WO2008049678A1 - Burner, in particular for a gas turbine - Google Patents

Burner, in particular for a gas turbine Download PDF

Info

Publication number
WO2008049678A1
WO2008049678A1 PCT/EP2007/059097 EP2007059097W WO2008049678A1 WO 2008049678 A1 WO2008049678 A1 WO 2008049678A1 EP 2007059097 W EP2007059097 W EP 2007059097W WO 2008049678 A1 WO2008049678 A1 WO 2008049678A1
Authority
WO
WIPO (PCT)
Prior art keywords
burner
main
outlet opening
fuel
vane
Prior art date
Application number
PCT/EP2007/059097
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
Priority to EP20060022322 priority Critical patent/EP1918638A1/en
Priority to EP06022322.9 priority
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2008049678A1 publication Critical patent/WO2008049678A1/en

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00Combustion apparatus characterised by arrangements for air supply
    • F23C7/002Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D11/00Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/102Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D14/00Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air
    • F23R3/12Air inlet arrangements for primary air inducing a vortex
    • F23R3/14Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001Air swirling vanes incorporating fuel injectors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D2900/00Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D2900/00Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14Special features of gas burners
    • F23D2900/14021Premixing burners with swirling or vortices creating means for fuel or air
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D2900/00Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14Special features of gas burners
    • F23D2900/14701Swirling means inside the mixing tube or chamber to improve premixing

Abstract

A burner, in particular a gas turbine burner, comprising at least one swirler (2), the swirler (2) having vanes (12) with vane walls delimiting external air passages (14) between the vanes (12) wherein at least one of the vanes (12) comprise at least one main inlet opening (100), at least one main outlet opening (102) located in a vane wall and at least one internal main passage (104) extending from the at least one main inlet opening (100) through the vane (12) to the at least one main outlet opening (102) and a fuel injection system inside at least one of the vanes (12) which comprises at least one fuel outlet opening (108) being open towards the internal main passage (104) so as to allow for injecting fuel into the at least one internal main passage (104) and thereby mixing air with fuel.

Description

Description

Burner, in particular for a gas turbine

The present invention relates to a burner and in particular to gas turbine burner comprising at least one swirler.

In a gas turbine burner a fuel is burned to produce hot pres¬ surised exhaust gases which are then fed to a turbine stage where they, while expanding and cooling, transfer momentum to turbine blades thereby imposing a rotational movement on a turbine rotor. Mechanical power of the turbine rotor can then be used to drive a generator for producing electrical power or to drive a machine. However, burning the fuel leads to a number of undesired pollutants in the exhaust gas which can cause damage to the environment. Therefore, it takes considerable effort to keep the pollutants as low as possi¬ ble. One kind of pollutant is nitrous oxide (NOx). The rate of formation of nitrous oxide depends exponentially on the temperature of the combustion flame. It is therefore at¬ tempted to reduce the temperature over the combustion flame in order to keep the formation of nitrous oxide as low as possible .

There are two main measures by which reduction of the tem¬ perature of the combustion flame is achievable. The first is to use a lean stoichiometry, e.g. a fuel/air mixture with a low fuel fraction. The relatively small fraction of fuel leads to a combustion flame with a low temperature. The sec- ond measure is to provide a thorough mixing of fuel and air before the combustion takes place. The better the mixing is the more uniformly distributed the fuel is in the combustion zone. This helps to prevent hotspots in the combustion zone which would arise from local maxima in the fuel/air mixing ratio.

Modern gas turbine engines therefore use the concept of pre- mixing air and fuel in lean stoichiometry before the combus- tion of the fuel/air mixture. Usually the pre-mixing 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 leads to a mixing of fuel and air before the mixture enters the combustion zone.

DE 38 19 898 Al describes a burner for a combustion chamber of a gas turbine with a swirler having flow profile shaped swirler vanes. The swirler vanes comprise internal fuel channels that open out to the external air passages between the swirler vanes on the pressure sides of the vanes. Com¬ bustion air passes through the external air passages and mixes with the fuel exiting from the internal fuel channels in the swirler vanes. Further downstream the fuel evaporates within the preheated air stream. The swirled fuel/air mix then enters the combustion zone and is ignited by the heat of the air.

If the air injection system comprises a control mechanism for controlling air allocation to the distributed air inlet openings, it is possible to adapt the air injection to different conditions of the burner. This provides flexible control of fuel placement through a wide range of burner conditions. The combustion system thus will be enabled to accommodate the changes in air density and flow rates experienced, for exam¬ ple at off-design conditions, more readily than it is possi¬ ble with existing burner systems.

The injected amount of fuel is dependent on one or more burner conditions and on the load conditions of the gas tur¬ bine engine.

With respect to the mentioned state of the art it is an ob¬ jective of the invention to provide a burner, in particular a gas turbine burner, which is advantageous in providing a ho¬ mogenous fuel/air mixture. This objective is solved by a burner according to claim 1. The dependent claims describe advantageous developments of the invention.

An inventive burner comprises at least one swirler, the swirler having vanes with vane walls delimiting external air passages between the vanes wherein at least one of the vanes comprise at least one main inlet opening, at least one main outlet opening located in a vane wall and at least one inter- nal main passage extending from the at least one main inlet opening through the vane to the at least one main outlet opening. It further comprises a fuel injection system inside at least one of the vanes which comprises at least one fuel outlet opening being open towards the internal main passage so as to allow for injecting fuel into the at least one in¬ ternal main passage and thereby mixing air with fuel. In particular, all of the vanes may comprise at least one main inlet opening, at least one main outlet opening located in a vane wall and at least one internal main passage extending from the at least one main inlet opening through the vane to the at least one main outlet opening. Further, a fuel injec¬ tion system may be provided in all vanes, as well.

The fuel injection system may either be a liquid fuel injec- tion system or a gaseous fuel injection system. When it is a liquid fuel injection system the inventive burner helps to atomise the liquid fuel before it is introduced into an ex¬ ternal air passage which in turn reduces the fraction of ni¬ trous oxide in the exhaust gases of a gas turbine engine due to a more uniform distribution of the liquid fuel in the air stream.

It is particularly advantageous when turbulence of the fuel/air mix is provided as upstream as possible. Therefore the fuel injection opening that opens out to the internal main passage of a vane is used to already inject fuel into an air stream flowing in from the main inlet opening before exiting the vane and to produce turbulence in the air flow. Consequently, a better distribution of the injected fuel can be achieved over the cross sectional area of the internal main passage. In addition, the homogeneity of the fuel/air mixture over the cross sectional area can be increased. This in turn reduces the formation of hot spots which are the main areas of nitrous oxide formation. As a consequence, reduc¬ tion of the number and the temperature of hot spots reduce the emission of nitrous oxides from the burner.

The fuel/air mix then exits from the main outlet opening located in one of the vane walls delimiting an external air passage. A second air flow passes through the external air passages further increasing the portion of air in the fuel/air mix exiting from the main outlet opening of the in- ternal main passage and further increasing the turbulence.

The preferred location of the fuel injection system is be¬ tween mid-height and 2/3rds of the vane height as measured from the vane root or floor of the external air passages.

Advantageously the main inlet opening of the internal main passage is positioned in the vane wall that faces radially outwards. This allows for a straight internal main passage which ensures a minimum pressure loss. The internal main passage can also be curved when using different production methods .

In a further development of the inventive burner, the fuel/air mix is injected into the second air flow in the ex- ternal air passage by the main outlet opening, wherein the cross-section of the main outlet opening is reduced compared to the cross-section of the internal main passage. The reduc¬ tion of the cross-section may advantageously be achieved by a prefilmer lip which partly covers the main outlet opening. The prefilmer lip not only reduces the cross-section of the main outlet opening but also results in a separation of the flow at the prefilmer lip causing an additional turbulence in the fuel/air mix in the external air passage downstream of the prefilmer lip. As a consequence, the droplet size of the atomised fuel introduced into the external air passage is re¬ duced.

The prefilmer lip may be a wedge-like element fixed to the main wall of the vane. This provides a simple design with little assembly effort. The prefilmer lip may have a straight edge running across the main outlet opening which provides a sharp edge for increased flow separation and thus atomising and mixing.

The main outlet opening can be provided with turbulence en¬ hancing features, in particular if it is driven with gaseous fuel. Those features may be present on the circumference of the main outlet opening and may e.g. comprise triangular cuts on the circumference. The turbulence enhancing features pro¬ vide additional mixing and direction of a gaseous fuel/air mixture leaving the internal main passage. Turbulence en¬ hancing features in or on the prefilmer lip are possible, al- though they are less preferable than the turbulence enhancing features on the main outlet opening.

In another advantageous embodiment of the invention the burner comprises an additional fuel injection system inside all or at least one of the vanes which comprises at least one fuel outlet opening being open towards an external air pas¬ sage so as to allow for injecting gaseous or liquid fuel into the external air passage. Preferably, the main outlet open¬ ing and the additional outlet opening are positioned at oppo- site vane walls.

Further features, properties and advantages of the present invention will become clear from the following description of embodiments of the invention in conjunction with the accompa- nying drawings.

Figure 1 schematically shows a section through an inventive burner of a combustion chamber assembly. Figure 2 shows a perspective view of a swirler shown in Fig¬ ure 1. Figure 3 shows perspective view of a vane of the swirler shown in Figure 2. Figure 4 shows a top view of the vane shown in Figure 3.

Figure 1 shows a longitudinal section through a burner and a combustion chamber assembly for a gas turbine engine. A burner with a burner head 1 with a swirler 2 for mixing air and fuel is attached to an upstream end of a combustion cham¬ ber comprising, in flow series, a combustion pre-chamber 3 which is sometimes also called transition piece and a combus¬ tion main chamber 4. In general, the pre-chamber 3 may be implemented as a one part continuation of the burner towards the main chamber 4, as a one part continuation of the main chamber 4 towards the burner, or as a separate part between the burner and the main chamber 4. The burner and the combustion chamber assembly show rotational symmetry about a longitudinally symmetry axis S.

A fuel conduit 5 is provided for leading a gaseous or liquid fuel to the burner which is to be mixed with in-streaming air 6 in the swirler 2. The fuel air mixture 7 is then led to¬ wards a primary combustion zone 9 in the main chamber 4 where it is burnt to form hot, pressurised exhaust gases 8 stream¬ ing in a direction indicated by arrows to a turbine (not shown) of the gas turbine engine.

The swirler 2 is shown in detail in Figure 2. It comprises a ring-shaped swirler vane support 10 carrying six swirler vanes 12. The swirler vanes 12 can be fixed to the burner head 1 with their sides opposite to the swirler vane support 10.

Between neighbouring swirler vanes 12 external air passages 14 are formed which each extend between an air inlet opening 16 and an air outlet opening 18. The external air passages 14 are delimited by opposing end faces 20, 22 of neighbouring swirler vanes 12, by the surface 24 of the swirler vane sup¬ port 10 that faces towards the burner head 1 and by a surface of the burner head 1 to which the swirler vanes 12 are to be fixed. The end faces 20, 22, the surfaces of the swirler vane support 10 and of the burner head 1 form external air passage walls delimiting the external air passages 14.

Figure 3 schematically shows a perspective view of an iso¬ lated swirler vane 12 with a fuel injection system. The top face 101 of the swirler vane 12 according to the orientation of the vane 12 as shown in Fig. 3 would be connected to the swirler vane support 10. The preferred location of the fuel injection system is between mid-height and 2/3rds of the vane height as measured from the vane root or floor of the exter- nal air passages 14.

The swirler vane fuel injection system comprises an internal main passage 104 which in turn comprises a main inlet opening 100 and a main outlet opening 102. The main inlet opening 100 is located in the wall of the swirler vane 12 that faces radially outwards when the vane is fixed to the swirler vane support 10. The main outlet opening 102 is placed in one of the swirler vane walls that delimit the external air passage 14. Air A can be introduced into the internal main passage 104 through the main inlet opening 100.

A wedge 103 is attached to the swirler vane 12. The wedge comprises, in the present embodiment, a liquid fuel inlet opening 106, a liquid fuel injection passage 110 and a liquid fuel outlet opening 108. The liquid fuel inlet opening 106 is located in the wall of the wedge 103 which is to be fixed to the burner head 1 and a liquid fuel outlet opening 108 is located in the wall of the wedge that is fixed to the swirler vane 12. So the liquid fuel outlet opening 108 connects a bended liquid fuel injection passage 110 to the internal main passage 104. Although a liquid fuel injection system is described with respect to the present embodiment, the invention can also be implemented with a gaseous fuel injection system comprising a gaseous fuel outlet opening instead of the liq¬ uid fuel outlet opening 108, a gaseous fuel inlet opening in¬ stead of the liquid fuel inlet opening 106 and a gaseous fuel injection passage instead of the liquid fuel injection pas- sage 110.

The wedge 103 partly covers the main outlet opening 102 and comprises an edge 105 which extends over this opening.

Figure 4 shows a view onto the top face 101 of the vane with the attached wedge. Here, the transition from the liquid fuel injection passage 110 to the internal main passage 104 can be seen more clearly. The liquid fuel injection passage 110 in the wedge 103 opens out into the internal main passage 104 of the vane 12 and provides a flow connection to the in¬ ternal main passage 104. The internal main passage 104 can be straight or e.g. curved when using different production methods .

The Wedge 103 forms a prefilmer lip 105 by reducing the cross-sectional area of the main outlet opening 102 by cover¬ ing a part of the main outlet opening 102.

The wedge 103 can be attached to the swirler vane 12 by fas- tening bolts 118, screws, by other suitable connecting means or, e.g., by welding.

In operation of the swirler of the present embodiment, liquid fuel F flows from the liquid fuel inlet opening 106 in the wedge 103 through the liquid fuel injection passage 110 into the internal main passage 104 where it is mixed with air A. Some fraction of the liquid fuel forms a film flowing along the wedge face 107 towards the wedge's edge 105.

In operation of the swirler, air A is introduced through the main inlet opening 100 and flows through the internal main passage 104 to the main outlet opening 102. The main inlet opening 100, the internal main passage 104 and the main out- let opening 102 are implemented to direct air into the vane 12, to let it mix with fuel exiting the liquid fuel outlet opening 108 and to then direct the fuel/air mix F/A out of the vane 12. The edge 105 of the wedge 103 generates turbu- lences in the fuel/air mixture F/A due to a separation of flow of the fuel/air mixture flowing through the opening. Those turbulences atomize the liquid fuel flowing along the wedge face 107 towards the main outlet opening 102.

As has been already mentioned, a gaseous fuel injection sys¬ tem may be present instead of the liquid fuel injection sys¬ tem. In such a case, the mixing quality of the fuel/air concentration in the flow leaving the main outlet opening 102 depends on where the fuel enters the internal main passage 104. Closer to the main inlet opening 100, potentially yields higher mixing whereas gas fuel injected closer to the main outlet opening 102 will have more pilot like characteristics .

The main outlet opening 102 of the internal main passage may comprise additional turbulence enhancing features at its cir¬ cumference. These features can, e.g. be implemented as tri¬ angular cuts on the circumference (not shown) .

Finally the fuel/air mix F/A is delivered into the external air passage 14 where it is again mixed with air and at the same time swirled.

The fuel/air mixture then leaves the external air passage 14 through the air outlet opening 18 and streams through a central opening 30 of the swirler vane support 10 into the pre- chamber 3 (see Figure 1) . From the pre-chamber 3 it streams into the combustion zone 9 of the main chamber 4 where it is burned.

As an option, there is an additional liquid or gaseous fuel injection system which comprises at least one fuel inlet opening 112, at least one gas passage 116 and at least one gas outlet opening 114. In the present embodiment, the addi¬ tional fuel injection system is a gaseous fuel injection sys¬ tem.

The gas injection system is integrated in the vane 12 and at least one gas inlet opening 112 is located in the vane face to be fixed to the burner head 1. Gas G is taken in through the gas inlet opening 112 and then directed through the at least one gas passage 116. The gas exits through the at least one gas outlet opening 114 into the external air pas¬ sage 14 where it mixes with air. So the gas turbine can be operated with liquid fuel or with gaseous fuel.

Although the swirler of the present embodiment has six swirler vanes and six external air passages, the invention may be implemented with a swirler having a different number of swirler vanes and external air passages, which may either be higher or lower than in the described embodiment. The walls 20, 22, 24 of the external air passage 14 may be straight or curved when using different production methods.

The parts of the burner are usually made of machined metal, in particular stainless steel. The internal fuel channels can comprise different sections with different diameters. Their inlets are located in the face which is attached to the burner head.

Claims

Claims
1. A burner, in particular a gas turbine burner, comprising:
- at least one swirler (2), the swirler (2) having vanes (12) with vane walls delimiting external air passages (14) be¬ tween the vanes (12) wherein at least one of the vanes (12) comprise at least one main inlet opening (100), at least one main outlet opening (102) located in a vane wall and at least one internal main passage (104) extending from the at least one main inlet opening (100) through the vane (12) to the at least one main outlet opening (102) and
- a fuel injection system inside at least one of the vanes (12) which comprises at least one fuel outlet opening (108) being open towards the internal main passage (104) so as to allow for injecting fuel into the at least one internal main passage (104) and thereby mixing air with fuel.
2. The burner, as claimed in claim 1, wherein the fuel injec¬ tion system is located between mid-height and 2/3rds of the vane height.
3. The burner, as claimed in claim 1, wherein the main outlet opening (102) of the internal main passage (104) is posi¬ tioned in one of the vane walls that delimit the external air passage (14) .
4. The burner, as claimed in claim 1, which has an axial and a radial direction wherein the vanes (12) comprise a wall that faces radially outwards and wherein the main inlet open- ing (100) of the internal main passage (104) is positioned in the vane wall that faces radially outwards.
5. The burner, as claimed any of the preceding claims, wherein the fuel injection system is a liquid fuel injection system.
6. The burner, as claimed in any of the claims 1 to 4, wherein the fuel injection system is a gaseous fuel injection system.
7. The burner, as claimed in any of the preceding claims, wherein the cross-section of the main outlet opening (102) is reduced compared to the cross-section of the internal main passage (104) .
8. The burner, as claimed in claim 7, wherein the cross- section is reduced by a prefilmer lip (105) which partly covers the main outlet opening (102) .
9. The burner, as claimed in claim 8, wherein the prefilmer lip (105) is a wedge-like element (103) fixed to the vane wall in which the main outlet opening (102) is located.
10. The burner, as claimed in claim 8 or 9, wherein the pre¬ filmer lip (105) has a straight edge running across the main outlet opening (102) .
11. The burner, as claimed in any of the preceding claims, wherein the main outlet opening (102) is provided with turbulence enhancing features.
12. The burner, as claimed in claim 11, wherein the turbulence enhancing features comprise triangular cuts on the cir¬ cumference of the main outlet opening (102) .
13. The burner, as claimed in any of the preceding claims, comprising an additional fuel injection system inside at least one of the vanes which comprises at least one fuel out¬ let opening (114) being open towards an external air passage (14) so as to allow for injecting fuel into the external air passage (14) .
14. The burner, as claimed in claim 13, wherein the main outlet opening (102) and the outlet opening (114) of the addi¬ tional fuel injection system are positioned on opposite vane walls .
PCT/EP2007/059097 2006-10-25 2007-08-31 Burner, in particular for a gas turbine WO2008049678A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP20060022322 EP1918638A1 (en) 2006-10-25 2006-10-25 Burner, in particular for a gas turbine
EP06022322.9 2006-10-25

Publications (1)

Publication Number Publication Date
WO2008049678A1 true WO2008049678A1 (en) 2008-05-02

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ID=37807871

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Application Number Title Priority Date Filing Date
PCT/EP2007/059097 WO2008049678A1 (en) 2006-10-25 2007-08-31 Burner, in particular for a gas turbine

Country Status (2)

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EP (1) EP1918638A1 (en)
WO (1) WO2008049678A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045950A1 (en) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se swirl generator
US20110113784A1 (en) * 2009-11-18 2011-05-19 Paul Headland Swirler Vane, Swirler and Burner Assembly
JP2015534632A (en) * 2012-10-01 2015-12-03 アルストム テクノロジー リミテッドALSTOM Technology Ltd A combustor comprising a stepped been premixed by the pilot in the radial direction for improved maneuverability
JP2017519172A (en) * 2014-04-03 2017-07-13 ゼネラル・エレクトリック・カンパニイ Low emission gas turbine combustor air fuel premixing device
CN107466354A (en) * 2015-04-01 2017-12-12 西门子股份公司 Swirler, burner and combustor for a gas turbine engine

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Publication number Priority date Publication date Assignee Title
EP2169312A1 (en) 2008-09-25 2010-03-31 Siemens Aktiengesellschaft Stepped swirler for dynamic control
EP2236919A1 (en) * 2009-03-17 2010-10-06 Siemens Aktiengesellschaft Burner and method for operating a burner, in particular for a gas turbine
DE102009038845A1 (en) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Swirl blade, burner and gas turbine
KR20160071791A (en) * 2014-12-12 2016-06-22 한화테크윈 주식회사 Swirler assembly
KR20160071792A (en) * 2014-12-12 2016-06-22 한화테크윈 주식회사 Swirler assembly

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US3300976A (en) * 1964-02-21 1967-01-31 Rolls Royce Combined guide vane and combustion equipment for bypass gas turbine engines
US3455108A (en) * 1966-02-28 1969-07-15 Technology Uk Combustion devices
JPS60126521A (en) * 1983-12-08 1985-07-06 Nissan Motor Co Ltd Fuel injection valve of combustor for gas turbine
DE3819898A1 (en) * 1988-06-11 1989-12-14 Daimler Benz Ag Combustion chamber for a thermal turbo-engine
GB2293001A (en) * 1994-09-12 1996-03-13 Gen Electric Dual fuel mixer for gas turbine combustor
US5816049A (en) * 1997-01-02 1998-10-06 General Electric Company Dual fuel mixer for gas turbine combustor
US20020174656A1 (en) * 1999-10-29 2002-11-28 Olaf Hein Turbine engine burner

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3300976A (en) * 1964-02-21 1967-01-31 Rolls Royce Combined guide vane and combustion equipment for bypass gas turbine engines
US3455108A (en) * 1966-02-28 1969-07-15 Technology Uk Combustion devices
JPS60126521A (en) * 1983-12-08 1985-07-06 Nissan Motor Co Ltd Fuel injection valve of combustor for gas turbine
DE3819898A1 (en) * 1988-06-11 1989-12-14 Daimler Benz Ag Combustion chamber for a thermal turbo-engine
GB2293001A (en) * 1994-09-12 1996-03-13 Gen Electric Dual fuel mixer for gas turbine combustor
US5816049A (en) * 1997-01-02 1998-10-06 General Electric Company Dual fuel mixer for gas turbine combustor
US20020174656A1 (en) * 1999-10-29 2002-11-28 Olaf Hein Turbine engine burner

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045950A1 (en) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se swirl generator
US20110113784A1 (en) * 2009-11-18 2011-05-19 Paul Headland Swirler Vane, Swirler and Burner Assembly
JP2015534632A (en) * 2012-10-01 2015-12-03 アルストム テクノロジー リミテッドALSTOM Technology Ltd A combustor comprising a stepped been premixed by the pilot in the radial direction for improved maneuverability
JP2017519172A (en) * 2014-04-03 2017-07-13 ゼネラル・エレクトリック・カンパニイ Low emission gas turbine combustor air fuel premixing device
CN107466354A (en) * 2015-04-01 2017-12-12 西门子股份公司 Swirler, burner and combustor for a gas turbine engine

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