EP2137460A1 - Swirler - Google Patents

Swirler

Info

Publication number
EP2137460A1
EP2137460A1 EP08736322A EP08736322A EP2137460A1 EP 2137460 A1 EP2137460 A1 EP 2137460A1 EP 08736322 A EP08736322 A EP 08736322A EP 08736322 A EP08736322 A EP 08736322A EP 2137460 A1 EP2137460 A1 EP 2137460A1
Authority
EP
European Patent Office
Prior art keywords
swirler
twisted
central axis
vanes
sections
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Withdrawn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
EP08736322A
Other languages
German (de)
French (fr)
Inventor
Nigel Wilbraham
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP08736322A priority Critical patent/EP2137460A1/en
Publication of EP2137460A1 publication Critical patent/EP2137460A1/en
Withdrawn legal-status Critical Current

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.
EP08736322A 2007-04-23 2008-04-17 Swirler Withdrawn EP2137460A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08736322A EP2137460A1 (en) 2007-04-23 2008-04-17 Swirler

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07008236A EP1985924A1 (en) 2007-04-23 2007-04-23 Swirler
EP08736322A EP2137460A1 (en) 2007-04-23 2008-04-17 Swirler
PCT/EP2008/054658 WO2008128955A1 (en) 2007-04-23 2008-04-17 Swirler

Publications (1)

Publication Number Publication Date
EP2137460A1 true EP2137460A1 (en) 2009-12-30

Family

ID=38521629

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07008236A Withdrawn EP1985924A1 (en) 2007-04-23 2007-04-23 Swirler
EP08736322A Withdrawn EP2137460A1 (en) 2007-04-23 2008-04-17 Swirler

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07008236A Withdrawn EP1985924A1 (en) 2007-04-23 2007-04-23 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)

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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
CN103851623B (en) * 2014-03-28 2017-03-15 李延新 A kind of combustor of pressure Hui Yan
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

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Also Published As

Publication number Publication date
WO2008128955A1 (en) 2008-10-30
CN101668989A (en) 2010-03-10
EP1985924A1 (en) 2008-10-29
RU2009143010A (en) 2011-05-27
US20100175381A1 (en) 2010-07-15
CN101668989B (en) 2012-01-04
RU2467253C2 (en) 2012-11-20

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