EP3296637A1 - Kraftstoffverbrennungsverfahren und brenner zu dessen implementierung - Google Patents

Kraftstoffverbrennungsverfahren und brenner zu dessen implementierung Download PDF

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Publication number
EP3296637A1
EP3296637A1 EP16189148.6A EP16189148A EP3296637A1 EP 3296637 A1 EP3296637 A1 EP 3296637A1 EP 16189148 A EP16189148 A EP 16189148A EP 3296637 A1 EP3296637 A1 EP 3296637A1
Authority
EP
European Patent Office
Prior art keywords
stream
air
fuel
annular
section
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.)
Withdrawn
Application number
EP16189148.6A
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English (en)
French (fr)
Inventor
E.D. Vinogradov
Stanislav Vesely
J.I. Zacharov
Vaclav Janisnin
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.)
Ekol Spol S RO
Original Assignee
Ekol Spol S RO
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Ekol Spol S RO filed Critical Ekol Spol S RO
Priority to EP16189148.6A priority Critical patent/EP3296637A1/de
Publication of EP3296637A1 publication Critical patent/EP3296637A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention concerns the power, transport and chemical engineering and it can be used in the gas turbine units.
  • Fig 1 There burner according to the state of the art shown in Fig 1 contains at least one cylindrical annular for-chamber formed by the elements of the burner, inside of which there is the coaxial bladed air swirl and the combustible supplying device with the holes for the combustible, and in the outlet of the for-chamber there is one or more coaxial combustion stabilizer/s, whereas the holes (or group of holes) for the supply of the combustible to the for-chamber are set with displacement in relation of each other along the burner axis such a way that the value of the relation L 2 + k * D / L 1 + k * D
  • the burner possesses the deficiency of the method: insufficient stability of the combustion process.
  • the geometrical characteristics of the burner D, L1 and L2 determine (at a constant flow rate) the characteristic time intervals T feed , T mix , and T comb in the method of combustion. Therefore, similarly to the method, at certain relation of geometric characteristics the stability of the combustion process will be insufficient.
  • the physical mechanism of this phenomena consists in the fact that in case of the appearance the weak perturbation with frequency f in the air-combustible mixture, the phase shift between the fluctuations of consumption, pressure and heat release caused by the time delay T leads to the situation when phases of the heat release and the mixture concentration o the combustion zone coincide and resonance occurs.
  • T comb As an interval of time from the moment of intake air-fuel mixture into the filled-in semi bounded space till the moment when the heat release during the combustion riches its maximum value.
  • T comb can be determined by the calculation using the known methods of digital modeling of acting streams or by experiment.
  • the amplitudes of fluctuation at every of these frequencies will be lower than in case of lamp swirling of entire air stream, because the energy of fluctuation process during the air-fuel mixture combustion divides among various fluctuation processes.
  • the task is solved by the swirling the air annular stream maintaining the relation T feed + T mix + T comb / T mix + T comb > 2.
  • Every semi bounded (with one open end) space filled in with the hot combustion products has its own frequency f sobstv that depends on the size and form of this space and parameters of the combustion products.
  • the burner for realization if the known method of combustion that contains at least one cylindrical annular for-chamber formed by the elements of the burner, inside of which there is the coaxial bladed air swirl and the combustible supplying device with the holes for the combustible, and in the outlet of the for-chamber there is one or more coaxial combustion stabilizer/s, whereas the holes (or group of holes) for the supply of the combustible to the for-chamber are set with displacement in relation of each other along the burner axis such a way that the value of the relation L T 2 + k * H / L T 1 + k * H ,
  • the task to be solved by the claimed method of combustion is the increasing of the stability of the process of combustion by reducing of possibility of appearance of the fluctuation of pressure with high amplitudes.
  • the method is characterized by features in claim 1 and the burner in claim 3.
  • Fig.1 is a functional diagram of the burner according to the invention
  • Fig. 2 is a construction diagram of the burner with one prechamber according to the invention
  • Fig.3 is top view on unrolled fuel tube of the burner of Fig.2 with the illustration of distribution of the fuel protrusions and whirl blades on the circumference of the fuel tube, the blades are displaced to each other and thus creating two parallel rows in this unrolled state
  • Fig.1 is a functional diagram of the burner according to the invention
  • Fig. 2 is a construction diagram of the burner with one prechamber according to the invention
  • Fig.3 is top view on unrolled fuel tube of the burner of Fig.2 with the illustration of distribution of the fuel protrusions and whirl blades on the circumference of the fuel tube, the blades are displaced to each other and thus creating two parallel rows in this unrolled state
  • FIG. 4 is a construction diagram of the burner with two prechambers according to the invention, where in the first prechamber the whirler is spirally placed along the length of the fuel tube and in second prechamber the whirler is arranged only in one location along the length in a circle around the whole perimeter
  • Fig. 5 is a top view of the unrolled fuel tube of the burner of Fig. 4 with the illustration of the distribution of fuel protrusions and whirl blades on the circumference of the fuel tube, the blades are displaced to each other and thus creating always two parallel rows in this unrolled state
  • Fig. 5 is a top view of the unrolled fuel tube of the burner of Fig. 4 with the illustration of the distribution of fuel protrusions and whirl blades on the circumference of the fuel tube, the blades are displaced to each other and thus creating always two parallel rows in this unrolled state
  • Fig. 4 is a construction diagram of the burner with two prechambers according to the invention, where in the first prechamber
  • FIG. 6 is a construction diagram of the burner with one prechamber according to the invention with a long whirler having blades arranged along the length of the fuel tube in one location only, where the protrusions are spaced on a helix, while the length of the whirl occupies the entire height of the helix created by protrusions and thus the protrusions are in each case arranged between two adjacent blades
  • Fig. 7 is a top view of the unrolled fuel tube of the burner of Fig. 6 with the illustration of the distribution of fuel protrusions and whirl blades.
  • the air stream in form at least one annular stream is swirled and supplied into the semi bounded (with one open end) space filled in with the hot combustion products, before this it is preliminary mixed up with the fuel, wherein the fuel flow is divided in the stream (or group of streams) that are supplied successively in different sections of the annular air stream such a way that distance from the section I - I in which the first stream (group of streams) of fuel is provided till the section II - II in which the last stream (group of streams) of fuel is provided, the annular air stream passes during the time T feed , after what the fuel and the air are mixed up during time T mix up to the moment of the supply of the received air-fuel mixture into the semi bounded (with one open end) space in form of the annular swirled stream where the fuel-air mixture burns during the time T comb with the products of combustion and the heat release, wherein the supply of the streams (groups of streams) of fuel into the air flow is done such a way that the value of the relation
  • the annular air stream is swirled gradually during time T feed during which the flow crosses the distance from the section IV - IV in which the swirling of the stream is started till the section V - V in which the swirling of the stream is ended, and after it the air in the swirled stream is mixed up with the fuel during time T mix till the moment of delivery in the section III - III of the air-fuel mixture into the semi bounded (with one open end) space filled in with the hot combustion products, wherein the swirling of the annular air stream is done the way that observes the relation 1 , 2 ⁇ T feed + T mix + T comb / T mix + T comb ⁇ 2 would be inside the respective limits, but in comparison with the prototype the annular air stream is swirled gradually during time T feed during which the flow crosses the distance from the section IV - IV in which the swirling of the stream is started till the section V - V in which the swirling of the stream is ended, and after it the air in the swirled stream is mixed up with the fuel during time T mix till the
  • the injection of the stream (group of streams) of the combustible in the air flow is made the way that maintains the relation T feed + T mix + T comb / T mix + T comb > 2.
  • the burner for realization of fuel combustion method (see fig. 2 , fig.3 ) containing one cylindrical annular pre-chamber 1, the pre-chamber 1 is made by the external cylindrical shell 2 and between this shell 2 and coaxial fuel feed tube 3, a coaxial bladed air swirl 4 with blades 5 is located and from the tube 3 fuel distribution devices made in form of pylons 6 are protruding. They are disposed in a helical arrangement around the tube 3 and along this tube in a specific mutual distance. Thy pylons 6 have groups of holes for supply of fuel from the feed tube 3 into the pre-chamber 1.
  • the burner according Fig.3 has the axial distances L B1 , L B2 forming part of the above relations, from the closest and the distant blades 5 (group of blades) of swirler 4 respectively till the outlet from the pre-chamber 1, and the axial distances L T1 , L T2 from the closest and the distant hole (group of holes) respectively up to the outlet of the pre-chamber, that ensure the method of fuel combustion, can determine while knowing the burner dimensions and the air consumption in it.
  • L B 2 W os * T feed + T mix
  • L T 1 W os * T mix
  • L T 2 W os * T feed + T mix .
  • the holes (or group of holes) for combustible injection to the for-chamber are located with displacement along the burner's axis between each other the way that maintains the relation L B 2 + K * H / L B 1 + k * H > 2.
  • the variant of burner for realization of combustion method contains two coaxial cylindrical annular pre-chambers 1.
  • the pre-chamber 1 is made between the external wall of the of the annular fuel feed tube 9 and internal wall of a cylindrical shell 10 and in this space the blades 5 of the air swirls 4 are located and fuel distribution devices made as pylons 6 with the hole groups for fuel supply from fuel feed tube 9 to the pre-chamber 1, and there is the outlet 11 from pre-chamber in the end of fuel freed tube 9.
  • the pylons 6 and blades 5 are both in pre-chamber located with the axial displacement in relation of each other in the way that fulfills the respective relations indicated above.
  • the variant of burner for realization of combustion method contains one cylindrical annular pre-chamber 1.
  • Pre-chamber 1 is made by the cylindrical shell 2 and coaxial fuel feed tube 3 inside of which there are the coaxial air swirl 4 with blades 5 and fuel distributing devices made in form of pylons 6 with groups of holes for fuel supply from tube 3 to pre-chamber 1, and there is the outlet 7 from the pre-chamber.
  • the pylons 6 in the pre-chamber 1 are located with the axial displacement in relation of each other such a way that observes the respective relation.
  • the long bladed air swirl 4 is made with the axially installed blades 5 that provide gradual (during established time T feed ) swirling of the annular air stream.
  • the longitude of the blades 5 is selected in view of the preserving of respective relation.
  • the arrangement of blades 5 and pylons 6 can be well seen in fig.7 .
  • the method of combustion is realized during the burner operation that takes place the following way.
  • the air stream in form of annular stream formed in the annular pre-chamber 1 (see Fig.2 , Fig.3 , Fig.6 and Fig.7 ) is swirled gradually during the established time by the coaxial bladed air swirl device 4 with blades 5 and is delivered into the semi bounded space 12 filled in with the hot combustion products ad made by the flue at the outlet 7 from pre-chamber 1 at the end of tube 3
  • the fuel stream is divided into groups that are supplied gradually in the different sections of the annular air stream through the holes in the pylons 6.
  • the mixture burns out after coming out at the outlet 7 at the end of the tube 3 with the release of combustion products and heat.
  • the combustion process is carried out in case of operation of a burner with two or more pre-chambers.
EP16189148.6A 2016-09-16 2016-09-16 Kraftstoffverbrennungsverfahren und brenner zu dessen implementierung Withdrawn EP3296637A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16189148.6A EP3296637A1 (de) 2016-09-16 2016-09-16 Kraftstoffverbrennungsverfahren und brenner zu dessen implementierung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16189148.6A EP3296637A1 (de) 2016-09-16 2016-09-16 Kraftstoffverbrennungsverfahren und brenner zu dessen implementierung

Publications (1)

Publication Number Publication Date
EP3296637A1 true EP3296637A1 (de) 2018-03-21

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EP16189148.6A Withdrawn EP3296637A1 (de) 2016-09-16 2016-09-16 Kraftstoffverbrennungsverfahren und brenner zu dessen implementierung

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1852656A1 (de) * 2006-04-04 2007-11-07 Nauchno-proizvodstvennoe predpriatie "EST" Verfahren zur Kraftstoffverbrennung und Verbrennungsvorrichtung
US7578130B1 (en) * 2008-05-20 2009-08-25 General Electric Company Methods and systems for combustion dynamics reduction
US20100126176A1 (en) * 2008-11-26 2010-05-27 Ik Soo Kim Dual swirler
US20130133329A1 (en) * 2011-11-25 2013-05-30 Institute Of Engineering Thermophysics, Chinese Academy Of Sciences Air fuel premixer having arrayed mixing vanes for gas turbine combustor
US20130139511A1 (en) * 2011-03-16 2013-06-06 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor and gas turbine
US20150153041A1 (en) * 2013-10-03 2015-06-04 Plum Combustion, Inc. Low NOx Burner with Low Pressure Drop

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1852656A1 (de) * 2006-04-04 2007-11-07 Nauchno-proizvodstvennoe predpriatie "EST" Verfahren zur Kraftstoffverbrennung und Verbrennungsvorrichtung
EP1852656B1 (de) 2006-04-04 2012-01-18 Nauchno-proizvodstvennoe predpriatie "EST" Verfahren zur Kraftstoffverbrennung
US7578130B1 (en) * 2008-05-20 2009-08-25 General Electric Company Methods and systems for combustion dynamics reduction
US20100126176A1 (en) * 2008-11-26 2010-05-27 Ik Soo Kim Dual swirler
US20130139511A1 (en) * 2011-03-16 2013-06-06 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor and gas turbine
US20130133329A1 (en) * 2011-11-25 2013-05-30 Institute Of Engineering Thermophysics, Chinese Academy Of Sciences Air fuel premixer having arrayed mixing vanes for gas turbine combustor
US20150153041A1 (en) * 2013-10-03 2015-06-04 Plum Combustion, Inc. Low NOx Burner with Low Pressure Drop

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