heat energy "K" produced by the burner system 100 should preferably be between about 1:8.0x1011 and 1:1.20x1012.

[00060] Other important measurement ratios involve the circumferential length "C" of the intake air-flow chamber 222.
For instance, the ratio of the circumferential length "C" of the intake air-flow chamber 222 to the cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d should preferably be between about 1:2.59x10-3 and 1:3.88x10-3, and the ratio of the circumferential length "C" of the intake air-flow chamber 222 to the circumferential length "L" of the substantially annular turbulent air-flow chamber 230 should preferably be between about 1:0.44 and 1:0.68.

[00061] Yet another important measurement ratio is the minimum cross-sectional area "B" of the first air-flow opening 224a to the circumferential length "L" of the substantially annular turbulent air-flow chamber 230, which should preferably be between about 1:340 and 1:500.

[00062] The minimum cross-sectional area "B" of the first air-flow opening 224a compared to other measurements is also important. The ratio of the minimum cross-sectional area "B" of the first air-flow opening 224a to the minimum cross-sectional area "G" of the substantially annular turbulent air-flow chamber 230 should preferably be between about 1:0.9 and 1:1.35, while the minimum cross-sectional area "B" of the first air-flow opening 224a to the length "H" of the first air-flow channel 240a should preferably be between about 1:240 and 1:360, and the minimum cross-sectional area "B" of the first air-flow opening 224a to the minimum cross-sectional area "I" of the first air-flow channel 240a should preferably be between about 1:0.11 and 1:0.19.
Further, the minimum cross-sectional area "B" of the first air-flow opening 224a to the airflow "J" through the burner system 100 should preferably be between about 1:85 and 1:145, and the ratio of the minimum cross-sectional area "B" of the first air-flow opening 224a to the heat energy "K" produced by the burner system 100 should preferably be between about 1:8.0x1011 and 1:1.20x1012.

[00063] Yet another important measurement ratio involves the cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d. This is important because it influences the amount of air flow between the intake air-flow chamber 222 and the turbulent air-flow chamber 230, and also because it influences the amount of turbulence in the air flow within the turbulent air-flow chamber 230. The cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d to the circumferential length "L" of the substantially annular turbulent air-flow chamber 230 should preferably be between about between about 1:139 and 1:207.

[00064] For similar reasons, the cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d to the minimum cross-sectional area "G" of the substantially annular turbulent air-flow chamber 230 should preferably be between about 1:0.38 and 1:0.54.

[00065] Other similar relationships include the cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d to the length "H" of the first air-flow channel 240a, which should preferably be between about 1:100 and 1:148, and the cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d to the minimum cross-sectional area "I" of the first air-flow channel 240a, which should preferably be between about 1:0.48 and 1:0.72.

[00066] Another important relation is as follows. The cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d to the airflow "J" through the burner system 100 should preferably be between about 1:37 and 1:57, the cumulative ("B"+"D"+"E"+"F") minimum cross-sectional area "B" of the first air-flow opening 224a plus the minimum cross-sectional area "D" of the second air-flow opening 224b plus the minimum cross-sectional area "E" of the third air-flow opening 224c plus the minimum cross-sectional area "F" of the fourth air-flow opening 224d to the heat energy "K" produced by the burner system 100 is between about 1:3.85x1011 and 1:5.77x1011.

[00067] One last important relation involves the minimum cross-sectional area "G" of the substantially annular turbulent air-flow chamber 230. More specifically, the minimum cross-sectional area "G" of the substantially annular turbulent air-flow chamber 230 to the length "H" of the first air-flow channel 240a is between about 1:210 and 1:330, and the minimum cross-sectional area "G" of the substantially annular turbulent air-flow chamber 230 to the minimum cross-sectional area "I" of the first air-flow channel 240a is between about 1:0.09 and 1:0.17.
Further, the minimum cross-sectional area "G" of the substantially annular turbulent air-flow chamber 230 to the airflow "J" through the burner system 100 is between about 1:80 and 1:120, and the minimum cross-sectional area "G" of the substantially annular turbulent air-flow chamber 230 to the heat energy "K" produced by the burner system 100 is between about 1:8.0x1011 and 1:1.20x1012.

[00068] In another aspect, the present invention comprises an air conveying structure 300 having the air conveying passageway 150. As discussed above, the air conveying passageway 150 has, in seriatim and in fluid communication one with the next, the first air-receiving inlet 151a, the intake air-flow chamber 222, the at least one air-flow opening 224, the turbulent air-flow chamber 230, the first air flow channel 240a, and the air-emitting outlet 152. The at least one air-flow opening 224 comprises the first air-flow opening 224a, the second air-flow opening 224b, the third air-flow opening 224c, and the fourth air-flow opening 224d. The wall 226 acts as a chamber-separating structure that separates the intake air-flow chamber 222 and the turbulent air-flow chamber 230 one from the other, and defines the first air-flow opening 224a, the second air-flow opening 224b, the third air-flow opening 224c, and the fourth air-flow opening 224d.

[00069] Further, a fuel conveying structure 310 has the fuel conveying passageway 160, which itself has in seriatim and in fluid communication one with the next, the fuel-receiving inlet 161, the main passageway 164, and the fuel-emitting outlet 162.
The air-emitting outlet 152 and the fuel-emitting outlet 162 are positioned and oriented to permit delivery of air from the air-emitting outlet 152 and delivery of fuel from the fuel-emitting outlet 162 each to a destination, namely the combustion chamber 170, for subsequent combustion generally within the combustion chamber 170.

[00070] The ratio of the minimum cross-sectional area "A" of the intake air flow chamber 222 to the minimum cross-sectional area "G" of the turbulent air flow chamber 230 is between about 1:0.7 and 1:1.1.

[00071] In another aspect of the present invention the burner system 100 comprises an air-flow disruption structure 320 having in seriatim and in fluid communication one with the next, the first air-receiving inlet 151a, the intake air-flow chamber 222, the at least one air flow opening 224, the turbulent air flow chamber 230, and an air-transfer egress 322. The at least one air-flow opening 224 comprises the first air-flow opening 224a, the second air-flow opening 224b, the third air-flow opening 224c, and the fourth air-flow opening 224d. The wall 226 acts as a chamber-separating structure that separates the intake air-flow chamber 222 and the turbulent air-flow chamber 230 one from the other, and defines the first air-flow opening 224a, the second air-flow opening 224b, the third air-flow opening 224c, and the fourth air-flow opening 224d.

[00072]The chamber-separating structure 226 separates the intake air-flow chamber 222 and the turbulent air-flow chamber 230 one from the other and defines the first air-flow opening 224a.

[00073] There is also an air-flow delivery structure 330 having in seriatim and in fluid communication one with the next, an air transfer ingress 332, the first air-flow channel 240a, and the air-emitting outlet 152. The air transfer ingress 332 is in fluid communication with the air-emitting outlet 152 of the air-flow disruption structure 320.

[00074] The burner system 100 also comprises the fuel conveying structure 310 that has in seriatim and in fluid communication one with the next, the fuel-receiving inlet 161, the fuel passageway 150, and the fuel-emitting outlet 162.

[00075] The air-emitting outlet 152 and the fuel-emitting outlet 162 are positioned and oriented to permit delivery of air from the air-emitting outlet 152 and delivery of fuel from the fuel-emitting outlet 162 each to a destination, namely the combustion chamber 174, for subsequent combustion.

[00076] As stated previously, the ratio of the minimum cross-sectional area "A" of the intake air-flow chamber 222 to the minimum cross-sectional area "G" of the turbulent air flow chamber is between about 1:0.7 and 1:1.1.

[00077] As can be understood from the above description and from the accompanying drawings, the present invention provides a fuel nozzle that causes a burner to burn fuel very efficiently, that produces minimal unwanted emissions, that can be used with various types of gaseous and liquid fuel, and that is cost effective, all of which features are unknown in the prior art.

[00078] Other variations of the above principles will be apparent to those who are knowledgeable in the field of the invention, and such variations are considered to be within the scope of the present invention. Further, other modifications and alterations may be used in the design and manufacture of the burner of the present invention without departing from the spirit and scope of the accompanying claims.

Claims

CLAIMS:

1. An air-flow disruption structure for use in a burner system comprising, in seriatim and in fluid communication with the next, a first air-receiving inlet, an intake air-flow chamber, at least one air-flow opening, a turbulent air-flow chamber, and an air-transfer egress; wherein the minimum cross-sectional area of the intake air-flow chamber to the minimum cross-sectional area of the turbulent air-flow chamber is between about 1:0.8 and 1:1.2.