CA2181748C - Burner for liquid fuels - Google Patents
Burner for liquid fuelsInfo
- Publication number
- CA2181748C CA2181748C CA002181748A CA2181748A CA2181748C CA 2181748 C CA2181748 C CA 2181748C CA 002181748 A CA002181748 A CA 002181748A CA 2181748 A CA2181748 A CA 2181748A CA 2181748 C CA2181748 C CA 2181748C
- Authority
- CA
- Canada
- Prior art keywords
- inlet ports
- burner
- fuel
- air
- tlle
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D1/00—Burners for combustion of 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
- F23D11/36—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 com-bustion chamber. A first plurality of inlet ports is ar-ranged concentrically about the central port for introd-ucing 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
C~lldlal~ Pat~e~ plication 2131~8KLS COllsultin I~B
No. KLS-012-~ Po/McG/IIl Burner for Liquid Fuels .
The invention relates to an apparatus ~or burning liquid fuels when introduced into a combustion chamber, where the 10 fuel can be an atomized liquid or a pulverized solid fuel atomized witll a suitable liquid.
Various burners are avai.lable in the art for combusting liquid fuels such as oil. of different grades as well as for 15 combusting solid fuels, particularly coal, peat or t~le like in pulverized form. Pulverized solid fuels are normally introduced illtO a combu~tion chamber as a mixture of t~le solid fuel with a carrier liquid such as water or oil in tile form of an emulsion. In practice, combhstion of sus-20 pended soli.d fuels has proven relatively difficult. Prob-lems often arise due to clogging of the fuel ports or nozzles, wllich can lead to irregular fuel and air supply, causing a reduction in combustion efficiency.
The US Patellt 4,726,760 discloses a burner by W~liC~I a cen-tral injection port opening into the combustion chamber is provided witll a continuous knife edge facing the center axis of the port. A plu~-ality of air inlet ports are evenly distributed about tlle circumference of the knife edge port and the inlet ports are connected to a variable source of compressed air to aid atomization.
Even Wit~l tllis arrangement o~ the US Patent, the atomiz-ation of tlle fuels coulcl be improved. The mixing of the i - 2 - 21817~18 uel3 Wit~l air also appears to be insufficient, limiting tlle acllievable degree oE combustion efficiency.
It is tllerefore an obje~-t of tlle present inven~:ion to prov-5 ide an apparatus for burning liquid fuels by whicll atomiz-ation of tlle fuel can be improved and by which a better mixing of the atomized Euel with combustion air can be acllieved to thereby improve combustion efficiellcy.
lo ~ummarv of the i nventi In accordance wit~l tlle ]?resent invention, an apparatus for burning liquid fuels to be introduced into a combustion chanlber is provided, wllere t~le liquid fuels preferably 15 comprise lleating oils or heavy oils. In adaition, solid fuels in pulveri:~ed form such as lignite coal, bituminous coal, gas coal, I?eat or the like can be f ired w~lell admixed to a suitable carrier liquid.
2~ T~le apparatus comprises a central port arranged at a down-stream end along a longitudinal axis of tlle apparatus, wllic}l serves as t~le supl~ly opening into a combustion c~lam-ber. A rirst plurality of inlet ports are arranged Goncen-trically about the longitudinal axis ~or introducing a 25 first fuel and/or air f~ ow into a space immediately up-stream of tlle central port. These inlet ports preferably supply a relatively lligll-speed air flow from a compressed air source. More preferably, tlle center axes of tlle inlet ports are arranged sliglltly oblique to a radial direction 30 rom tlle longitudinal a}2is, to thereby impart a rotational or vortex-type motion in the fuel-air mixture to be formed.
A second plurality of irllet ports is also arranged concen-trically about the longi.tudinal axis, wllere tllis second 35 plurality of inlet ports introduces a second fuel and/or ., ~
~ 3 - 218 1~48 air flow, wllich substantially intersects the inlet flows of the first plurality of inlet ports. T}le second plurality of illlet ports preferably ~lave their center axes arranged ge}l-erally alollg t~le longitudinal direction. Prererably t~le 5 first and second plurality of inlet ports comprise the same number of ports respect ively and the flow from the res-pective ports intersect when entering the space before tlle central port at an angle of about 60 to 90.
10 In a preferred embodiment, tlle first plurality of ports in-ject compressed air int~ the space, while t~le second plur-ality of ports inj ect fuel at an intersecting angle of about 90 witll the comp]^essed air flow.
Witll tlle ahove arrangement of intersecting inlet ports, llighl; ef~icient atomization of tlle liquid ~uel can be ob-tained wit~l respect to droplet size and distribution. In a preferred embodiment, vortex flow can be simultaneously ac~lieved of the fuel-ai]^ mixture exiting the central port 20 of: t~le burner.
Brief descriPtion of t;he drawinqs Tlle invention will IIOW ~e described in more detail Wit~l 25 reference to an embodiment of the apparatus as illustrated in tlle drawing of Figs. 1 and 2.
Fig. 1 sllows a cross-section along the longitudinal axis of tlle burner apparatus according to an embodiment of f:he 30 presellt invention.
Fig. 2 shows a preferred arrangement of the ~irst inlet ports witll respect to t~le second inlet ports.
~ 4 ~ 21817~8 T~le elements necessary for the actual operatioll of ~ e burning apparatus of the present inve~ltion, for example air sources and fuel sources as well as tlle combustion c~lamber itself are not shown in the drawing, ~lowever will be known 5 to tllose skilled ill t~le present art.
Detailed descril~tion of the preferred embodiments The fuel burner illustrated in Fig . 1 comprises a j et body 36 extending about a longitudinal axi6 26. Tlle downstream end of tlle jet body 36 is fitted Wit~l a nozzle piece 50 wllich comprises a central fuel port 10 opening into a com-bustion c~lamber 16 (not shown in detail). The flow direc-tiOII is indicated by the arrows ill the lef t of Fig .
15 indicating f~lel and/or air streams flowing toward the nozzle piece 50. The central port 10 is preferably recessed or disposed upstream of an end wall IZ of t~le combustion chamber 16 as will be discussed below.
20 Tlle 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.
~le passage 14 supplies primary air for combustion, w~lich may be ellriched Wit~l higher temperature combustion gasses 25 in a recyclillg system. The term "primary air" used ~lereill-after is to be understood as air or a mixture of air and recycled combustion gasses. The air exiting t31e annular port 24 llas a flow velocity of about 100 to about 200 m/sec., preferably 120 to 140 m/sec.. The side walls 20 and 30 22 defining t~le annular port 24 are of conical configur-ation to provide a cone-shaped air flow wllich broadells as it enters t~le combustion chamber. Swirl or baffle plates are provided in passage 14 at an angle of about 70 to t~lereby give t~le primary air a vo~tex movemellt about the 35 longitudinal axis 26. T~le primary air is supplied to tlle I
21817~8 passage 1~ at a pressure o~ about 1000 to about 1200 mm E~20 ~
~ second passage 18 is ~)rovided concentrically about pas-5 sage 14 and defined by cln inner jacket 38 and an outer ~acket 3g. Passage 18 at its downstream end merges into a second annular inlet port 28 defined by tlle conical side walls 30 and 32. Tlle second annular inlet llowever is dir-ected to form a converg-ing conical flow of secondary air, 10 W~liC~ ltersects Wit~l tl~e f~rpi:~n~l; ng conical profil~ of primary air from tlle fi]-st annular input port 24. Swirl baf1es may also be located in passage 18 to impart a vor-tex ~low of secondary air if desired. 1~ deflection angle of 40 to 45 of tlle baffl~s with respect to tlle lollgitudinal 15 axis 26 is preferred. T~le discharge of velocity oi tlle secondary air is preferably in the rallge of 120 to 180 m/sec., more preferably 130 to 150 m/sec.. T~le intersection of tlle collically converging secondary air witll Lhe conic-ally ~p~n~ g primary air provides additional agitation 20 and mixing of ~ e fuel-air mixture sllortly aLter it enters illtO ~le combustion cha~nber 16. The secondary air is pref-erably fed into tlle passage 18 at a pressure of about 1000 to abo~lt 1200 mm H2O. Tlle vortex deflectioll angle of tlle secolldary air when employed is preferably in t~le same dir-25 ection as t~le deflectioll of the primary air. ~s with tlleprimary air, tlle secolldary air can also be admixed witl combustion gasses from the furnace as desired.
Tlle discllarge velocities of the primary and secondary air 30 from tlle annular outlets 24 and 28 respectively gellerally remain tlle same under most operating conditions from start-up to full load. Depend:ing on tlle ~pe of fuel being com-busted, tlle discllarge velocity and/or discllarge volume can be varied by increasing or decreasing the gap widtll of the 35 annular ports 24 and 28. This is accomplis~led by axial - 6 - 21817~8 displacement of t~e annular mout~l piece 34 connected Wit~
~ile tubular jacket 33 which separates tlle two passages 14 alld 18.
5 Ill accordance Wit~l the present invention, the burner appar-atus is provided with a particular configuration of tlle nozzle piecc 50, whicll comprises the central port 10.
Embodimellts of tlle nozzle construction are sllowll in Figs. 1 and 2. Ill the preferred embodiments, t~le central port 10 is 10 defined by a continuous, circular knife edge 40 facirlg tow-ard the longitudinal axis 26. The knife edge has taperillg side portions seen in cross-section and, preferably ~las a triangular-like cross-section Wit~l sloping sides 43 as sllown in Fig, 1.
: ' -According to the invention a first plurality of air inlet ports 42 are! arran~ed ccncentrically about tlle 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 20 49 is gellerally of cylindrical form and communicates witll bot~l tlle i:irst inlet ports 42 and the second inlet ports 47 to be discussed below. ~'he inner surface 60 of ~lle nozzle piece 50, whlc~l faces the part 10 may be concave in shape as shown in Fig. 2.
Preferably, th~ 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, w~ich 30 generally determines t~le flow direction into the space 49.
Preferably tlle center a}ces of the inlet ports 42 are arrangod at an angle in the range of 60 to 90 witll respect to the longitudinal axis 26, preferably at an angle in the range of 70 to ~0 ., ~ 7 ~ 21817~8 A second plurality of in.let ports is also arranged concen-trically about the longitudinal axis 26 in the nozzle piece 50. T~lese 6econd inlet E~orts 47 are arranged to introduce a second fuel and/or air flow into the space 49, where tlle second flow from tlle inlet ports 47 substalltially illter- =
sects the first flow from the inlet ports 42 as can best be seell in Fig . 3 . Fig . 3 represents a f ront view along the longitudillal axis 26 looking in tlle upstream directioli.
The second plurality of inlet ports 47 as seen in Fig. 1 or Fig. 2 are defined as each having a center axis arranged at an angle in tlle range of 0 to 30 Wit~l respect to tlle longitudinal axis 26.
As S~IOWII in Fig. 3, tlle inlet ports 42 are also directed obliquely to a radial ray extending from the longitudillal axis 26 by an angle o~ of 5 to 40, preferably 15 to 30.
T~lis 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 t~le fuel-air mixture form-ed in tlle space 49. This vortex motion originati~lg in the space 49 con~ pR with downstream flow out of the central port 10 and into t~le coirbustion chamber 16. As can be seen from Fig. 3, one Inlet port 42 is provided for eac~ llet port ~7. The number of first and second inlet ports 42, 47 respectively is variable, preferably 6 to 14, more prefer-ably 10 to 12 set:s of ports are provided. To acllieve best fuel-air mixture and atomization, t~le ports 42 and 47 are arranged to intersect at an angle of about 60 to 90, wllere an angle in t~le range of 80 to 90 is most pref-erred .
Again ~referring to Fig. 1, the central port 10 and the first and second pluralities of inlet ports 42, 47 are ., 8- 21817~8 provided in a single no~zle piece 50 This nozzle piece 50 is fitted, for example, by threaded connection, to tlle dowllstream end of a jet body 36. Tlle jet body is mounted at an upstream end (not shown) in a manner that it can be 5 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 mout~l piece 3~ to form the first annular air inlet 24 .
T~le axial displacement of the jet body 36 allows adjustlnent -of tlle no~zle 50 Wit~l respect to the combustion wall 12.
This feature allows adj~stment of the vortex flow out of t~le port 10, depending on the type of fuel being burned and 15 in conjunction t~lerewith the amount and velocity of primary and secondary air flows. It is particularly preferred tllat tile j et body be adjusted such that the central port 10 is located sliglltly upstream of the combustion wall 12. Fur-t~le~more, for burning heating oil, it is preferred t~lat the 20 central port 10 of t~le nozzle piece 50 be disposed upstream of tlle end extension of the annular mouth piece 34.
Preferably, t~le fuel burner of the present invention is operated by supplying fuel, preferably oil, t~lroug}l ~lle 25 second inlet ports 47 provided in common fluid communication with an upstream source of fuel (not shown in Fig. 1). In t~lis case, t~le ~irst inlet ports 42 are pro~-ided in common fluid communication via passage 44 wit~l a preferably variable source of compressed air.
Alternatively, fuel can be injected in the first inlet ports 42 w~lile compressed air is injected i~l the first inlet ports 47.
.
218~7~
With tlle de~ined struct~ral arrangement, t~le primary air exiting from t~le annular port 24 envelopes t~le vortex flow of fuel-air mixture exi~ing from the space 49. This spray cone or expanding cone is then almost immediately inter-S sected by t~le converging cone of secondary air whicllprovides further mixing and secondary combustion further illtO t~le combustion chamber.
~11 of tlle f eatures disclosed in the present papers are 10 claimed as being essential to t~le invention to t~le extent to w~lich t~ley are novel over the prior art eitller individ-ually or in combination.
No. KLS-012-~ Po/McG/IIl Burner for Liquid Fuels .
The invention relates to an apparatus ~or burning liquid fuels when introduced into a combustion chamber, where the 10 fuel can be an atomized liquid or a pulverized solid fuel atomized witll a suitable liquid.
Various burners are avai.lable in the art for combusting liquid fuels such as oil. of different grades as well as for 15 combusting solid fuels, particularly coal, peat or t~le like in pulverized form. Pulverized solid fuels are normally introduced illtO a combu~tion chamber as a mixture of t~le solid fuel with a carrier liquid such as water or oil in tile form of an emulsion. In practice, combhstion of sus-20 pended soli.d fuels has proven relatively difficult. Prob-lems often arise due to clogging of the fuel ports or nozzles, wllich can lead to irregular fuel and air supply, causing a reduction in combustion efficiency.
The US Patellt 4,726,760 discloses a burner by W~liC~I a cen-tral injection port opening into the combustion chamber is provided witll a continuous knife edge facing the center axis of the port. A plu~-ality of air inlet ports are evenly distributed about tlle circumference of the knife edge port and the inlet ports are connected to a variable source of compressed air to aid atomization.
Even Wit~l tllis arrangement o~ the US Patent, the atomiz-ation of tlle fuels coulcl be improved. The mixing of the i - 2 - 21817~18 uel3 Wit~l air also appears to be insufficient, limiting tlle acllievable degree oE combustion efficiency.
It is tllerefore an obje~-t of tlle present inven~:ion to prov-5 ide an apparatus for burning liquid fuels by whicll atomiz-ation of tlle fuel can be improved and by which a better mixing of the atomized Euel with combustion air can be acllieved to thereby improve combustion efficiellcy.
lo ~ummarv of the i nventi In accordance wit~l tlle ]?resent invention, an apparatus for burning liquid fuels to be introduced into a combustion chanlber is provided, wllere t~le liquid fuels preferably 15 comprise lleating oils or heavy oils. In adaition, solid fuels in pulveri:~ed form such as lignite coal, bituminous coal, gas coal, I?eat or the like can be f ired w~lell admixed to a suitable carrier liquid.
2~ T~le apparatus comprises a central port arranged at a down-stream end along a longitudinal axis of tlle apparatus, wllic}l serves as t~le supl~ly opening into a combustion c~lam-ber. A rirst plurality of inlet ports are arranged Goncen-trically about the longitudinal axis ~or introducing a 25 first fuel and/or air f~ ow into a space immediately up-stream of tlle central port. These inlet ports preferably supply a relatively lligll-speed air flow from a compressed air source. More preferably, tlle center axes of tlle inlet ports are arranged sliglltly oblique to a radial direction 30 rom tlle longitudinal a}2is, to thereby impart a rotational or vortex-type motion in the fuel-air mixture to be formed.
A second plurality of irllet ports is also arranged concen-trically about the longi.tudinal axis, wllere tllis second 35 plurality of inlet ports introduces a second fuel and/or ., ~
~ 3 - 218 1~48 air flow, wllich substantially intersects the inlet flows of the first plurality of inlet ports. T}le second plurality of illlet ports preferably ~lave their center axes arranged ge}l-erally alollg t~le longitudinal direction. Prererably t~le 5 first and second plurality of inlet ports comprise the same number of ports respect ively and the flow from the res-pective ports intersect when entering the space before tlle central port at an angle of about 60 to 90.
10 In a preferred embodiment, tlle first plurality of ports in-ject compressed air int~ the space, while t~le second plur-ality of ports inj ect fuel at an intersecting angle of about 90 witll the comp]^essed air flow.
Witll tlle ahove arrangement of intersecting inlet ports, llighl; ef~icient atomization of tlle liquid ~uel can be ob-tained wit~l respect to droplet size and distribution. In a preferred embodiment, vortex flow can be simultaneously ac~lieved of the fuel-ai]^ mixture exiting the central port 20 of: t~le burner.
Brief descriPtion of t;he drawinqs Tlle invention will IIOW ~e described in more detail Wit~l 25 reference to an embodiment of the apparatus as illustrated in tlle drawing of Figs. 1 and 2.
Fig. 1 sllows a cross-section along the longitudinal axis of tlle burner apparatus according to an embodiment of f:he 30 presellt invention.
Fig. 2 shows a preferred arrangement of the ~irst inlet ports witll respect to t~le second inlet ports.
~ 4 ~ 21817~8 T~le elements necessary for the actual operatioll of ~ e burning apparatus of the present inve~ltion, for example air sources and fuel sources as well as tlle combustion c~lamber itself are not shown in the drawing, ~lowever will be known 5 to tllose skilled ill t~le present art.
Detailed descril~tion of the preferred embodiments The fuel burner illustrated in Fig . 1 comprises a j et body 36 extending about a longitudinal axi6 26. Tlle downstream end of tlle jet body 36 is fitted Wit~l a nozzle piece 50 wllich comprises a central fuel port 10 opening into a com-bustion c~lamber 16 (not shown in detail). The flow direc-tiOII is indicated by the arrows ill the lef t of Fig .
15 indicating f~lel and/or air streams flowing toward the nozzle piece 50. The central port 10 is preferably recessed or disposed upstream of an end wall IZ of t~le combustion chamber 16 as will be discussed below.
20 Tlle 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.
~le passage 14 supplies primary air for combustion, w~lich may be ellriched Wit~l higher temperature combustion gasses 25 in a recyclillg system. The term "primary air" used ~lereill-after is to be understood as air or a mixture of air and recycled combustion gasses. The air exiting t31e annular port 24 llas a flow velocity of about 100 to about 200 m/sec., preferably 120 to 140 m/sec.. The side walls 20 and 30 22 defining t~le annular port 24 are of conical configur-ation to provide a cone-shaped air flow wllich broadells as it enters t~le combustion chamber. Swirl or baffle plates are provided in passage 14 at an angle of about 70 to t~lereby give t~le primary air a vo~tex movemellt about the 35 longitudinal axis 26. T~le primary air is supplied to tlle I
21817~8 passage 1~ at a pressure o~ about 1000 to about 1200 mm E~20 ~
~ second passage 18 is ~)rovided concentrically about pas-5 sage 14 and defined by cln inner jacket 38 and an outer ~acket 3g. Passage 18 at its downstream end merges into a second annular inlet port 28 defined by tlle conical side walls 30 and 32. Tlle second annular inlet llowever is dir-ected to form a converg-ing conical flow of secondary air, 10 W~liC~ ltersects Wit~l tl~e f~rpi:~n~l; ng conical profil~ of primary air from tlle fi]-st annular input port 24. Swirl baf1es may also be located in passage 18 to impart a vor-tex ~low of secondary air if desired. 1~ deflection angle of 40 to 45 of tlle baffl~s with respect to tlle lollgitudinal 15 axis 26 is preferred. T~le discharge of velocity oi tlle secondary air is preferably in the rallge of 120 to 180 m/sec., more preferably 130 to 150 m/sec.. T~le intersection of tlle collically converging secondary air witll Lhe conic-ally ~p~n~ g primary air provides additional agitation 20 and mixing of ~ e fuel-air mixture sllortly aLter it enters illtO ~le combustion cha~nber 16. The secondary air is pref-erably fed into tlle passage 18 at a pressure of about 1000 to abo~lt 1200 mm H2O. Tlle vortex deflectioll angle of tlle secolldary air when employed is preferably in t~le same dir-25 ection as t~le deflectioll of the primary air. ~s with tlleprimary air, tlle secolldary air can also be admixed witl combustion gasses from the furnace as desired.
Tlle discllarge velocities of the primary and secondary air 30 from tlle annular outlets 24 and 28 respectively gellerally remain tlle same under most operating conditions from start-up to full load. Depend:ing on tlle ~pe of fuel being com-busted, tlle discllarge velocity and/or discllarge volume can be varied by increasing or decreasing the gap widtll of the 35 annular ports 24 and 28. This is accomplis~led by axial - 6 - 21817~8 displacement of t~e annular mout~l piece 34 connected Wit~
~ile tubular jacket 33 which separates tlle two passages 14 alld 18.
5 Ill accordance Wit~l the present invention, the burner appar-atus is provided with a particular configuration of tlle nozzle piecc 50, whicll comprises the central port 10.
Embodimellts of tlle nozzle construction are sllowll in Figs. 1 and 2. Ill the preferred embodiments, t~le central port 10 is 10 defined by a continuous, circular knife edge 40 facirlg tow-ard the longitudinal axis 26. The knife edge has taperillg side portions seen in cross-section and, preferably ~las a triangular-like cross-section Wit~l sloping sides 43 as sllown in Fig, 1.
: ' -According to the invention a first plurality of air inlet ports 42 are! arran~ed ccncentrically about tlle 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 20 49 is gellerally of cylindrical form and communicates witll bot~l tlle i:irst inlet ports 42 and the second inlet ports 47 to be discussed below. ~'he inner surface 60 of ~lle nozzle piece 50, whlc~l faces the part 10 may be concave in shape as shown in Fig. 2.
Preferably, th~ 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, w~ich 30 generally determines t~le flow direction into the space 49.
Preferably tlle center a}ces of the inlet ports 42 are arrangod at an angle in the range of 60 to 90 witll respect to the longitudinal axis 26, preferably at an angle in the range of 70 to ~0 ., ~ 7 ~ 21817~8 A second plurality of in.let ports is also arranged concen-trically about the longitudinal axis 26 in the nozzle piece 50. T~lese 6econd inlet E~orts 47 are arranged to introduce a second fuel and/or air flow into the space 49, where tlle second flow from tlle inlet ports 47 substalltially illter- =
sects the first flow from the inlet ports 42 as can best be seell in Fig . 3 . Fig . 3 represents a f ront view along the longitudillal axis 26 looking in tlle upstream directioli.
The second plurality of inlet ports 47 as seen in Fig. 1 or Fig. 2 are defined as each having a center axis arranged at an angle in tlle range of 0 to 30 Wit~l respect to tlle longitudinal axis 26.
As S~IOWII in Fig. 3, tlle inlet ports 42 are also directed obliquely to a radial ray extending from the longitudillal axis 26 by an angle o~ of 5 to 40, preferably 15 to 30.
T~lis 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 t~le fuel-air mixture form-ed in tlle space 49. This vortex motion originati~lg in the space 49 con~ pR with downstream flow out of the central port 10 and into t~le coirbustion chamber 16. As can be seen from Fig. 3, one Inlet port 42 is provided for eac~ llet port ~7. The number of first and second inlet ports 42, 47 respectively is variable, preferably 6 to 14, more prefer-ably 10 to 12 set:s of ports are provided. To acllieve best fuel-air mixture and atomization, t~le ports 42 and 47 are arranged to intersect at an angle of about 60 to 90, wllere an angle in t~le range of 80 to 90 is most pref-erred .
Again ~referring to Fig. 1, the central port 10 and the first and second pluralities of inlet ports 42, 47 are ., 8- 21817~8 provided in a single no~zle piece 50 This nozzle piece 50 is fitted, for example, by threaded connection, to tlle dowllstream end of a jet body 36. Tlle jet body is mounted at an upstream end (not shown) in a manner that it can be 5 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 mout~l piece 3~ to form the first annular air inlet 24 .
T~le axial displacement of the jet body 36 allows adjustlnent -of tlle no~zle 50 Wit~l respect to the combustion wall 12.
This feature allows adj~stment of the vortex flow out of t~le port 10, depending on the type of fuel being burned and 15 in conjunction t~lerewith the amount and velocity of primary and secondary air flows. It is particularly preferred tllat tile j et body be adjusted such that the central port 10 is located sliglltly upstream of the combustion wall 12. Fur-t~le~more, for burning heating oil, it is preferred t~lat the 20 central port 10 of t~le nozzle piece 50 be disposed upstream of tlle end extension of the annular mouth piece 34.
Preferably, t~le fuel burner of the present invention is operated by supplying fuel, preferably oil, t~lroug}l ~lle 25 second inlet ports 47 provided in common fluid communication with an upstream source of fuel (not shown in Fig. 1). In t~lis case, t~le ~irst inlet ports 42 are pro~-ided in common fluid communication via passage 44 wit~l a preferably variable source of compressed air.
Alternatively, fuel can be injected in the first inlet ports 42 w~lile compressed air is injected i~l the first inlet ports 47.
.
218~7~
With tlle de~ined struct~ral arrangement, t~le primary air exiting from t~le annular port 24 envelopes t~le vortex flow of fuel-air mixture exi~ing from the space 49. This spray cone or expanding cone is then almost immediately inter-S sected by t~le converging cone of secondary air whicllprovides further mixing and secondary combustion further illtO t~le combustion chamber.
~11 of tlle f eatures disclosed in the present papers are 10 claimed as being essential to t~le invention to t~le extent to w~lich t~ley are novel over the prior art eitller individ-ually or in combination.
Claims (9)
1. A burner for burning liquid fuels when introduced into a combustion chamber, said burner comprising a nozzle piece having:
a central port arranged on a downstream end of a longitudinal axis of an 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 said space is partially defined by a concave inner surface of the nozzlepiece, the second plurality of inlet ports having their outlets in said concave surface, and wherein the first plurality of inlet ports have central axes directed obliquely to a radial ray extending from the longitudinal axis by an angle a in the range of 5° to 40° to provide a vortex flow of the fuel-air mixture.
a central port arranged on a downstream end of a longitudinal axis of an 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 said space is partially defined by a concave inner surface of the nozzlepiece, the second plurality of inlet ports having their outlets in said concave surface, and wherein the first plurality of inlet ports have central axes directed obliquely to a radial ray extending from the longitudinal axis by an angle a in the range of 5° to 40° to provide a vortex flow of the fuel-air mixture.
2. The burner of Claim 1, wherein the number of the first and second plurality of inlet ports is the same, and the first and second flows from the respective inlet ports intersect one another at an angle of 60° to 90°.
3. The burner of Claim 2, wherein said first plurality of inlet ports have centre axes determining the flow direction into said space, and said axes arranged at an angle in the range of 60° to 90° with respect to said longitudinal axis.
4. The burner of Claim 2, wherein said second plurality of inlet ports have centre 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.
5. The burner of Claim 2, wherein said central port is defined by a circular knife edge of substantially triangular cross-section.
6. The burner 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.
7. The burner of Claim 1, wherein said nozzle piece is fitted on the downstream end of a jet body, said jet body being mounted to be axially displaceable along said longitudinal axis of the apparatus.
8. The burner of Claim 7, wherein the downstream end of the jet body is surrounded by an axially displaceable annular mouthpiece having a down stream extension, an inner surface of which, along with an outer surface of the jet body, defines a first annular air inlet and an outer surface of the annular mouthpiece, along with an inner surface of a jacket, defines a second annular air inlet.
9. The burner of Claim 8, wherein the downstream end of said jet body with nozzle piece is disposed upstream of the downstream end extension of said annular mouthpiece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002181748A CA2181748C (en) | 1996-07-22 | 1996-07-22 | Burner for liquid fuels |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002181748A CA2181748C (en) | 1996-07-22 | 1996-07-22 | Burner for liquid fuels |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2181748A1 CA2181748A1 (en) | 1997-01-12 |
| CA2181748C true CA2181748C (en) | 1999-08-24 |
Family
ID=4158642
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002181748A Expired - Fee Related CA2181748C (en) | 1996-07-22 | 1996-07-22 | Burner for liquid fuels |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2181748C (en) |
-
1996
- 1996-07-22 CA CA002181748A patent/CA2181748C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CA2181748A1 (en) | 1997-01-12 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |