WO2008128955A1 - Swirler - Google Patents

Swirler Download PDF

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Publication number
WO2008128955A1
WO2008128955A1 PCT/EP2008/054658 EP2008054658W WO2008128955A1 WO 2008128955 A1 WO2008128955 A1 WO 2008128955A1 EP 2008054658 W EP2008054658 W EP 2008054658W WO 2008128955 A1 WO2008128955 A1 WO 2008128955A1
Authority
WO
WIPO (PCT)
Prior art keywords
swirler
twisted
central axis
vanes
sections
Prior art date
Application number
PCT/EP2008/054658
Other languages
French (fr)
Inventor
Nigel Wilbraham
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to US12/597,261 priority Critical patent/US20100175381A1/en
Priority to CN2008800133415A priority patent/CN101668989B/en
Priority to EP08736322A priority patent/EP2137460A1/en
Publication of WO2008128955A1 publication Critical patent/WO2008128955A1/en

Links

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
    • F23R3/02—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
    • 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
    • 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

Definitions

  • the invention relates to a fuel injection system and improvements for the further diminishment of air pollutants such as nitrogen oxides (NO x ) .
  • the first is to use a fine distribution of fuel in the air, generating a fuel/air mixture with a low fuel fraction.
  • the thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and limits the temperature rise of the products of combustion to a level where thermal NO x is not excessively formed.
  • the second measure is to provide a thorough mixing of fuel and air prior to combustion. The better the mixing, the fewer regions exist where the fuel concentration is significantly higher than average, the fewer the regions reaching higher temperatures than average, the lower the fraction of thermal NO x will be.
  • premixing of fuel and air in a gas turbine engine takes place by injecting fuel into an air stream in a swirling zone of a combustor which is located upstream from the combustion zone.
  • the swirling produces a mixing of fuel and air before the mixture enters the combustion zone.
  • An object of the invention is to provide a swirler, allowing for a better pre-mixing of gaseous fuel and compressor air to provide a homogeneous fuel/air mixture and thereby reduce formation of NO x .
  • Another objective is to provide a burner with an improved swirler.
  • Still another objective is to provide a gas turbine with an improved swirler.
  • An inventive swirler incorporates a modified radial swirler assembly.
  • the modification is best described by a partly twisted radial swirler.
  • None of the prior art is targeting the generation of turbulent secondary flows along the swirl vanes with the specific aim of assisting fuel air mixing.
  • the twisted vanes comprise straight parts at the base portions of the twisted vanes.
  • This feature provides a well defined shear layer region for any reverse flow into the swirler assembly. This is advantageous because it increases the stability of any flame in that region.
  • the height of the straight parts should not exceed 50% of the twisted vanes' height in order to benefit from the turbulent secondary flows generated in the twisted parts. Therefore it is also advantageous to twist the vanes by an angle of up to 120°. However, twisted vanes with angles differing considerably from 120° will also provide desirable turbulent secondary flows.
  • Figure 1 shows a perspective view of a prior art radial swirler
  • Figure 2 shows a perspective view of a swirler in accordance with the present invention
  • Figure 3 shows another perspective view of a swirler with twisted vanes in accordance with the present invention.
  • FIG. 1 a typical prior art radial swirler 1 is shown.
  • the turning vanes 9 of a radial swirler 1 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body.
  • the vanes 9 are of pie slice type with substantially triangular cross-sections 4 (see Figure 3) and rectangular side faces 13 and a slightly curved outer surface 10.
  • the turning vanes 9 are fixed to a second plate 8 with their sides showing away from the first plate 2.
  • Swirler passages 14 are formed by opposing side faces 13 of swirler vanes 9, by the surface of the first plate 2 and by a surface of the second plate 8.
  • the second plate 8 is connected to a combustion pre-chamber 11.
  • This configuration of the swirler 1 forces the airflow (as shown by the arrows) to move within the passages 14 radially inwardly towards the central axis 3 of the swirler 1 body.
  • a radial swirler 1 is capable of creating strong swirl and thorough mixing with little concern of the problem of aerodynamic wake flows.
  • FIG 2 shows the view of an embodiment of the inventive swirler 1.
  • Respective base portions 6 of the turning vanes 9 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body and the cross-sections 4 (see Figure 3) of the vanes 9 are of substantially triangular shape.
  • the vanes 9 are twisted and will be referred to as twisted vanes 5.
  • the embodiment of Figure 2 comprises twisted vanes 5 with straight base portions 6 and twisted parts 7.
  • the straight base portions 6 have a shape described by a translation of the vane cross-sections 4 (see Figure 3) parallel to the central axis 3 of the swirler 1, whereas the twisted parts 7 have a shape described by a further translation of the vane cross-sections 4 along the central axis 3 superimposed by a rotation of the vane cross- sections 4 about the central axis 3.
  • an inventive swirler 1 is shown without second plate 8 and combustor pre-chamber 11 (see Figures 1 and 2) where the twisted vanes 5 are arranged on a first plate 2.
  • the substantially triangular vane cross- sections 4 can be seen very clearly in this view.
  • Figure 3 shows the turbulent secondary flows 12 generated along the twisted vanes 5, improving fuel/air mixing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Disclosed is a swirler (1), comprising a plate (2) normal to a central axis (3) of the swirler (1), a plurality of vane cross-sections (4) arranged on the plate (2) and radially positioned about the central axis (3) and a plurality of twisted vanes (5).

Description

Description
Swirler
Field of the Invention
The invention relates to a fuel injection system and improvements for the further diminishment of air pollutants such as nitrogen oxides (NOx) .
BACKGROUND OF THE INVENTION
Air pollution is a worldwide concern and many countries have enacted stricter laws further limiting the emission of pollutants from gas turbine engines or offer fiscal or other benefits for environmentally sound installations. Although the prior techniques for reducing the emissions of NOx from gas turbine engines are steps in the right direction, the need for additional improvements remains.
There are two main measures by which reduction of the temperature of the combustion flame can be achieved. The first is to use a fine distribution of fuel in the air, generating a fuel/air mixture with a low fuel fraction. The thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and limits the temperature rise of the products of combustion to a level where thermal NOx is not excessively formed. The second measure is to provide a thorough mixing of fuel and air prior to combustion. The better the mixing, the fewer regions exist where the fuel concentration is significantly higher than average, the fewer the regions reaching higher temperatures than average, the lower the fraction of thermal NOx will be.
Usually the premixing of fuel and air in a gas turbine engine takes place by injecting fuel into an air stream in a swirling zone of a combustor which is located upstream from the combustion zone. The swirling produces a mixing of fuel and air before the mixture enters the combustion zone.
SUMMARY OF THE INVENTION
An object of the invention is to provide a swirler, allowing for a better pre-mixing of gaseous fuel and compressor air to provide a homogeneous fuel/air mixture and thereby reduce formation of NOx. Another objective is to provide a burner with an improved swirler. Still another objective is to provide a gas turbine with an improved swirler.
These objectives are achieved by the claims. The dependent claims describe advantageous developments and modifications of the invention.
An inventive swirler incorporates a modified radial swirler assembly. The modification is best described by a partly twisted radial swirler.
Unlike axial swirlers where the air inflow is predominantly entering the swirler and being deflected by the action of an aerofoil, air is admitted to the swirler over the entire length of the swirl slot or vane section, where it is deflected into a swirling motion.
The added advantage of such a configuration is that the twisted vane ensures that the air entry flow is 'tumbled' and hence provides a means for enhanced fuel air mixing.
None of the prior art is targeting the generation of turbulent secondary flows along the swirl vanes with the specific aim of assisting fuel air mixing.
In an advantageous arrangement the twisted vanes comprise straight parts at the base portions of the twisted vanes. This feature provides a well defined shear layer region for any reverse flow into the swirler assembly. This is advantageous because it increases the stability of any flame in that region. The height of the straight parts should not exceed 50% of the twisted vanes' height in order to benefit from the turbulent secondary flows generated in the twisted parts. Therefore it is also advantageous to twist the vanes by an angle of up to 120°. However, twisted vanes with angles differing considerably from 120° will also provide desirable turbulent secondary flows.
By such a design a better pre-mixing of gaseous fuel with compressor air and a homogeneous fuel/air mixture is achieved to reduce formation of NOx.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will now be further described with reference to the accompanying drawings in which:
Figure 1 shows a perspective view of a prior art radial swirler,
Figure 2 shows a perspective view of a swirler in accordance with the present invention, and Figure 3 shows another perspective view of a swirler with twisted vanes in accordance with the present invention.
In the drawings like references identify like or equivalent parts .
DETAILED DESCRIPTION OF THE INVENTION
Referring to Figure 1, a typical prior art radial swirler 1 is shown. The turning vanes 9 of a radial swirler 1 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body. The vanes 9 are of pie slice type with substantially triangular cross-sections 4 (see Figure 3) and rectangular side faces 13 and a slightly curved outer surface 10. The turning vanes 9 are fixed to a second plate 8 with their sides showing away from the first plate 2. Swirler passages 14 are formed by opposing side faces 13 of swirler vanes 9, by the surface of the first plate 2 and by a surface of the second plate 8. The second plate 8 is connected to a combustion pre-chamber 11.
This configuration of the swirler 1 forces the airflow (as shown by the arrows) to move within the passages 14 radially inwardly towards the central axis 3 of the swirler 1 body.
Already with this simple prior art straight vane geometry, a radial swirler 1 is capable of creating strong swirl and thorough mixing with little concern of the problem of aerodynamic wake flows.
Figure 2 shows the view of an embodiment of the inventive swirler 1. Respective base portions 6 of the turning vanes 9 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body and the cross-sections 4 (see Figure 3) of the vanes 9 are of substantially triangular shape. Unlike prior art, the vanes 9 are twisted and will be referred to as twisted vanes 5. The embodiment of Figure 2 comprises twisted vanes 5 with straight base portions 6 and twisted parts 7. The straight base portions 6 have a shape described by a translation of the vane cross-sections 4 (see Figure 3) parallel to the central axis 3 of the swirler 1, whereas the twisted parts 7 have a shape described by a further translation of the vane cross-sections 4 along the central axis 3 superimposed by a rotation of the vane cross- sections 4 about the central axis 3.
With reference to Figure 3, an inventive swirler 1 is shown without second plate 8 and combustor pre-chamber 11 (see Figures 1 and 2) where the twisted vanes 5 are arranged on a first plate 2. The substantially triangular vane cross- sections 4 can be seen very clearly in this view. Figure 3 shows the turbulent secondary flows 12 generated along the twisted vanes 5, improving fuel/air mixing.

Claims

ClaimsWhat is claimed is:
1. A swirler (1), comprising: a plate (2) normal to a central axis (3) of the swirler (1); a plurality of vane cross-sections (4) arranged on the plate (2) and radially positioned about the central axis (3); and a plurality of twisted vanes (5) arranged on the vane cross- sections (4) .
2. The swirler (1) as claimed in claim 1, further comprising straight base portions (6) arranged on the cross-sections (4) and included in the twisted vanes (5) .
3. The swirler (1) as claimed in claim 2, wherein straight base portions (6) have a shape described by a translation of the vane cross-sections (4) parallel to the central axis (3).
4. The swirler (1) as claimed in claim 1, wherein twisted parts (7) of the twisted vanes (5) have a shape described by a translation of the vane cross-sections (4) along the central axis (3) superimposed by a rotation about the central axis (3) .
5. The swirler (1) as claimed in claim 1 or claim 4, wherein an angle of rotation is up to 120°.
6. The swirler (1) as claimed in claim 2 or claim 3, wherein the straight base portions (6) have a height less than 50% of a twisted vane height.
7. A burner comprising a swirler (1) as claimed in any of the preceding claims .
8. A turbine engine with a burner as claimed in claim 7.
PCT/EP2008/054658 2007-04-23 2008-04-17 Swirler WO2008128955A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US12/597,261 US20100175381A1 (en) 2007-04-23 2008-04-17 Swirler
CN2008800133415A CN101668989B (en) 2007-04-23 2008-04-17 Swirler
EP08736322A EP2137460A1 (en) 2007-04-23 2008-04-17 Swirler

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07008236A EP1985924A1 (en) 2007-04-23 2007-04-23 Swirler
EP07008236.7 2007-04-23

Publications (1)

Publication Number Publication Date
WO2008128955A1 true WO2008128955A1 (en) 2008-10-30

Family

ID=38521629

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/054658 WO2008128955A1 (en) 2007-04-23 2008-04-17 Swirler

Country Status (5)

Country Link
US (1) US20100175381A1 (en)
EP (2) EP1985924A1 (en)
CN (1) CN101668989B (en)
RU (1) RU2467253C2 (en)
WO (1) WO2008128955A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2612694C2 (en) * 2014-03-28 2017-03-13 Яньсинь ЛИ Combustion chamber with forced flow reversing

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8517719B2 (en) * 2009-02-27 2013-08-27 Alstom Technology Ltd Swirl block register design for wall fired burners
SI22991A (en) * 2009-03-19 2010-09-30 BRINOX@@d@o@o Enhanced processing device for coating particles based on a new air vortex generator concept
WO2012156631A1 (en) * 2011-05-17 2012-11-22 Snecma Annular combustion chamber for a turbomachine
DK2718644T3 (en) * 2011-06-10 2020-11-30 Carrier Corp EJECTOR WITH DRIVING POWER VILLAGE
EP2685160B1 (en) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Premix burner of the multi-cone type for a gas turbine
EP3236157A1 (en) * 2016-04-22 2017-10-25 Siemens Aktiengesellschaft Swirler for mixing fuel with air in a combustion engine
JP2023007855A (en) * 2021-07-02 2023-01-19 本田技研工業株式会社 fuel nozzle device
US20230212984A1 (en) * 2021-12-30 2023-07-06 General Electric Company Engine fuel nozzle and swirler

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4203598C1 (en) * 1992-02-07 1993-06-24 Industrial Technology Research Institute, Chutung, Hsing-Chu, Tw Burner swirl-inducing component with axial vanes - has deflection points on curved vanes determined dependent on inner and outer radii edge curvature and passage diameter
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
EP0902237A2 (en) * 1997-09-10 1999-03-17 Mitsubishi Heavy Industries, Ltd. Combustor swirler with twisted vanes
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
US20030172655A1 (en) * 2002-03-12 2003-09-18 Verdouw Albert J. Dry low combustion system with means for eliminating combustion noise

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2657741A (en) * 1948-07-06 1953-11-03 Ralph C Brierly Air control ring
JPS6097351U (en) * 1983-12-09 1985-07-03 アイシン精機株式会社 Swirler for Stirling engine
US4681532A (en) * 1985-05-02 1987-07-21 Landy Chung Boiler furnace air register
US5144804A (en) * 1989-07-07 1992-09-08 Fuel Systems Textron Inc. Small airblast fuel nozzle with high efficiency inner air swirler
DE4110507C2 (en) * 1991-03-30 1994-04-07 Mtu Muenchen Gmbh Burner for gas turbine engines with at least one swirl device which can be regulated in a load-dependent manner for the supply of combustion air
JPH06272862A (en) * 1993-03-18 1994-09-27 Hitachi Ltd Method and apparatus for mixing fuel into air
US5450724A (en) * 1993-08-27 1995-09-19 Northern Research & Engineering Corporation Gas turbine apparatus including fuel and air mixer
CN1162089A (en) * 1995-12-21 1997-10-15 Abb研究有限公司 Combustion device of heat generator
FR2752917B1 (en) * 1996-09-05 1998-10-02 Snecma ADVANCED HOMOGENIZATION INJECTION SYSTEM
US5899075A (en) * 1997-03-17 1999-05-04 General Electric Company Turbine engine combustor with fuel-air mixer
EP0918191B1 (en) * 1997-11-21 2003-07-02 Alstom Burner for the operation of a heat generator
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
DE19859829A1 (en) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Burner for operating a heat generator
US7104066B2 (en) * 2003-08-19 2006-09-12 General Electric Company Combuster swirler assembly
US7131273B2 (en) * 2004-12-17 2006-11-07 General Electric Company Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers
WO2006094939A1 (en) * 2005-03-09 2006-09-14 Alstom Technology Ltd Burner comprising a premix for combustion chamber
US7237730B2 (en) * 2005-03-17 2007-07-03 Pratt & Whitney Canada Corp. Modular fuel nozzle and method of making
WO2007036964A1 (en) * 2005-09-30 2007-04-05 Ansaldo Energia S.P.A. Method for starting a gas turbine equipped with a gas burner, and axial swirler for said burner
FR2896031B1 (en) * 2006-01-09 2008-04-18 Snecma Sa MULTIMODE INJECTION DEVICE FOR COMBUSTION CHAMBER, IN PARTICULAR A TURBOREACTOR
JP4719059B2 (en) * 2006-04-14 2011-07-06 三菱重工業株式会社 Gas turbine premixed combustion burner
US7762058B2 (en) * 2007-04-17 2010-07-27 Pratt & Whitney Rocketdyne, Inc. Ultra-compact, high performance aerovortical rocket thruster
US8037689B2 (en) * 2007-08-21 2011-10-18 General Electric Company Turbine fuel delivery apparatus and system
US8015821B2 (en) * 2008-01-11 2011-09-13 Spytek Aerospace Corporation Apparatus and method for a gas turbine entrainment system
US20090249789A1 (en) * 2008-04-08 2009-10-08 Baifang Zuo Burner tube premixer and method for mixing air and gas in a gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4203598C1 (en) * 1992-02-07 1993-06-24 Industrial Technology Research Institute, Chutung, Hsing-Chu, Tw Burner swirl-inducing component with axial vanes - has deflection points on curved vanes determined dependent on inner and outer radii edge curvature and passage diameter
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
EP0902237A2 (en) * 1997-09-10 1999-03-17 Mitsubishi Heavy Industries, Ltd. Combustor swirler with twisted vanes
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
US20030172655A1 (en) * 2002-03-12 2003-09-18 Verdouw Albert J. Dry low combustion system with means for eliminating combustion noise

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2612694C2 (en) * 2014-03-28 2017-03-13 Яньсинь ЛИ Combustion chamber with forced flow reversing

Also Published As

Publication number Publication date
EP1985924A1 (en) 2008-10-29
RU2009143010A (en) 2011-05-27
CN101668989B (en) 2012-01-04
RU2467253C2 (en) 2012-11-20
US20100175381A1 (en) 2010-07-15
CN101668989A (en) 2010-03-10
EP2137460A1 (en) 2009-12-30

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