EP0961905B1 - Vorrichtung und verfahren zum verbrennen von brennstoff - Google Patents

Vorrichtung und verfahren zum verbrennen von brennstoff Download PDF

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Publication number
EP0961905B1
EP0961905B1 EP98907987A EP98907987A EP0961905B1 EP 0961905 B1 EP0961905 B1 EP 0961905B1 EP 98907987 A EP98907987 A EP 98907987A EP 98907987 A EP98907987 A EP 98907987A EP 0961905 B1 EP0961905 B1 EP 0961905B1
Authority
EP
European Patent Office
Prior art keywords
fire tube
air line
air
burner according
axis
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 - Lifetime
Application number
EP98907987A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0961905A1 (de
Inventor
Anatolij Vladimirovic Sudarev
Jevgenij Dimitrijevic Vinogradov
Jurij Ivanovic Zacharov
Stanislav Vesely
Gustav Poslusny
Karl Peters
Karl-Heinz Scholz
Erik Zizow
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 Sro
EON Ruhrgas AG
Original Assignee
Ekol Spol Sro
Ruhrgas AG
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 Sro, Ruhrgas AG filed Critical Ekol Spol Sro
Publication of EP0961905A1 publication Critical patent/EP0961905A1/de
Application granted granted Critical
Publication of EP0961905B1 publication Critical patent/EP0961905B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines

Definitions

  • the invention relates to a burner for spraying, in particular gaseous ones Fuels, with a substantially cylindrical flame tube, an am upstream end of the flame tube arranged flame tube cover, one fuel nozzle opening centrally in the flame tube cover and a plurality of first and second means for introducing combustion air into the flame tube.
  • Such a burner is known for example from FR-A2 272 338.
  • a flame tube has two combustion zones into which combustion air flows through a plurality of first and second openings.
  • the invention further relates to a method for operating the above-mentioned burner.
  • a combustion zone is usually formed in the head region of the burner, in which the combustion air through corresponding openings in the flame tube cover and in Flame tube is blown in, whereby the flame tube material is cooled. Further combustion air is supplied through scale-like openings that over the entire flame tube are distributed.
  • the invention is therefore based on the object, the temperature distribution equalize in the flame tube and thereby reduce the generation of pollutants.
  • the means for introducing combustion air into the flame tube as an air guide are formed so that the first and second air guide in the counterflow direction Axis of the flame tube are inclined so that the first air guide on the flame tube end while the second air guiding pipe extends into the flame tube, and that every second air guide stub a first air guide stub upstream directly assigned.
  • the method of the type mentioned is thereby to solve the problem characterized in that the combustion air is blown into the combustion zone in this way is that in a plane perpendicular to the axis of the flame tube a highly turbulent Toroidal vortex arises, its direction of rotation in the inner area in counterflow is directed to the flow of the combustion products in the axial direction.
  • the toroidal swirl or swirl ring generated in the head area of the burner creates a very intensive turbulent circulation and thus a good mixing of fuel and air.
  • Increasing the degree of homogeneity of the fuel-air mixture reduces the number of local areas which have stoichiometric or near-stoichiometric mixture concentrations and, because of their extreme temperatures, form the main sources of the NO x emissions.
  • the combustion chamber according to the invention belongs to the so-called diffusion chambers, in which the speed of the combustion process is determined by the speed of the fuel-air swirling and not by the speed of the chemical reactions. Therefore, the increased mixing intensity due to the highly turbulent toroidal vortex in the upstream area of the flame tube leads to a shorter residence time of the combustion products in the high-temperature area, which has a favorable effect on the reduction of the NO x generation.
  • the invention leads to increased penetration of the fuel flow through from the first and air jets emerging air jets, which preferably a significant proportion of the total combustion air form.
  • the inside of the flame tube protruding second air guiding connection contribute to the construction of the vertebrae. This creates an even air distribution achieved over the flame tube cross-section and on this Way a reduction in the irregularities of the gas temperature field in the combustion zone. This is particularly so essential even when the combustion chamber is used as a turbine combustion chamber, in which actually one of their main areas of application is. Temperature peaks place a significant load on the turbine blades and shorten their lifespan.
  • the air jets flowing out of the second air duct penetrate deep into the hot gas flow. You cool thereby the high temperature area up to the axis of the flame tube.
  • the second air guiding nozzles protrude into the combustion zone into it, however, the temperature load masters that every second air guide upstream first air guide and preferably also a downstream third air guiding nozzle directly is assigned adjacent.
  • the second air baffle will be So by the from the first air guide and if necessary. Air exiting from the third air duct is cooled.
  • the number of similar first and third air guiding spigots can be increased by the same fourth air guide nozzle be seen in the circumferential direction, each between Adjacent second air guide are arranged. It was found that the cross-sectional distribution between the uniformity of the two types of air guide Temperature distribution at the combustion chamber outlet increased significantly.
  • a critical value for training an optimal highly turbulent toroidal vertebra is in addition to the arrangement the air guide stub whose angle of inclination against the axis of the Flame tube.
  • An angle of inclination has proven to be very favorable from 55 to 60 °.
  • Is critical furthermore the axial distance of the first air guide stub from the Fuel nozzle. It was found that this distance from the Flame tube diameter depends and preferably about the 0.70- is up to 0.85 times the flame tube diameter.
  • the invention not only enables intensification the fuel-air swirling and thus the combustion process, but also a high level of stabilization the pilot light in all load ranges.
  • Additional combustion air can be in the area of the flame tube cover are fed and cool them. Further there is the possibility of combustion air downstream of the air guide through openings in the flame tube wall. This measure proves to be advantageous for the reduction of carbon monoxide production.
  • the burner according to FIGS. 1 and 2 has a flame tube cover 1, in the center of which is connected to a gas lance Fuel nozzle 2 opens. On the flame tube cover 1 is followed by a cylindrical flame tube 3, the Diameter is indicated with d.
  • a plurality of first and second are on the flame tube 3 Air guide 4 or 5 arranged.
  • the first air guiding pipe 4 an upstream first row 6 and the second air guide 5 an immediately adjacent downstream second row 7.
  • All air control sockets 4 and 5 are in countercurrent to the axis of the Flame tube 3 inclined, namely by a common angle ⁇ , which is 60 ° in the case of the exemplary embodiment.
  • the combustion air is predominantly introduced into the combustion zone through the air guide nozzles 4 and 5 in such a way that a highly turbulent toroidal vortex or vortex ring is formed, which is indicated in FIG. 1 by dashed arrow lines.
  • the intensive mixing leads to a homogeneous distribution of the fuel in the combustion air, with the result of reduced NO x formation due to the reduced time spent in the combustion zone, combined with an even temperature distribution in the flame tube.
  • the distance x between the air guide 4 of the first Row 6 and the fuel nozzle 2 is 0.70 times that Flame tube diameter d. This helps to stabilize the Vortex ring and also ensures a stable Ignition behavior over the entire performance range.
  • the mouths are aligned of the first air guide stub 4 with the first row 6 the flame tube, while the second air guide 5 of protrude second row 7 into the flame tube, namely around a distance y which is 0.17 times the diameter of the flame tube d is.
  • the emerging from the second air guide 5 Air jets penetrate to the axis of the flame tube 3 into the combustion zone, capture the central one Area of the combustion zone and then form in the course of their upstream movement along with those from the first air nozzle 4 emerging air jets the mentioned highly turbulent toroidal vertebrae. That kind of Injection of the combustion air via the balanced combination the air guide 4 and the air guide 5 guaranteed a very even distribution across the cross-section the combustion zone, which helps to even out the Temperature distribution contributes.
  • the main air entry takes place through the first air duct 4.
  • the arrangement of the air guide stubs 4 and 5 is such that that upstream of every second air guide 5 first air guide 4 is located.
  • the in the combustion zone protruding second air guide socket 5 are through the emerging from the assigned first air guide 4 Reliably cooled combustion air.
  • Another feature that is used for vortex formation or mixture formation and to homogenize the mixture and so to lower the temperature and make the Temperature distribution contributes is that the Cross section of the first air guiding nozzle 4 - in contrast to the cylindrical cross section of the second air guide stub 5 - Is elongated in the direction of the flame tube axis, so that So the air intake over a certain axial length extends.
  • Two vanes 8 in the first Air guiding 4 contribute to the combustion air initiate specifically in the flame tube 3.
  • the favorable flow also contributes to the fact that respective outlet mouth of the second air guide 5 of the second row 7 in a plane perpendicular to the axis of the associated Air guide is located.
  • the flame tube cover 1 forms on the inside a conical starting from the fuel nozzle 2 Extension to flame tube 3.
  • This design of the Flame tube cover area helps to stabilize the vortex flow at.
  • the gas is inclined outwards blown in, for which purpose the fuel nozzle outlet openings 9 has in the direction of flow away from the axis of the Flame tube 3 are inclined.
  • Figures 3 and 4 represent a very particularly advantageous Embodiment of the burner, which differs from the according to FIGS. 1 and 2 essentially differs in that that the second air guide 5 downstream third air guide 4 'are assigned.
  • the latter therefore deliver one proportional jet of air located at the downstream Side of the associated air duct 5 extended. This enhances the cooling effect and supports the rest of the Formation of the highly turbulent toroidal vertebra.
  • both embodiments have in common that, as from the Figures 2 and 4 can be seen, fourth air guide 4 '' provided are. Viewed in the axial direction, these are each between adjacent second air guide stub 5. At they are in the embodiment according to FIGS. 1 and 2 at the level of the first air guiding spout 4. In the embodiment according to Figures 3 and 4, they are aligned, in the circumferential direction seen, with the first and third air guide 4 and 4 '. Otherwise, they correspond to the angle of inclination and arrangement of the first and third air guide stubs.
  • the number of second air guide stubs is less than that the different types of air duct. This also applies to that Cross-sectional ratio. So the total cross section is second air guide nozzle 5 0.6 to 0.7 times the total cross section of the first and fourth air guiding pieces 4, 4 '' (Fig. 1 and 2) or the total cross section of the first, third and fourth air guide 4, 4 ', 4' '(Fig. 3 and 4).
  • the flame tube 3 has both exemplary embodiments further openings for Combustion air to reduce CO formation. Likewise openings in the flame tube cover 1 are not shown and in the upstream region of the flame tube 3, wherein the combustion air entering here mainly for cooling of flame tube cover and flame tube.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Fuel Cell (AREA)
  • Gas Burners (AREA)
EP98907987A 1997-02-08 1998-01-24 Vorrichtung und verfahren zum verbrennen von brennstoff Expired - Lifetime EP0961905B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19704802A DE19704802A1 (de) 1997-02-08 1997-02-08 Vorrichtung und Verfahren zum Verbrennen von Brennstoff
DE19704802 1997-02-08
PCT/EP1998/000398 WO1998035184A1 (de) 1997-02-08 1998-01-24 Vorrichtung und verfahren zum verbrennen von brennstoff

Publications (2)

Publication Number Publication Date
EP0961905A1 EP0961905A1 (de) 1999-12-08
EP0961905B1 true EP0961905B1 (de) 2001-10-24

Family

ID=7819693

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98907987A Expired - Lifetime EP0961905B1 (de) 1997-02-08 1998-01-24 Vorrichtung und verfahren zum verbrennen von brennstoff

Country Status (13)

Country Link
US (1) US6193502B1 (cs)
EP (1) EP0961905B1 (cs)
AT (1) ATE207593T1 (cs)
AU (1) AU6616098A (cs)
CA (1) CA2280169A1 (cs)
CZ (1) CZ292330B6 (cs)
DE (2) DE19704802A1 (cs)
EA (1) EA000904B1 (cs)
ES (1) ES2163257T3 (cs)
HU (1) HUP0001053A3 (cs)
NO (1) NO993801L (cs)
SK (1) SK106399A3 (cs)
WO (1) WO1998035184A1 (cs)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2774745B1 (fr) * 1998-02-10 2000-03-17 Air Liquide Procede de chauffage de produits dans une enceinte et bruleur pour la mise en oeuvre de ce procede
US20050003316A1 (en) * 2003-05-31 2005-01-06 Eugene Showers Counterflow fuel injection nozzle in a burner-boiler system
CN101235970B (zh) * 2007-01-31 2012-05-02 通用电气公司 具有逆流喷射装置的燃气轮机燃烧器
US8677759B2 (en) * 2009-01-06 2014-03-25 General Electric Company Ring cooling for a combustion liner and related method
EP3026346A1 (en) * 2014-11-25 2016-06-01 Alstom Technology Ltd Combustor liner
US20190024895A1 (en) * 2017-07-18 2019-01-24 General Electric Company Combustor dilution structure for gas turbine engine
US11268438B2 (en) * 2017-09-15 2022-03-08 General Electric Company Combustor liner dilution opening

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2974485A (en) * 1958-06-02 1961-03-14 Gen Electric Combustor for fluid fuels
US3574508A (en) * 1968-04-15 1971-04-13 Maxon Premix Burner Co Inc Internally fired industrial gas burner
US3643430A (en) * 1970-03-04 1972-02-22 United Aircraft Corp Smoke reduction combustion chamber
DE2018641C2 (de) * 1970-04-18 1972-05-10 Motoren Turbinen Union Umkehrbrennkammer fuer gasturbinentriebwerke
US3831854A (en) * 1973-02-23 1974-08-27 Hitachi Ltd Pressure spray type fuel injection nozzle having air discharge openings
US3951584A (en) * 1974-05-23 1976-04-20 Midland-Ross Corporation Self-stabilizing burner
JPS5129726A (cs) * 1974-09-06 1976-03-13 Mitsubishi Heavy Ind Ltd
FR2379028A1 (fr) * 1977-02-01 1978-08-25 Gaz De France Bruleur metallique a gaz sans premelange et a contre-rotation
US4301657A (en) * 1978-05-04 1981-11-24 Caterpillar Tractor Co. Gas turbine combustion chamber
DE4012923A1 (de) * 1990-04-23 1991-10-24 Skoog Kurt Vorrichtung zum verbrennen fluider, insbesondere fluessiger brennstoffe, wie oel o. dgl.
NZ255966A (en) * 1992-09-18 1995-10-26 Luminis Pty Ltd Precessing jet nozzle burner and different attribute burner to give combined controllable flame heat release profile
AUPN156295A0 (en) * 1995-03-07 1995-03-30 Luminis Pty Limited Variable flame precessing jet nozzle
US5984662A (en) * 1997-07-31 1999-11-16 Superior Fireplace Company Karman vortex generating burner assembly

Also Published As

Publication number Publication date
CA2280169A1 (en) 1998-08-13
EA199900730A1 (ru) 2000-02-28
NO993801D0 (no) 1999-08-06
ATE207593T1 (de) 2001-11-15
WO1998035184A1 (de) 1998-08-13
HUP0001053A2 (hu) 2001-04-28
DE59801858D1 (de) 2001-11-29
DE19704802A1 (de) 1998-08-13
ES2163257T3 (es) 2002-01-16
NO993801L (no) 1999-09-15
EP0961905A1 (de) 1999-12-08
HUP0001053A3 (en) 2001-05-28
EA000904B1 (ru) 2000-06-26
CZ262799A3 (cs) 2000-04-12
CZ292330B6 (cs) 2003-09-17
AU6616098A (en) 1998-08-26
SK106399A3 (en) 2000-06-12
US6193502B1 (en) 2001-02-27

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