EP2583033A1 - Turbinenbrenner - Google Patents
TurbinenbrennerInfo
- Publication number
- EP2583033A1 EP2583033A1 EP11711862.0A EP11711862A EP2583033A1 EP 2583033 A1 EP2583033 A1 EP 2583033A1 EP 11711862 A EP11711862 A EP 11711862A EP 2583033 A1 EP2583033 A1 EP 2583033A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel nozzle
- fuel
- blades
- turbine burner
- 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.)
- Granted
Links
- 239000000446 fuel Substances 0.000 claims abstract description 91
- 238000002156 mixing Methods 0.000 claims abstract description 16
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 6
- 239000012530 fluid Substances 0.000 claims abstract description 5
- 238000002485 combustion reaction Methods 0.000 claims description 24
- 238000007599 discharging Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 26
- 230000015572 biosynthetic process Effects 0.000 description 19
- 238000003786 synthesis reaction Methods 0.000 description 18
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 15
- 239000003345 natural gas Substances 0.000 description 9
- 239000000203 mixture Substances 0.000 description 5
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 2
- 206010016754 Flashback Diseases 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000009257 reactivity Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
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
- F23R3/36—Supply of different fuels
-
- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
-
- 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
- F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
-
- 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
- F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
-
- 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
- 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
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
-
- 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
- F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits
Definitions
- Turbine burner The invention relates to a turbine burner according to the preamble of claim 1.
- the combustible components of the synthesis gases are essentially CO and H2.
- the calorific value of the synthesis gas is about 5 to 10 times smaller compared to the calorific value of natural gas.
- Main constituents in addition to CO and H2 are inert fractions such as nitrogen and / or water vapor and possibly also carbon dioxide. Due to the low calorific value, ⁇ high volumetric flows of fuel gas must be supplied through the burner of the combustion chamber ⁇ . This has the consequence that one or more separate fuel passages must be made available for the combustion of low calorific fuels - such as synthesis gas.
- the synthesis gas is fed to the combustion chamber in the burner of the prior art-as described in EP 1 649 219 B1-via a ring-chamber passage arranged around the burner axis.
- the gas is carried out upstream of the burner nozzle by a nozzle ring provided in the burner nozzle with salaried holes, wherein the gas is acted upon by a facultysgeschwin ⁇ dtechnikskomponente.
- the synthesis gas directly on the nozzle a relatively low Mach number is impressed. Associated with this is due to the low fuel pulse also relatively low intensity in terms of mixing with the combustion air, which encloses the annular flow of fuel from both inside and outside.
- aggravating for a quick mixing of the fuel with the combustion air is the geometric design of the annular gap with a relatively large gap width and a correspondingly large mixing path.
- the nozzle ring EP 1649219 Bl with employed bores was ⁇ value, selected in particular for the synthesis gases with a relatively high heating to achieve a suffi ⁇ accordingly high for the acoustic stability loss of pressure at the nozzle without changing the main dimensions substantially.
- this embodiment has aerodynamic disadvantages. As discrete rays are generated, which can not be sufficiently made uniform on the burner outlet to the available path Kgs ⁇ NEN, resulting in increased NOX emissions. By the currents mung commutations inside and in front of the nozzle a considerable total pressure loss occurs about it on out, so this is not a mixture of energy supply Availability checked ⁇ ⁇ In pulse-loss hereafter. It is therefore an object of the invention to provide an improved
- Combustion zone effected as in the nozzle of the prior art.
- FIG. 1 shows such a turbine burner according to the invention.
- FIG. 2 shows a fuel nozzle according to the invention.
- the turbine burner according to FIG. 1 has a secondary supply unit for supplying a secondary fuel or air and for discharging the fuel or air from an opening 6 into a combustion zone 10.
- the secondary fuel may include natural gas and air.
- the Sekundärzu ⁇ drove unit has a radius Ri.
- the Sekundärzu 1500ein ⁇ unit may also include a pilot burner 2, which is designed for another fuel such as oil.
- a further, arranged around the pilot burner 2 annular natural gas duct 35 may be provided for supplying natural gas Gn.
- the natural gas can be diluted with steam or water to control the NOx levels.
- the Sekundärzu ⁇ circulating unit may comprise a further annular air channel 30 Vorse ⁇ hen, flows into the compressor air L '.
- the Sekundärzu slaughter- unit comprises at the downstream end at least one swirl generator, a so-called axial grid 22 for generating a twist.
- the Axialgitter 22 can check 30 the Sekundärzu Switzerland in the downstream end of the air duct ⁇ ⁇ rtigen be ordered.
- the natural gas Gn of the channel 35 is flowed before Axi ⁇ algitter 22 in the air duct 30th
- the so entste ⁇ rising air-natural gas mixture is then swirled through the Axialgitter 22 in the combustion zone 10 is introduced.
- the burner further comprises a primary supply unit which has a primary mixing tube 11 and a fuel nozzle 1 with an opening facing the combustion zone to the fuel nozzle outlet 4 for supplying a primary fuel, the fuel nozzle 1 and the primary mixing tube 11 being arranged concentrically around the secondary supply unit.
- the primary mixing tube 11 and the fuel nozzle 1 have a fluid flow connection. Through the primary mixer tube 11 and the fuel nozzle 1 of the combustion zone 10 synthesis gas is supplied.
- a ring ⁇ channel 40 is arranged around the primary supply, which has a plurality of circumferentially arranged Swirler 45 with or without fuel nozzles. Compressor air L "flows through this annular channel 40, into which fuel can be injected by means of the swirlers 45. The resulting compressor air L '' - fuel mixture or the air L '' is also introduced into the combustion zone 10 twisted.
- the fuel nozzle 1 has an annular wall 9, wel ⁇ che in the axial direction is radially spaced from the Sekundärzu meltech, so that a gap height h is formed by the annular wall 9 and Se ⁇ kundärzu 1500iser.
- the fuel nozzle to the secondary feeding unit ge ⁇ directed inner wall 50
- the inner wall 50 has annularly arranged blades 12 ( Figure 2).
- the blades 12 may be disposed on the outer wall of the secondary feed unit (not shown).
- the fuel nozzle 1 also has a fuel nozzle inlet 20 and a fuel nozzle outlet 4.
- the pressure loss at the fuel nozzle outlet 4 is ge ⁇ sets. This has the advantage that higher acoustic Sta ⁇ stability in the combustion zone 10, that is GE stability ⁇ gen to the known hum in the combustion zone 10 than in the nozzles of the burner of the prior art provides a ⁇ .
- the pressure loss can also be adjusted in this embodiment on the speed of the synthesis gas or the cross section of the fuel nozzle outlet.
- the fuel nozzle 1 is formed downstream at least partially conical.
- the blades 12 have on the upstream side a blade inlet edge 51 and opposite a blade trailing edge 60.
- the blade inlet edge 51 has an axial distance s from the fuel nozzle inlet 20.
- the ratio of distance s and gap height h is greater than 1 and less than 4.
- the fuel nozzle inlet 20 is designed with a larger gap height h.
- the maximum utilization of the acceptable pressure loss and the avoidance of parasitic pressure losses takes place at the fuel nozzle outlet 4. This results in stable combustion.
- the fuel nozzle inlet 20 is also rounded, the rounding having a fuel nozzle inlet radius Re.
- the rounding points away from a fuel nozzle interior.
- the ratio of the fuel nozzle inlet radius Re and the gap height h is greater than 0.2 and less than 0.8. Since ⁇ by carried to the blade leading 51 a gleichze- ssige flow acceleration, which the minimization
- Inlet pressure losses and on the blades 12 causes a gleichmäßi ⁇ ges flow profile.
- this can also be done by a straight nozzle 1 with a straight fuel nozzle inlet 20 are caused by an angle ⁇ 75 ° (not shown).
- the blade inflow edge 51 has the above-mentioned upstream relative axial distance of approximately Ks (distance) / h (gap height) ⁇ 4 to the fuel nozzle inlet 20.
- the nozzle 1 is thus designed such that by reducing the gap height h at the fuel nozzle inlet 20, the axial velocity is increased before the blades 12 and a uniform acceleration of the gas until it exits the nozzle 1 he follows ⁇ .
- the gap height h at Brennstoffdüsenaus ⁇ occurs 4 between O.Kh (gap height) /Ra ⁇ 0.2, where Ra represents the outer fuel nozzle radius Ra, so that a Mach number in the range 0.4 ⁇ Ma ⁇ O.8 is maintained, which is better Acoustic decoupling of the fuel system of combustion ⁇ pressure oscillations causes.
- an increase in the mixing energy is associated with the higher Mach number. Due to the smaller gap height h than in the case of the prior art nozzles at the nozzle outlet 4, mixing paths are also minimized.
- the blades 12 additionally have a blade angle of attack (FIG. 2).
- the blade pitch angle to currency ⁇ len in which a very high swirl number S is set, however, without causing flow separation on the blade trailing edge 60 and the hub 70, wherein the swirl ⁇ number S sets the rotation pulse current in relation to the Axialimpulsstrom.
- the hub 70 that part of the seconds ⁇ därzuchttechnik refers, which is located on the axial grid 22 and which represents the inner boundary of the fuel nozzle 1 at the nozzle outlet 4.
- the swirl number S is in a range of greater than 1.2 and less than 1.7.
- the ratio of the radius Ri of the secondary feed unit to the outer fuel nozzle radius Ra of the fuel nozzle 1 at the fuel nozzle outlet 4 must be greater than 0.6 and less than 0.8. Since the swirl number S depends on the ratio Ri / Ra, compliance with the ratio, that the synthesis gas flow still follows the contour of the fuel nozzle 1, without detaching itself on the hub side.
- the fuel-air mixture which flows through the axial grid 22, also has a tangential flow direction 100 (swirl). Also in the fuel nozzle 1 Syn ⁇ synthesis gas stream is imparted by an angle of attack of the blades 12 a tangential flow direction 110th The blade angle of attack can now be arranged so that the tangential flow directions 100 and 110 are now in opposite directions
- the blades 12 and the axial grid 22 must have an opposing arrangement. This causes a significant increase in the mixing intensity due to the increased shear rates in the contact zones of the flows 100 and 110. Because of the counter-roll, namely, the relative velocities between the air-fuel mixture and synthesis gas is well above the relative velocities of a co-directional arrangement, which in turn significantly higher mixing both streams entails. This in turn has a positive effect on NOx emissions. Also, the air flowing through the annular passage 40 has a twist 120. This is preferably gleichgerich ⁇ tet to the swirl flow 100. The fuel nozzle 1, seen in the flow direction after the blades 12 still have holes 130.
- the air of the annular channel 40 can occur when the burner is not in the synthesis gas operation.
- an operation of the burner without synthesis gas is possible when fuel is supplied via the pilot burner or fuel via the Ergaspassage 35.
- no hot gas, which is present in the combustion zone 10 can flow back through the nozzle 1 during operation without synthesis gas.
- the holes 130 may be formed in the flow direction with an inlet shell (7), which projects into the channel 40.
- Combustion zone 10 flows back into the nozzle 1.
- FIG. 2 shows a fuel nozzle 1 according to the invention in detail.
- This nozzle 1 has an inner wall 50.
- the show ⁇ blades 12 are arranged annular over the circumference of the inner wall 50.
- the nozzle 1 has a conical shape over the entire area of the hub 70 (FIG. 1), resulting in a smaller gap height h (FIG. 1) at the fuel nozzle outlet 4 than is the case with the nozzles of the prior art.
- the volume flow of the synthesis gas which must be supplied by the burner according to the invention to the combustion zone 10, can be reduced with the same NOx emissions.
- the better acoustic stability allows an extended operating range of the burner according to the invention in terms of load and fuel quality.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11711862.0A EP2583033B1 (de) | 2010-06-18 | 2011-03-29 | Turbinenbrenner |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10166431A EP2397764A1 (de) | 2010-06-18 | 2010-06-18 | Turbinenbrenner |
EP11711862.0A EP2583033B1 (de) | 2010-06-18 | 2011-03-29 | Turbinenbrenner |
PCT/EP2011/054777 WO2011157458A1 (de) | 2010-06-18 | 2011-03-29 | Turbinenbrenner |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2583033A1 true EP2583033A1 (de) | 2013-04-24 |
EP2583033B1 EP2583033B1 (de) | 2014-06-25 |
Family
ID=43086876
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10166431A Withdrawn EP2397764A1 (de) | 2010-06-18 | 2010-06-18 | Turbinenbrenner |
EP11711862.0A Active EP2583033B1 (de) | 2010-06-18 | 2011-03-29 | Turbinenbrenner |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10166431A Withdrawn EP2397764A1 (de) | 2010-06-18 | 2010-06-18 | Turbinenbrenner |
Country Status (4)
Country | Link |
---|---|
US (1) | US8869535B2 (de) |
EP (2) | EP2397764A1 (de) |
CN (1) | CN102947650B (de) |
WO (1) | WO2011157458A1 (de) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2312215A1 (de) * | 2008-10-01 | 2011-04-20 | Siemens Aktiengesellschaft | Brenner und Verfahren zum Betrieb eines Brenners |
CN105393057B (zh) * | 2013-09-23 | 2017-06-30 | 西门子股份公司 | 用于燃气涡轮机的燃烧器和用于减少燃气涡轮机中的热声振荡的方法 |
US10731861B2 (en) * | 2013-11-18 | 2020-08-04 | Raytheon Technologies Corporation | Dual fuel nozzle with concentric fuel passages for a gas turbine engine |
EP2993406A1 (de) | 2014-09-03 | 2016-03-09 | Siemens Aktiengesellschaft | Verfahren zum Betreiben einer Gasturbine und Brenner für eine Gasturbine |
DE102021002508A1 (de) | 2021-05-12 | 2022-11-17 | Martin GmbH für Umwelt- und Energietechnik | Düse zum Einblasen von Gas in eine Verbrennungsanlage mit einem Rohr und einem Drallerzeuger, Rauchgaszug mit einer derartigen Düse und Verfahren zur Verwendung einer derartigen Düse |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0580683B1 (de) * | 1991-04-25 | 1995-11-08 | Siemens Aktiengesellschaft | Brenneranordnung, insbesondere für gasturbinen, zur schadstoffarmen verbrennung von kohlegas und anderen brennstoffen |
DE19549143A1 (de) * | 1995-12-29 | 1997-07-03 | Abb Research Ltd | Gasturbinenringbrennkammer |
WO1999004196A1 (de) * | 1997-07-17 | 1999-01-28 | Siemens Aktiengesellschaft | Brenneranordnung für eine feuerungsanlage, insbesondere eine gasturbinenbrennkammer |
DE19757617A1 (de) * | 1997-12-23 | 1999-03-25 | Siemens Ag | Verbrennungssystem sowie Brenner eines Verbrennungssystems |
ES2306925T3 (es) | 2003-07-25 | 2008-11-16 | Ansaldo Energia S.P.A. | Quemador de turbina de gas. |
EP1659339A1 (de) * | 2004-11-18 | 2006-05-24 | Siemens Aktiengesellschaft | Verfahren zum Anfahren eines Brenners |
US8104285B2 (en) * | 2005-09-30 | 2012-01-31 | Ansaldo Energia S.P.A. | Gas turbine equipped with a gas burner and axial swirler for the burner |
US7685823B2 (en) * | 2005-10-28 | 2010-03-30 | Power Systems Mfg., Llc | Airflow distribution to a low emissions combustor |
US8393891B2 (en) * | 2006-09-18 | 2013-03-12 | General Electric Company | Distributed-jet combustion nozzle |
-
2010
- 2010-06-18 EP EP10166431A patent/EP2397764A1/de not_active Withdrawn
-
2011
- 2011-03-29 WO PCT/EP2011/054777 patent/WO2011157458A1/de active Application Filing
- 2011-03-29 CN CN201180030001.5A patent/CN102947650B/zh active Active
- 2011-03-29 US US13/699,801 patent/US8869535B2/en active Active
- 2011-03-29 EP EP11711862.0A patent/EP2583033B1/de active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2011157458A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2011157458A1 (de) | 2011-12-22 |
EP2397764A1 (de) | 2011-12-21 |
US20130074506A1 (en) | 2013-03-28 |
CN102947650A (zh) | 2013-02-27 |
US8869535B2 (en) | 2014-10-28 |
EP2583033B1 (de) | 2014-06-25 |
CN102947650B (zh) | 2014-12-17 |
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