CA2122167C - Apparatus for burning liquid and/or pulverized solid fuels - Google Patents
Apparatus for burning liquid and/or pulverized solid fuelsInfo
- Publication number
- CA2122167C CA2122167C CA002122167A CA2122167A CA2122167C CA 2122167 C CA2122167 C CA 2122167C CA 002122167 A CA002122167 A CA 002122167A CA 2122167 A CA2122167 A CA 2122167A CA 2122167 C CA2122167 C CA 2122167C
- Authority
- CA
- Canada
- Prior art keywords
- inlet ports
- fuel
- air
- longitudinal axis
- inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C1/00—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air
- F23C1/10—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air liquid and pulverulent fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
- F23D11/12—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
Abstract
An apparatus for burning liquid fuels or solid pulverized fuels in a liquid carrier is provided comprising a central port arranged to introduce a fuel-air mixture into a combustion chamber. A first plurality of inlet ports is arranged concentrically about the central port for introducing a first fuel and/or air flow into a space upstream of the central port. In addition, a second plurality of inlet ports is arranged to introduce a second fuel and/or air flow substantially intersecting the inlet flow from the first ports to provide improved fuel-air mixing for introduction into the combustion chamber.
Description
Canadian Patent Application KLS Consulting AB
No. KLS-011-CA Po/McG/kl -- 1 -- , 21221~7 Apparatus for burning liquid and/or pulverized solid fuels Backqround of the invention The invention relates to an apparatus for burning liquid fuels when introduced into a combustion chamber, where the fuel can be an atomized liquid or a pulverized solid fuel atomized with a suitable liquid.
Various burners are available in the art for combusting li~uid fuels such as oil of different grades as well as for combusting solid fuels, particularly coal, peat or the like in pul~-erized form. Pul~erized solid fuels are normally introduced into a combustion chamber as a mixture of the solid fuel with a carrier liquid such as water or oil in the form of an emulsion. In practice, combustion of ~us-pended solid fuels has proven relatively difficult. Prob-lems often arise due to clogging of the fuel ports or nozzles, which can lead to irregular fuel and air supply, causing a reduction in combustion efficiency.
The US Patent 4,726,760 discloses a burner by which a cen-tral injection port opening into the combustion chamber is provided with a continuous knife edge facing -~he center ~0 axis of the port. A plurality of air inlet ports are evenly distributed about the circumference of the knife edge port and the inlet ports are connected to a ~ariable source of compressed air to aid atomization.
Even with this arrangement of the US Patent, the atomiz-ation of the fuels could be improved. The mixing of the ~ fuels with air also appears to be insufficient, limiting the achie~able degree of combustion efficiency.
It is therefore an o~ject of the present invention to prov-ide an apparatus for burning liquid fuels by which atomiz-ation of the fuel can be improved and by which a better mixing of the atomized fuel with combustion air can be achieved to thereby improve combustion efficiency.
Summar~ of the in~ention In accordance with the present invention, an apparatus for burning liquid fuels to be introduced into a combustion chamber is provided, where the liquid fuels preferably comprise heating oils or heavy oils. In addition, solid fuels in pulverized form such as lignite coal, bituminous coal, gas coal, peat or the like can be fired when admixed to a suitable carrier liquid.
The apparatus comprises a central port arranged at a down-stream end along a longitudinal axis of the apparatus, which serves as the supply opening into a combustion cham-ber. A first plurality of inlet ports are arranged concen-trically about the longitudinal axis for introducing a first fuel and/or air flow into a space immediately up-stream of the central port. These inlet ports preferably supply a relatively high-speed air flow from -a compressed air source. More preferably, the center axes of the inlet ports are arranged slightly oblique to a radial direction from the longitudinal axis, to thereby impart a rotational or vortex-type motion in the fuel-air mixture to be formed.
~ 3 ~ 2122167-., A second plurality of inlet ports is also arranged concen-trically about the longitudinal axis, where this second plurality of inlet ports introduces a second fuel and/or air flow, which substantially intersects the inlet flows of the first plurality of inlet ports. The second plurality of inlet ports preferably have their center axes arranged gen-erally along the longitudinal direction. Preferably the first and second plurality of inlet ports comprise the same number of ports respectively and the flow from the res-0 pective ports intersect when entering the space before thecentral port at an angle of about 60~ to 90~.
In a preferred embodiment, the first plurality of ports in-ject compressed air into the space, while the second plur-ality of ports inject fuel at an intersecting angle ofabout gO~ with the compressed air flow.
With the above arrangement of intersecting inlet ports, highly efficient atomization of the liquid fuel can be ob-tained with respect to droplet size and distribution. In apreferred embodiment, vortex flow can be simultaneously achieved of the fuel-air mixture exiting the central port of the burner.
No. KLS-011-CA Po/McG/kl -- 1 -- , 21221~7 Apparatus for burning liquid and/or pulverized solid fuels Backqround of the invention The invention relates to an apparatus for burning liquid fuels when introduced into a combustion chamber, where the fuel can be an atomized liquid or a pulverized solid fuel atomized with a suitable liquid.
Various burners are available in the art for combusting li~uid fuels such as oil of different grades as well as for combusting solid fuels, particularly coal, peat or the like in pul~-erized form. Pul~erized solid fuels are normally introduced into a combustion chamber as a mixture of the solid fuel with a carrier liquid such as water or oil in the form of an emulsion. In practice, combustion of ~us-pended solid fuels has proven relatively difficult. Prob-lems often arise due to clogging of the fuel ports or nozzles, which can lead to irregular fuel and air supply, causing a reduction in combustion efficiency.
The US Patent 4,726,760 discloses a burner by which a cen-tral injection port opening into the combustion chamber is provided with a continuous knife edge facing -~he center ~0 axis of the port. A plurality of air inlet ports are evenly distributed about the circumference of the knife edge port and the inlet ports are connected to a ~ariable source of compressed air to aid atomization.
Even with this arrangement of the US Patent, the atomiz-ation of the fuels could be improved. The mixing of the ~ fuels with air also appears to be insufficient, limiting the achie~able degree of combustion efficiency.
It is therefore an o~ject of the present invention to prov-ide an apparatus for burning liquid fuels by which atomiz-ation of the fuel can be improved and by which a better mixing of the atomized fuel with combustion air can be achieved to thereby improve combustion efficiency.
Summar~ of the in~ention In accordance with the present invention, an apparatus for burning liquid fuels to be introduced into a combustion chamber is provided, where the liquid fuels preferably comprise heating oils or heavy oils. In addition, solid fuels in pulverized form such as lignite coal, bituminous coal, gas coal, peat or the like can be fired when admixed to a suitable carrier liquid.
The apparatus comprises a central port arranged at a down-stream end along a longitudinal axis of the apparatus, which serves as the supply opening into a combustion cham-ber. A first plurality of inlet ports are arranged concen-trically about the longitudinal axis for introducing a first fuel and/or air flow into a space immediately up-stream of the central port. These inlet ports preferably supply a relatively high-speed air flow from -a compressed air source. More preferably, the center axes of the inlet ports are arranged slightly oblique to a radial direction from the longitudinal axis, to thereby impart a rotational or vortex-type motion in the fuel-air mixture to be formed.
~ 3 ~ 2122167-., A second plurality of inlet ports is also arranged concen-trically about the longitudinal axis, where this second plurality of inlet ports introduces a second fuel and/or air flow, which substantially intersects the inlet flows of the first plurality of inlet ports. The second plurality of inlet ports preferably have their center axes arranged gen-erally along the longitudinal direction. Preferably the first and second plurality of inlet ports comprise the same number of ports respectively and the flow from the res-0 pective ports intersect when entering the space before thecentral port at an angle of about 60~ to 90~.
In a preferred embodiment, the first plurality of ports in-ject compressed air into the space, while the second plur-ality of ports inject fuel at an intersecting angle ofabout gO~ with the compressed air flow.
With the above arrangement of intersecting inlet ports, highly efficient atomization of the liquid fuel can be ob-tained with respect to droplet size and distribution. In apreferred embodiment, vortex flow can be simultaneously achieved of the fuel-air mixture exiting the central port of the burner.
2~ Rrief descri~tion of the drawinqs The invention will now be descri~ed in more detail with reference to an embodiment of the apparatus as illustrated in the drawing of Figs. 1 and 2. ~' Fig. 1 shows a cross-section along the longitudinal axis of the burner apparatus according to an embodiment of the present invention.
~ 4 ~ 2 12 2 16 ~
Fig. 2 shows a preferred arrangement of the f-irst inlet ports with respect to the second inlet ports.
The elements necessary for the actual operation of the burning apparatus of the present invention, for example air sources and fuel sources as well as the combustion chamber itself are not shown in the drawing, however will be known to those skilled in the present art.
Detailed description of the ~referred embodiments The fuel burner illustrated in Fig. 1 comprises a jet body 36 extending about a longitudinal axis 26. The downstream end of the jet body 36 is fitted with a nozzle piece 50 which comprises a central fuel port 10 opening into a com-bustion chamber 16 (not shown in detail). The flow direc-tion is indicated by the arrows in the left of Fig. 1 indicating fuel and/or air streams flowing toward the nozzle piece 50. The central port 10 is preferably recessed or disposed upstream of an end wall 12 of the combustion chamber 16 as will be discussed below.
The jet body 36 is surrounded by two gas and/or air pass-ages 14, 18. The passage 14 opens into the combustion cham-ber 16 at its downstream end via an annular inlet port 24.The passage 14 supplies primary air for combustion, which may be enriched with higher temperature combustion gasses in a recycling system. The term "primary air" used herein-after is to be understood as air or a mixture'of air and recycled combustion gasses . The air exiting the annular port 24 has a flow velocity of about 100 to about 200 m/sec., preferably 120 to 140 m/sec.. The side walls 20 and 22 defining the annular port 24 are of conical configur-ation- to provide a cone-shaped air flow which broadens as it enters the combustion chamber. Swirl or baffle plates are provided in passage 14 at an angle of about 70~ to thereby give the primary air a vortex movement about the longitudinal axis 26. The primary air is supplied to the passage 14 at a pressure of about 1000 to about 1200 mm A second passage 18 is provided concentrically about pas-sage 14 and defined by an inner jacket 38 and an outer jacket 39. Passage 18 at its downstream end merges into a second annular inlet port 28 defined by the conical side walls 30 and 32. The second annular inlet however is dir-ected to form a converging conical flow of secondary air, ~hich intersects with the expanding conical profile of primary air Erom the first annular input port 24. Swirl ~5 baffles may also be located in passage 18 to impart a vor-tex flow of secondary air if desired. A deflection angle of 40~ to 45~ of the baffles with respect to the longitudinal axis 26 is preferred. The discharge of velocity of the secondary air is preferably in the range of 120 to 180 m/sec., more preferably 130 to 150 m/sec... The intersection cf the conically converging secondary air with the conic-ally expanding primary air provides additional agitation and mixing of the fuel-air mixture shortly after it enters into the combustion chamber 16. The secondary air is pref-2~ erably fed into the passage 18 at a pressure of about 1000 to about 1200 mm H2O. The vortex deflection angle of the secondary air when employed is preferably in the same dir-ection as the deflection of the primary air. As with the primary air, the secondary air can also be ad~ixed with 30 combustion gasses from the furnace as desired.
The discharge velocities of the primary and secondary air from the annular outlets 24 and 28 respectively generally remain the same under most operating conditions from start-3~ up to full load. Depending on the type of fuel being com-21221~7 busted, the discharge ~elocity and/or discharge volume canbe ~aried by increasing or decreasing the gap width of the annular ports 24 and 28. This is accomplished by axial displacement of the annular mouth piece 34 connected with the tubular jacket 38 which separates the two passages 14 and 18.
In accordance with the present invention, the burner appar-atus is provided with a particular configuration of the nozzle piece 50, which comprises the central port 10. In a particularly preferred embodiment, the central port 10 is defined by a continuous, circulzr knife edge 40 facing tow-ard the longitudinal axis 26. The knife edge has tapering side portions seen in cross-section and, preferably has a 1~ triangular-like cross-section with sloping sides 48 as shown in Fig. 1.
According to the invention a first plurality of air inlet ports 42 are arranged concentrically about the longitudinal axis 26 for introducing a first fuel and/or air flow into a space 49 located upstream of the central port 10. The space 49 is generally of cylindrical form and communicates with both the first inlet ports 42 and the second inlet ports 47 to be discussed below. Preferably, the first plurality of inlet ports 42 are in common fluid communication with a compressed air passage 46 by means of an annular passage 44. The inlet ports 42 are defined by a center axis for each port respectively, which generally determines the flow direction into the space 49. Preferably the c~nter axes of 3~ the inlet p~rts 42 are arrar~ged at an angle in the range of 60~ to 90~ with respect to the longitudinal axis 26, pref-erably at an angle in the range of 70~ to 80~.
A second plurality of inlet ports is also arranged concen-trically about the longitudinal axis 26 in the nozzle piece ~ - 7 ~ 21221G7 50. These second inlet ports 47 are arranged to introduce a second fuel and/or air flow into the space 49, where the second flow from the inlet ports 47 substantially inter-sects the first flow from the inlet ports 42 as can best be seen in Pig. 2. ~ig. 2 represents a side view along the longitudlnal axis 26 looking in the upstream direction.
The second plurality of inlet ports as seen in Fig. 1 are defined as each having a center axis arranged at an angle in the range of 0~ to 30~ with respect to the longitudinal axis 26. In a preferred embodiment as shown in Fig. 2, the inlet ports 42 are also directed obliquely to a radial ray extending from the longitudinal axis 26 by an angle ~ of about 10~ to 30~.
This arrangement of intersecting flows provides not only direct mixing of the fuel and air inlet flows but also im-parts rotary or vortex motion of the fuel-air mixture form-ed in the space 49. This vortex motion originating in the space 49 continues with downstream flow out of the central port 10 and into the com~usticn chamber 15. As can ~e seen from Fig. 2, one inlet port 42 is pro~ided for each inlet port 47. The number of first and second inlet ports 42, 47 respectively is variable, preferably 6 to 10, more prefer-~5 ably 8 sets of ports are provided. To achie~e best fuel-air mixture and atomization, the ports 42 and 47 are arranged to intersect at an angle of about 60~ to 90~, where an angle in the range of 80~ to 90~ is most preferred.
Again referring to Fig. 1, the central port lo and the first and second pluralities of inlet ports 42, 47 are provided in a single nozzle piece 50. This nozzle piece 50 is fitted, for example, by threaded connection, to the downstream end of a jet body 36. The jet body is mounted at an upstream end (not shown) in a manner that it can be - 8 ~ 21221~7 axially displaced along the longitudinal axis~26. As men-tioned above, the outer surface 20 of the jet body is sur-rounded by the inner surface 22 of the axially displaceable annular mouth piece 34 to form the first annular air inlet 24.
The axial displacement of the jet body 36 allows adjustment of the nozzle 50 with respect to the combustion wall 12.
This feature allows adjustment of the vortex flow out of the port 10, depending on the type of fuel being burned and in conjunction therewith the amount and velocity of primary and secondary air flows. It is particularly preferred that the jet body be adjusted such that the central port 10 is located slightly upstream of the combustion wall 12. Fur-1, thermore, for burning heating oil, it is preferred that thecentral port 10 of the nozzle piece 50 be disposed upstream of the end extension of the annular mouth piece 34.
Preferably, the fuel burner of the present invention is ~G operated by supplying fuel through the second inlet ports 47 pro-vided in co~on fluid communication with an upstream source of fuel (not shown in Fig. 1). In this case, the first inlet ports 42 are provided in common fluid commun-ication via passage 44 with a preferably -~ariable source of compressed air.
Alternatively, fuel can be injected in the first inlet ports 42 while compressed air is injected in the first inlet ports 47. -' ~o With the defined structural arrangement, the primary air exiting from the annular port 24 envelopes the vortex flow of fuel-air mixture exiting from the space 49. This spray cone or expanding cone is then almost immediately inter-3~ sected by the converging cone of secondary air which provides further mixing and secondary combustion furtherinto the combustion chamber.
All of the features disclosed in the present papers are claimed as being essential to the invention to the extent to which they are novel over the prior art either individ-ually or in combination.
~ 4 ~ 2 12 2 16 ~
Fig. 2 shows a preferred arrangement of the f-irst inlet ports with respect to the second inlet ports.
The elements necessary for the actual operation of the burning apparatus of the present invention, for example air sources and fuel sources as well as the combustion chamber itself are not shown in the drawing, however will be known to those skilled in the present art.
Detailed description of the ~referred embodiments The fuel burner illustrated in Fig. 1 comprises a jet body 36 extending about a longitudinal axis 26. The downstream end of the jet body 36 is fitted with a nozzle piece 50 which comprises a central fuel port 10 opening into a com-bustion chamber 16 (not shown in detail). The flow direc-tion is indicated by the arrows in the left of Fig. 1 indicating fuel and/or air streams flowing toward the nozzle piece 50. The central port 10 is preferably recessed or disposed upstream of an end wall 12 of the combustion chamber 16 as will be discussed below.
The jet body 36 is surrounded by two gas and/or air pass-ages 14, 18. The passage 14 opens into the combustion cham-ber 16 at its downstream end via an annular inlet port 24.The passage 14 supplies primary air for combustion, which may be enriched with higher temperature combustion gasses in a recycling system. The term "primary air" used herein-after is to be understood as air or a mixture'of air and recycled combustion gasses . The air exiting the annular port 24 has a flow velocity of about 100 to about 200 m/sec., preferably 120 to 140 m/sec.. The side walls 20 and 22 defining the annular port 24 are of conical configur-ation- to provide a cone-shaped air flow which broadens as it enters the combustion chamber. Swirl or baffle plates are provided in passage 14 at an angle of about 70~ to thereby give the primary air a vortex movement about the longitudinal axis 26. The primary air is supplied to the passage 14 at a pressure of about 1000 to about 1200 mm A second passage 18 is provided concentrically about pas-sage 14 and defined by an inner jacket 38 and an outer jacket 39. Passage 18 at its downstream end merges into a second annular inlet port 28 defined by the conical side walls 30 and 32. The second annular inlet however is dir-ected to form a converging conical flow of secondary air, ~hich intersects with the expanding conical profile of primary air Erom the first annular input port 24. Swirl ~5 baffles may also be located in passage 18 to impart a vor-tex flow of secondary air if desired. A deflection angle of 40~ to 45~ of the baffles with respect to the longitudinal axis 26 is preferred. The discharge of velocity of the secondary air is preferably in the range of 120 to 180 m/sec., more preferably 130 to 150 m/sec... The intersection cf the conically converging secondary air with the conic-ally expanding primary air provides additional agitation and mixing of the fuel-air mixture shortly after it enters into the combustion chamber 16. The secondary air is pref-2~ erably fed into the passage 18 at a pressure of about 1000 to about 1200 mm H2O. The vortex deflection angle of the secondary air when employed is preferably in the same dir-ection as the deflection of the primary air. As with the primary air, the secondary air can also be ad~ixed with 30 combustion gasses from the furnace as desired.
The discharge velocities of the primary and secondary air from the annular outlets 24 and 28 respectively generally remain the same under most operating conditions from start-3~ up to full load. Depending on the type of fuel being com-21221~7 busted, the discharge ~elocity and/or discharge volume canbe ~aried by increasing or decreasing the gap width of the annular ports 24 and 28. This is accomplished by axial displacement of the annular mouth piece 34 connected with the tubular jacket 38 which separates the two passages 14 and 18.
In accordance with the present invention, the burner appar-atus is provided with a particular configuration of the nozzle piece 50, which comprises the central port 10. In a particularly preferred embodiment, the central port 10 is defined by a continuous, circulzr knife edge 40 facing tow-ard the longitudinal axis 26. The knife edge has tapering side portions seen in cross-section and, preferably has a 1~ triangular-like cross-section with sloping sides 48 as shown in Fig. 1.
According to the invention a first plurality of air inlet ports 42 are arranged concentrically about the longitudinal axis 26 for introducing a first fuel and/or air flow into a space 49 located upstream of the central port 10. The space 49 is generally of cylindrical form and communicates with both the first inlet ports 42 and the second inlet ports 47 to be discussed below. Preferably, the first plurality of inlet ports 42 are in common fluid communication with a compressed air passage 46 by means of an annular passage 44. The inlet ports 42 are defined by a center axis for each port respectively, which generally determines the flow direction into the space 49. Preferably the c~nter axes of 3~ the inlet p~rts 42 are arrar~ged at an angle in the range of 60~ to 90~ with respect to the longitudinal axis 26, pref-erably at an angle in the range of 70~ to 80~.
A second plurality of inlet ports is also arranged concen-trically about the longitudinal axis 26 in the nozzle piece ~ - 7 ~ 21221G7 50. These second inlet ports 47 are arranged to introduce a second fuel and/or air flow into the space 49, where the second flow from the inlet ports 47 substantially inter-sects the first flow from the inlet ports 42 as can best be seen in Pig. 2. ~ig. 2 represents a side view along the longitudlnal axis 26 looking in the upstream direction.
The second plurality of inlet ports as seen in Fig. 1 are defined as each having a center axis arranged at an angle in the range of 0~ to 30~ with respect to the longitudinal axis 26. In a preferred embodiment as shown in Fig. 2, the inlet ports 42 are also directed obliquely to a radial ray extending from the longitudinal axis 26 by an angle ~ of about 10~ to 30~.
This arrangement of intersecting flows provides not only direct mixing of the fuel and air inlet flows but also im-parts rotary or vortex motion of the fuel-air mixture form-ed in the space 49. This vortex motion originating in the space 49 continues with downstream flow out of the central port 10 and into the com~usticn chamber 15. As can ~e seen from Fig. 2, one inlet port 42 is pro~ided for each inlet port 47. The number of first and second inlet ports 42, 47 respectively is variable, preferably 6 to 10, more prefer-~5 ably 8 sets of ports are provided. To achie~e best fuel-air mixture and atomization, the ports 42 and 47 are arranged to intersect at an angle of about 60~ to 90~, where an angle in the range of 80~ to 90~ is most preferred.
Again referring to Fig. 1, the central port lo and the first and second pluralities of inlet ports 42, 47 are provided in a single nozzle piece 50. This nozzle piece 50 is fitted, for example, by threaded connection, to the downstream end of a jet body 36. The jet body is mounted at an upstream end (not shown) in a manner that it can be - 8 ~ 21221~7 axially displaced along the longitudinal axis~26. As men-tioned above, the outer surface 20 of the jet body is sur-rounded by the inner surface 22 of the axially displaceable annular mouth piece 34 to form the first annular air inlet 24.
The axial displacement of the jet body 36 allows adjustment of the nozzle 50 with respect to the combustion wall 12.
This feature allows adjustment of the vortex flow out of the port 10, depending on the type of fuel being burned and in conjunction therewith the amount and velocity of primary and secondary air flows. It is particularly preferred that the jet body be adjusted such that the central port 10 is located slightly upstream of the combustion wall 12. Fur-1, thermore, for burning heating oil, it is preferred that thecentral port 10 of the nozzle piece 50 be disposed upstream of the end extension of the annular mouth piece 34.
Preferably, the fuel burner of the present invention is ~G operated by supplying fuel through the second inlet ports 47 pro-vided in co~on fluid communication with an upstream source of fuel (not shown in Fig. 1). In this case, the first inlet ports 42 are provided in common fluid commun-ication via passage 44 with a preferably -~ariable source of compressed air.
Alternatively, fuel can be injected in the first inlet ports 42 while compressed air is injected in the first inlet ports 47. -' ~o With the defined structural arrangement, the primary air exiting from the annular port 24 envelopes the vortex flow of fuel-air mixture exiting from the space 49. This spray cone or expanding cone is then almost immediately inter-3~ sected by the converging cone of secondary air which provides further mixing and secondary combustion furtherinto the combustion chamber.
All of the features disclosed in the present papers are claimed as being essential to the invention to the extent to which they are novel over the prior art either individ-ually or in combination.
Claims (11)
1. An apparatus for burning liquid fuels introduced into a combustion chamber, said apparatus comprising:
a central port arranged on a downstream end of a longitudinal axis of the apparatus for supplying a fuel-air mixture to the combustion chamber:
a first plurality of inlet ports arranged concentrically about said longitudinal axis for introducing a first fuel and/or air flow into a space upstream of said central port;
a second plurality of inlet ports arranged concentrically about said longitudinal axis for introducing a second fuel and/or air flow, substantially intersecting said first flow, into said space to form the fuel-air mixture, wherein the first and second flows from the respective inlet ports intersect one another at an angle of about 60°
to 90°.
a central port arranged on a downstream end of a longitudinal axis of the apparatus for supplying a fuel-air mixture to the combustion chamber:
a first plurality of inlet ports arranged concentrically about said longitudinal axis for introducing a first fuel and/or air flow into a space upstream of said central port;
a second plurality of inlet ports arranged concentrically about said longitudinal axis for introducing a second fuel and/or air flow, substantially intersecting said first flow, into said space to form the fuel-air mixture, wherein the first and second flows from the respective inlet ports intersect one another at an angle of about 60°
to 90°.
2. The apparatus of claim 1, wherein the number of the first and second plurality of inlet ports is the same.
3. The apparatus of claim 2, wherein said first plurality of inlet ports have centre axes determining the flow direction into said space, said axes arranged at an angle in the range 60° to 90° with respect to said longitudinal axis.
4. The apparatus of claim 3, wherein the center axes of said first plurality of inlet ports are directed obliquely to a radial ray extending from the longitudinal axis by an angle .alpha.
in the range of about 10° to 30° to provide a vortex flow of the fuel-air mixture.
in the range of about 10° to 30° to provide a vortex flow of the fuel-air mixture.
5. The apparatus of claim 2, wherein said second plurality of inlet ports have center axes determining the flow direction into said space, said axes arranged at an angle in the range of 0° to 30° with respect to said longitudinal axis.
6. The apparatus of claim 2, wherein said central port is defined by a circular knife edge of substantially triangular cross-section.
7. The apparatus of claim 2, wherein the first plurality of inlet ports is provided in common fluid communication with a preferably variable source of compressed air and the second plurality of inlet ports is provided in common fluid communication with a source of liquid fuel.
8. The apparatus of claim 2, wherein the first plurality of inlet ports is provided in common fluid communication with a source of liquid fuel and the second plurality of inlet ports is provided in common fluid communication with a preferably variable source of compressed air.
9. The apparatus of claim 1, wherein said central port and said first and second pluralities of inlet ports are provided in a nozzle piece fitted on the downstream end of a jet body, said jet body mounted to be axially displaceable along said longitudinal axis of the apparatus.
10. The apparatus of claim 9, wherein the downstream end of the jet body is surrounded by an axially displaceable annular mouthpiece, an inner surface of which, along with an outer surface of the jet body, defines a first annular inlet; and an outer surface of the annular mouthpiece, along with an inner surface of a jacket, defines a second annular air inlet.
11. The apparatus of claim 10, wherein the downstream end of said jet body with nozzle piece is disposed upstream of a downstream end extension of said annular mouthpiece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002122167A CA2122167C (en) | 1994-04-26 | 1994-04-26 | Apparatus for burning liquid and/or pulverized solid fuels |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002122167A CA2122167C (en) | 1994-04-26 | 1994-04-26 | Apparatus for burning liquid and/or pulverized solid fuels |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2122167A1 CA2122167A1 (en) | 1995-10-27 |
| CA2122167C true CA2122167C (en) | 1999-07-06 |
Family
ID=4153465
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002122167A Expired - Fee Related CA2122167C (en) | 1994-04-26 | 1994-04-26 | Apparatus for burning liquid and/or pulverized solid fuels |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2122167C (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111819394B (en) * | 2017-09-25 | 2023-03-24 | 北京中宇先创能源科技有限公司 | Burner and method of using same |
-
1994
- 1994-04-26 CA CA002122167A patent/CA2122167C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CA2122167A1 (en) | 1995-10-27 |
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