WO2014173578A1 - Combustion séquentielle avec gaz de dilution - Google Patents

Combustion séquentielle avec gaz de dilution Download PDF

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Publication number
WO2014173578A1
WO2014173578A1 PCT/EP2014/054355 EP2014054355W WO2014173578A1 WO 2014173578 A1 WO2014173578 A1 WO 2014173578A1 EP 2014054355 W EP2014054355 W EP 2014054355W WO 2014173578 A1 WO2014173578 A1 WO 2014173578A1
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WO
WIPO (PCT)
Prior art keywords
mixer
injection
injection tubes
combustion chamber
tubes
Prior art date
Application number
PCT/EP2014/054355
Other languages
English (en)
Inventor
Xianfeng GAO
Luis TAY WO CHONG HILARES
Original Assignee
Alstom Technology Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from PCT/EP2013/058650 external-priority patent/WO2014063835A1/fr
Application filed by Alstom Technology Ltd filed Critical Alstom Technology Ltd
Priority to KR1020157033471A priority Critical patent/KR20160023658A/ko
Priority to EP14708266.3A priority patent/EP2989389B1/fr
Priority to CN201480023116.5A priority patent/CN105121962B/zh
Priority to JP2016509340A priority patent/JP2016516975A/ja
Publication of WO2014173578A1 publication Critical patent/WO2014173578A1/fr
Priority to US14/918,787 priority patent/US10502423B2/en

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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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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 invention refers to a sequential combustor arrangement for a gas turbine with admixing dilution gas into the combustor arrangement.
  • the invention additionally refers to a method for operating a gas turbine with admixing dilution gas into a combustor arrangement.
  • emission limit values and overall emission permits are becoming more stringent, so that it is required to operate at lower emission values, keep low emissions also at part load operation and during transients, as these also count for cumulative emission limits.
  • State-of-the-art combustion systems are designed to cope with a certain variability in operating conditions, e.g. by adjusting the compressor inlet mass flow or controlling the fuel split among different burners, fuel stages or combustors. However, this is not sufficient to meet the new requirements.
  • the object of the present disclosure is to propose a sequential combustor arrangement with a mixing section for dilution gas admixing between the first combustion chamber and the second burner.
  • the dilution gas is admixed in the mixing section to provide proper inlet flow conditions for the second burner.
  • the hot gases are cooled to a predetermined temperature profile. High local inlet temperatures may result in high emissions (in particular
  • Flashback and NOx are induced by the reduced self-ignition time for the injected fuel due to a high inlet gas temperature or high oxygen concentration, which causes earlier ignition (leading to flashback) or reduced time for fuel air mixing resulting in local hot spots during combustion and consequently increases NOx emission.
  • Low temperature regions can cause CO emissions, due to the increased self-ignition time. This can reduce the time for CO to CO2 burnout, and a reduced local flame temperature, which is can further slowdown the CO to CO2 burnout.
  • local hot spots may lead to overheating of certain parts downstream of the mixer.
  • a sequential combustor arrangement comprises a first burner, a first combustion chamber, a mixing device for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection, wherein the mixer is adapted to guide combustion gases in a hot gas flow path extending between the first combustion chamber and the second burner comprising a duct having an inlet at an upstream end adapted for connection to the first combustion chamber and an outlet at a downstream end adapted for connection to the second burner.
  • a local high oxygen concentration can have a similar effect as a local high temperature, e.g. fast reaction reducing the time for mixing, high combustion temperatures, increased NOx emissions and possibly flash back.
  • a local low oxygen concentration can have a similar effect as a local low temperature, e.g. slow reaction leading to increased CO and UHC (unburned hydrocarbon) emissions.
  • a high or low local inlet velocity can lead to increased or reduced residence time in the second burner and subsequent second combustion chamber, which has similar negative effects as inhomogeneous self-ignition times, e.g. a reduced residence time in the second burner can lead to incomplete mixing and high NOx.
  • a reduced residence time in the second combustor can lead to incomplete combustion resulting in increased CO emissions.
  • a reduced flow velocity in the second burner can lead to early ignition and flash back. Further important requirements from the aerodynamic point of view are minimised pressure loss in the hot gas path and the dilution gas supply. Both can impact the performance of a gas turbine operating with such a sequential combustor arrangement.
  • the mixer comprises a plurality of injection tubes (also called injection pipe), which are pointing inwards from the walls of the duct for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber to provide appropriate inlet conditions to the second burner.
  • injection tubes also called injection pipe
  • the diameter, length and number of these tubes are designed to admix dilution gas into the hot gas flow such that the required local mass flow and temperature drop are achieved with a low pressure drop.
  • the injection tubes allow admixing of dilution gas with a pressure drop of 0.4% to 2% of the total pressure of the dilution gas pressure before admixing. With a low pressure drop at the inlet of the injector tubes, a pressure drop of 0.2% to 1 % of the total pressure of the dilution gas pressure before admixing can be sufficient. To reduce the inlet pressure drop rounded tube inlets can be used.
  • the sequential combustor arrangement comprises at least three groups of injection tubes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber.
  • the injection tubes of each group are arranged circumferentially distributed along the side wall of the mixer and wherein the first injection tubes of the first group have a first protrusion depth into the hot gas flow path, the second injection tubes of the second group have a protrusion depth, and the third injection tubes of the third group have a third protrusion depth.
  • the length of the tubes extending into the hot gas path is equal to the protrusion depth.
  • the distance in flow direction between the center point of first injection tube and center point of the second injection tube is between 0.1 and 2 times the diameter of the first injection tube.
  • the distance in flow direction between the center point of second injection tube and center point of the third injection tube is between 0.1 and 2 times the diameter of the second injection tube.
  • the injection tubes of two neighboring groups are not arranged directly downstream of each other but offset in circumferential direction, thus a distance in axial direction of less than the diameter of the injection tubes is possible.
  • the duct wall is at least partly effusion cooled. Due to admixing of dilution gas the average temperature of the hot gas in the mixer is reduced downstream of the injection tubes. Typically, a reduced cooling requirement and less diffusion cooling are expected. However, due to locally increased turbulence the heat load on the side wall downstream of an injection tube can be increased. Therefore in first effusion cooled regions downstream of each first injection tube and upstream of an array of subsequent third injection tube the number of effusion cooling holes per unit area can be increased. It is for example at least 30% bigger than the number of effusion cooling holes per unit area in a second region extending upstream of the first injection tube.
  • the second region extends for one to three diameters of the first injection tube upstream of the first injection tube. Downstream of the last injection tube the hot gas temperature can be reduced to a level where no diffusion cooling is required or other cooling methods are applied. Thus a third region without effusion cooling can be arranged towards the exit of the mixer.
  • the first effusion cooled region has a trapezoidal shape with bases normal to the main flow direction of the hot gases, and wherein the downstream base of the trapezoidal first region is longer than the upstream base of the trapezoidal first region.
  • the length of the upstream base of the trapezoidal first region can for example be in the order of 1 to 2 times the diameter of the first injection tube.
  • the first region can for example have the shape of an isosceles trapezoid.
  • the effusion cooling holes have a diameter in a range from 0.5 to 1 .2 mm. Further the distance between neighboring effusion cooling holes is in a range from 3 to 10 mm in the first region and in a range from 6 to 20 mm in the second region.
  • the first injection tubes are arranged upstream of the second injection tubes, and upstream of the third injection tubes. Further, the third injection tubes can be arranged downstream of the second injection tubes.
  • Such an arrangement allows the injection of dilution gas to different regions of the mixer with minimum interference between the dilution gas injected by different injection tubes.
  • the third injection tubes are arranged upstream of the second injection tubes, and upstream of the first injection tubes.
  • the first injection tubes can be arranged downstream of the second injection tubes.
  • the shorter injection tubes are upstream of the longer injection tubes first the dilution gas injected by the short injection tubes reduces the heat load of the subsequent longer injection tubes.
  • the long injection tubes are in the flow path of the dilution gas of an upstream injection tube the long injection tube is cooled due to a cool shower effect.
  • the diameter of the first injection tube is larger than the diameter of the second injection tube.
  • the diameter of the second injection tube can be larger than the diameter of the third injection tube.
  • the first injection tubes are arranged circumferentially distributed along the side wall of the mixer in a plane normal to the main flow direction of the hot gases flowing through the mixer, and the second injection tubes are arranged circumferentially distributed along the side wall of the mixer in one plane normal to the main flow direction of the hot gases flowing through the mixer.
  • the number of second injection tubes can be equal to the number of first injection tubes.
  • the second injection tubes can be arranged downstream or upstream of the first injection tubes wherein in radial direction they are in the center between two first injection tubes.
  • the third injection tubes are arranged circumferentially distributed along the side wall of the mixer and staggered relative to a plane which is normal to the main flow direction of the hot gases flowing through the mixer.
  • the stagger of the injection tubes reduces flow blockage due to the injection tubes.
  • the stagger can for example be in a range of 0.1 to 3.5 times the diameter of the third injection tube.
  • the tubes of the mixer are exposed to the hot gases leaving the first combustion chamber.
  • the tubes are inherently cooled by the dilution gas which is flowing through them.
  • additional measures to reduce the temperature of the tubes can be applied. Therefore, according to one embodiment of the sequential combustor arrangement at least part of the outer surface of the injection tubes is coated with TBC. Further, at least part of the inner surface of the side wall of the mixer can be coated with TBC to reduce the cooling requirements of the wall, and to thereby avoid cool peripheral regions in the hot gas flow leaving the mixer.
  • the heat transfer coefficient on the inside of the tube is increased.
  • ribs and/or a pin field can be arranged on the inner surface of the injection tubes.
  • the mixer additionally comprises injection holes arranged along the side wall.
  • the first, second and third injection tubes are arranged to admix dilution gas towards the central region of the hot gas flow path and the injection holes are arranged to admix dilution gas into the wall regions of the hot gas flow path.
  • the injection tubes are inclined at an angle of less than 90° relative to the flow direction of the hot gases such that the dilution gas leaving the tubes have a flow component in the direction of the hot gas flow at the location of injection.
  • the injection tubes can be inclined at an angle such that the axial component of the dilution gas leaving the tubes is equal to or within +/-
  • a gas turbine comprising such a sequential combustor arrangement is subject of the present disclosure.
  • a gas turbine comprises at least a compressor, a sequential combustor arrangement with a first burner, a first combustion chamber, a mixing device for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in fluid flow connection, wherein the mixer is adapted to guide combustion gases in a hot gas flow path extending between the first combustion chamber and the second burner comprising a duct having an inlet at an upstream end adapted for connection to the first combustion chamber and an outlet at a downstream end adapted for connection to the second burner, and at least one turbine.
  • the mixer comprises at least three groups of injection tubes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber during operation.
  • the injection tubes of each group are arranged circumferentially distributed along the side wall of the mixer and wherein the first injection tubes of the first group have a first protrusion depth into the hot gas flow path, the second injection tubes of the second group have a second protrusion depth, and the third injection tubes of the third group have a third protrusion.
  • the mixer is arranged such that the dilution gas is admixed during operation to cool the hot gases.
  • the number of injection tubes in a group with a small protrusion depth can be larger than the number of injection tubes in a group with a high protrusion depth, e.g. if the second protrusion depth is bigger than the third protrusion depth the number of third injection tubes can be bigger than the number of second injection tubes.
  • the number of injection tubes can for example be chosen such that the distance between the exit openings of neighboring injection tubes in two groups are similar. Similar in this context can mean that the distance between exit openings in the group with larger penetration depth one to three times the distance between exit openings of injection tubes of the group with smaller penetration depth.
  • the distance between exit openings can further be increased with the exit diameter of the injection tubes. For example it can be proportional to the exit diameter.
  • Dilution gas can be admixed to the hot gases in the mixer such that the hot gases are cooled.
  • dilution gas is admixed into different regions of the cross section of the mixer via the first, second and third injection tubes.
  • the first injection tubes are arranged to admix dilution gas towards the central region of the hot gas flow path.
  • Effusion cooling might be used to cool the combustor walls and/or side walls of the mixing section.
  • Downstream of the dilution air injection mixing between dilution air and hot gas can be enhanced by a contraction of the flow path.
  • the combination of combustors can be disposed as follows:
  • Both, the first and second combustors are configured as sequential can-can architecture.
  • the first combustor is configured as an annular combustion chamber and the second combustor is configured as a can configuration.
  • the first combustor is configured as a can-architecture and the secondary combustor is configured as an annular combustion chamber.
  • Both, the first and second combustor are configured as annular combustion chambers.
  • Fig. 1 a, 2a show a generic gas turbine using sequential combustion with a mixer for admixing dilution gas
  • Fig. 1 b shows a sequential combustor arrangement with a mixer with first, second, and third injection tubes
  • Fig. 2b shows a sequential combustor arrangement with a mixer with first, second, and third injection tubes
  • Fig. 3 shows a mixer section with first, second, and third injection tubes
  • Fig. 4 shows a mixer section with first, second, and third injection tubes
  • Fig. 5 shows a section of mixer in an annular architecture with diffusion cooling
  • Fig. 6 shows an injection tube
  • Fig. 1 a and 2a show a gas turbine 100 with a sequential combustor arrangement 104 according to the disclosure. It comprises a compressor 103, a sequential combustor arrangement 104, and a turbine 105.
  • the sequential combustor arrangement 104 comprises a first burner 1 12, a first combustion chamber 101 , and a mixer 1 17 for admixing a dilution gas to the hot gases leaving the first combustion chamber 101 during operation. Downstream of the mixer 1 17 the sequential combustor arrangement 104 further comprises a second burner 1 13, and a second combustion chamber 102.
  • the first burner 1 12, first combustion chamber 101 , mixer 1 17, second burner 1 13 and second combustion chamber 102 are arranged sequentially in a fluid flow connection.
  • Fuel can be introduced into the first burner 1 12 via a first fuel injection 123, mixed with compressed air which is compressed in the compressor 103, and combusted in the first combustion chamber 101 . Dilution gas is admixed in the subsequent mixer 1 17. Additional fuel can be introduced into the second burner via a second fuel injection 124, mixed with hot gases leaving the mixer 1 17, and combusted in the second combustion chamber 102. The hot gases leaving the second combustion chamber 102 are expanded in the subsequent turbine 105, performing work.
  • the turbine 105 and compressor 103 are arranged on a shaft 106.
  • the remaining heat of the exhaust gas 107 leaving the turbine 105 can be further used in a heat recovery steam generator or boiler (not shown) for steam generation.
  • compressor exit gas is admixed as dilution gas.
  • compressor exit gas is compressed ambient air.
  • the compressor exit gas is a mixture of ambient air and recirculated flue gas.
  • the gas turbine system includes a generator (not shown) which is coupled to a shaft 106 of the gas turbine 100.
  • FIG. 2a shows a first example with a mixer comprising first injection tubes 1 14 with length of second injection tube 11 , second injection tubes 1 15 with a length of second injection tube I2, and third injection tubes 1 16 with a length of second injection tube I3.
  • the second injection tubes 1 15 are arranged downstream of the first injection tubes 1 14, and the third injection tubes 1 16 are arranged downstream of the second injection tubes 1 15.
  • the length of the injection tubes is decreasing in flow direction.
  • compressed gas from the compressor plenum is guided along the combustor liner in a connection duct 1 1 1 as dilution gas 1 10. From the connection duct 1 1 1 the dilution gas 1 10 is injected into the mixer via the first injection tubes 1 14, second injection tubes 1 15, and third injection tubes.
  • the mixer 1 17 has a cross section with a height.
  • the mixer can be arranged with an annular cross section.
  • the height is the difference between the diameter of an outer wall of the annular flow section and the inner wall of the annular flow section.
  • the height is the diameter of the cross section.
  • the length 11 , I2, and I3 of the first, second and third injection tubes 1 14, 1 15, 1 16 are chosen such that good mixing of injected dilution gas 1 10 with the hot gas leaving the first combustion chamber 101 is assured.
  • Fig. 2b shows example which is based on the example of Fig. 1 b.
  • the dilution gas 1 10 is directly supplied to the first injection tubes 1 14, second injection tubes 1 15, and third injection tubes 1 16 from the compressor plenum (downstream of the compressor 103).
  • the first injection tubes 1 14, and second injection tubes 1 15 are extending into the compressor plenum and therefore dilution gas 1 10 with a higher pressure and lower temperature (no temperature pick-up due to the cooling of the combustor before use as dilution gas) is available.
  • Fig. 3 shows an example of the mixer 1 17 of figs. 1 b, 2b in detail.
  • the first injection tube 1 14 has a diameter of the first injection tube D1 which is bigger than the diameter of the second injection tube D2.
  • the second injection tube 1 15 has a diameter of the second injection tube D2 which is bigger than the diameter of the third injection tube D3.
  • the second injection tube 1 15 is arranged downstream of the first injection tube 1 14 with a distance in flow direction a1 in the main flow direction of the hot gas 127.
  • the third injection tube 1 16 is arranged downstream of the second injection tube 1 15 with a distance in flow direction a2.
  • Fig. 4 shows another example of a mixer 1 17.
  • the second injection tube 1 15 is arranged downstream of the short third injection tube 1 16.
  • the long first injection tube 1 14 is arranged downstream of the second injection tube 1 15.
  • the dilution gas 1 10 injected from the third injection tube 1 16 at least partly cools the first and/or second injection tube 1 14, 1 15.
  • the dilution gas 1 10 injected from the second injection tube 1 15 at least partly cools the first injection tube 1 14.
  • Fig. 5 shows an example of a section of mixer in a can architecture. It shows a cut-out of a cylindrical side wall 1 19. First, second, and 3 injection tubes 1 14, 1 15, 1 16 are arranged on the cylindrical side wall 1 19. The second injection tubes 1 15 are arranged downstream of the first injection tubes 1 14 n the main flow direction of the hot gas 127. A staggered array of third injection tubes 1 16 is arranged downstream of the second injection tubes 1 15. Neighbouring third injection tubes 1 16 are staggered by a stagger s in direction of the main flow direction of the hot gas 127 relative to a plane normal to the hot gas flow direction.
  • the inlet to the injection tubes 1 14, 1 15, 1 16 is rounded to reduce the pressure loss of the dilution gas entering the injection tubes 1 14, 1 15, 1 16.
  • the side wall 1 19 of the mixer is diffusion cooled. Diffusion cooling holes 120 are distributed over a large area of the side wall 1 19.
  • a homogeneously cooled second region 126 the wall extends upstream of the first injection tubes 1 14.
  • the first region 125 has an increased density of diffusion cooling holes 120 relative to the second region 126.
  • the first region 125 has the shape of an isosceles trapezoid.
  • the shorter base extends in a direction normal to the main flow direction of the hot gases 127 in both directions from the centre of the first injection tube 1 14.
  • the legs of the trapezoid typically have an angle of about 30° to 45° relative to the main flow direction of the hot gases 127.
  • the first region 125 extends in the main flow direction of the hot gases 127 to the upstream side of subsequent third injection tubes 1 16.
  • the hot gas temperature can be reduced to a level where no diffusion cooling is required or other cooling methods are applied.
  • a third region 128 without effusion cooling is shown arranged towards the exit of the mixer 1 17.
  • Fig. 6 shows an injection tube 1 14, 1 15, 1 16 attached to the side wall 1 19.
  • the outer surface of the injection tube 1 14, 1 15, 1 16 is coated with thermal barrier coating 122 to reduce the heat transfer to the hot gas flow.
  • Ribs 121 are applied on the inner surface of the injection tube 1 14, 1 15, 1 16 to increase the heat transfer for better cooling of the injection tube 1 14, 1 15, 1 16.
  • the first combustion chamber 101 and the second combustion chamber 102 can be arranged in a combustor can-can-architecture, i.e. the first combustion chamber 101 and second combustion chamber 102 are can combustion chamber.
  • the first combustion chamber 101 and the second combustion chamber 102 can be arranged in a combustor can-annular-architecture, i.e. the first combustion chamber 101 is arranged as an annular combustion chamber and second combustion chamber 102 is arranged as can combustion chamber.
  • the first combustion chamber 101 and the second combustion chamber 102 can be arranged in a combustor annular-can-architecture, i.e. the first combustion chamber 101 is arranged as can combustion chamber and second combustion chamber 102 is arranged as an annular combustion chamber.
  • the first combustion chamber 101 and the second combustion chamber can be arranged in a combustor annular-can-architecture, i.e. the first combustion chamber 101 is arranged as can combustion chamber and second combustion chamber 102 is arranged as an annular combustion chamber.
  • the first combustion chamber 101 and second combustion chamber 102 can be arranged in a combustor annular-annular-architecture, i.e. the first combustion chamber 101 and second combustion chamber 102 are annular combustion chambers.
  • the mixing quality of the mixer 1 17 is crucial since the burner system of the second combustion chamber 102 requires a prescribed inlet temperature and inlet velocity profile. All the explained advantages are not limited just to the specified combinations but can also be used in other combinations or alone without departing from the scope of the disclosure. Other possibilities are optionally conceivable, for example, for deactivating individual burners or groups of burners.
  • the dilution gas can be re-cooled in a cooling air cooler before admixing in the mixer 1 17.
  • the arrangement of the injection tubes or injection holes can be reversed, i.e. the short second injection tubes or holes can be arranged upstream of the long first injection tubes. Further, there can be additional tube types with further tube length and tube diameter combinations.

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

Abstract

L'invention concerne un agencement de chambres de combustion séquentiel (104) comportant un premier brûleur (112), une première chambre de combustion (101), un mélangeur (117) permettant d'incorporer un gaz de dilution dans les gaz chauds sortant de la première chambre de combustion (101) lors du fonctionnement, un second brûleur (113) et une seconde chambre de combustion (102) agencés de manière séquentielle en un raccordement d'écoulement de fluide. Le mélangeur (117) comporte au moins trois groupes de tuyaux d'injection (114, 115, 116) pointant vers l'intérieur depuis les parois latérales (119) du mélangeur (117) à des fins d'incorporation du gaz de dilution pour refroidir les gaz de carneau chauds sortant de la première chambre de combustion (101). Les premiers tuyaux d'injection (114) du premier groupe ont une première profondeur de protubérance (l1), les deuxièmes tuyaux d'injection (115) du deuxième groupe ont une profondeur de protubérance (l2) et les troisièmes tuyaux d'injection (116) du troisième groupe ont une troisième profondeur de protubérance (l3). L'invention concerne en outre une turbine à gaz (100) et un procédé permettant de faire fonctionner une turbine à gaz (100) avec un tel agencement de chambres de combustion séquentiel (104).
PCT/EP2014/054355 2012-10-24 2014-03-06 Combustion séquentielle avec gaz de dilution WO2014173578A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
KR1020157033471A KR20160023658A (ko) 2012-10-24 2014-03-06 희석 가스에 의한 순차적 연소
EP14708266.3A EP2989389B1 (fr) 2013-04-25 2014-03-06 Combustion séquentielle avec gaz de dilution
CN201480023116.5A CN105121962B (zh) 2013-04-25 2014-03-06 具有稀释气体的连续燃烧
JP2016509340A JP2016516975A (ja) 2013-04-25 2014-03-06 希釈ガスを備えた多段燃焼
US14/918,787 US10502423B2 (en) 2012-10-24 2015-10-21 Sequential combustion with dilution gas

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EPPCT/EP2013/058650 2013-04-25
PCT/EP2013/058650 WO2014063835A1 (fr) 2012-10-24 2013-04-25 Combustion séquentielle avec mélangeur de gaz d'appoint

Related Child Applications (1)

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US14/918,787 Continuation US10502423B2 (en) 2012-10-24 2015-10-21 Sequential combustion with dilution gas

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WO2014173578A1 true WO2014173578A1 (fr) 2014-10-30

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CN (1) CN105121962B (fr)
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CN105716111A (zh) * 2014-12-22 2016-06-29 通用电器技术有限公司 用于将稀释空气掺合至热气流的混合器
EP3037728A1 (fr) * 2014-12-22 2016-06-29 Alstom Technology Ltd Mélangeur axialement étagé avec injection d'air de dilution
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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US20170370589A1 (en) * 2016-06-22 2017-12-28 General Electric Company Multi-tube late lean injector

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