EP3220050A1 - Brenner für eine gasturbine - Google Patents

Brenner für eine gasturbine Download PDF

Info

Publication number
EP3220050A1
EP3220050A1 EP16160740.3A EP16160740A EP3220050A1 EP 3220050 A1 EP3220050 A1 EP 3220050A1 EP 16160740 A EP16160740 A EP 16160740A EP 3220050 A1 EP3220050 A1 EP 3220050A1
Authority
EP
European Patent Office
Prior art keywords
fuel
swirler
burner
air
chamber
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Withdrawn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
EP16160740.3A
Other languages
English (en)
French (fr)
Inventor
Ghenadie Bulat
Suresh Sadasivuni
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 EP16160740.3A priority Critical patent/EP3220050A1/de
Publication of EP3220050A1 publication Critical patent/EP3220050A1/de
Withdrawn legal-status Critical Current

Links

Images

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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the present invention relates to a burner for a gas turbine, to a gas turbine and to a method for operating a burner of a gas turbine.
  • Gas turbines are commonly used in industrial applications.
  • the gas turbine may be operated in a DLE (dry low emission) combustion mode, wherein the gas turbine produces low emissions, especially low NOx emissions.
  • DLE dry low emission
  • combustion hardware for gas turbine (GT) engines is designed for a specific fuel (i.e. natural gas, diesel, syngas, landfill gas and other hydrocarbon fuels with varying Wobbe Index).
  • a specific fuel i.e. natural gas, diesel, syngas, landfill gas and other hydrocarbon fuels with varying Wobbe Index.
  • flashback flame burning on the combustor surface
  • flameout engine shutdown
  • combustion dynamics hardware integrity
  • high pressure drop performance loss
  • Low NOx-emission combustors utilize reduced peak flame temperatures within the combustor to limit the formation of thermal NOx through staging strategies such as lean premixed combustion. As combustion temperatures are decreased in low NOx applications, several other undesirable combustion phenomena become more prevalent and must be addressed. The low-NOx limit is often bounded by the onset of combustion instability in the form of Lean Blow Out (LBO) also known as flameout. Lean Blow Out occurs when the thermal energy generated by the burning fuel/air mixture is no longer sufficient to heat the incoming fuel-air mixture to the ignition point.
  • LBO Lean Blow Out
  • a burner for a gas turbine comprising a chamber for combusting a fuel mixture, a first injector for injecting a first fuel (in particular H 2 ) into the chamber, an downstream swirler for introducing a mixture of a second fuel (in particular CH 4 ) and air into the chamber, and a upstream swirler for introducing a mixture of a third fuel (in particular NH 3 ) different from the second fuel and further air into the chamber.
  • the burner may be adapted to simultaneously burn the first fuel, the second fuel and the third fuel.
  • the downstream swirler and the upstream swirler may be of a similar configuration/geometry but may have different dimensions.
  • the upstream swirler may have a larger size than the downstream swirler.
  • the upstream swirler may introduce a larger amount (e.g. per time) of the third fuel into the chamber than the downstream swirler introduces an amount (e.g. per time) of the second fuel into the chamber.
  • the second fuel and the third fuel are different and may have different combustion properties and also different thermo-chemical properties, such as diffusivity, calorific value, ignition temperature, flame speed.
  • the configurations (in particular relative configuration or dimensions) of the downstream and the upstream swirler may be selected. Further, the relative positioning of the downstream swirler and the upstream swirler in the burner may depend on the different combustion properties of the different fuels and may also depend on the relative amounts of the second fuel and the third fuel being introduced into the chamber during the operation of the burner.
  • the burner may achieve a reliable combustion of the three different fuels and may also achieve relatively low NOx emissions.
  • a controller may control the operation of the burner, wherein the controller in particular may adjust the mass flows of the first fuel, the second fuel and the third fuel and may also control the amount of air introduced via the downstream swirler and/or via the upstream swirler.
  • a volume flow rate of the upstream swirler and/or a position of the upstream swirler relative to the downstream swirler is selected based on a combustion property of the third fuel, in particular relative to a combustion property of the second fuel, and/or based on a mass flow of the third fuel into the combustion chamber, in particular relative to a mass flow of the second fuel into the combustion chamber, wherein the volume flow rate of the upstream swirler is in particular between 2 and 5 times the volume flow rate of the downstream swirler.
  • the combustion property of the fuel may include for example diffusivity, calorific value, ignition temperature, flame speed among others.
  • the combustion properties of the second fuel and the third fuel may allow to optimally design the geometry and/or size of the downstream and upstream swirler.
  • the downstream swirler and/or the upstream swirler may have a design of a so-called radial swirler which introduces air and the respective fuel using swirler vanes which guide the air into an inside of the respective swirler, wherein one or more injectors for the respective fuel are provided at the swirler vanes, in order to achieve a mixing of the air with the respective fuel.
  • the downstream swirler and/or the upstream swirler may have substantially a cylindrical geometry and may at least partially surround the chamber of the burner, in particular a pre-chamber of the burner.
  • the burner is adapted to simultaneously burn a second fuel together with a third fuel, the third fuel mass flow rate being between 70% and 97% of a total mass flow rate burned, wherein a calorific value of the second fuel is in particular between 1.2 and 5 times a calorific value of the third fuel, which may in particular comprises ammonia (NH 3
  • a position of the downstream swirler is, in an axial direction away from the first injector (pilot burner), spaced apart from a position of the upstream swirler, in particular between 0.5 and 2 times a diameter of a prechamber of the combustion chamber.
  • the upstream swirler may thus be closer (in the axial direction) located at the first injector from pilot burner than the downstream swirler.
  • the third fuel introduced via the upstream swirler into the chamber of the burner may stream along a longer mixing path to reach a combustion region of the burner than the second fuel which is introduced via the downstream swirler.
  • a larger amount of the third fuel is efficiently supported and also a lower calorific value relative to the calorific value of the second fuel may be accounted for.
  • the first, the second and the third fuels flow rates, at least partially mixed with air, along flow paths having a first, second and third premixing length (L1, L2, L3), respectively from an injection location in the burner to a combustion region within the burner, wherein the burner is adapted such that the first premixing length is smaller than the second premixing length and the second premixing length is smaller than the third premixing length, wherein the first premixing length is in particular between 20 mm and 100 mm, wherein the second premixing length is in particular between 40 mm and 300 mm, wherein the third premixing length is in particular between 60 mm and 400 mm.
  • L1, L2, L3 first, second and third premixing length
  • the first fuel may have a highest calorific value
  • the second fuel may have a medium calorific value
  • the third fuel may have the lowest calorific value of all fuels used during operation of the burner.
  • the downstream swirler comprises second injectors and the upstream swirler comprises third injectors for supplying the second and third fuels respectively, into the swirlers, wherein a diameter (e.g. inner pitch circle diameter) of the upstream swirler is in particular between 150 mm and 450 mm, wherein inner pitch circle diameter of the downstream swirler is in particular between 50 mm and 250 mm.
  • a diameter e.g. inner pitch circle diameter
  • the diameters of the upstream swirler and the downstream swirler may be selected based on an amount of the respective fuel introduced via the respective swirler into the chamber of the burner and may also be selected based on the respective calorific value (and/or other combustion properties) of the fuel. The more the mass flow per time is introduced via the respective swirler into the chamber, the larger the diameter of the respective swirler may be selected. Thereby, an efficient premixing within the respective swirler of the respective fuel with the air may be achieved before introducing the premixed fuel/air into the chamber of the burner.
  • the swirler comprises plural swirler vanes, circumferentially spaced apart, for guiding air entering from radially outwards into the swirler radially inwards and partially in a circumferential direction
  • the upstream swirler comprises plural further swirler vanes, circumferentially spaced apart, for guiding upstream air entering from radially outwards into the upstream swirler radially inwards and partially in a circumferential direction.
  • the swirler vanes may comprise each a substantially flat or plane surface along which air introduced radially is guided towards inwards section of the swirler.
  • the injectors may be formed as one, two or more holes within the surface of the swirler vane.
  • the second injectors are arranged on the swirler vanes such as to partially mix the second fuel with the guided air
  • the third injectors are arranged on the upstream swirler vanes such as to partially mix the third fuel with the guided further air, wherein in particular two or more injectors in the swirlers are formed at each of the swirler vanes.
  • the swirlers may in particular be configured as radial swirlers.
  • the chamber comprises a prechamber and a combustion chamber, having a larger radial extent than the prechamber, wherein the swirler and the further swirler enclose the prechamber such that the second fuel partially mixed with air enters the prechamber radially inwards and such that the third fuel partially mixed with air enters the prechamber radially inwards.
  • the first injectors may be arranged on a front face (of a wall) of the combustor. Thereby, the first fuel is enabled to be injected closer to a central axis (running in the axial direction) of the burner than the second fuel and the third fuel.
  • the combustion chamber may have a cylindrical shape and the central axis may represent a cylinder axis of the combustion chamber.
  • the first fuel may have a highest reactivity compared of the reactivities of the second fuel and the third fuel. Thus, the first fuel may be ignited fastest and may provide a flame close to the central axis and also close to the first injector.
  • This initial flame may act to ignite the mixture of the second fuel and air and also to ignite the mixture of the third fuel and air further axially downstream away from the first injector, such that an extended flame region is formed.
  • a pilot zone may be formed close to the first injector and close to the central axis of the burner.
  • a central recirculation zone may be formed close to the central axis of the burner and axially spaced apart or extending from the region where the first injector or first injectors are arranged.
  • a forward flow (away from the front plate and streaming substantially in an axial direction) may be formed primarily by a mixture of the second fuel and air and a mixture of the third fuel and air in a region radially close to the downstream and upstream swirler but spaced apart from the central axis of the burner.
  • a backflow may be formed in a region close to the central axis of the burner.
  • the flame may form/establish in a region where the burning velocity of a fuel and air mixture is relatively close to the incoming flow speed so that equilibrium is formed or the difference (between burning velocity against the flow speed) is small or substantially zero.
  • the flame may extend in the axial direction and may be spaced apart from the central axis the more, the more the flame is axially spaced apart from the front plate or the first injectors.
  • the three different fuels or fuel air mixtures may contribute in different regions of the flame to a different amount.
  • the first fuel mixed with air may contribute to the flame to a highest degree axially close to the front plate or close to the first injectors and also close to the central axis of the burner.
  • the mixture of the second fuel with air may contribute most to the flame in a region farther spaced apart from the central axis (to a medium degree) and also spaced apart in the axial direction from the front plate in a medium degree.
  • the third fuel mixed with air may contribute to the flame in a region of the flame which is spaced by an even larger amount in the axial direction from the front plate and which is spaced also in the radial direction from the central axis more than the mixtures of the other fuels with the air.
  • Other configurations are possible.
  • the burner further comprises at least one temperature sensor arranged to measure a temperature in at least one region of the inside of the burner and a controller adapted to adjust a mass flow of fuel and/or a mass flow of air into the downstream swirler and/or the upstream swirler and/or the first injector based on the measured temperature.
  • the controller may allow to optimally adjust the mass flow of the fuels and the air to efficiently burn the fuels, while limiting the emissions.
  • a gas turbine which comprises the burner as described in the embodiments above and which further comprises a compressor stage and a turbine stage of a rotor having plural blade vanes connected to it.
  • a gas turbine comprising a shaft having blade vanes connected to it and at least one burner according to one of the embodiments described above, arranged such that combustion gas expelled by the burner impacts on the blade vanes and thereby drives the shaft.
  • the air or at least a portion of the air required to burn the first fuel is provided via the upstream swirler and/or via the downstream swirler.
  • the upstream swirler may provide the majority of air required to burn the first fuel.
  • a compromise may be found in order to optimize a premixing path length of a mixing path of the third fuel mixed or mixing with air and the requirement that sufficient air is supplied close to the first injector outlets, in order to ignite and burn the first fuel.
  • a synthetic fuel such as ammonia (NH3) or hydrogen (H2) is used according to embodiments of the present invention to generate the required energy. Due to different thermo-chemical properties (such as diffusivity, calorific value, ignition temperatures, flame speed) of these synthetic fuels the combustion process becomes complex. For example, in conventional gas turbines the hydrogen-air combustion occurs at higher flame speeds and may result in flashback.
  • the invention provides a solution for these disadvantages.
  • ammonia-air combustion may be initiated efficiently in embodiments of the present invention.
  • Reliable combustion in gas turbine engines may be achieved in embodiments of the present invention wherein a mixture of these synthetic fuels is used within the system.
  • Embodiments of the present invention present an injection system capable to achieve reliable combustion of differing synthetic fuels (such as NH 3 and H 2 ) as well as acceptable NOx emissions. This is achieved if the combustion dynamics is reduced and/or ensuring a better mixing of the pilot fuel stream.
  • differing synthetic fuels such as NH 3 and H 2
  • this invention disclosure proposes the DLE combustion system for efficient burning of ammonia (on its own) and also the combination of ammonia and Hydrogen enriched with hydrocarbon fuels such as methane and propane.
  • Embodiments of the invention improve the capability of the combustion system of a gas turbine to burn primarily synthetic fuels such as NH 3 or H 2 .
  • FIG. 1 shows an example of a gas turbine engine 10 in a sectional view.
  • 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 about and 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 section or burner section 16.
  • the burner section 16 comprises a burner plenum 26, one or more combustion chambers 28 and at least one burner 30 fixed to each combustion chamber 28.
  • the combustion chambers 28 and the burner injection portions 30 are located inside the burner plenum 26.
  • the compressed air passing through the compressor 14 enters a diffuser 32 and is discharged from the diffuser 32 into the burner plenum 26 from where a portion of the air enters the burner injection portion 30 and is mixed with a gaseous or liquid fuel.
  • the air/fuel mixture is then burned and the combustion gas 34 or working gas from the combustion is channelled through the combustion chamber 28 to the turbine section 18 via a transition duct 17.
  • This exemplary gas turbine engine 10 has a cannular combustor section arrangement 16, which is constituted by an annular array of combustor cans 19 each having the burner injection portion 30 and the combustion chamber 28, the transition duct 17 has a generally circular inlet that interfaces with the combustor chamber 28 and an outlet in the form of an annular segment.
  • An annular array of transition duct outlets form an annulus for channelling the combustion gases to the turbine 18.
  • 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 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 stages of annular arrays of turbine blades 38. Between the exit of the combustion chamber 28 and the leading turbine blades 38 inlet guiding vanes 44 are provided and turn the flow of working gas onto the turbine blades 38.
  • the combustion gas 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 optimise the angle of the combustion or working gas on the turbine blades 38.
  • the turbine section 18 drives the compressor section 14.
  • the compressor section 14 comprises an axial series of vane stages 46 and rotor blade stages 48.
  • the rotor blade stages 48 comprise a rotor disc supporting an annular array of blades.
  • the compressor section 14 also comprises a casing 50 that surrounds the rotor stages and supports the vane stages 48.
  • the guide vane stages include an annular array of radially extending vanes that are mounted to the casing 50. The vanes are provided to present gas flow at an optimal angle for the blades at a given engine operational point.
  • Some of the guide vane stages have variable vanes, where the angle of the vanes, about their own longitudinal axis, can be adjusted for angle according to air flow characteristics that can occur at different engine operations conditions.
  • the casing 50 defines a radially outer surface 52 of the passage 56 of the compressor 14.
  • a radially inner surface 54 of the passage 56 is at least partly defined by a rotor drum 53 of the rotor which is partly defined by the annular array of blades 48.
  • the present invention is described with reference to the above exemplary turbine engine having a single shaft or spool connecting a single, multi-stage compressor and a single, one or more stage turbine.
  • the present invention is equally applicable to two or three shaft engines and which can be used for industrial, aero or marine applications.
  • upstream and downstream refer to the flow direction of the airflow and/or working gas flow through the engine unless otherwise stated.
  • forward and rearward refer to the general flow of gas through the engine.
  • axial, radial and circumferential are made with reference to the rotational axis 20 of the engine.
  • the gas turbine 10 illustrated in Fig. 1 comprises a burner 100 according to an embodiment of the present invention.
  • the burner 100 may be configured in a similar manner as the burners illustrated in Figs. 2 , 3 or 4 .
  • the burner injection portion 30 may comprise fuel injectors, swirlers and a prechamber, as detailed below.
  • Fig. 2 illustrates only an upper half of the sectional view of the entire burner 200.
  • the burner 200 according to an embodiment of the present invention illustrated in Fig. 2 in a schematic sectional view comprises a chamber for combusting a fuel mixture, wherein the chamber is formed by a prechamber 201 and a combustion chamber 203.
  • the burner 200 further comprises a first injector 205 for injecting a first fuel 204 into the prechamber 201 and main combustion chamber 203.
  • the first fuel 204 may for example comprise hydrogen.
  • the injector 205 is arranged at a front face 207 of the prechamber 201.
  • Reference sign 209 indicates a central axis of the burner 200.
  • the injector 205 injects the first fuel 204 into the prechamber 201 and from there into the combustion chamber 203.
  • the burner 200 further comprises a swirler 211 for introducing a mixture of a second fuel 213 and air 215 into the prechamber 201, main combustion chamber 203.
  • the burner further comprises a upstream swirler 217 for introducing a mixture of a third fuel 219 and further air 221 into the prechamber 201, main combustion chamber 203.
  • the swirler 211 has an inner space 223 in which the second fuel 213 is at least partially mixed with the air 215.
  • the swirler 211 comprises swirler vanes which are not illustrated in detail but partially illustrated in Fig. 4 .
  • the upstream swirler 217 comprises also an inner space 225 in which the third fuel 219 is at least partially mixed with the further air 221.
  • the inner space 225 of the upstream swirler is larger than the inner space 223 of the downstream swirler, in particular in the case, where a larger mass flow of the third fuel 219 is introduced into the upstream swirler than the mass flow of the second fuel 213 which is introduced in the downstream swirler 211.
  • the sizes of the inner spaces 225, 223 of the upstream swirler and the downstream swirler, respectively, may be selected based on the combustion properties of the third fuel 219 and the second fuel 213.
  • the position P1 (for example central position) of the downstream swirler 211 is spaced apart in the axial direction (parallel to the central axis 209) from the front face 207 by an amount a1.
  • the position P2 of the upstream swirler 217 is spaced apart from the front face or front wall 207 of the burner 200 by an amount a2 which is smaller than the amount a1.
  • the position P1 is thus spaced apart from the position P2 by a1-a2.
  • a first flow path 227 of the first fuel 204 is indicated having a first premixing length L1.
  • a second flow path 229 of the second fuel 213 is indicated which has a second premixing length L2.
  • a third flow path 231 of the third fuel 219 mixed or partially mixed with the air 221 is indicated having a third premixing length L3.
  • a flame is generated during the operation of the burner 200.
  • the different fuel air mixtures generated by the first fuel 204 injected via the injector 205, by the second fuel 213 introduced via the downstream swirler 211 and the third fuel 219 introduced partially mixed with air using the upstream swirler 217 contribute at different regions of the flame 233.
  • the downstream swirler 211 For injecting the second fuel 213, the downstream swirler 211 comprises second injectors 235 which are arranged at not illustrated swirler vanes.
  • the upstream swirler 217 For injecting the third fuel 219, the upstream swirler 217 comprises third injectors 237 which may be arranged at not illustrated swirler vanes.
  • the third fuel 219 by introducing the third fuel 219 via the upstream swirler 217 and mixing the third fuel 219 at least partially with the upstream portion of air 221, the third fuel 219 partially mixed with the air 221 enters the prechamber 201 radially inwards.
  • the burner 200 (optionally) further comprises at least one temperature sensor 239 to measure a temperature in at least one region of the inside of the burner 200.
  • the temperature sensor 239 generates a measurement signal 241 which is supplied to a controller 245 which is also comprised in the burner 200.
  • the controller 245 receives the measurement signal 241, in particular from different regions within the burner 200 and adjusts the mass flows of the first fuel 204, the second fuel 213 and/or the third fuel 219.
  • the mass flow of the air is controlled with the engine shaft speed 22 across the load range and by selecting the area of the swirlers in particular the air 215 and the further air 221.
  • the controller 245 receives the measurement signal 241, and adjust the fuel in order to control the combustion process based on the measured temperature or measured temperatures in different regions of the combustion chamber and/or the prechamber 201, main combustion chamber 203.
  • the combustion chamber 203 is limited by a combustion chamber wall 206.
  • Fig. 3 schematically illustrates a burner 300 according to an embodiment of the present invention which may for example be incorporated into the gas turbine illustrated in Fig. 1 as the burner 100.
  • Fig. 3 shows a burner 300 which has a number of similarities to the burner 200 illustrated in Fig. 2 .
  • fuel galleries 351 are indicated which allow supply of the first fuel 304 via the first injectors 305 into the prechamber 301 and from there into the combustion chamber 303. Further, the fuel galleries 351 allow the introduction of the second fuel 313 via the downstream swirler 311 into the prechamber 301 and from there into the combustion chamber 303. Further, the fuel galleries 351 allow the introduction of the third fuel 319 via the upstream swirler 317 into the prechamber 301 and from there into the combustion chamber 303.
  • the flow field of the introduced fuels partially mixed with air is also indicated as a forward flow field 353, a backward flow field 355 and a further backward flow field 357.
  • the flame may stabilize between the forward flow field 353 and the backward flow field 355.
  • the flow field 355 may also be referred to as central recirculation zone and the flow field 357 may also referred to as outer recirculation zone.
  • the region close to the first injectors 305 may also be called pilot zone.
  • the burner 300 further comprises an outer casing 359 which is not explicitly illustrated in the burner 200 illustrated in Fig. 2 .
  • the first injectors are installed in a pilot body 361.
  • Fig. 4 illustrates in a perspective view a burner 400 according to an embodiment of the present invention which may be used in the gas turbine illustrated in Fig. 1 .
  • the burner 400 comprises a first injector 405 for injecting a first fuel 404. Further, the burner 400 comprises a downstream swirler 411 for introducing a mixture of a second fuel 413 and air into a prechamber 401. Further, the burner 400 comprises a upstream swirler 417 for introducing a third fuel 419 into the prechamber, mixed with air.
  • the combustion chamber is limited by a combustion chamber wall 406.
  • a transition duct 408 Downstream the combustion chamber, a transition duct 408 is arranged which guides the hot combustion gas via nozzle guide vanes 410 towards a turbine section of a gas turbine, such as turbine section 18 of the gas turbine illustrated in Fig. 1 .
  • the swirlers comprise swirler vanes 416
  • the proposed invention provides a design of a combustion system capable of burning synthetic fuels where the synthetic fuel is a mix of at least two or more components that have differing combustion properties.
  • the fuels are injected at differing positions (principally defined by the flow-stream length to the reaction zone (e.g. flame)), where those positions are selected based on the combustion properties of the fuel component (diffusivity, flame speed, calorific value, ignition, etc).
  • Dedicated swirlers are provided so that improved mixing and its control is achieved if simultaneous operation of fuels is required.
  • the fuel injection system is designed to ensure that fuel is introduced as a function of its combustion property.
  • the most reactive fuel (higher calorific value, i.e. the first fuel) is injected at a nominal distance from the flame location, L1, principally defined by the flow-stream length to the reaction zone, see figure 2 .
  • L1 the flame location
  • the distance is designed to ensure that the fuel is delivered quickly to the flame 233, however is not injected immediately onto the flame front, thus premixing with air prior to burning.
  • the main purpose of this fuel stream is to promote flame stability. It is estimated that for normal full load operation up to 20 % of fuel is introduced in this manner. However up to 100% of fuel can be injected during startup or part load operation. Injection holes are designed for base load.
  • a typical L1 may be estimated to be in the range of 20 mm to 150 mm with most devices operating in the region of 50 mm.
  • a typical L2 may be in the range of 40 mm to 300 mm with most devices operating in the region of 100 mm.
  • a typical L3 may be in the range of 60 mm to 400 mm with most devises operating in the region of 150 mm.
  • the external diameter of the NH 3 swirler i.e. the upstream swirler 217, 317, 417) could be between 150 mm and 450 mm (typically around 250 mm), whilst the external diameter of the CH 4 swirler (i.e. the downstream swirler 211, 311, 411) could be between 50 and 250 mm (typically 100 mm).
  • the effective area of both swirlers may be balanced to achieve an air mass flow for a required flame temperature. Different heights of the injection holes may be used to ensure better mixing within the swirler vanes.
  • the main advantage of the described system may be the best premixing of each fuel stream with air and thus resulting in a single desirable flame location when burning synthetic fuels, i.e. stable, correct flame location, tolerant to load or fuel changeovers.
  • An intelligent control method of fuel injection such as described in WO2007/082608 may be used to ensure the most optimal fuel ratio between the fuel streams.
  • the control method would rely on inputs such as metal temperatures and differing frequency bands of combustion dynamics.
  • the invention step provides a novel burner configuration with a fuel injection system capable of burning synthetic fuels.
  • the proposed method is based on physical properties of these fuels such as diffusivity and flame speed to ensure an optimal flame location.
  • the advantage lays in the improved and more rapid response in the fuel delivery to the flame to avoid flameout during part load, thus increasing the engine reliability.
  • Low NOx due to premixing of fuel streams and a more uniform flame temperature across the combustion system may be achieved.
  • Increased reliability of the combustion system when operated on synthetic fuels due to proximity of the most reactive fuel stream closer to the flame and the use of the intelligent control of the fuel streams may be achieved.
EP16160740.3A 2016-03-16 2016-03-16 Brenner für eine gasturbine Withdrawn EP3220050A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16160740.3A EP3220050A1 (de) 2016-03-16 2016-03-16 Brenner für eine gasturbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16160740.3A EP3220050A1 (de) 2016-03-16 2016-03-16 Brenner für eine gasturbine

Publications (1)

Publication Number Publication Date
EP3220050A1 true EP3220050A1 (de) 2017-09-20

Family

ID=55542534

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16160740.3A Withdrawn EP3220050A1 (de) 2016-03-16 2016-03-16 Brenner für eine gasturbine

Country Status (1)

Country Link
EP (1) EP3220050A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2020139699A (ja) * 2019-02-28 2020-09-03 株式会社Ihi 燃焼器
WO2022079523A1 (en) * 2020-10-14 2022-04-21 King Abdullah University Of Science And Technology Adjustable fuel injector for flame dynamics control
WO2022101608A1 (en) * 2020-11-12 2022-05-19 University College Cardiff Consultants Limited Combustor systems and methods
US11920525B2 (en) 2022-08-05 2024-03-05 Rtx Corporation Liquid and hydrogen/methane fuel injector

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US6151899A (en) * 1998-05-09 2000-11-28 Alstom Gas Turbines Limited Gas-turbine engine combustor
US20040238654A1 (en) * 2003-01-22 2004-12-02 Hagen David L. Thermodynamic cycles using thermal diluent
WO2007082608A1 (en) 2006-01-19 2007-07-26 Siemens Aktiengesellschaft Fuel ratio control in a combustion apparatus with multiple fuel supply lines
US20080083224A1 (en) * 2006-10-05 2008-04-10 Balachandar Varatharajan Method and apparatus for reducing gas turbine engine emissions
US20100126176A1 (en) * 2008-11-26 2010-05-27 Ik Soo Kim Dual swirler
EP2902708A1 (de) * 2014-06-12 2015-08-05 Kawasaki Jukogyo Kabushiki Kaisha Gasturbinenbrennkammer für mehrere brennstoffe

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US6151899A (en) * 1998-05-09 2000-11-28 Alstom Gas Turbines Limited Gas-turbine engine combustor
US20040238654A1 (en) * 2003-01-22 2004-12-02 Hagen David L. Thermodynamic cycles using thermal diluent
WO2007082608A1 (en) 2006-01-19 2007-07-26 Siemens Aktiengesellschaft Fuel ratio control in a combustion apparatus with multiple fuel supply lines
US20080083224A1 (en) * 2006-10-05 2008-04-10 Balachandar Varatharajan Method and apparatus for reducing gas turbine engine emissions
US20100126176A1 (en) * 2008-11-26 2010-05-27 Ik Soo Kim Dual swirler
EP2902708A1 (de) * 2014-06-12 2015-08-05 Kawasaki Jukogyo Kabushiki Kaisha Gasturbinenbrennkammer für mehrere brennstoffe

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2020139699A (ja) * 2019-02-28 2020-09-03 株式会社Ihi 燃焼器
JP7205299B2 (ja) 2019-02-28 2023-01-17 株式会社Ihi 燃焼器
WO2022079523A1 (en) * 2020-10-14 2022-04-21 King Abdullah University Of Science And Technology Adjustable fuel injector for flame dynamics control
US20230332544A1 (en) * 2020-10-14 2023-10-19 King Abdullah University Of Science And Technology Adjustable fuel injector for flame dynamics control
WO2022101608A1 (en) * 2020-11-12 2022-05-19 University College Cardiff Consultants Limited Combustor systems and methods
US11920525B2 (en) 2022-08-05 2024-03-05 Rtx Corporation Liquid and hydrogen/methane fuel injector

Similar Documents

Publication Publication Date Title
CN107735618B (zh) 用于燃气涡轮的燃烧器和操作燃烧器的方法
EP3679300B1 (de) Gasturbinenbrennkammeranordnung mit hohlraum zum erzeugen eines eingeschlossenen wirbels und verfahren zum betreiben einer gasturbinenbrennkammer
US7966820B2 (en) Method and apparatus for combusting fuel within a gas turbine engine
EP2738355B1 (de) Gasturbinentriebwerk und zugehöriges Verfahren
US20090056336A1 (en) Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
US20140090396A1 (en) Combustor with radially staged premixed pilot for improved
EP2244014B1 (de) Radialer Brenner mit magerer Direkteinspritzung
EP2889542B1 (de) Verfahren zum betrieb einer brennkammer für eine gasturbine und brennkammer für eine gasturbine
US8707704B2 (en) Method and apparatus for assembling turbine engines
EP3303929B1 (de) Brennkammer
KR101774630B1 (ko) 가스 터빈 엔진에 사용되는 예비혼합된 연료와 공기를 가진 접선방향의 애뉼러형 연소실
EP3220050A1 (de) Brenner für eine gasturbine
US11060729B2 (en) Fuel nozzle assembly and gas turbine combustor including the same
JP7165211B2 (ja) ガスタービンにおいて燃焼安定性を向上させるシステムおよび方法
KR101832026B1 (ko) 가스 터빈 엔진에 사용되는 접선방향의 무염 애뉼러형 연소실
WO2022214384A1 (en) Combustor for a gas turbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20180321