EP2933559A1 - Kraftstoffmischanordnung und Brennkammer mit einer solchen Mischanordnung - Google Patents

Kraftstoffmischanordnung und Brennkammer mit einer solchen Mischanordnung Download PDF

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Publication number
EP2933559A1
EP2933559A1 EP14164859.2A EP14164859A EP2933559A1 EP 2933559 A1 EP2933559 A1 EP 2933559A1 EP 14164859 A EP14164859 A EP 14164859A EP 2933559 A1 EP2933559 A1 EP 2933559A1
Authority
EP
European Patent Office
Prior art keywords
fuel
combustor
mixing arrangement
fuel mixing
arrangement
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Withdrawn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
EP14164859.2A
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English (en)
French (fr)
Inventor
Hanspeter Knöpfel
Adnan Eroglu
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 EP14164859.2A priority Critical patent/EP2933559A1/de
Publication of EP2933559A1 publication Critical patent/EP2933559A1/de
Withdrawn legal-status Critical Current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
    • 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
    • F23D—BURNERS
    • F23D91/00—Burners specially adapted for specific applications, not otherwise provided for
    • F23D91/02—Burners specially adapted for specific applications, not otherwise provided for for use in particular heating operations
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • 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
    • F23D2900/21—Burners specially adapted for a particular use
    • F23D2900/21003—Burners specially adapted for a particular use for heating or re-burning air or gas in a duct
    • 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
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the present invention relates to combustors of a gas turbine especially for a reheat system with sequential combustion or for a staged system which are proved to excel in achieving very low emissions at high firing temperatures.
  • combustion systems fulfil also a number of stringent requirements, such as low pressure drop, low cooling air consumption, long lifetime and fuel flexibility, an additional improvement of mixing quality of fuel with air and/or flue gas within a temperature range of 350 to 1500 °C should be achieved with a special fuel mixing arrangement.
  • the operating conditions allow self-ignition (spontaneous ignition) of the fuel air mixture without additional energy being supplied to the mixture.
  • the residence time therein must not exceed the auto ignition delay time. This criterion ensures flame-free zones inside the burner. This criterion poses challenges in obtaining appropriate distribution of the fuel across the burner exit area.
  • SEV-burners are currently designed for operation on natural gas and oil only. Therefore, the momentum flux of the fuel is adjusted relative to the momentum flux of the main flow so as to penetrate in to the vortices. This is done by using air from the last compressor stage (high-pressure carrier air). The high-pressure carrier air is bypassing the high-pressure turbine. The subsequent mixing of the fuel and the oxidizer at the exit of the mixing zone is just sufficient to allow low NOx emissions (mixing quality) and avoid flashback (residence time), which may be caused by auto ignition of the fuel air mixture in the mixing zone.
  • EP 2 211 109 A1 discloses a burner of a gas turbine having a duct that comprises at least a vortex generator and downstream of it a plurality of nozzles for injection a fuel within the duct wherein the nozzles are arranged along the wall of the duct and are arranged for injecting fuel toward the inner of the duct.
  • Fig. 1 inline fuel injection
  • Fig. 2 inclined fuel injection
  • the first embodiment to this concept is to stagger the vortex generators 23 embedded on the streamlined bodies or flutes 22 as shown in Figure 1 .
  • the vortex generators 23 are located sufficiently upstream of the fuel injection location to avoid flow recirculation.
  • the vortex generator attack and sweep angles are chosen to produce highest circulation rates at a minimum pressure drop.
  • attack angle ⁇ in the range of 15-20° and/or a sweep angle ⁇ in the range of 55-65°, for a definition of these angles reference is made to Fig. 1d ), where for an orientation of the vortex generator in the air flow 14 as given in Fig. 1 a) the definition of the attack angle ⁇ is given in the upper representation which is an elevation view, and the definition of the sweep angle ⁇ is given in the lower representation, which is a top view onto the vortex generator.
  • the body 22 is defined by two lateral surfaces 33 joined in a smooth round transition at the leading edge 25 and ending at a small radius/sharp angle at the trailing edge 24 defining the cross-sectional profile 48.
  • the vortex generators 23 are located upstream of trailing edge.
  • the vortex generators are of triangular shape with a triangular lateral surface 27 converging with the lateral surface 33 upstream of the vortex generator, and two side surfaces 28 essentially perpendicular to a central plane 35 of the body 22.
  • the two side's surfaces 28 converge at a trailing edge 29 of the vortex generator 23, and this trailing edge is typically just upstream of the corresponding fuel nozzle 15.
  • the lateral surfaces 27 but also the side surfaces 28 may be provided with effusion/film cooling holes 32.
  • the whole body 22 is arranged between and bridging opposite the two walls of the combustor, so along a longitudinal axis 49 essentially perpendicular to the walls. Parallel to this longitudinal axis there is, according to this embodiment, the leading edge 25 and the trailing edge 24. It is however also possible that the leading edge 25 and/or the trailing edge are not linear but are rounded.
  • the nozzles 15 for fuel injection are located. In this case fuel injection takes place along the injection direction 35 which is parallel to the central plane 35 of the body 22. Fuel as well as carrier air are transported to the nozzles 15 as schematically illustrated by arrows 30 and 31, respectively. Typically the fuel supply is provided by a central tubing, while the carrier air is provided in a flow adjacent to the walls 33 to also provide internal cooling of the structures 22. The carrier airflow is also used for supply of the cooling holes 32. Fuel is injected by generating a central fuel jet along direction 34 enclosed circumferentially by a sleeve of carrier air.
  • the staggering of vortex generators 23 helps in avoiding merging of vortices resulting in preserving very high net longitudinal vorticity.
  • the local conditioning of fuel air mixture with vortex generators close to respective fuel jets improves the mixing.
  • the overall burner pressure drop is significantly lower for this concept.
  • the respective vortex generators produce counter rotating vortices which at a specified location pick up the axially spreading fuel jet.
  • FIG. 2 Another second embodiment of this first concept is shown in Fig. 2 , where the fuel is injected at a certain angle (can be increased up to 90°).
  • the fuel is directed into the vortices and this has shown to improve mixing even further. More specifically in this case there are, along the row of nozzles 15, a first set of three nozzles 15, which are directing the fuel jet 34 out of plane 35 at one side of plane 35, and the second set of nozzles 15' directing the corresponding fuel jet out of plane at the other side of plane 35.
  • Fig. 3 shows the basic design of a lobed flute injector with inline fuel injection, wherein in Fig 3a ) a cut of the flute 22 perpendicular to the longitudinal axis is shown, in Fig. 3b ) a side view, in Fig. 3c ) a view onto the trailing edge and against the main flow, and in Fig. 3d ) a prospective view are shown.
  • the injector can be part of a burner, as already described elsewhere.
  • the main flow is passing the lobed mixer, resulting in velocity gradients. These result in intense generation of shear layers, into which fuel can be injected.
  • the lobe angles are chosen in such way to avoid flow separation.
  • the streamlined body 22 has a leading edge 25 and a trailing edge 24.
  • the leading edge 25 defines a straight line and in the leading edge portion of the shape the shape is essentially symmetric, so in the upstream portion the body has a rounded leading edge and no lobing.
  • the leading edge 25 extends along the longitudinal axis 49 of the flute 22. Downstream of this upstream section the lobes successively and smoothly develop and grow as one goes further downstream towards the trailing edge 24. In this case the lobes are given as half circles sequentially arranged one next to the other alternating in the two opposite directions along the trailing edge, as particularly easily visible in Fig. 3c ).
  • each turning point 47 which is also located on the central plane 35, there is located a fuel nozzle which injects the fuel inline, so essentially along the main flow direction 14.
  • the trailing edge is not a sharp edge but has width w which is in the range of 5 to 10 mm.
  • the maximum width W of the flute element 22 is in the range of 25-35 mm and the total height h of the lobing is only slightly larger than this width W.
  • a blade for a typical burner in this case has a height H in the range of 100-200 mm.
  • the periodicity ⁇ is around 40-60 mm.
  • the lobes could be staggered in order to improve the mixing performance and the lobe size can be varied to optimize both pressure drop and mixing.
  • the burner wall has a converging portion and three lobed injectors 22 are arranged in this cavity.
  • the central injector (body 22) is arranged parallel to the main flow direction 14, while the lateral injectors (bodies 22) are arranged in a converging manner adapted to the convergence of the two side walls of the burner/combustor.
  • Such configuration should be well suited for annular combustion systems (as in the GT24/26 developed by the applicant) as well as for a can combustor configuration where the temperature at the inlet to the mixer is in a range of 350 to 1500 °C.
  • the fuel mixing arrangement for mixing fuel and an oxidizing medium for example air, air and flue gas mixtures or flue gas, for combustion in a combustor of a gas turbine, comprises a flute fuel injection system with at least two streamline bodies with at least one fuel nozzle, wherein the streamline bodies comprise either vortex generators or lobes and at least one body is arranged parallel to the flow direction of the oxidizing medium. It is characterized in that the at least second other streamline body is arranged inclined to the at least first streamline body.
  • the fuel mixing arrangement can be placed as an advantage in a burner/mixer with a round or a square cross section.
  • the fuel supply is very simple and not dependent on the contour of the burner/mixer.
  • the fuel mixing arrangement according to the invention is placed in the main flow of the combustor or in a different embodiment it is placed in a by-pass passage in the wall of the combustor.
  • an axial staging arrangement could also be used by placing at least two mixing arrangements one after another in the direction according to the main flow.
  • the present disclosure also relies on multipoint fuel injection device with a streamlined body and with dedicated vortex generators or lobes allowing a more homogeneous fuel distribution.
  • the fuel injection system is applied to mixer configuration placed in approach medium within a temperature range of 350-1500 °C.
  • the oxidizing medium could be air, an air/flue gas mixture or simply flue gas.
  • Fig.4a) to Fig. 4c) show as an overview three possible embodiments for the fuel injection devices, wherein on the axial direction A-A the shape of the body 22 of the injection device has an aerodynamic profile, similar to a symmetric airfoil of for example a turbine blade.
  • the design is similar to the described in WO 2011/054757 A2 resp. WO 2011/054766 A2 (see Fig. 1-3 ). The only differences are the unequal size of the vortex generators 23 at the opposite lateral surfaces 33 of the body 22.
  • the vortex generators (VG) 23 are coupled with inline injection of fuel:
  • the injector nozzles are aligned with the main hot gas flow. Mixing is enhanced by dedicated VGs creating vertical structures helping the distribution of the fuel.
  • the VGs on one lateral surface 33 are bigger than the VGs on the opposite lateral surface 33 of the body 22.
  • the advantages of the inline injection are cheaper manufacturability, lower impact of momentum flux ratio on performances, higher flashback margin / fuel flexibility.
  • the vortex generators 23 are coupled with inclined injection of fuel:
  • the injector nozzles 15 are inclined so that the fuel can better penetrate into the vertical structures created by VGs similar to the embodiment according to Fig. 4a ).
  • VGs on one lateral surface 33 are bigger than the VGs on the opposite lateral surface 33 of the body 22.
  • Fig. 4c shows a lobed structure with inline fuel injection, which creates the velocity field necessary to optimize mixing of fuel and air. Lobes can achieve similar mixing levels with smaller pressure drop.
  • the core of the invention is that for further improving the mixing quality the fuel mixing arrangement 100 of the described fuel injectors is changed. So far the fuel injectors (streamline body 22 with the described VGs or lobed structure) are arranged parallel to the main flow direction 14, neighbouring injectors (bodies 22) are placed parallel or nearly parallel in a converging manner adapted to a possible convergence of the two side walls of a burner or combustor. According to the present invention, additional streamline bodies 22 are arranged inclined to the first ones, for example one embodiment is a square arrangement of the fuel injectors, where the additional streamline bodies 22 are arranged perpendicular to the first mentioned bodies 22.
  • Fig. 5 and Fig. 6 show such a square arrangement in a round burner or mixer 60 ( Fig. 5 ) and in a square burner or mixer 70 ( Fig. 6 ).
  • a triangle arrangement is of course also possible to use.
  • Fuel is injected through the nozzles 15 into a gaseous medium, preferable air, an air and flue gas mixture or simply flue gas.
  • Fig. 7a) to Fig. 7c) describe the general architecture of a combustor 80 with walls 81 using the fuel injection arrangement 100 resp. mixer according to the present invention for operating a turbine 90 (schematically is shown only the turbine vane 1 of the turbine 90).
  • Fig. 7a is illustrated that the mixer with the fuel injector arrangement 100 is placed directly in the main flow 14 of the gaseous medium, for example air or flue gas, in the combustor 80.
  • the mixing arrangement 100 can fit to a round or a square cross section of the combustor 80.
  • the fuel and the air/flue gas are mixed in a very good quality and then combusted.
  • the combustion gases enter the inlet of the turbine 90, expand in the turbine thereby bringing/maintaining the turbine in rotation.
  • the better mixing in the mixer arrangement 100 leads to a less emission release during combustion.
  • the fuel supply could be easily realized and it is further independent on the contour of the combustor.
  • Fig. 7b) and Fig. 7c show that the fuel injector arrangement 100 according to the invention is placed in a by-pass passage to the main flow 14 in the wall 81 of the combustor 80.
  • This has the advantage of a compact design and a less pressure drop of the fuel.
  • more than one mixing arrangements 100 could be placed in axial direction (according to the main flow direction 14) one after another (axial staging).
  • Fig. 8 illustrates schematically a combustor system with two serial combustors 80, 80'.
  • the fuel mixing arrangement 100 according to the invention is placed between the two combustors 80, 80' in the main flow 14.
  • the temperature at the inlet of the mixer 100 is in the range of 350 to 1500 °C.
  • the suggested fuel mixing arrangement 100 could also be placed in the walls 81 of the second combustor 80' analogue to Fig. 7b) and Fig. 7c ).
  • round and square mixers are possible.
  • the disclosed fuel mixer arrangement 100 has the following advantages:

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP14164859.2A 2014-04-16 2014-04-16 Kraftstoffmischanordnung und Brennkammer mit einer solchen Mischanordnung Withdrawn EP2933559A1 (de)

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EP14164859.2A EP2933559A1 (de) 2014-04-16 2014-04-16 Kraftstoffmischanordnung und Brennkammer mit einer solchen Mischanordnung

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EP14164859.2A EP2933559A1 (de) 2014-04-16 2014-04-16 Kraftstoffmischanordnung und Brennkammer mit einer solchen Mischanordnung

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018132766A1 (de) * 2018-12-19 2020-06-25 Man Energy Solutions Se Drallerzeuger zur Einbringung von Brennstoff in eine Gasturbine
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4932861A (en) 1987-12-21 1990-06-12 Bbc Brown Boveri Ag Process for premixing-type combustion of liquid fuel
US5351474A (en) 1991-12-18 1994-10-04 General Electric Company Combustor external air staging device
EP0620403A1 (de) * 1993-04-08 1994-10-19 ABB Management AG Misch- und Flammenstabilisierungseinrichtung in einer Brennkammer mit Vormischverbrennung
US5431018A (en) 1992-07-03 1995-07-11 Abb Research Ltd. Secondary burner having a through-flow helmholtz resonator
EP0713058A1 (de) * 1994-11-19 1996-05-22 ABB Management AG Brennkammer mit Mehrstufenverbrennung
US5626017A (en) 1994-07-25 1997-05-06 Abb Research Ltd. Combustion chamber for gas turbine engine
WO1997017574A1 (en) * 1995-11-07 1997-05-15 Westinghouse Electric Corporation Gas turbine combustor with enhanced mixing fuel injectors
US6192688B1 (en) 1996-05-02 2001-02-27 General Electric Co. Premixing dry low nox emissions combustor with lean direct injection of gas fule
US20020187448A1 (en) 2001-06-09 2002-12-12 Adnan Eroglu Burner system
EP2211109A1 (de) 2009-01-23 2010-07-28 Alstom Technology Ltd Brenner einer Gasturbine und Verfahren zum Mischen eines Kraftstoffs mit einem gasförmigen Strom
WO2011037646A1 (en) 2009-09-24 2011-03-31 Siemens Energy, Inc. Fuel nozzle assembly for use in a combustor of a gas turbine engine
WO2011054757A2 (en) 2009-11-07 2011-05-12 Alstom Technology Ltd Reheat burner injection system with fuel lances
WO2011054766A2 (en) 2009-11-07 2011-05-12 Alstom Technology Ltd Reheat burner injection system
US20120297787A1 (en) * 2011-05-11 2012-11-29 Alstom Technology Ltd Flow straightener and mixer

Patent Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809B1 (de) 1987-12-21 1991-05-15 BBC Brown Boveri AG Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner
US4932861A (en) 1987-12-21 1990-06-12 Bbc Brown Boveri Ag Process for premixing-type combustion of liquid fuel
US5351474A (en) 1991-12-18 1994-10-04 General Electric Company Combustor external air staging device
US5431018A (en) 1992-07-03 1995-07-11 Abb Research Ltd. Secondary burner having a through-flow helmholtz resonator
EP0620403A1 (de) * 1993-04-08 1994-10-19 ABB Management AG Misch- und Flammenstabilisierungseinrichtung in einer Brennkammer mit Vormischverbrennung
US5626017A (en) 1994-07-25 1997-05-06 Abb Research Ltd. Combustion chamber for gas turbine engine
US5645410A (en) 1994-11-19 1997-07-08 Asea Brown Boveri Ag Combustion chamber with multi-stage combustion
EP0713058A1 (de) * 1994-11-19 1996-05-22 ABB Management AG Brennkammer mit Mehrstufenverbrennung
WO1997017574A1 (en) * 1995-11-07 1997-05-15 Westinghouse Electric Corporation Gas turbine combustor with enhanced mixing fuel injectors
US6192688B1 (en) 1996-05-02 2001-02-27 General Electric Co. Premixing dry low nox emissions combustor with lean direct injection of gas fule
US20020187448A1 (en) 2001-06-09 2002-12-12 Adnan Eroglu Burner system
EP2211109A1 (de) 2009-01-23 2010-07-28 Alstom Technology Ltd Brenner einer Gasturbine und Verfahren zum Mischen eines Kraftstoffs mit einem gasförmigen Strom
WO2011037646A1 (en) 2009-09-24 2011-03-31 Siemens Energy, Inc. Fuel nozzle assembly for use in a combustor of a gas turbine engine
WO2011054757A2 (en) 2009-11-07 2011-05-12 Alstom Technology Ltd Reheat burner injection system with fuel lances
WO2011054766A2 (en) 2009-11-07 2011-05-12 Alstom Technology Ltd Reheat burner injection system
US20120297787A1 (en) * 2011-05-11 2012-11-29 Alstom Technology Ltd Flow straightener and mixer

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018132766A1 (de) * 2018-12-19 2020-06-25 Man Energy Solutions Se Drallerzeuger zur Einbringung von Brennstoff in eine Gasturbine
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

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