EP3819540B1 - Burner assembly, method for operating said burner assembly and plant comprising said burner assembly - Google Patents

Burner assembly, method for operating said burner assembly and plant comprising said burner assembly Download PDF

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Publication number
EP3819540B1
EP3819540B1 EP20206294.9A EP20206294A EP3819540B1 EP 3819540 B1 EP3819540 B1 EP 3819540B1 EP 20206294 A EP20206294 A EP 20206294A EP 3819540 B1 EP3819540 B1 EP 3819540B1
Authority
EP
European Patent Office
Prior art keywords
burner assembly
duct
inlet
air
wall
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.)
Active
Application number
EP20206294.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3819540A1 (en
Inventor
Ruggiero DADDUZIO
Vincenzo PANEBIANCO
Thomas GIANI
Marco TORRESI
Alessandro Saponaro
Massimo ROGORA
Giuseppe CAIVANO
Giovanni MAININI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AC Boilers SpA
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AC Boilers SpA
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Publication date
Application filed by AC Boilers SpA filed Critical AC Boilers SpA
Publication of EP3819540A1 publication Critical patent/EP3819540A1/en
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Publication of EP3819540B1 publication Critical patent/EP3819540B1/en
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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
    • F23D2201/00—Burners adapted for particulate solid or pulverulent fuels
    • F23D2201/20—Fuel flow guiding devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2201/00—Burners adapted for particulate solid or pulverulent fuels
    • F23D2201/30—Wear protection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/01001—Pulverised solid fuel burner with means for swirling the fuel-air mixture
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K2203/00—Feeding arrangements
    • F23K2203/008—Feeding devices for pulverulent fuel

Definitions

  • the present invention relates to a burner assembly and a method for operating said burner assembly.
  • the present invention relates to a burner assembly configured to burn pulverised fuel such as, for example, pulverised coal or pulverised biomass.
  • the present invention also relates to a thermal steam generation plant comprising said burner assembly.
  • one object of the present invention is to provide a burner assembly, which is capable of optimizing the combustion of solid fuels and, at the same time, of complying with the legal limits in terms of emissions.
  • the present invention relates to a burner assembly for burning pulverised fuel, comprising:
  • a further object of the present invention is to provide a method for operating a burner assembly as claimed in claim 10.
  • Still a further object of the present invention is to provide a steam generation plant as claimed in claim 11.
  • reference number 1 indicates a burner assembly according to the present invention.
  • the burner assembly 1 is configured to burn pulverised solid fuel and is part of a thermal plant for generating steam.
  • the burner assembly 1 is configured to burn pulverised coal.
  • the burner assembly 1 is configured to burn biomass (for example pellets, pits of various kinds and types, shells of various kinds and types, etc.), or to burn secondary solid fuel (CSS), etc.
  • biomass for example pellets, pits of various kinds and types, shells of various kinds and types, etc.
  • CSS secondary solid fuel
  • the burner assembly 1 can burn any solid fuel that can be adequately pulverised.
  • the burner assembly 1 comprises a primary duct 2, a secondary duct 3, a tertiary duct 5 and an inlet assembly 6.
  • the primary duct 2 extends along a longitudinal axis A and is provided with an inlet 7 connected to the inlet assembly 6, and an outlet 8 facing the combustion chamber of the thermal plant (not shown for simplicity).
  • the outlet 8 and the inlet 7 are preferably axial.
  • the secondary duct 3 extends around at least a portion of the primary duct 2 and is coaxial with the primary duct 2.
  • the secondary duct 3 extends around an outlet portion 9 of the primary duct 2, which includes the outlet 8.
  • the tertiary duct 5 extends around the secondary duct 3 and is coaxial with the primary duct 2 and the secondary duct 3.
  • a mixture of air and pulverised fuel flows in the primary duct 2 in a direction D coming from the inlet assembly 6.
  • the inlet assembly 6 receives a mixture of air and pulverised fuel from a dryer mill (not shown for simplicity).
  • Air normally defined in technical jargon as “secondary air” flows in the secondary duct 3
  • air normally defined in technical jargon as “tertiary air” flows in the tertiary duct 5.
  • the inlet assembly 6 is provided with an elbow duct 10 and at least one inclined portion 13.
  • the first elbow duct 10 is coupled to the inlet 7 of the primary duct 2.
  • the inclined portion 13 is arranged upstream of the first elbow duct 10 along the flow direction of the flow in the inlet assembly 6.
  • the first elbow duct 10 is provided with a back wall 11.
  • the back wall 11 is preferably transverse to the longitudinal axis A.
  • the back wall 11 forms with the longitudinal axis A an angle ⁇ facing the inlet 7.
  • the angle ⁇ is greater than 90°, more preferably greater than 120°.
  • the first elbow duct 10 defines a curve of approximately 90°.
  • the inclined portion 13 is directly coupled to the first elbow duct 10.
  • One embodiment provides that an intermediate duct, preferably substantially rectilinear, is arranged between the first elbow duct 10 and the inclined portion 13.
  • the inclined portion 13 is configured to deflect the flow of air and fuel in such a way that the flow itself has a velocity component opposite to direction D.
  • the inclined portion 13 is defined by a first wall 16 provided with a first outer lateral surface 17 facing the primary duct 2, and a second wall 18 provided with a second outer lateral surface 19 not facing the primary duct 2.
  • the inclined portion 13 is configured in such a way that at least the first wall 16 helps to deflect the flow of air and pulverised fuel.
  • the first wall 16 is inclined with respect to the longitudinal axis A.
  • the first wall 16 is inclined so as to form with the longitudinal axis A an angle ⁇ facing the elbow duct 10, preferably less than 60°.
  • the second wall 18 also helps to deflect the flow of air and pulverised fuel.
  • the second wall 18 is also inclined with respect to the longitudinal axis A.
  • first wall 16 and the second wall 18 have the same inclination with respect to the longitudinal axis A.
  • One embodiment, not shown, provides that the second wall 18 has a different inclination from that of the first wall 16 with respect to the longitudinal axis A.
  • the inclined portion 13 substantially defines a further elbow duct of the inlet assembly 6.
  • the inclined portion 13 has a constant passage section. Therefore, the axis of extension B of the inclined portion 13 forms with the longitudinal axis A an angle facing the primary duct 2 substantially identical to the angle ⁇ .
  • the inclined portion 13 is arranged between a coupling portion 20 of the elbow duct 10 and an inlet portion 22 of the inlet assembly 6, connected to the dryer mill (not shown for simplicity).
  • the coupling portion 20 and the inlet portion 22 are preferably configured so as to extend substantially along respective axes C, D orthogonal to the longitudinal axis A.
  • the distance between the axes C and D is equal to the diameter of the inclined portion 13.
  • the coupling portion 20 and the inlet portion 22 also have a constant passage section.
  • the burner assembly 1 also includes a baffle element 25, a swirler device 27, a stabiliser device 28 and a lance 30 (optional), a part of which extends inside the primary duct 2 along the longitudinal axis A.
  • the lance 30 is an oil lance.
  • One embodiment, not shown, provides that the lance 30 is fuelled by gas or diesel.
  • the lance 30 is housed in a lance holder tube 31 extending along the longitudinal axis A.
  • the baffle element 25 is housed, at least in part, in the elbow duct 10 of the inlet assembly 6.
  • the baffle element 25 is housed in a coupling portion 23 of the elbow duct 10, which is coupled, in use, to the inlet 7 of the primary duct 2.
  • the baffle element 25 is provided with at least one axial portion 32.
  • the axial portion 32 includes two axial fins 34 (as better visible in Figure 2 ), which extend on opposite sides of the longitudinal axis A.
  • the axial fins 34 extend in the same plane passing through the longitudinal axis A.
  • the axial fins 34 extend in a plane passing through the longitudinal axis A and orthogonal to the axis C of extension of the coupling portion 20 of the elbow duct 10.
  • the axial fins 34 are substantially identical.
  • the baffle element 25 is substantially in contact with the back wall 11.
  • the baffle element 25 is arranged in such a way that the axial fins 34 are also substantially in contact with the back wall 10.
  • the axial length of the axial fins 34 is determined as a function of the diameter of the inclined portion 13.
  • the baffle element 25 is provided with a seat 35 extending along the axis A and configured to house at least a portion of the lance holder tube 31.
  • the baffle 25 deflects the flow entering the primary duct 2 and coming from the inlet assembly 6.
  • the swirler device 27 is housed inside the primary duct 2 and substantially centred on the longitudinal axis A.
  • the swirler device 27 is configured to rotate the inlet flow so as to convey the pulverised fuel towards the inner wall of the primary duct 2.
  • the swirler device 27 comprises a main body 47, which extends along the longitudinal axis A, and a plurality of blades 49, which are fixed to an outer surface 48 of the main body 47 and are evenly distributed around the longitudinal axis A.
  • the main body 47 is preferably provided with a substantially central, axial cavity 50 designed to house the lance holder tube 31.
  • the outer surface 48 of the main body 47 comprises a first truncated-cone portion 51, a second truncated-cone portion 52, and a cylindrical portion 53 arranged between the first truncated-cone portion 51 and the second truncated-cone portion 52.
  • the first truncated-cone portion 51 faces the inlet 7 of the primary duct 2
  • the second truncated-cone portion 52 faces the outlet 8 of the primary duct 2.
  • the first truncated-cone portion 51 has a radius increasing along the direction D
  • the second truncated-cone portion 52 has a radius decreasing along the direction D.
  • the second truncated-cone portion 52 has an inclination with respect to the axial direction at least 3 times greater than the inclination with respect to the axial direction of the first truncated-cone portion 51.
  • the plurality of blades 49 is fixed to the cylindrical portion 53.
  • the homogeniser device 26 comprises a hollow body 37, which is substantially centred on the longitudinal axis A and provided with an outer surface 38 and an inner surface 39.
  • the flow of air and pulverised fuel flows inside and outside the hollow body 37.
  • the homogeniser device 26 is provided with at least one swirler arranged on the outer surface 38 and/or on the inner surface 39 so as to create a gradient between the tangential components of the velocities of the flow of air and fuel flowing outside the hollow body 37 and flowing inside the hollow body 37.
  • the tangential component of the velocity of the flow of air and fuel flowing outside the hollow body 37 is opposite to the tangential component of the velocity of the flow of air and fuel flowing inside the hollow body 37.
  • the homogeniser device 26 comprises an outer swirler 40 coupled to the outer surface 38 of the hollow body 37 and an inner swirler 41 coupled to the inner surface 39 of the hollow body 37.
  • the homogeniser device 26 is fixed to the lance holder tube 31.
  • the hollow body 37 is cylindrical.
  • the outer swirler 40 is configured to give the flow a first tangential velocity component and the inner swirler 41 is configured to give the flow a second tangential velocity component different from the first tangential velocity component.
  • the first tangential velocity component is opposite to the second tangential velocity component.
  • the outer swirler 40 is configured to rotate the flow in direction V1.
  • the inner swirler 41 is configured to rotate the flow in direction V2 opposite to direction V1.
  • the outer swirler 40 comprises a plurality of outer fins 43, which protrude from the outer surface 38 of the hollow body 37.
  • the outer fins 43 extend orthogonally from the outer surface 38 and are arranged parallel and equidistant from one another along the outer surface 38.
  • the outer fins 43 are arranged along a direction transverse to the longitudinal axis A.
  • the inner swirler 41 comprises a plurality of inner fins 45, which protrude from the inner surface 39 of the hollow body 37.
  • the inner fins 45 extend orthogonally from the inner surface 39 and are arranged parallel and equidistant from one another along the inner surface 39.
  • the inner fins 45 are arranged along a direction transverse to the longitudinal axis A.
  • the plurality of inner fins extends inside the hollow body 37 up to the lance holder tube 31.
  • At least one of the inner fins 45 has one end coupled to the lance holder tube 31 and one end coupled to the inner surface 39 in order to fix the homogeniser device 26 to the lance holder tube 31.
  • One embodiment, not shown, provides that the inner ends of the inner fins 45 can be coupled to a tubular portion which, in use, will be fitted on the lance holder tube 31.
  • the burner assembly 1 includes the homogeniser device 26 and the swirler device 27, both housed inside the primary duct 2.
  • the homogeniser device 26 is housed downstream of the baffle element 25 and upstream of the swirler device 27 along direction D.
  • the stabiliser device 28 is arranged at the outlet 8 of the primary duct 2.
  • the stabiliser device 28 comprises an annular element 55 centred on the longitudinal axis A and provided with an inner surface 56 and an outer surface 57, and a plurality of cooling fins 59 coupled to the outer surface 57 and facing the secondary duct 3.
  • the cooling fins 59 are substantially evenly distributed around the longitudinal axis A and arranged equidistant.
  • the cooling fins 59 are arranged transverse to the longitudinal axis A.
  • the cooling fins 59 are configured to deflect the secondary air flow without changing its tangential component.
  • the annular element 55 is provided with an inlet 61 coupled to the primary duct 2, and an outlet 62 facing the combustion chamber (not shown).
  • the inner surface 56 of the annular element is substantially cylindrical and preferably has a diameter d2 substantially identical to the diameter d1 of the primary duct 2.
  • the stabiliser device 28 also comprises a toothed ring 65 arranged along the inner surface 56 near the outlet 62.
  • the toothed ring 65 can be arranged flush with the outlet 65 or in a slightly rearward position (as shown in the examples of Figures 1 , 7 and 8 ).
  • the toothed ring 65 is provided with a plurality of radially arranged and evenly distributed teeth 66.
  • the outer surface 57 of the annular element 55 comprises at least a first truncated-cone portion 68 and a second truncated-cone portion 69, which are preferably contiguous.
  • the outer surface 57 also comprises a cylindrical portion 70 coupled to the second truncated-cone portion 69.
  • the second truncated-cone portion 69 is arranged between the first truncated-cone portion 68 and the cylindrical portion 70.
  • the cylindrical portion 70 is near the inlet 61 of the annular element 55, whereas the first truncated-cone portion 68 is near the outlet 62 of the annular element 55.
  • the inclination ⁇ 1 of the first truncated-cone portion 68 and the inclination ⁇ 2 of the second truncated-cone portion 69 with respect to a direction parallel to the longitudinal axis A are different.
  • the inclination ⁇ 1 of the first truncated-cone portion 68 is greater than the inclination ⁇ 2 of the second truncated-cone portion 69 with respect to a direction parallel to the longitudinal axis A.
  • first truncated-cone portion 68 and the second truncated-cone portion 69 have a radius increasing in the advancing direction D of the flow.
  • annular face 72 is defined at the outlet, which face preferably extends along a plane orthogonal to the longitudinal axis A.
  • the mixture of air and fuel powder is fed to the inlet assembly 6.
  • the conformation of the inlet assembly 6 causes a deflection of the flow of air and fuel powder such as to concentrate the fuel powder in a given area of the primary duct 2.
  • the conformation of the inlet assembly 6 causes a deflection of the flow of air and fuel powder such as to concentrate the fuel powder near the back wall 11 of the elbow duct 10 of the inlet assembly 6.
  • the succession of the baffle element 25 and the swirler element 27 helps to generate a flow entering the stabiliser device 28 in which the fuel powder is homogeneously concentrated in a peripheral annular ring.
  • the annular ring with a high concentration of fuel powder impacts on the toothed ring 65, which slows down the fuel powder and conveys it along the axis of the duct 2.
  • the special conformation of the stabiliser device 28 causes the generation of a flame provided with, near the outlet 62, a recirculation area with low air content and high fuel content in which, advantageously, volatiles are released.
  • the toothed ring 65 slows down the fuel-rich flow and conveys it along the axis of the duct 2, whilst the arrangement of the two truncated-cone portions 68 and 69 facilitates the creation of recirculation areas with low air content.
  • the primary air in fact, is concentrated in the axial area, whereas the secondary air is deflected by the two truncated-cone portions 68 and 69 away from the axial area.
  • the toothed ring 65 forces the carbon particles to slow down below the backfire speed of the fuel. This causes the ignition to occur substantially at the toothed ring 65, and the resulting hot exhaust gases are carried to the recirculation areas. The recirculation of the hot gases self-sustains the ignition of fresh fuel entering the chamber despite the presence of a low-oxygen area.
  • the burner assembly 1 causes the generation of a substantially toroidal recirculation volume VR with low air content, surrounded by an area ZO with higher oxygen concentration.
  • the fuel flow is drawn into a recirculation motion instead of immediately leaving the combustion chamber. Therefore, the residence time of the fuel in the combustion chamber increases. This facilitates the completion of the combustion and therefore reduces the unburnt materials.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Incineration Of Waste (AREA)
  • Control Of Steam Boilers And Waste-Gas Boilers (AREA)
  • Regulation And Control Of Combustion (AREA)
EP20206294.9A 2019-11-06 2020-11-06 Burner assembly, method for operating said burner assembly and plant comprising said burner assembly Active EP3819540B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT102019000020510A IT201900020510A1 (it) 2019-11-06 2019-11-06 Gruppo bruciatore, metodo per operare detto gruppo bruciatore e impianto comprendente detto gruppo bruciatore

Publications (2)

Publication Number Publication Date
EP3819540A1 EP3819540A1 (en) 2021-05-12
EP3819540B1 true EP3819540B1 (en) 2022-05-18

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EP20206294.9A Active EP3819540B1 (en) 2019-11-06 2020-11-06 Burner assembly, method for operating said burner assembly and plant comprising said burner assembly

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EP (1) EP3819540B1 (es)
ES (1) ES2925850T3 (es)
IT (1) IT201900020510A1 (es)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116839024B (zh) * 2023-06-25 2024-05-07 北京天地融创科技股份有限公司 一种煤粉提浓器及其设计方法、煤粉燃烧系统

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Publication number Priority date Publication date Assignee Title
US4611543A (en) * 1981-12-17 1986-09-16 Combustion Engineering, Inc. Restrictor application for in line gas entrained solids redistribution
JP5021999B2 (ja) * 2006-10-20 2012-09-12 三菱重工業株式会社 難燃性燃料用バーナ
CN104776428A (zh) * 2015-04-04 2015-07-15 哈尔滨博深科技发展有限公司 多钝体浓淡分离煤粉燃烧装置

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ES2925850T3 (es) 2022-10-20
IT201900020510A1 (it) 2021-05-06
EP3819540A1 (en) 2021-05-12

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