WO2005068913A1 - Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer - Google Patents
Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer Download PDFInfo
- Publication number
- WO2005068913A1 WO2005068913A1 PCT/EP2005/050105 EP2005050105W WO2005068913A1 WO 2005068913 A1 WO2005068913 A1 WO 2005068913A1 EP 2005050105 W EP2005050105 W EP 2005050105W WO 2005068913 A1 WO2005068913 A1 WO 2005068913A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- flow
- swirl
- section
- contour
- combustion chamber
- Prior art date
Links
Classifications
-
- 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
-
- 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
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2209/00—Safety arrangements
- F23D2209/20—Flame lift-off / stability
Definitions
- the invention relates to a premix burner and a method for operating a combustion chamber with a liquid and / or gaseous fuel with a swirl generator for a combustion supply air flow to form a swirl flow and means for injecting fuel into the swirl flow, the swirl generator being indirect via a mixing zone or directly adjacent to the combustion chamber in each case via a burner outlet, a cross-sectional widening which is unstable in the flow direction of the swirl flow being provided at the burner outlet and through which the swirl flow bursts open with the formation of a return flow zone.
- Premix burners of the aforementioned type are known from a large number of previously published documents, for example from EP A1 0210462 and EP B1 0 321 809, to name just a few.
- Premix burners of this type are based on the general principle of operation, within a swirl generator, which is usually in the form of a cone and which provides at least two partial cone shells composed with a corresponding overlap, to produce a swirl flow consisting of a fuel-air mixture, which within a in the direction of flow, the combustion chamber following the premix burner is ignited to form a spatially stable premix flame.
- the spatial position of the premixing flame is determined by the aerodynamic behavior of the swirl flow, the swirl number of which increases with increasing propagation along the burner axis, so that it becomes unstable and ultimately bursts due to an unstable cross-sectional transition between burner and combustion chamber into an annular swirl flow with the formation of a backflow zone in the latter the premix flame forms in the front area.
- the vortex backflow zone has only limited stability properties, which is why a large number of proposals have already been made to improve the stability properties of such backflow zones.
- the axial profile of the swirl flow generated by the swirl body should be low-swirl in the center, that is to say in the region of the burner axis, and there should also be an excess of axial speed there.
- the double-cone burner described in this document is shown schematically in FIG. 2 in the form of a longitudinal section and has a conical swirl generator 1, the two conical shells of which one inside the other each include two air inlet slots 2.
- the swirl generator 1 opens directly into the combustion chamber 4 at the burner outlet 3 via an inconsistent cross-sectional widening.
- the tangential feed of the combustion supply air along the air inlet slots 2 produces a swirl flow which spreads in the axial flow direction with increasing swirl around the axial direction of the swirl generator. Due to the increasing swirl along the axial flow direction, the instability of the swirl flow increases and changes into an annular swirl flow with backflow.
- a backflow zone 5 is formed essentially within the combustion chamber 4 in the area of the burner outlet 3, with a front or a stagnation point 6 in the direction of flow, the axial position of which, relative to the premix burner 1, is essentially determined by the cone angle 2 ⁇ and the slot width of the air inlet slots 2 is determined.
- the size and appearance of the backflow zone 5 can essentially be determined by the size selection of the above geometric values.
- the premixing flame 7 is formed within the backflow zone 5 and stabilizes at the front area of the inner backflow zone 5.
- the premixing burner described above is used to generate hot gases for driving a gas turbine system, it is important to keep the pressure loss across the burner as low as possible for reasons of optimizing the efficiency of the gas turbine system. Since the number of swirls and the pressure loss are directly proportional to one another, the lowest possible number of swirls within the swirling flow is desired, which should be chosen so large that an inner backflow zone is formed.
- the invention has for its object to develop a premix burner according to the features of the preamble of claim 1 such that, on the one hand, the aerodynamic stability of the inner return flow zone, in particular in the region of the front stagnation point, is to be increased without having to accept any significant additional burner pressure loss. Furthermore, it is necessary to specify a corresponding method for operating a combustion chamber, which is intended both to avoid the occurrence of thermoacoustic vibrations and to attempt to achieve the lowest possible loss of burner pressure.
- the premix burner according to the invention is based on the idea that the aerodynamic stability of the free inner backflow zone can be increased by locally increasing the swirl gradient of the swirl flow in the direction of flow in front of the backflow zone which is formed. Due to the local increase in the swirl gradient, i.e. along the axially spreading swirl flow within the premix burner, it is necessary to increase the swirl number in the axial flow direction spatially limited from an initial swirl number to a larger swirl number and then immediately to the initial swirl number or a smaller swirl number compared to this. It turns out that with the measure according to the invention the total burner pressure loss is only insignificant is increased, resulting in no or very little impact on the overall efficiency of a gas turbine.
- a premix burner with the features of the preamble of claim 1 is characterized in that upstream of the burner outlet there is a contour that tapers locally in the flow direction of the swirl generator or, if present, the mixing zone in the flow direction.
- This contour which tapers the flow cross-section locally, advantageously has a longitudinal section oriented in the flow direction, which is comparable to that of a Venturi nozzle arrangement, i. H. the contour has a first gate section in the flow direction, which continuously reduces the flow cross-section, which continuously merges into a second gate section with a smallest flow cross-section, which is followed in the flow direction by a third gate section which increases the flow cross-section again.
- the contour tapering the flow cross section along the burner axis within the premix burner advantageously has to be positioned in such a way that the contour is provided in the area of the foremost front, preferably in the direction of flow directly in front of the backflow zone that is formed.
- the premix burner is a double-cone burner, the swirl generator of which essentially consists of two partial cone shells placed one inside the other, and furthermore, no further mixing tube is provided between the double-cone burner and the combustion chamber, so that the swirl generator with its burner outlet directly into the combustion chamber via an inconsistent cross-sectional expansion ends
- the arrangement according to the invention which on the one hand can be added as an additional form at a suitable axial point along the inner circumferential edge of the two partial cone shells, which makes it possible to retrovistatize, or which is already integrally formed in the inner side of both partial cone shells, for one elliptical cross-sectional shape at the location of the narrowest or smallest flow cross-section due to the contour.
- the measure according to the invention can also be used in premix burner systems whose swirl generators are composed of more than two partial cone shells or provide a mixing tube as an additional mixing zone between the swirl generator and the combustion chamber. If mixing tubes are provided, the contour tapering the flow cross section must be provided in the inner wall area of the mixing tube near the burner outlet at the transition to the combustion chamber.
- the concept of local flow cross-section tapering according to the invention for the purpose of aerodynamically stabilizing the backflow zone that forms within a premix burner, which is preferably used to operate a combustion chamber that is used to fire a gas turbine system, is based on the procedural idea of aerodynamic conditions at the location of the foremost stagnation point of the backflow zone to create, which prevent an axial migration of the stagnation point.
- the swirl flow oriented in the axial flow direction is caused by the contour-related nozzle effect accelerated within the premix burner, for example within the swirl generator axially in front of the foremost stagnation point of the return flow zone and likewise decelerated in the flow direction before the stagnation point of the return flow zone in such a way that the greatest possible velocity gradient with reversal of the flow direction prevails at the axial location of the stagnation point.
- This can be achieved by a convergent and divergent flow routing that is specifically located in front of the location of the stagnation point. Further details can be found in the description of the exemplary embodiments below.
- FIG. 1 is a schematic partial longitudinal sectional view through a swirl generator
- FIG. 2 is a schematic longitudinal sectional view through a premix burner with a combustion chamber
- 5 shows a diagram to show the pressure fluctuations at low temperatures
- FIG. 6 shows a diagram with emission values.
- Figure 1 shows a schematic section of a longitudinal section through a swirl generator of a double-cone premix burner with a burner wall 8 which includes a half cone angle v with the burner axis A.
- a contour 9 tapering the axial flow cross section is provided on the inside of the burner wall 8.
- the contour 9 reduces the flow cross section along the burner axis A within a local area 10 such that the shape and size of the burner outlet 3 are not affected by the contour 9.
- the contour 9 has a first link section 91, through which the flow cross section is continuously reduced.
- a second link section 92 which specifies the smallest flow cross section.
- the second link section 92 is preferably only point-shaped or line-shaped.
- the area of the smallest flow cross section is followed downstream by a third link section 93, through which the flow cross section is widened again, preferably to a degree that is predetermined by the burner wall 8 on the outlet side.
- the contour 9 tapering the flow cross section runs in the circumferential direction in a largely closed manner to the two partial cone shells, so that the interaction of the contours 9 respectively attached to both partial cone shells forms a flow backdrop which corresponds to that of a Venturi nozzle.
- R1 radial distance between the central axis of a partial cone shell and the surface of the contour at location x along the central axis
- RB radial distance between the central axis of a partial cone shell and the surface of the original partial cone shell at location x along the central axis
- R2 elevation of the contour measured from the surface the partial cone shell at location x along the central axis
- ⁇ angle between a tangential surface on the contour and the central axis of the partial cone shell at location x along the central axis
- Y half the cone angle.
- burner axis and central axis of the respective partial cone shells
- each individual partial cone shell has an associated partial cone center axis, in short the central axis of the respective partial cone shell. Due to the spatial arrangement of the partial cone shells, these corresponding central axes do not coincide. For the above design parameter requirements, however, the corresponding central axes of the partial cone shells must be raised.
- FIG. 3 shows a schematic cross section through a double-cone burner in the region of the narrowest flow cross-section 92 due to the contour.
- Both partial cone shells 10, 11 each have associated central axes M11, M12 and are set one inside the other in such a way that they enclose two opposing tangential air inlet slots 2.
- Due to the contours 9, the entire flow cross section is narrowed by the swirl generator in the manner of an ellipse (dashed line).
- Such an elliptical flow cross-section advantageously has aerodynamically stabilizing effects on the burner behavior over a wide operating range.
- the contours 9 in these areas are thinned out in accordance with the flow, so as not to ultimately reduce the slot width.
- FIG. 4 shows a diagram to illustrate the axial speed profile through the premix burner or swirl generator.
- the x-axis corresponds to the burner axis
- the y-axis the flow velocity u of the burner flow oriented in the axial flow direction.
- the contour 9 according to the invention which locally narrows the flow cross-section (see solid line)
- the axial flow velocity within the premix burner increases is slowed down due to increasing flow instability and, not least because of the irregular cross-sectional expansion at the burner outlet, there is a local flow reversal (see location of the Stagnation point 6), whereby the above-mentioned backflow zone (5) is formed.
- the contour 9 which is also shown schematically above the diagram and which narrows the flow cross section, is used Due to the Bernoulli effect, the flow velocity initially accelerates in the x-direction and, after exceeding the area with the smallest flow cross-section, leads to an efficient flow deceleration, as a result of which the velocity profile experiences a larger gradient, particularly in the front stagnation point 6 (see dashed line). This local increase in the speed or swirl gradient due to the convergent divergent flow control increases the aerodynamic stability of the stagnation point 6 without having to accept significant burner pressure losses.
- FIG. 5 shows a diagram for this purpose, along the x-axis the flame temperature and along the y-axis the strength of pressure fluctuations in a standardized representation.
- the line with the square markings corresponds to the operation of a premix burner with contouring according to the invention
- the graph with diamonds corresponds to a conventional premix burner. It is very clearly shown that, especially at low flame temperatures, far lower pressure fluctuations occur in the premix burner designed according to the invention than in a conventional one.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Combustion Of Fluid Fuel (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05701493A EP1706672B1 (de) | 2004-01-20 | 2005-01-12 | Vormischbrenneranordnung sowie Verfahren zum Betreiben einer Brennkammer |
DE502005005999T DE502005005999D1 (de) | 2004-01-20 | 2005-01-12 | Vormischbrenneranordnung sowie Verfahren zum Betreiben einer Brennkammer |
US10/586,816 US7896646B2 (en) | 2004-01-20 | 2005-01-12 | Premixing burner arrangement for operating a combustion chamber in addition to a method for operating a combustion chamber |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH722004 | 2004-01-20 | ||
CH00072/04 | 2004-01-20 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005068913A1 true WO2005068913A1 (de) | 2005-07-28 |
Family
ID=34754189
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2005/050105 WO2005068913A1 (de) | 2004-01-20 | 2005-01-12 | Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer |
Country Status (6)
Country | Link |
---|---|
US (1) | US7896646B2 (de) |
EP (1) | EP1706672B1 (de) |
CN (1) | CN100538183C (de) |
AT (1) | ATE414874T1 (de) |
DE (1) | DE502005005999D1 (de) |
WO (1) | WO2005068913A1 (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8479720B1 (en) | 2008-10-16 | 2013-07-09 | Oscar Enrique Figueroa | Heating device and method |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0321809A1 (de) * | 1987-12-21 | 1989-06-28 | BBC Brown Boveri AG | Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner |
US5193346A (en) * | 1986-11-25 | 1993-03-16 | General Electric Company | Premixed secondary fuel nozzle with integral swirler |
EP0849531A2 (de) * | 1996-12-20 | 1998-06-24 | United Technologies Corporation | Verbrennungsverfahren mit geringen akustischen Tönen |
US20030074885A1 (en) * | 2000-02-14 | 2003-04-24 | Rokke Nils A | Device in a burner for gas turbines |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3662462D1 (en) | 1985-07-30 | 1989-04-20 | Bbc Brown Boveri & Cie | Dual combustor |
DE19736902A1 (de) * | 1997-08-25 | 1999-03-04 | Abb Research Ltd | Brenner für einen Wärmeerzeuger |
DE59807856D1 (de) * | 1998-01-23 | 2003-05-15 | Alstom Switzerland Ltd | Brenner für den Betrieb eines Wärmeerzeugers |
CN101243287B (zh) * | 2004-12-23 | 2013-03-27 | 阿尔斯托姆科技有限公司 | 具有混合段的预混燃烧器 |
-
2005
- 2005-01-12 US US10/586,816 patent/US7896646B2/en not_active Expired - Fee Related
- 2005-01-12 EP EP05701493A patent/EP1706672B1/de not_active Not-in-force
- 2005-01-12 CN CNB2005800027291A patent/CN100538183C/zh not_active Expired - Fee Related
- 2005-01-12 AT AT05701493T patent/ATE414874T1/de not_active IP Right Cessation
- 2005-01-12 DE DE502005005999T patent/DE502005005999D1/de active Active
- 2005-01-12 WO PCT/EP2005/050105 patent/WO2005068913A1/de active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5193346A (en) * | 1986-11-25 | 1993-03-16 | General Electric Company | Premixed secondary fuel nozzle with integral swirler |
EP0321809A1 (de) * | 1987-12-21 | 1989-06-28 | BBC Brown Boveri AG | Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner |
EP0849531A2 (de) * | 1996-12-20 | 1998-06-24 | United Technologies Corporation | Verbrennungsverfahren mit geringen akustischen Tönen |
US20030074885A1 (en) * | 2000-02-14 | 2003-04-24 | Rokke Nils A | Device in a burner for gas turbines |
Also Published As
Publication number | Publication date |
---|---|
EP1706672A1 (de) | 2006-10-04 |
DE502005005999D1 (de) | 2009-01-02 |
US7896646B2 (en) | 2011-03-01 |
EP1706672B1 (de) | 2008-11-19 |
US20080227039A1 (en) | 2008-09-18 |
CN100538183C (zh) | 2009-09-09 |
ATE414874T1 (de) | 2008-12-15 |
CN1910403A (zh) | 2007-02-07 |
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