EP2644999A1 - Installation de turbine à gaz dotée d'un injecteur fluidique - Google Patents

Installation de turbine à gaz dotée d'un injecteur fluidique Download PDF

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Publication number
EP2644999A1
EP2644999A1 EP12162013.2A EP12162013A EP2644999A1 EP 2644999 A1 EP2644999 A1 EP 2644999A1 EP 12162013 A EP12162013 A EP 12162013A EP 2644999 A1 EP2644999 A1 EP 2644999A1
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EP
European Patent Office
Prior art keywords
fuel
combustion chamber
gas turbine
fluidic
fluidic injector
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Withdrawn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
EP12162013.2A
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German (de)
English (en)
Inventor
Andrea Ciani
John Philip Wood
Christian Oliver Paschereit
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP12162013.2A priority Critical patent/EP2644999A1/fr
Publication of EP2644999A1 publication Critical patent/EP2644999A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14482—Burner nozzles incorporating a fluidic oscillator

Definitions

  • the present invention relates to a gas turbine plant, in particular for driving a generator for generating electricity in a power plant.
  • the invention further relates to the introduction of a fuel into an oxidizer stream for supplying a combustion chamber of a gas turbine plant.
  • a gas turbine plant which is used in a power plant for driving a generator for generating electricity, comprises a compressor, a combustion chamber downstream of the compressor and a gas turbine downstream of the combustion chamber, in which the hot combustion exhaust gases of the combustion chamber are expanded.
  • the gas turbine can drive a generator.
  • the compressor is initially followed by a high-pressure combustion chamber, the exhaust gas of which is expanded in a high-pressure gas turbine.
  • the high-pressure gas turbine is then followed by a low-pressure combustion chamber, the exhaust gas is expanded in a low-pressure gas turbine.
  • the high pressure gas turbine and the low pressure gas turbine are associated with a common rotor shaft which can be used to drive a generator.
  • the high-pressure combustion chamber and the low-pressure combustion chamber operate according to different combustion principles.
  • the high-pressure combustion chamber operates with a flame or with a flame front for igniting a fuel-oxidizer mixture, which is supplied to the combustion chamber for combustion.
  • the low-pressure combustion chamber usually works with a self-ignition of the introduced fuel-oxidizer mixture. This is mainly due to the high inlet temperatures attributed to the low-pressure combustion chamber.
  • a stable operation of such a low-pressure combustion chamber with auto-ignition thus depends on different parameters, such as temperature, pressure, flow velocity and residence time within the combustion chamber.
  • improved mixing of fuel and oxidizer is desired before auto-ignition occurs in the combustion chamber.
  • the nitrogen oxide emissions (NOX) can be reduced by improved mixing of the fuel introduced into the oxidizer stream.
  • improved fuel mixture mixing may be beneficial when using fuels having increased reactivity over natural gas.
  • a fuel gas composed of a mixture of natural gas and hydrogen gas may be used.
  • fluidic injectors are known, by means of which a fluid can be injected into a combustion chamber.
  • a fluid can be injected into a combustion chamber.
  • Q. Huang and R. Chen in SAE Paper 960768: "Investigating the Use of Fluidic Devices as Gas Fuel Injectors for Natural Gas Engines” describe various variants of such fluidic injectors that introduce natural gas into the combustion chambers of an internal combustion engine can be.
  • Such a fluidic injector is characterized in that the flow direction of a fluid within the fluidic injector can be changed without the use of moving parts. In particular, comparatively large mass flows can be controlled without wear.
  • the present invention addresses the problem of finding a way for a gas turbine plant that allows pollutant emissions, especially NOX emissions.
  • pollutant emissions especially NOX emissions.
  • the use of fuels of higher reactivity should be simplified.
  • the invention is based on the general idea of using a fluidic injector for introducing the fuel into the oxidant stream.
  • a fluidic injector for introducing the fuel into the oxidant stream.
  • a fluidic injector can be designed so that it generates an injection jet that changes permanently between a first injection angle and a second injection angle.
  • This change of the injection or injection angle is expediently carried out without interruption of the injection beam, so that the injection beam thus permanently covers a predetermined angular range whose range limits are determined by the first injection angle and the second injection angle.
  • the occurring oscillation speed or oscillation frequency can be adjusted by an appropriate vote of the fluidic injector to the desired volume flow of the fuel.
  • a desired cross-sectional area can be supplied with fuel in an oxidizer gas path.
  • the oxidant stream is gaseous.
  • the oxidant stream is a lean, that is, substoichiometric, combustion exhaust gas from the preceding combustor that has been expanded in the previous gas turbine.
  • the fuel which is injected via the fluidic injector in this Oxidatorstrom, be gaseous. Preference is given to natural gas or a natural gas-hydrogen gas mixture. In principle, hydrogen gas can also be used as fuel. Gaseous fuels require comparatively high volume flows, which, however, can be handled in a particularly simple and wear-free manner with such a fluidic injector.
  • the fluidic injector so that a liquid fuel can be injected into the oxidant gas stream. With liquid fuel, the volume flows are smaller. Nevertheless, the use of the fluidic injector is also of significant advantage here.
  • the Fluidic injector basically works without moving parts and thus without wear.
  • the oscillation of the injection beam in the predetermined angular range allows a large-area or large-volume distribution of the injection jet within the oxidizer, which favors the evaporation of the injected droplets.
  • By dimensioning the fluidic injector and by the pressures in the fuel and in the oxidizer it is also possible to specify a droplet size which the injection jet possesses. Thus, it is easy to choose a droplet size that ensures a sufficiently rapid evaporation of the liquid fuel at the present flow conditions and temperatures.
  • a gas turbine plant according to the invention which is equipped with such a fluidic injector, thus comprises a combustion chamber which works with auto-ignition of a fuel-oxidizer mixture, a gas path for supplying an oxidant flow to the combustion chamber, a fuel line for supplying fuel to the combustion chamber and at least one such Fluidic injector of the type described above, which is connected on the inlet side to the fuel line and the outlet side to the gas path.
  • such a fluidic injector has an interaction space in which the switching between the two injection angles takes place with the aid of fluid-dynamic forces. Furthermore, the fluidic injector has an inlet nozzle, through which the fuel is injected into the interaction space, and an outlet nozzle, through which the fuel exits from the interaction space or enters the oxidant stream.
  • the interaction space expediently has a flow-through cross section which is greater than the flow-through cross sections of the inlet nozzle and the outlet nozzle.
  • the flow-through cross-section of the interaction space is at least twice as large as the flow-through cross section of the inlet nozzle or the outlet nozzle.
  • the outlet nozzle may in principle be designed conical, so that it widens three-dimensionally in the flow direction of the fuel. In principle, however, an embodiment is possible in which the outlet nozzle is fan-shaped, so that it only widens two-dimensionally in the flow direction of the fuel.
  • the injection beam which oscillates in the injection angle range defines, at least in the case of a fan-shaped outlet nozzle, an injection means plane in which the propagation directions of the oscillating injection jet are located.
  • the fluidic injector can now be connected to the gas path such that the injection medium plane is oriented parallel to the flow direction of the oxidizer flow.
  • an embodiment is preferred in which the arrangement of the fluidic injector takes place at the gas path such that the injection medium plane is oriented substantially inclined to the flow direction of the oxidizer flow.
  • the injection jet can sweep over a predetermined cross-sectional area of the oxidizer stream in an oscillating manner within the gas path.
  • the fluidic injector can be expediently also equipped with a first return line and with a second return line. Both return lines connect separately, ie separately, an inlet region of the outlet nozzle with an outlet region of the inlet nozzle.
  • the two return lines allow an automatic, automatic change of the discharge direction of the injection jet by the feedback at the inlet of the Outlet nozzle prevailing pressure to the outlet of the inlet nozzle, and vice versa.
  • the fuel jet within the interaction space permanently between two flow states switch back and forth and thus switch the exit direction of the injection beam in the manner of a flip-flop switch between the two exit directions.
  • the inlet nozzle and the outlet nozzle can expediently be aligned coaxially to a longitudinal central axis of the fluidic injector in the case of the fluidic injector, whereby the interaction space can also have a symmetrical structure with respect to the longitudinal central axis of the fluidic injector. It is also particularly expedient to arrange the two return lines in a mirror-symmetrical manner to a longitudinal center plane contained in the longitudinal center axis. Thus, the two main injection directions are symmetrical to the longitudinal center plane of the fluidic injector, which can be favored in particular by the above-described fan-shaped configuration of the outlet nozzle.
  • the outlet nozzle itself opens into the gas path, which leads the oxidizer stream to the combustion chamber.
  • the attachment of the fluidic injector to the gas path can preferably be carried out so that the longitudinal center plane of the fluidic injector extends substantially parallel to the flow direction of the oxidant stream in the gas path, so that thus the oscillating movement of the injection beam, which is transverse to the longitudinal center plane, transverse takes place to the flow direction of the oxidizer.
  • the fluidic injector can be connected to the gas path such that a central outlet direction of the fluidic injector, with which the fuel exits on average from the fluidic injector, is aligned substantially perpendicular to a main flow direction of the oxidator flow present in the region of the connection point ,
  • a particularly intensive mixing between fuel and oxidizer can be achieved.
  • Such a design can be realized particularly inexpensive, since the fluidic injector in In this case, it can be connected directly to a wall of the gas path.
  • the fluidic injector to the gas path such that a central exit direction of the fluidic injector, with which the fuel exits the fluidic injector on average, is parallel to a main flow direction of the oxidator flow present in the region of the connection point is aligned.
  • negative influences can be reduced by a swirl in the oxidant flow or by varying the flow rates of the oxidant flow.
  • the risk of dead water in the oxidizer stream downstream of the fluidic injector is reduced.
  • Such an arrangement can be realized, for example, with the aid of a fuel lance, which is inserted at a suitable location in the gas path and carries the fluidic injector in the region of its lance tip.
  • Another alternative proposes to connect the fluidic injector to the gas path such that a central exit direction of the fluidic injector, with which the fuel exits the fluidic injector on average, at an angle between 0 ° and 90 ° to a in the Oriented area of the junction present main flow direction of the oxidizer.
  • the above-mentioned angle existing between the main flow direction of the oxidizer gas and the central exit direction of the fluidic injector also intervenes the main flow direction of the oxidizer and injector plane of the fan-shaped oscillating fluidic injector.
  • the combustion chamber can be designed annular.
  • the fluidic injector can then basically also be designed annular, so that at least the outlet nozzle extends annularly.
  • a plurality of fluidic injectors may be provided, which are distributed in the circumferential direction of the combustion chamber.
  • a plurality of outlet nozzles in the circumferential direction preferably uniformly distributed.
  • the respective fluidic injector thereby has a comparatively simple structure.
  • the gas turbine plant is configured as a two-stage or sequential gas turbine plant in which the combustion chamber is designed as a low-pressure combustion chamber, which is arranged downstream of a low-pressure gas turbine and upstream of a high-pressure gas turbine.
  • the high pressure gas turbine is then preceded by a high pressure combustor which operates with a flame to ignite the fuel oxidizer mixture.
  • the two gas turbines are arranged on a common rotor. On this rotor may also be arranged a compressor upstream of the high-pressure combustion chamber. Through the common rotor, the gas turbines can drive a generator for power generation when used in a power plant.
  • Corresponding Fig. 1 comprises a gas turbine plant 1, which is designed in two stages or sequentially, a compressor 2, a compressor 2 downstream high-pressure combustion chamber 3, a high-pressure combustion chamber 3 downstream high-pressure gas turbine 4, a high-pressure gas turbine 4 downstream low-pressure combustion chamber. 5 and a low-pressure gas turbine 6 arranged downstream of the low-pressure combustion chamber 5.
  • a first line 7 supplies fresh gas to the compressor 2, which is compressed in the compressor 2.
  • a second line 8 supplies the compressed fresh gas to the high-pressure combustion chamber 3.
  • this second line 8 is an oxidizer line for supplying the high-pressure combustion chamber 3 with oxidizer.
  • a high-pressure fuel supply device 9 supplies fuel to the oxidizer supplied to the high-pressure combustion chamber 3.
  • the high-pressure fuel supply device 9 is connected via a corresponding third line 10 to the oxidant line of the high-pressure combustion chamber 3, that is, to the second line 8.
  • the high-pressure combustion chamber 3 then takes place an implementation of the fuel with the oxidizer.
  • the expanded in the high-pressure gas turbine 4 combustion exhaust gas is supplied via a fifth line 12 as the oxidant gas of the low-pressure combustion chamber 5.
  • a low-pressure fuel supply device 13 serves to supply a fuel to the low-pressure combustion chamber 5 supplied oxidizer. Accordingly, the low-pressure fuel supply device 13 is connected via a sixth line 14 to the fifth line 12, that is to the oxidant line of the low-pressure combustion chamber 5.
  • connection takes place via a fluidic injector 15, which is described below with reference to the Fig. 2 to 4 is explained in more detail.
  • the fuel is reacted with the oxidizer gas. This results in hot combustion exhaust again, which is supplied via a seventh conduit 16 of the low-pressure gas turbine 6 and is relaxed therein.
  • An eighth conduit 17 discharges the expanded working gas from the low-pressure gas turbine 6.
  • a common rotor 18 is provided, which carries the Laufbeschaufelept of the compressor 2, the high-pressure gas turbine 4 and the low-pressure gas turbine 6 and which may be drivingly connected to a generator 19 which can be used in a power plant to generate electricity.
  • the high-pressure combustion chamber 3 works to ignite the fuel-Oxidatorgemischs with a flame.
  • the low pressure combustion chamber 5 works with autoignition of the fuel-oxidizer mixture.
  • a fluidic injector 15 is used, whereby a particularly intensive mixing between the oxidant gas and the fuel injected therein can be realized.
  • the fuel may be gaseous or liquid. The following is based on the Fig. 2 to 4 a preferred structure for such a fluidic injector 15 explained in more detail.
  • such a fluidic injector 15 has an interaction space 20, an inlet nozzle 21, an outlet nozzle 22, a first return line 23 and a second return line 24.
  • the fuel can now according to an arrow 25 via a corresponding fuel line, here the sixth line 14 are injected into the interaction chamber 20.
  • the outlet nozzle 22 the fuel can emerge from the interaction space 20 according to an arrow 26 and be injected into a corresponding oxidizer line, here into the fourth line 12.
  • the first return line 23 leads back from an inlet region 27 of the outlet nozzle 22 to an outlet region 28 of the inlet nozzle 21.
  • the second return line 24 is arranged diametrically opposite the first return line 23 and likewise leads back from the inlet region 27 of the outlet nozzle 22 to the outlet region 28 of the inlet nozzle 21.
  • the inlet nozzle 21 and the outlet nozzle 22 are arranged coaxially with respect to a longitudinal central axis 29 of the fluidic injector 15 and aligned with each other.
  • the nozzles 21, 22, the chamber 20 and the lines 23 are arranged mirror-symmetrically to a longitudinal center plane 50 of the fluidic injector 15, in which the longitudinal central axis 29 is located and perpendicular to the plane of the drawing Fig. 2 and 3 stands.
  • Fig. 3a the fuel flows within the interaction space 20 according to an arrow 30 along one of the second return line 24 facing wall 31 of the interaction space 20, whereby the emerging from the outlet nozzle 22 injection jet 32 according to the arrow 26 has a first injection direction, with respect to the longitudinal central axis 29 has a first angle 33.
  • the pressure conditions prevailing in this state cause fuel to flow from the outlet region 28 of the inlet nozzle 21 to the inlet region 27 of the outlet nozzle 22 in the first return line 23 according to arrows 34, which drives the injection jet 32 in the direction of the longitudinal central axis 29.
  • a flow which leads from the inlet region 27 of the outlet nozzle 22 to the outlet region 28 of the inlet nozzle 21, arises in the second return line 24 according to arrows 35.
  • This flow also causes the injection jet 26 to move in the direction of the longitudinal central axis 29.
  • a return flow region 36 that enters the Fig. 2 . 3a and 3c is indicated by a recirculation vortex.
  • the injection jet 32 inter alia passes through the middle state Fig. 3b in which the injection jet 32 is aligned coaxially with the longitudinal central axis 29 of the fluidic injector 15.
  • the state is in accordance Fig. 3c before, in which the fuel in the interaction space 20 according to an arrow 37 along a wall 38 of the interaction space 20 flows, which faces the first return line 23.
  • the injection jet 32 is oriented in a second injection direction, which has a second injection angle 39 with respect to the longitudinal central axis 29.
  • the injection jet 32 oscillates in an injection plane extending in the Fig. 3a to 3c extends in the plane of the drawing.
  • the oxidizer stream 43 thereby moves along a gas path 44 which, in the oxidizer line 12 or in the fifth line 12, respectively Fig. 1 is trained.
  • the fluidic injector 15 is connected to the gas path 44 such that an average outlet direction of the fluidic injector 15 indicated by an arrow 45 is oriented perpendicular to a main flow direction 46 of the oxidizer flow 43.
  • the mean outlet direction 45 results from the mean value, from the different exit directions of the injection jet 32 with which the fuel exits the fluidic injector 15 on average.
  • the average outlet direction 45 thus corresponds to the in Fig. 3b shown state.
  • the main flow direction 46 of the oxidizer flow 43 prevails in the region of the connection point 47 in the gas path 44.
  • the fluidic injector 15 can be attached directly to the oxidizer line 12.
  • the fluidic injector 15 may be connected to the gas path 44 such that the central exit direction 45 is aligned parallel to the main flow direction 46 of the oxidant flow 43.
  • the fluidic injector 15 may be integrated into a lance 48, by means of which the fluidic injector 15 can be positioned preferably coaxially and centrally in the oxidizer line 12.
  • Fig. 4c shows a further alternative in which the fluidic injector 15 is connected to the gas path 44, that the central outlet direction 45 relative to the main flow direction 46 includes an angle 49 which is greater than 0 ° and which is smaller than 90 °. In the example shown, the injection angle 49 is about 45 °.
  • the plane in which the injection jet 32 extends in an oscillating manner relative to its central exit direction 45 extends essentially perpendicular to the plane of the drawing.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP12162013.2A 2012-03-29 2012-03-29 Installation de turbine à gaz dotée d'un injecteur fluidique Withdrawn EP2644999A1 (fr)

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EP12162013.2A EP2644999A1 (fr) 2012-03-29 2012-03-29 Installation de turbine à gaz dotée d'un injecteur fluidique

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Application Number Priority Date Filing Date Title
EP12162013.2A EP2644999A1 (fr) 2012-03-29 2012-03-29 Installation de turbine à gaz dotée d'un injecteur fluidique

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013106682A1 (de) * 2012-11-29 2014-06-18 Krones Ag Verfahren zum Betreiben einer Brennkammer und Brennkammer
US10399093B2 (en) 2014-10-15 2019-09-03 Illinois Tool Works Inc. Fluidic chip for spray nozzles
DE102018125848A1 (de) * 2018-10-18 2020-04-23 Man Energy Solutions Se Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben
US11913409B2 (en) * 2021-05-13 2024-02-27 Aero Engine Academy Of China Afterburner structure with self-excited sweeping oscillating fuel injection nozzles

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3748852A (en) * 1969-12-05 1973-07-31 L Cole Self-stabilizing pressure compensated injector
US4052002A (en) * 1974-09-30 1977-10-04 Bowles Fluidics Corporation Controlled fluid dispersal techniques
EP1331447A1 (fr) * 2002-01-23 2003-07-30 ALSTOM (Switzerland) Ltd Régulation fluidique de combustible
EP2390568A2 (fr) * 2010-05-28 2011-11-30 General Electric Company Buse de combustible de turbomachine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3748852A (en) * 1969-12-05 1973-07-31 L Cole Self-stabilizing pressure compensated injector
US4052002A (en) * 1974-09-30 1977-10-04 Bowles Fluidics Corporation Controlled fluid dispersal techniques
EP1331447A1 (fr) * 2002-01-23 2003-07-30 ALSTOM (Switzerland) Ltd Régulation fluidique de combustible
EP2390568A2 (fr) * 2010-05-28 2011-11-30 General Electric Company Buse de combustible de turbomachine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013106682A1 (de) * 2012-11-29 2014-06-18 Krones Ag Verfahren zum Betreiben einer Brennkammer und Brennkammer
US10399093B2 (en) 2014-10-15 2019-09-03 Illinois Tool Works Inc. Fluidic chip for spray nozzles
DE102018125848A1 (de) * 2018-10-18 2020-04-23 Man Energy Solutions Se Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben
US11913409B2 (en) * 2021-05-13 2024-02-27 Aero Engine Academy Of China Afterburner structure with self-excited sweeping oscillating fuel injection nozzles

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