WO2020203518A1 - 予混合燃焼バーナ - Google Patents
予混合燃焼バーナ Download PDFInfo
- Publication number
- WO2020203518A1 WO2020203518A1 PCT/JP2020/013210 JP2020013210W WO2020203518A1 WO 2020203518 A1 WO2020203518 A1 WO 2020203518A1 JP 2020013210 W JP2020013210 W JP 2020013210W WO 2020203518 A1 WO2020203518 A1 WO 2020203518A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- peripheral wall
- mixing
- header chamber
- cooling passage
- fuel
- Prior art date
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
- F23D14/58—Nozzles characterised by the shape or arrangement of the outlet or outlets from the nozzle, e.g. of annular configuration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/62—Mixing devices; Mixing tubes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/66—Preheating the combustion air or gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/78—Cooling burner parts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Definitions
- the present invention relates to a premixed combustion burner that premixes gas fuel and air and ejects them.
- a premixed combustion burner in which a premixed mixture in which fuel and oxygen are mixed in an optimum ratio in advance is burned at a crater.
- the premixed combustion burner has an advantage that a stable flame can be created by premixing air with the fuel.
- a premixed combustion burner burns a gas fuel with a high combustion speed such as hydrogen gas, the flame approaches the vicinity of the crater, causing high temperature of parts, oxidative thinning, melting loss, and flashback. There is a problem that it occurs.
- the flashback is a phenomenon in which the flame returns from the crater to the gas supply side.
- Patent Document 1 proposes a technique for preventing flashback in a premixed combustion burner.
- the premixed combustion burner of Patent Document 1 has a fuel passage including a folded portion for folding and circulating fuel between the base end side and the terminal side, a premixed air passage surrounding the fuel passage, and fuel passing through the fuel passage. It includes a fuel introduction unit that introduces air from the base end side to the end side of the premixture passage, and an air supply part that supplies air to the premixture passage on the base end side.
- the outer periphery of the fuel passage is cooled by passing the low-temperature fuel through the folded portion provided in the fuel passage. The flame that has entered the premixture passage interferes with the outer circumference of the low temperature fuel passage and is extinguished.
- the premixed combustion burner of Patent Document 1 can prevent flashback, but the temperature rise, oxidative thinning, and melting of parts caused by the flame approaching the vicinity of the crater. It cannot be said that the loss has been fully resolved.
- the present invention has been made in view of the above circumstances, and an object of the present invention is to provide a technique for preventing high temperature, oxidative thinning and melting damage of parts caused by a flame approaching the vicinity of a crater in a premixed combustion burner. To make a suggestion.
- the premixed burner according to one aspect of the present invention is A mixing portion having a first peripheral wall centered on the burner axis, a mixing region for mixing gas fuel and air is formed on the inner circumference, and a plurality of air supply ports arranged in the circumferential direction are opened on the first peripheral wall.
- a premixed air passage provided on the tip end side of the mixing portion, having a second peripheral wall centered on the burner axis, and a premixed air passage continuous with the mixing region is formed on the inner circumference of the second peripheral wall, and the second peripheral wall.
- the nozzle part where the cooling passage is formed inside the A first header chamber, a fuel supply port for supplying gas fuel to the first header chamber, a second header chamber, and the second header chamber are communicated with the mixing region, which are provided on the base end side of the mixing portion. It is provided with a header part in which a fuel injection port is formed. Inside the first peripheral wall, an outward path connecting the first header chamber and the inlet of the cooling passage and a return path connecting the outlet of the cooling passage and the second header chamber are formed. is there.
- a series of fuel passages including a first header chamber, an outward passage, a cooling passage, a return passage, and a second header chamber are formed, and low-temperature gas fuel flows through these fuel passages.
- the peripheral wall of the nozzle portion and the peripheral wall of the mixing portion are cooled by heat exchange with the low-temperature gas fuel flowing inside.
- the peripheral wall of the nozzle portion is cooled, and the temperature rise of the surface of the peripheral wall is suppressed. Therefore, the formation of oxide scale on the surface of the peripheral wall of the nozzle portion is suppressed, and the oxidation thinning of the nozzle portion is suppressed.
- the temperature rise of the premixed air passing through the premixed air passage is suppressed by cooling the nozzle portion, so that the increase in the combustion speed of the premixed air can be suppressed. Further, since the temperature rise of the premixture is suppressed by cooling the peripheral wall of the mixing portion, it is possible to more effectively suppress the increase in the combustion rate of the premixture.
- the premixed combustion burner in the premixed combustion burner, the increase in the combustion speed of the premixed mixture is suppressed, so that the flame can be kept away from the crater as compared with the case where the nozzle portion is not cooled. As a result, the temperature rise of the nozzle portion can be further suppressed, and the melting damage of the nozzle portion due to the flame can be prevented. Further, in the premixed combustion burner having the above configuration, the occurrence of flashback is suppressed by suppressing the increase in the combustion speed as described above.
- FIG. 1 is a cross-sectional perspective view of a premixed combustion burner according to an embodiment of the present invention.
- FIG. 2 is a cross-sectional view of the premixed combustion burner shown in FIG.
- FIG. 3 is a sectional view taken along line III-III of FIG.
- FIG. 4 is a sectional view taken along line IV-IV of FIG.
- FIG. 5 is a sectional view taken along line VV of FIG.
- FIG. 6 is a sectional view taken along line VI-VI of FIG.
- FIG. 7 is a sectional view taken along line VII-VII of FIG.
- FIG. 8 is a cross-sectional view taken along the line VIII-VIII of FIG.
- FIG. 9 is a sectional view taken along line IX-IX of FIG.
- FIG. 10 is a developed view of a circumferential cross section of the peripheral wall of the nozzle portion, showing the cooling passage 4A according to the first modification.
- FIG. 11 is a developed view of a circumferential cross section of the peripheral wall of the nozzle portion, showing the cooling passage 4B according to the modified example 2.
- FIG. 1 is a cross-sectional perspective view of the premixed combustion burner 1 according to the embodiment of the present invention
- FIG. 2 is a cross-sectional view of the premixed combustion burner 1 shown in FIG. 3 to 9 are cross-sectional views of reference numerals III to IX corresponding to the drawing numbers of the premixed combustion burner 1 shown in FIG. 2, respectively.
- the burner axis A is defined at the center thereof, and the extension direction of the burner axis A is defined as the axial direction A1.
- the axial direction A1 is parallel to the ejection direction of the premixed gas fuel and air.
- the premixed combustion burner 1 exhibits a thick-walled cylindrical shape with the base end closed and the tip open with the burner axis A as the axis.
- the premixed combustion burner 1 has a nozzle portion 11, a mixing portion 12 on the proximal end side of the nozzle portion 11, and a header portion 13 on the proximal end side of the mixing portion 12.
- the nozzle portion 11 has a thick cylindrical shape centered on the burner axis A.
- a premixed air passage 18 is formed on the inner circumference of the nozzle portion 11.
- the tip of the nozzle portion 11 is a crater 14 from which the premixture flowing in the axial direction A1 through the premixture passage 18 is ejected.
- a cooling passage 4 through which gas fuel passes is stretched inside the second peripheral wall 111 of the nozzle portion 11.
- the cooling passage 4 has a plurality of inlets 41 and outlets 42 at the base end portion of the nozzle portion 11.
- the inlet 41 and the outlet 42 are alternately arranged in the circumferential direction C1 of the nozzle portion 11.
- four sets of inlets 41 and outlets 42 are alternately arranged in the circumferential direction.
- FIG. 9 is a developed view of a circumferential cross section of the second peripheral wall 111 of the nozzle portion 11.
- the cooling passage 4 includes a plurality of straight portions 45 arranged in the circumferential direction C1 of the nozzle portion 11, a folded-back portion 46 connecting the adjacent straight portions 45 at the tip portion of the nozzle portion 11, and a nozzle portion. It has a folded-back portion 47 that connects adjacent straight portions 45 at the base end portion of 11.
- the folded-back portion 46 at the tip end portion and the folded-back portion 47 at the base end portion are alternately provided in a series of cooling passages 4. That is, the cooling passage 4 repeats the straight portion 45, the folded portion 46, the straight portion 45, and the folded portion 47 in this order.
- Such a cooling passage 4 advances in the circumferential direction C1 of the nozzle portion 11 while meandering in the axial direction A1.
- the mixing portion 12 has a thick cylindrical shape centered on the burner axis A.
- a mixing region 15 in which gas fuel and air are mixed is formed on the inner peripheral side of the mixing portion 12.
- the mixing region 15 and the premixed air passage 18 are continuous in the axial direction A1.
- a plurality of air supply ports 51 for introducing air are opened in the first peripheral wall 121 of the mixing portion 12.
- the plurality of air supply ports 51 are arranged in the circumferential direction. Between the adjacent air supply ports 51, there is a pillar portion 52 extending in the axial direction A1.
- An outward path 53 or a return path 54 extending in the axial direction A1 is provided in each pillar portion 52.
- the outward path 53 is connected to the inlet 41 of the cooling passage 4.
- the return path 54 is connected to the outlet 42 of the cooling passage 4. Therefore, similarly to the inlet 41 and the outlet 42 of the cooling passage 4, the outward path 53 and the return path 54 are alternately arranged in the circumferential direction.
- the header section 13 includes a first header chamber 61, a fuel supply port 64 for supplying gas fuel to the first header chamber 61, a second header chamber 62, and a second header chamber 62.
- a fuel injection port 65 is formed so as to communicate with the mixing region 15.
- the first header chamber 61 and the second header chamber 62 are arranged in the axial direction A1, and the first header chamber 61 is on the proximal end side of the second header chamber 62.
- the first header chamber 61 is connected to the gas fuel supply source via the fuel supply port 64. Gas fuel is supplied to the first header chamber 61 through the fuel supply port 64. Further, the first header chamber 61 is provided with an outward connection portion 53a. The outbound connection 53a is connected to the outbound 53 of the mixing unit 12. As a result, the gas fuel in the first header chamber 61 flows out to the outward path 53 via the outward path connecting portion 53a.
- the second header chamber 62 is provided with a return connection portion 54a.
- the return path connecting portion 54a is connected to the return path 54 of the mixing section 12.
- gas fuel flows into the second header chamber 62 from the return path 54.
- a plurality of fuel injection ports 65 are opened in the second header chamber 62.
- Each fuel injection port 65 opens parallel to the axial direction A1 toward the mixing region 15.
- the gas fuel in the second header chamber 62 is ejected in the axial direction A1 into the premixed air passage 18 through the fuel injection port 65.
- the gas fuel pumped from the gas fuel supply source flows into the first header chamber 61 through the fuel supply port 64.
- the gas fuel flowing into the first header chamber 61 is distributed to a plurality of outward paths 53 arranged in the circumferential direction, passes through the outward path 53 in the axial direction A1, and reaches the inlet 41 of the cooling passage 4.
- the gas fuel that has flowed into the cooling passage 4 from the inlet 41 passes through the cooling passage 4 and reaches the outlet 42.
- the second peripheral wall 111 of the nozzle portion 11 is cooled by the low-temperature gas fuel passing through the cooling passage 4.
- the gas fuel discharged from the outlet 42 of the cooling passage 4 passes through the return path 54 in the axial direction A1 and flows into the second header chamber 62.
- the gas fuel that has flowed into the second header chamber 62 is ejected into the mixing region 15 through the plurality of fuel injection ports 65.
- the air introduced from the air supply port 51 and the gas fuel are mixed to generate a premixture.
- the generated premixture passes through the premixture passage 18 in the axial direction A1 and is ejected from the crater 14.
- the premixed combustion burner 1 is provided on the mixing portion 12, the nozzle portion 11 provided on the tip side of the mixing portion 12, and the base end side of the nozzle portion 11. It includes a header unit 13.
- the mixing portion 12 has a first peripheral wall 121 centered on the burner axis A, a mixing region 15 for mixing gas fuel and air is formed on the inner circumference, and a plurality of air arranged in the circumferential direction on the first peripheral wall 121.
- the supply port 51 is open.
- the nozzle portion 11 has a second peripheral wall 111 centered on the burner axis A, a premixed air passage 18 continuous with the mixing region 15 is formed on the inner circumference, and a cooling passage 4 is formed inside the second peripheral wall 111.
- the header unit 13 is a fuel injection port that communicates the first header chamber 61, the fuel supply port 64 for supplying gas fuel to the first header chamber 61, the second header chamber 62, and the second header chamber 62 with the mixing region 15. 65 is formed. Inside the first peripheral wall 121 of the mixing portion 12, an outward path 53 connecting the first header chamber 61 and the inlet 41 of the cooling passage 4, and a return path 54 connecting the outlet 42 of the cooling passage 4 and the second header chamber 62. And are formed.
- a series of fuel flow paths including a first header chamber 61, an outward path 53, a cooling passage 4, a return path 54, and a second header chamber 62 are formed, and the fuel passage is cooled at a low temperature. Gas fuel flows. As a result, the second peripheral wall 111 of the nozzle portion 11 and the first peripheral wall 121 of the mixing portion 12 are cooled by heat exchange with the low-temperature gas fuel flowing inside.
- Oxidation thinning of the nozzle portion 11 proceeds due to the contact between the high-temperature premixture and the second peripheral wall 111 of the nozzle portion 11 to generate an oxide scale on the surface of the second peripheral wall 111, and cracking or peeling of this scale. ..
- the second peripheral wall 111 of the nozzle portion 11 is cooled, and the temperature rise of the surface of the second peripheral wall 111 is suppressed. Therefore, the formation of oxide scale on the surface of the second peripheral wall 111 of the nozzle portion 11 is suppressed, and the oxidation thinning of the nozzle portion 11 is suppressed.
- the temperature rise of the premixed air passing through the premixed air passage 18 is suppressed by cooling the nozzle portion 11, so that the combustion rate of the premixed air is increased. The rise can be suppressed. Further, since the temperature rise of the premixture is also suppressed by cooling the first peripheral wall 121 of the mixing portion 12, it is possible to more effectively suppress the increase in the combustion rate of the premixture.
- the flame can be kept away from the crater 14 as compared with the case where the nozzle portion 11 is not cooled. As a result, the temperature rise of the nozzle portion 11 can be further suppressed, and the melting damage of the nozzle portion 11 due to the flame can be prevented.
- Flashback occurs when the combustion speed is faster than the flow velocity of the premixture.
- the occurrence of flashback is suppressed by suppressing the increase in the combustion speed as described above.
- the premixed combustion burner 1 according to the present embodiment since the second peripheral wall 111 of the nozzle portion 11 is continuously cooled, even if the flame enters the premixed air passage 18 through the crater 14, even if the flame enters the premixed air passage 18. The fire is extinguished by contacting the cooled second peripheral wall 111. Therefore, in the premixed combustion burner 1, flashback can be reliably prevented.
- Hydrogen gas has a faster combustion rate than natural gas. Therefore, a burner that burns a fuel containing hydrogen gas is more likely to cause a flashback than a burner that burns only natural gas as a fuel.
- the premixed combustion burner 1 according to the present embodiment since the occurrence of flashback is suppressed as described above, it is possible to use high-concentration hydrogen gas that cannot be used in a normal burner as fuel.
- the cooling passage 4 has a plurality of straight portions 45 arranged in the circumferential direction C1 of the nozzle portion 11 and adjacent straight portions at the tip end portion or the base end portion of the nozzle portion 11. It has folded portions 46 and 47 connecting the 45, and advances in the circumferential direction C1 of the nozzle portion 11 while meandering in the axial direction A1.
- the folded-back portion 46 is provided at the tip portion of the nozzle portion 11 having the highest temperature.
- the second peripheral wall 111 of the nozzle portion 11 collides with the gas fuel flowing through the cooling passage 4, so that the second peripheral wall 111 of the nozzle portion 11 can be cooled more effectively.
- the cooling passage 4 meanders inside the second peripheral wall 111 of the nozzle portion 11, whereby gas fuel can be evenly passed through the second peripheral wall 111. Therefore, it is possible to prevent the cooling of the second peripheral wall 111 from being biased and the gas fuel from being stagnant in the cooling passage 4.
- the mixing section 12 has a plurality of sets of outward paths 53 and return paths 54 extending in the axial direction A1 of the burner axis A, and the outward paths 53 and return paths 54 are the circumferences of the mixing section 12. They are arranged alternately in the direction.
- the outward path 53 through which the gas fuel flows before entering the cooling passage 4 and the return path 54 through which the gas fuel flows after passing through the cooling passage 4 are arranged in the circumferential direction. Appears alternately. As a result, the first peripheral wall 121 of the mixing unit 12 can be uniformly cooled.
- cooling passage 4 can be changed as follows, for example.
- FIG. 10 is a developed view of a circumferential cross section of the second peripheral wall 111A of the nozzle portion 11A, showing the cooling passage 4A according to the first modification.
- the cooling passage 4A according to the first modification meanders in the second peripheral wall 111A of the nozzle portion 11A in the circumferential direction C1. More specifically, the cooling passage 4A is adjacent to the introduction portion 81 extending in the axial direction A1, the bent portion 82 provided at the tip of the nozzle portion 11, and the plurality of arc portions 83 arranged in the axial direction A1. It has a folded portion 84 that connects the arc portions.
- the cooling passage 4 first reaches the tip end portion of the nozzle portion 11 by the introduction portion 81 and the bent portion 82, and then repeats the arc portion 83 and the folded portion 84 in the circumferential direction C1 of the nozzle portion 11. Proceed in the axial direction A1 while meandering.
- the gas fuel flows from the tip portion of the nozzle portion 11 having the highest temperature first, so that the tip portion of the nozzle portion 11 is positively cooled.
- FIG. 11 is a developed view of a circumferential cross section of the second peripheral wall 111B of the nozzle portion 11B, showing the cooling passage 4B according to the modified example 2.
- the cooling passage 4B according to the modified example 2 is a tubular or divided tubular space 86 formed in the second peripheral wall 111B of the nozzle portion 11B.
- a straightening vane 87 that guides the gas fuel entering from the inlet 41 provided at the base end portion of the nozzle portion 11 to the tip end portion of the nozzle portion 11 is provided at an appropriate position.
- the straightening vane 87 also functions as a rib for reinforcing the second peripheral wall 111B.
- cooling passage 4B In such a cooling passage 4B, the flow of gas fuel tends to be somewhat biased as compared with the cooling passage 4 according to the embodiment, but the cooling passage 4B is easy to process.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
Description
バーナ軸線を中心とする第1周壁を有し、内周にガス燃料と空気とを混合させる混合領域が形成され、前記第1周壁に周方向に並ぶ複数の空気供給口が開口した混合部と、
前記混合部の先端側に設けられ、前記バーナ軸線を中心とする第2周壁を有し、前記第2周壁の内周に前記混合領域と連続する予混合気通路が形成され、前記第2周壁の内部に冷却通路が形成されたノズル部と、
前記混合部の基端側に設けられ、第1ヘッダ室、前記第1ヘッダ室へガス燃料を供給する燃料供給口、第2ヘッダ室、及び、前記第2ヘッダ室と前記混合領域を連通する燃料噴射口が形成されたヘッダ部と、を備え、
前記第1周壁の内部に、前記第1ヘッダ室と前記冷却通路の入口とを接続する往路と、前記冷却通路の出口と前記第2ヘッダ室とを接続する復路とが形成されているものである。
図10は、変形例1に係る冷却通路4Aを示す、ノズル部11Aの第2周壁111Aの周方向断面の展開図である。図10に示すように、変形例1に係る冷却通路4Aは、ノズル部11Aの第2周壁111A内を周方向C1に蛇行している。より詳細には、冷却通路4Aは、軸方向A1に延びる導入部81と、ノズル部11の先端部に設けられた折曲部82と、軸方向A1に並ぶ複数の円弧部83と、隣接する円弧部を接続する折返部84とを有する。そして、冷却通路4は、先ず、導入部81及び折曲部82によってノズル部11の先端部へ到達してから、円弧部83と折返部84とを繰り返すことによって、ノズル部11の周方向C1に蛇行しながら軸方向A1へ進む。
図11は、変形例2に係る冷却通路4Bを示す、ノズル部11Bの第2周壁111Bの周方向断面の展開図である。図11に示すように、変形例2に係る冷却通路4Bは、ノズル部11Bの第2周壁111B内に形成された、筒状又は分割筒状の空間86である。空間86内には、ノズル部11の基端部に設けられた入口41から入ったガス燃料を、ノズル部11の先端部に導く整流板87が適宜位置に設けられている。整流板87は第2周壁111Bを補強するリブとしても機能する。
4,4A,4B:冷却通路
11,11A,11B:ノズル部
12 :混合部
13 :ヘッダ部
14 :火口
15 :混合領域
18 :予混合気通路
41 :入口
42 :出口
45 :直線部
46 :折返部
47 :折返部
51 :空気供給口
52 :柱部
53 :往路
54 :復路
61 :第1ヘッダ室
62 :第2ヘッダ室
64 :燃料供給口
65 :燃料噴射口
81 :導入部
82 :折曲部
83 :円弧部
84 :折返部
86 :空間
87 :整流板
111,111A,111B:第2周壁
121 :第1周壁
A :バーナ軸線
A1 :軸方向
C1 :周方向
Claims (3)
- バーナ軸線を中心とする第1周壁を有し、内周にガス燃料と空気とを混合させる混合領域が形成され、前記第1周壁に周方向に並ぶ複数の空気供給口が開口した混合部と、
前記混合部の先端側に設けられ、前記バーナ軸線を中心とする第2周壁を有し、前記第2周壁の内周に前記混合領域と連続する予混合気通路が形成され、前記第2周壁の内部に冷却通路が形成されたノズル部と、
前記混合部の基端側に設けられ、第1ヘッダ室、前記第1ヘッダ室へガス燃料を供給する燃料供給口、第2ヘッダ室、及び、前記第2ヘッダ室と前記混合領域を連通する燃料噴射口が形成されたヘッダ部と、を備え、
前記第1周壁の内部に、前記第1ヘッダ室と前記冷却通路の入口とを接続する往路と、前記冷却通路の出口と前記第2ヘッダ室とを接続する復路とが形成されている、
予混合燃焼バーナ。 - 前記冷却通路は、前記ノズル部の周方向に並ぶ複数の直線部と、前記ノズル部の先端部又は基端部において隣接する前記直線部を接続する折返部とを有し、前記バーナ軸線の軸方向に蛇行しながら前記ノズル部の周方向に進む、
請求項1に記載の予混合燃焼バーナ。 - 前記混合部は前記バーナ軸線の軸方向に延びる複数組の前記往路及び前記復路を有し、前記往路及び前記復路が前記混合部の周方向に交互に並ぶ、
請求項1又は2に記載の予混合燃焼バーナ。
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202080025158.8A CN113646585B (zh) | 2019-03-29 | 2020-03-25 | 预混合燃烧器 |
EP20781866.7A EP3951262B1 (en) | 2019-03-29 | 2020-03-25 | Premixed combustion burner |
AU2020250404A AU2020250404B2 (en) | 2019-03-29 | 2020-03-25 | Premixed Combustion Burner |
CA3133218A CA3133218A1 (en) | 2019-03-29 | 2020-03-25 | Premixed combustion burner |
US17/599,784 US11892162B2 (en) | 2019-03-29 | 2020-03-25 | Premixed combustion burner |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2019066857A JP7260365B2 (ja) | 2019-03-29 | 2019-03-29 | 予混合燃焼バーナ |
JP2019-066857 | 2019-03-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2020203518A1 true WO2020203518A1 (ja) | 2020-10-08 |
Family
ID=72668392
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2020/013210 WO2020203518A1 (ja) | 2019-03-29 | 2020-03-25 | 予混合燃焼バーナ |
Country Status (7)
Country | Link |
---|---|
US (1) | US11892162B2 (ja) |
EP (1) | EP3951262B1 (ja) |
JP (1) | JP7260365B2 (ja) |
CN (1) | CN113646585B (ja) |
AU (1) | AU2020250404B2 (ja) |
CA (1) | CA3133218A1 (ja) |
WO (1) | WO2020203518A1 (ja) |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2643293A1 (de) * | 1976-09-25 | 1978-03-30 | Herbert Ahlgrimm | Oelbrenner |
JPH0842822A (ja) * | 1994-06-01 | 1996-02-16 | Boc Group Plc:The | 酸素−燃料燃焼機 |
WO2011044676A1 (en) * | 2009-10-14 | 2011-04-21 | Absolute Combustion International Inc. | Cooling jacket, heat transfer apparatus and heat recovery apparatus |
JP2015161460A (ja) * | 2014-02-27 | 2015-09-07 | 三菱日立パワーシステムズ株式会社 | バーナ |
JP2016090141A (ja) | 2014-11-05 | 2016-05-23 | 川崎重工業株式会社 | バーナ、燃焼器、及びガスタービン |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1254507A (en) * | 1917-02-05 | 1918-01-22 | Edward C Kahn | Liquid-fuel burner. |
GB1463663A (en) * | 1973-03-28 | 1977-02-02 | Shell Int Research | Porous media burner |
JP2886844B2 (ja) * | 1997-05-01 | 1999-04-26 | 川崎重工業株式会社 | 予混合型燃焼器を備えたガスタービン |
JP2003322314A (ja) * | 2002-04-30 | 2003-11-14 | Toho Gas Co Ltd | バーナ |
US7007477B2 (en) * | 2004-06-03 | 2006-03-07 | General Electric Company | Premixing burner with impingement cooled centerbody and method of cooling centerbody |
US8312722B2 (en) | 2008-10-23 | 2012-11-20 | General Electric Company | Flame holding tolerant fuel and air premixer for a gas turbine combustor |
JP2013174367A (ja) * | 2012-02-23 | 2013-09-05 | Hitachi Ltd | 予混合燃焼バーナ、燃焼器及びガスタービン |
JP6035123B2 (ja) * | 2012-11-26 | 2016-11-30 | 三菱日立パワーシステムズ株式会社 | ガスタービン燃焼器 |
JP6327826B2 (ja) | 2013-10-11 | 2018-05-23 | 川崎重工業株式会社 | ガスタービンの燃料噴射装置 |
CA2950566A1 (en) * | 2014-05-30 | 2015-12-03 | Kawasaki Jukogyo Kabushiki Kaisha | Combustion device for gas turbine engine |
US10234142B2 (en) * | 2016-04-15 | 2019-03-19 | Solar Turbines Incorporated | Fuel delivery methods in combustion engine using wide range of gaseous fuels |
-
2019
- 2019-03-29 JP JP2019066857A patent/JP7260365B2/ja active Active
-
2020
- 2020-03-25 AU AU2020250404A patent/AU2020250404B2/en active Active
- 2020-03-25 EP EP20781866.7A patent/EP3951262B1/en active Active
- 2020-03-25 CN CN202080025158.8A patent/CN113646585B/zh active Active
- 2020-03-25 US US17/599,784 patent/US11892162B2/en active Active
- 2020-03-25 WO PCT/JP2020/013210 patent/WO2020203518A1/ja unknown
- 2020-03-25 CA CA3133218A patent/CA3133218A1/en active Pending
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2643293A1 (de) * | 1976-09-25 | 1978-03-30 | Herbert Ahlgrimm | Oelbrenner |
JPH0842822A (ja) * | 1994-06-01 | 1996-02-16 | Boc Group Plc:The | 酸素−燃料燃焼機 |
WO2011044676A1 (en) * | 2009-10-14 | 2011-04-21 | Absolute Combustion International Inc. | Cooling jacket, heat transfer apparatus and heat recovery apparatus |
JP2015161460A (ja) * | 2014-02-27 | 2015-09-07 | 三菱日立パワーシステムズ株式会社 | バーナ |
JP2016090141A (ja) | 2014-11-05 | 2016-05-23 | 川崎重工業株式会社 | バーナ、燃焼器、及びガスタービン |
Non-Patent Citations (1)
Title |
---|
See also references of EP3951262A4 |
Also Published As
Publication number | Publication date |
---|---|
US20220146093A1 (en) | 2022-05-12 |
JP7260365B2 (ja) | 2023-04-18 |
EP3951262B1 (en) | 2024-05-22 |
AU2020250404A1 (en) | 2021-10-07 |
US11892162B2 (en) | 2024-02-06 |
JP2020165598A (ja) | 2020-10-08 |
CN113646585A (zh) | 2021-11-12 |
CN113646585B (zh) | 2024-01-09 |
AU2020250404B2 (en) | 2023-01-05 |
EP3951262A1 (en) | 2022-02-09 |
EP3951262A4 (en) | 2022-12-28 |
CA3133218A1 (en) | 2020-10-08 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4704900B2 (ja) | 燃焼加熱器 | |
US8365535B2 (en) | Fuel nozzle with multiple fuel passages within a radial swirler | |
JP2010048542A (ja) | 希薄直接噴射拡散チップ及び関連方法 | |
JP2017227431A (ja) | パイロット予混合ノズルおよび燃料ノズル組立体 | |
JP2012122715A (ja) | 空気多段拡散ノズル | |
KR20190116395A (ko) | 연소기용 노즐, 연소기 및 가스 터빈 | |
WO2020203518A1 (ja) | 予混合燃焼バーナ | |
JP3942466B2 (ja) | シングルエンド型ラジアントチューブ燃焼装置 | |
JP2005195214A (ja) | 燃焼装置 | |
KR20040058351A (ko) | 질소산화물 저 배출 연소기용 연소 챔버/벤츄리 냉각장치및 방법 | |
JP2005188776A (ja) | 熱風発生装置および制御方法 | |
WO2016063791A1 (ja) | 燃焼器、ガスタービン | |
JP2003279002A (ja) | 蓄熱式ラジアントチューブ燃焼装置 | |
JP4674001B2 (ja) | 貫流ボイラ | |
JP7230757B2 (ja) | 燃焼器 | |
JP7188341B2 (ja) | 燃焼器 | |
JP2004301369A (ja) | 加熱炉用の燃焼装置 | |
JP4953483B2 (ja) | 貫流ボイラ | |
JP2018009755A (ja) | 小型渦流燃焼器 | |
JPH0478886B2 (ja) | ||
JP3642037B2 (ja) | 旋回燃焼器 | |
JP2740138B2 (ja) | ジェットバーナー | |
JP2021055869A (ja) | 燃焼器 | |
JP3851831B2 (ja) | 燃焼装置 | |
JPH09250714A (ja) | ガス燃焼装置 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 20781866 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 3133218 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
ENP | Entry into the national phase |
Ref document number: 2020250404 Country of ref document: AU Date of ref document: 20200325 Kind code of ref document: A |
|
ENP | Entry into the national phase |
Ref document number: 2020781866 Country of ref document: EP Effective date: 20211029 |