WO2015121063A1 - Coupelle de turbulence pour brûleur de turbine à gaz - Google Patents

Coupelle de turbulence pour brûleur de turbine à gaz Download PDF

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Publication number
WO2015121063A1
WO2015121063A1 PCT/EP2015/051612 EP2015051612W WO2015121063A1 WO 2015121063 A1 WO2015121063 A1 WO 2015121063A1 EP 2015051612 W EP2015051612 W EP 2015051612W WO 2015121063 A1 WO2015121063 A1 WO 2015121063A1
Authority
WO
WIPO (PCT)
Prior art keywords
swirler
fuel
gas turbine
turbine engine
fuel injection
Prior art date
Application number
PCT/EP2015/051612
Other languages
English (en)
Inventor
Ghenadie Bulat
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 EP15702711.1A priority Critical patent/EP3105507A1/fr
Priority to US15/116,590 priority patent/US20160348914A1/en
Publication of WO2015121063A1 publication Critical patent/WO2015121063A1/fr

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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F23D11/26—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention is related to a fuel injection means for a swirler of a burner of a gas turbine engine, the swirler comprising a plurality of vanes and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means
  • the invention is related to a swirler for a burner of a gas turbine engine, comprising fuel injection means, a plurality of vanes and plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means comprising at least two injection ports to inject fuel into the channelled air, further to a burner of a gas turbine engine, comprising a swirler and a combustion chamber and further to a gas turbine engine, comprising at least one burner.
  • Such gas turbine engines are commonly used in industrial applications. Such gas turbine engines can comprise a pilot burner with a pilot burner fuel delivery arrangement
  • Fig. 1 shows a sectional view of an example of a gas turbine engine 10.
  • upstream and downstream refer to the flow direction of the air flow and/or working gas flow through the engine unless otherwise stated.
  • the terms forward and reward refer to the general flow of gas through the engine.
  • the term axial, radial and circumferential are made with reference to a rotational axis 20 of the gas turbine engine 10.
  • the gas turbine engine 10 comprises, in flow series, an inlet 12, a compressor section 14, a combustor section 16 and a turbine section 18 which are generally arranged in flow series and generally in the direction of a longitudinal or rotational axis 20.
  • the gas turbine engine 10 further comprises a shaft 22 which is rotatable about the rotational axis 20 and which extends longitudinally through the gas turbine engine 10.
  • the shaft 22 drivingly connects the turbine section 18 to the compressor section 14.
  • air 24 which is taken in through the air inlet 12, is compressed by the compressor section 14 and delivered to the combustion or burner section 16.
  • the burner section 16 comprises an array of combustors each having a combustor axis 17 and arranged thereabout a burner plenum 26, one or more combustion
  • the combustion chambers 28 and the burners 30 are located inside the burner plenum 26.
  • the turbine section 18 comprises a number of blade-carrying discs 36 attached to the shaft 22.
  • two discs 36 each carry an annular array of turbine blades 38.
  • the number of blade-carrying discs 36 could be different, i.e. only one disc or more than two discs.
  • guiding vanes 40 which are fixed to a stator 42 of the gas turbine engine 10, are disposed between the turbine blades 38. Between the exit of the combustion chamber 28 and the leading turbine blades 38 inlet guiding vanes 44 are provided .
  • the combustion gas 34 from the combustion chamber 28 enters the turbine section 18 and drives the turbine blades 38 which in turn rotate the shaft 22.
  • the guiding vanes 40, 44 serve to optimize the angle of the combustion or working gas on the turbine blades 38.
  • the compressor section 14 comprises an actual series of guide vane stages 46 and rotor blade stages 48.
  • Gas turbine engines in general are normally optimized for full load operation. Especially the mixing of fuel and air in a swirler of a burner of the gas turbine engine is crucial to achieve a high efficiency during the operation of the gas turbine engine. Therefore the parts, especially the fuel injection means, are designed such to achieve an optimum mixing of fuel and air for a full load operation of the gas turbine engine.
  • the reliability of the gas turbine engine may be affected by such poor mixing of fuel and air.
  • a good portion of liquid fuel cannot atomize and therefore liquid ligaments often attach and/or are deposited to the internal surface of the components and form a carbon build ⁇ up.
  • the engine may suffer from disadvantages such as obstruction of fuel injection ports by carbon build-up, poor ignition caused by obstructed igniter ports and/or pre- chamber covering with carbon build-up which may result in long-term damage of the gas turbine engine. It is known to enhance the reliability of gas turbine engines operated at part loads by bleeding compressed air from the engine and thus increasing the flame temperature. This leads to a burn-off of a portion of the carbon build-up.
  • a fuel injection means for a swirler of a burner of a gas turbine engine comprising a plurality of vanes and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means comprising at least two injection ports to inject fuel into the channelled air.
  • the fuel injection means according to the invention is characterized in that the fuel injection means is enabled to change the number of injection ports used for the fuel injection.
  • the swirler described in the preamble is used in a burner of a gas turbine engine to produce an air/fuel mixture. This air/fuel mixture is afterwards burned in a combustion chamber of the burner.
  • the fuel injection means used to inject fuel into the channelled air in the mixing channel comprises at least two injection ports. These injections ports are
  • injection means is enabled to change the number of injection ports used for the fuel injection. Therefore it is possible, to use many, especially all, injection ports for an operation of the gas turbine engine at full load. For an operation of the gas turbine engine at a part load only a few, even down to one, injection ports can be used. This feature allows to provide fuel by a fuel injection means at such a high
  • fuel injection means according to the invention can be characterized in that the fuel injection means comprises a spring loaded mechanism to change the number of injection ports used for the fuel injection.
  • a spring loaded mechanism is especially a mechanical easy way to change the number of used injection ports.
  • no other driving means are necessary and/or used to change the number of used injection ports.
  • no external engine such as an electric motor or a hydraulic system is necessary to achieve the change of the number of used injection ports.
  • the spring loaded mechanism is enabled to be driven by the pressure of the fuel to be injected. Especially, the force of the spring loaded
  • the mechanism can be directed against the pressure of the fuel.
  • the load level should be increased, more fuel is needed to achieve this high load operation of the gas turbine engine. This leads to an enlargement of the pressure in the fuel system of the gas turbine engine. Therefore, this higher pressure in the fuel system can be used to drive the spring loaded mechanism.
  • a higher pressure of the fuel in the fuel system of the gas turbine engine results in a higher force of the fuel against a spring of the spring loaded mechanism.
  • a spring loaded mechanism enabled to be driven by the pressure of the fuel to be injected is a very easy way to control such a spring loaded mechanism.
  • a spring loaded mechanism comprises a piston arranged in the common feeding pipe.
  • a feeding pipe can be used to feed the fuel to the several injection ports.
  • the injection ports are arranged at the feeding pipe, especially in a linear way.
  • the piston is arranged inside the feeding pipe and separates the fuel in the feeding pipe from a spring of the spring loaded mechanism.
  • For an operation at higher load more fuel is needed to be burned in the burner of the gas turbine engine. Therefore, in the fuel system of the gas turbine engine higher pressure is present. Through the force of the fuel at this higher pressure the piston is driven back inside the feeding pipe and consequently more injection ports are opened for injecting fuel into the air. By doing so, the number of used injection ports is automatically adapted to the load level of the operation of the gas turbine engine.
  • fuel injection means according to the invention can be characterized in that the fuel injection means are enabled to be arranged at a trailing edge of one of the vanes of the swirler.
  • the trailing edges of the vanes of the swirler are positioned at the end of the respective mixing channel.
  • a fuel injection means can be characterized in that the fuel injection means are constructed as a fuel injection lance. Such a fuel injection lance can be positioned inside the mixing channel. The positioning of the fuel injection lance inside the mixing channel can be done at the radially outer end of the mixing channel, at the radially inner end of the mixing channel or in between. Therefore it is possible, to choose the position of the fuel injection lance inside the mixing channel to meet the demands of the gas turbine engine to be used in.
  • fuel injection means can be characterized in that the injection ports are arranged in a counter-flow or a co-flow or a vertical spiral direction in respect to a direction of the channelled air.
  • a swirler for a burner of a gas turbine engine comprising fuel injection means, a plurality of vanes and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means comprising at least two injection ports to inject fuel into the channelled air.
  • a swirler according to the invention is characterized in that the fuel injection means is constructed according to the first aspect of the invention. The use of such a fuel injection means provides the same advantages, which have been discussed in detail according to the fuel injection means according to the first aspect of the
  • a burner of a gas turbine engine comprising a swirler and a combustion chamber.
  • a burner according to the invention is characterized in that the swirler is constructed according to the second aspect of the invention.
  • the use of such a swirler provides the same advantages which have been discussed in detail according to a swirler according to the second aspect of the invention.
  • a gas turbine engine comprising at least one burner.
  • a gas turbine engine according to the invention is characterized in that the burner is constructed according to the third aspect of the invention.
  • the use of such a burner provides the same advantages, which have been discussed in detail according to a burner according to the third aspect of the invention.
  • Fig. 1 a sectional view of a gas turbine according to prior art
  • Fig. 2a a fuel injection means according to prior art
  • Fig. 3a,b,c fuel injection means according to the invention.
  • a swirler 52 In fig. 2a, 2b parts of a swirler 52 according to prior art are shown. In detail, one of the vanes 54 and a mixing channel 56 is shown. In the mixing channel 56 air 24 is channelled from a radially outer end 58 to a radially inner end 60 of the mixing channel 56. Inside the mixing channel 56 a fuel injection means 50 is placed. This fuel injection means 50 is in this embodiment constructed as a fuel
  • injection lance 74 At the end of the fuel injection lance 74 an injection port 62 is located. Through this injection port 62 a fuel injection 66 of fuel 64 into the air 24 is carried out.
  • the shown fuel injection lance 74 is optimized and designed for a full load operation of the gas turbine engine 10. Therefore, at part load operations of the gas turbine engine less fuel 64 is injected 66 into the air 24. An atomization of the complete fuel 64 cannot be secured.
  • the fuel injection means 50 comprises a feeding pipe 70 in which a spring loaded mechanism 68 is placed.
  • the spring loaded mechanism 68 comprises at its end a piston 72 which separates the spring loaded mechanism 68 and the fuel 64 in the feeding pipe 70.
  • the three figures 3a, 3b, 3c show different fuel injections 66 for different load levels of the gas turbine engine 10. In fig. 3a a low level operation is carried out.
  • the pressure of the fuel 64 in a fuel system of the gas turbine engine 10 is low. Therefore the pressure of the fuel 64 which carries out a force on the piston 72 is small.
  • the piston 72 is pressed such that only one of the three injection ports 62 is opened. Only through this injection port 66 fuel 64 is injected into the air 24. The other two injection ports 62 stay closed. Due to the fact that only one of the injection ports 62 is used, a good atomization of the fuel 64 in the fuel injection 66 can nevertheless be secured.
  • fig. 3b a mid-level load operation of the gas turbine engine 10 is shown. The pressure in the fuel system has risen and therefore the piston 72 is pressed further against the spring level mechanism 68 inside the feeding pipe 70.
  • a second injection port 62 is opened and more fuel 64 is injected into the channelled air 24 in the mixing channel 56.
  • the third picture fig. 3c a full load operation of the gas turbine engine 10 is shown. The pressure of the fuel inside the feeding pipe 70 is high enough that all of the injection ports 62 are opened. A maximum amount of fuel 64 can be injected 66 into the channelled air 24 in the mixing channel 56.
  • injection means 50 allows a fuel injection 66 of fuel 64 into air 24 in a mixing channel 56 adapted to the load level of the gas turbine engine 10. By changing the number of used injection ports 62 a good
  • atomization of the fuel 64 can be secured at each load level of the operation of the gas turbine engine 10. This leads to a highly efficient operation of the gas turbine engine 10 independent of its load level. In addition carbon build-up on internal surfaces of the gas turbine engine 10, especially on injection ports 62, can be prohibited.
  • the fuel injection means 50 can vary the height above a base 57 of the mixing channel 56 or the axial extent 59 of the fuel injection 64 from the fuel injection ports 62.
  • the fuel is injected over a relatively small axial extent from one or the first fuel injection port 62A (see Fig.3B) .
  • the next or second fuel injection port 62B is exposed and fuel is
  • variable fuel subsequently in a pre-chamber 31 and the main combustion chamber 28 (see fig.l) . Therefore, the variable fuel
  • injection means 50 can inject fuel over a greater axial extent and vary the extent than prior art systems and ensure a higher degree of atomisation of the fuel in the air flow along with a better distribution of the fuel/air mixture. This results in improved mixing of fuel and air, better combustion characteristics, increased efficiency and
  • the spring loaded mechanism 68 has a generally linear bias such that the fuel pressure and position of the piston 72 in the common feeding pipe 70 have a linear relationship.
  • the spring loaded mechanism 68 has a non-linear bias and an increase in fuel pressure has a increasing bias the further the spring loaded mechanism 68 is compressed or forced away from the base 57.
  • a relatively small change in fuel pressure causes a relatively large movement of the piston at part load operation. This is particularly advantageous at part load operation where small variations in pressure usually occur and the effect of fuel mixing is important on combustion performance of the system.
  • a first increase in fuel pressure then exposes the second injection port 62B as shown in Fig.3B; to expose the third injection port 62C a second increase in fuel pressure is required and which is greater than the first increase in fuel pressure to move the piston 72 as shown in Fig.3C.
  • the positions or heights of the injection ports 62A, 62B, 62C are set based on the air flow characteristics through the channel 56.
  • the non-linear bias or stiffness of the spring mechanism 68 may be achieved in a number of ways.
  • One way is to have a spring with a helix having a variable tightness.
  • Another way is to have a spring with a varying thickness and therefore stiffness of the wire the helix is formed from.
  • Another way is to have a second spring or further springs extending part of the length of the main spring 68.
  • a helical spring is shown in the figures, other spring or resilient means may be utilised which could be mechanical or field derived.
  • the term spring mechanism is not intended to be restricted to helical wire springs.
  • the injection ports 62 are located at axially spaced apart locations.
  • the injection ports 62 are located along an axial line, that is to say they are aligned in the axial direction of combustor axis 17.
  • the injection ports 62 may be located at a radial offset from one another with respect to the combustor axis 17.
  • at least one of the injector ports 62A, 62B, 62C is closer to the combustor axis 17 than the others. This radial offset can ensure the injection of fuel 64 is placed into the best possible location of the air flowing through the mixing channel 56.
  • the common feeding pipe 70 is shown extending parallel to the combustor axis 17, the common feeding pipe 70 could be angled from the combustor axis 17 so as to enable one or more of the injector ports 62A, 62B, 62C to be radially offset.
  • the three (or more) injection ports 62A-C may be unequally spaced such that Dl > D2 or Dl ⁇ D2.
  • Dl > D2 at low loads it may be beneficial to require a greater fuel pressure to expose the middle or second injection port 62 such that the fuel is particularly well atomised by virtue of a high fuel mass flow and therefore velocity passing through the first injector port 62A to give a wider range of low load
  • injection ports 62A-C have similar outlet areas and therefore issue approximately the same amount of fuel when they are all fully exposed. However, in other examples the outlet areas may be different such that different quantities of fuel are issue from one or all the injection ports 62A-C. This can be beneficial to tailor the delivery of fuel into the different areas 64 of heights above the base 57 for different load demands while assuring good fuel atomisation.
  • the first injection port 62A may have a smaller area than second and third injection ports 62B, 62C. Thus at low load where approximately 10%-20% power is demanded good fuel atomisation occurs and the injection port 62A is sized for the respective fuel pressure to deliver an optimised fuel/air mixture.
  • the fuel pressure is sufficient to urge the piston 72 to expose the second injection port 62B where its larger outlet area gives the combination of the first and second outlet areas a wider range of operability.
  • the fuel pressure is sufficient to urge the piston 72 to expose the third injection port 62C where its outlet area, larger that the first injection port 62A, gives the
  • the common feeding pipe 70 and the spring loaded mechanism 68 could be arranged the opposite way to that shown in figs 3A-3C such that rather than fuel being supplied axially outwardly in a direction from the base 57, the fuel may be supplied axially inwardly in a direction towards the base 57 and from the axially outward part of the vane 54. Therefore the spring loaded mechanism 68 may be located between the base 57 and the piston 72. An increase in the fuel pressure would then drive the piston 72 towards the base. It should also be appreciated that any of the

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un moyen d'injection de carburant pour une coupelle de turbulence d'un brûleur de turbine à gaz, une coupelle de turbulence pour un brûleur de turbine à gaz, un brûleur de turbine à gaz, et une turbine à gaz. La présente invention concerne un moyen d'injection de carburant (50) pour une coupelle de turbulence (52) d'un brûleur de turbine à gaz (10), la coupelle de turbulence (52) comprenant une pluralité d'aubes (54) et une pluralité de canaux de mélange entre les aubes (54) pour acheminer l'air (24) d'une extrémité radialement extérieure du canal de mélange à une extrémité radialement intérieure du canal de mélange, le moyen d'injection de carburant (50) comprenant au moins deux orifices d'injection (62) pour injecter du carburant (64) dans l'air acheminé (24). En outre, l'invention concerne une coupelle de turbulence pour un brûleur de turbine à gaz, un brûleur de turbine à gaz, et une turbine à gaz.
PCT/EP2015/051612 2014-02-11 2015-01-27 Coupelle de turbulence pour brûleur de turbine à gaz WO2015121063A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15702711.1A EP3105507A1 (fr) 2014-02-11 2015-01-27 Coupelle de turbulence pour brûleur de turbine à gaz
US15/116,590 US20160348914A1 (en) 2014-02-11 2015-01-27 Swirler for a burner of a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14154756 2014-02-11
EP14154756.2 2014-02-11

Publications (1)

Publication Number Publication Date
WO2015121063A1 true WO2015121063A1 (fr) 2015-08-20

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ID=50071520

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2015/051612 WO2015121063A1 (fr) 2014-02-11 2015-01-27 Coupelle de turbulence pour brûleur de turbine à gaz

Country Status (3)

Country Link
US (1) US20160348914A1 (fr)
EP (1) EP3105507A1 (fr)
WO (1) WO2015121063A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2963862A (en) * 1960-03-21 1960-12-13 Orenda Engines Ltd Fuel systems
US2978870A (en) * 1957-12-26 1961-04-11 Gen Electric Fuel injector for a combustion chamber
US5983642A (en) 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US20030106320A1 (en) 2001-12-06 2003-06-12 Siemens Westinghouse Power Corporation Gas turbine pilot burner and method
EP1978307A2 (fr) * 2007-04-05 2008-10-08 Kawasaki Jukogyo Kabushiki Kaisha Chambre de combustion de turbine à gaz
GB2453114A (en) * 2007-09-25 2009-04-01 Siemens Ag A Swirler for use in a Burner of a Gas Turbine Engine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4751815A (en) * 1986-08-29 1988-06-21 United Technologies Corporation Liquid fuel spraybar
GB2333832A (en) * 1998-01-31 1999-08-04 Europ Gas Turbines Ltd Multi-fuel gas turbine engine combustor
US6962055B2 (en) * 2002-09-27 2005-11-08 United Technologies Corporation Multi-point staging strategy for low emission and stable combustion
GB2437977A (en) * 2006-05-12 2007-11-14 Siemens Ag A swirler for use in a burner of a gas turbine engine
US9464805B2 (en) * 2013-01-16 2016-10-11 Lochinvar, Llc Modulating burner

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2978870A (en) * 1957-12-26 1961-04-11 Gen Electric Fuel injector for a combustion chamber
US2963862A (en) * 1960-03-21 1960-12-13 Orenda Engines Ltd Fuel systems
US5983642A (en) 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US20030106320A1 (en) 2001-12-06 2003-06-12 Siemens Westinghouse Power Corporation Gas turbine pilot burner and method
EP1978307A2 (fr) * 2007-04-05 2008-10-08 Kawasaki Jukogyo Kabushiki Kaisha Chambre de combustion de turbine à gaz
GB2453114A (en) * 2007-09-25 2009-04-01 Siemens Ag A Swirler for use in a Burner of a Gas Turbine Engine

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Publication number Publication date
US20160348914A1 (en) 2016-12-01
EP3105507A1 (fr) 2016-12-21

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