EP3702670A1 - Chambre de combustion séquentielle pour turbine à gaz, procédé de fonctionnement de ladite chambre de combustion séquentielle et procédé de remise à neuf d'une chambre de combustion séquentielle d'une turbine à gaz - Google Patents

Chambre de combustion séquentielle pour turbine à gaz, procédé de fonctionnement de ladite chambre de combustion séquentielle et procédé de remise à neuf d'une chambre de combustion séquentielle d'une turbine à gaz Download PDF

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Publication number
EP3702670A1
EP3702670A1 EP19160086.5A EP19160086A EP3702670A1 EP 3702670 A1 EP3702670 A1 EP 3702670A1 EP 19160086 A EP19160086 A EP 19160086A EP 3702670 A1 EP3702670 A1 EP 3702670A1
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EP
European Patent Office
Prior art keywords
combustor
gas
fuel
burners
fuel line
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.)
Granted
Application number
EP19160086.5A
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German (de)
English (en)
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EP3702670B1 (fr
Inventor
Andrea Ciani
Mirko Ruben Bothien
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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Priority to EP19160086.5A priority Critical patent/EP3702670B1/fr
Priority to CN202010128447.2A priority patent/CN111623373B/zh
Publication of EP3702670A1 publication Critical patent/EP3702670A1/fr
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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
    • F23R3/28—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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/08—Preparation of fuel
    • F23K5/10—Mixing with other fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K2900/00—Special features of, or arrangements for fuel supplies
    • F23K2900/05004—Mixing two or more fluid 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
    • F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution
    • 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 the technical filed of the gas turbine assemblies for power plants.
  • the present invention relates to a method for operating a sequential combustor of a gas turbine.
  • This sequential combustor comprises an first combustor (or upstream combustor) configured for receiving the compressed air and mixing this air with fuel and a downstream second combustor (or reheat combustor) configured for receiving the hot gas leaving the first combustor and adding fuel into this hot gas for performing a self/spontaneous ignition.
  • the present invention refers also to a method for refurbishment the above first combustor in order to allow a current first combustor to be fed by a highly reactive fuel, for instance H2-based fuel.
  • a gas turbine assembly for power plants comprises a rotor provided with a compressor unit, a combustor unit and at least a turbine unit.
  • the compressor is configured for compressing air supplied at a compressor inlet.
  • the compressed air leaving the compressor flows into a plenum and from there into a combustor.
  • the combustor comprises a plurality of burners configured for injecting fuel in the compressed air.
  • the mixture of fuel and compressed air flows into a combustion chamber where this mixture is combusted.
  • the resulting hot gas leaves the combustion chamber and is expanded in the turbine performing work on the rotor.
  • the turbine comprises a plurality of stages, or rows, of rotor blades that are interposed by a plurality of stages, or rows, of stator vanes.
  • the rotor blades are connected to the rotor whereas the stator vanes are connected to a vane carrier that is a concentric casing surrounding the turbine unit.
  • a high turbine inlet temperature is required.
  • this high temperature involves an undesired high NOx emission level.
  • the so called “sequential" gas turbines is particularly suitable.
  • a sequential gas turbine comprises two combustors or combustion stages in series wherein each combustor is provided with a plurality of burners and with at least a relative combustion chamber. Following the main gas flow direction, usually the upstream or first combustor comprises a plurality of so-called "premix" burners.
  • premix burner we mean the burner in the first stage of the sequential combustor wherein each premix burner is configured for receiving the compressed air and injecting fuel in this coming air for realizing a diffusion flame (e.g. by pilot lance without any premix) and/or a premix flame.
  • the downstream or second combustor is called “reheat” or “sequential" combustor and it is fed by the hot gas leaving the first combustor.
  • the reheat combustor is provided with a plurality of reheat burners configured for injecting fuel in the hot gas coming from the first combustor. Due to the high gas temperature, the operating conditions downstream the reheat burners allow a self/spontaneous ignition of the fuel/air mixture. Also these reheat burners are configured for performing a premix for the hot gas and the fuel before the spontaneous ignition. Therefore in the following with terms reheat burners we mean only the burners at the second stage of combustion in the sequential combustor.
  • the premix and reheat combustors are annular shaped and are physically separated by a stage of turbine blades, called high pressure turbine.
  • the gas turbine is not provided with the high pressure turbine and the combustor unit is realized in form of a plurality of can-combustors.
  • each can-combustor comprises a premix (first stage) and the reheat (second stage) combustor arranged directly one downstream the other inside the common can shaped casing.
  • the burners are configured for injecting different kinds of fuel, i.e.
  • the burners are provided with separated channels or ducts for feeding the gas fuel, liquid fuel and carrying air to relevant burner nozzles.
  • a change in fuel reactivity implies a change in flame location.
  • higher fuel reactivity like H2 forces the flame to move upstream, increasing NOx emissions, and potentially overheating the burners. Consequently, when burning highly reactive fuels (e.g. fuels containing large quantities of either higher hydrocarbons or hydrogen) the flame moves upstream compared to the case of natural gas, thus increasing the risk of flashback.
  • highly reactive fuels e.g. fuels containing large quantities of either higher hydrocarbons or hydrogen
  • the flame moves upstream compared to the case of natural gas, thus increasing the risk of flashback. Since the position of the flame in the reheat combustor can be effectively controlled by the temperature at the inlet of the reheat combustor (self/spontaneous ignition), by lowering the inlet temperature it is therefore possible to move the flame downstream.
  • the negative effect of higher fuel reactivity (flashback) in the reheat combustor can be compensated by lowering the first stage temperature.
  • the premix combustor may be affected by flashback in this condition.
  • in order to mitigate the flashback risks by moving the flame back to its design position in the premix and in the reheat combustor is obtained by simply injecting less fuel in the first stage of combustion. In this way the position of the flame in the premix combustor is moved downstream and the inlet temperature of the second stage is lower.
  • a primary object of the present invention is to provide a sequential combustor for a gas turbine in order to overcome the drawbacks foregoing mentioned of the current prior art practice.
  • the scope of the present invention is to provide a method for refurbishment a current sequential combustor for a gas turbine in order to allow the sequential combustor to be supplied with a highly reactive fuel, for instance H2-based fuel having a % of H2 in vol. from 0% to 100%.
  • the starting point of the present invention is an innovative method developed by the Applicant for operating a sequential combustor for a gas turbine when the combustor is fed by a highly reactive fuel.
  • the sequential combustor configured for carrying out this operating method comprises:
  • the supplied compressed air is the air leaving a compressor upstream arranged in the gas turbine with respect to the sequential combustor.
  • the combustor operating method does not provide any limitation referring to the shape of the first combustor and in the following description of the drawings two different embodiments of the claimed first combustor will be described.
  • Each burner of this first combustor may be a particular kind of burner, namely a so-called "premix” burner. It is clear for a skill person in the field of the gas turbines that the definition "premix” burner means a burner configured for mixing the coming air and the injected fuel before the inlet of the combustion chamber.
  • the premix burner may comprise an outer conical casing configured for generating a swirl in the air flow wherein this conical casing is also provided with fuel injecting nozzles.
  • a "premix" burner may comprises also a pilot configured for injecting fuel directly in the air flow in the combustion chamber without any preliminary mixing feature.
  • this pilot may be realized in form of a lance axially extending along the outer conical casing.
  • a premix burner is a burner configured for generating to different kinds of flame in the combustion chamber, a so-called diffusion flame, for instance generated by the fuel injected by the pilot, and a premix flame, for instance generated by the swirled mixture air/fuel.
  • a premix burner may be operated to generate only a diffusion flame, only a premix flame or a combination of a diffusion and a premix flame with different rate of fuel supplied in the premix circuit and in the diffusion circuit.
  • the premix flame is preferable due to a less NOx generation.
  • the combustor operating method developed by the Applicant does not provide any limitation also referring to the shape of the second combustor.
  • Each second burner is a burner configured for injecting fuel in the hot gas flow leaving the first combustor. Due to the high temperature of the hot gas leaving the first combustor, the second burner is not provided with a spark igniter or any forced igniter device and the combustion is based on a self/spontaneous ignition. This second burner is also called "reheat" burner and the present invention does not require any structural modification of current reheat burners.
  • the present invention solves the problem to how safely perform the above operating step of feeding the burner with a high diffusion fuel rate.
  • a high diffusion fuel rate during the normal operation would require a high fuel pressure drop (more than 10 bar) and this high fuel pressure drop requires in turn a very high pressure inside the gas fuel line feeding the diffusion nozzles. This high pressure may damage the combustion system.
  • the engine would require fuel gas pressure levels not always available in the fuel gas lines.
  • the solution proposed by the present invention is to use in parallel another fuel supply line already present in the burner for feeding to the diffusion nozzles at least part of the fuel running in the gas fuel line.
  • the fuel supply line used for feeding to the diffusion nozzles at least part of the fuel running in the gas fuel line is the oil fuel line.
  • the solution proposed by the present invention is feeding part of the high reactive gas fuel running in the gas fuel line into the oil (liquid) fuel line; oil fuel line that are usually used only for oil fuel feeding.
  • a connection is provided between the pilot gas fuel line and the oil fuel line. This connection is provided with a valve configured for selectively allowing the flow of part of the high hydrogen gas fuel running in the gas line into the oil line.
  • this solution allows to reduce the pressure present in the gas fuel line without any detrimental impact on combustion. Indeed the NOx generation level remains the same with and without the high hydrogen gas fuel passing through the oil fuel line.
  • the valve connecting the gas line and the oil line is an on/off valve.
  • the valve connecting the gas line and the oil line is a mass flow controller.
  • the present invention refers to a method for refurbishment a current sequential combustor for a gas turbine comprising a premix burner and a reheat burner, wherein:
  • the method of the present invention comprises the step of adding a connection between the gas fuel line and the oil fuel line wherein this connection is configured for selectively allowing part of gas fuel running in the gas fuel line to enter in the oil fuel line. Once fed inside the oil fuel line the spilled part gas fuel is injected by the oil nozzles in the combustion chamber.
  • the method may comprise the step of providing the above connection with a valve, for instance an on/off valve or a mass flow controller.
  • FIG. 1 is a schematic view of a first example of a gas turbine 1 comprising a sequential combustor wherein the first burner with a pilot can be provided with the pilot fuel lines according to the present invention.
  • figure 1 discloses a gas turbine with a high pressure and a low pressure turbine.
  • the gas turbine 1 of figure 1 comprises a compressor 3, a first combustor 31, a high-pressure turbine 5, a second combustor 32 and a low-pressure turbine 7.
  • the compressor 3 and the two turbines 5, 7 are part of or are connected to a common rotor 8 rotating around an axis 9 and surrounded by a concentric casing 10.
  • the compressor 3 is supplied with air and is provided with rotating blades 18 and stator vanes 19 configured for compressing the air entering the compressor 3.
  • the compressed air flows into a plenum 11 and from there into a plurality of first burners 12 of the first combustor 31 arranged as a ring around the axis 9.
  • Each first burner 12 in configured for injecting fuel (supplied by a first fuel supply 13) in the air flow, in particular this first burner 12 may be defined as a "premix" burner because in configured for mixing the air and the injected fuel before the spark point.
  • Figures 4 and 5 disclose an example of a premix burner with a pilot that can be provided with the pilot fuel lines according to the present invention.
  • the fuel/compressed air mixture flows into a first combustion chamber 4 annularly shaped where this mixture are combusted via a forced ignition, for instance by a spark igniter.
  • the resulting hot gas leaves the first combustor chamber 4 and is partially expanded in the high-pressure turbine 5 performing work on the rotor 8.
  • Downstream of the high-pressure turbine 5 the hot gas partially expanded flows into a second burner 33 where fuel supplied by a fuel lance 14 is injected.
  • the partially expanded gas has a high temperature and contains sufficient oxygen for a further combustion that occurred based on a self-ignition in the second combustion chamber 6 arranged downstream the second burner 33.
  • This second burner 33 is also called "reheat" burner.
  • the reheated hot gas leaves the second combustion chamber 6 and flows in the low-pressure turbine 7 where it is expanded performing work on the rotor 8.
  • the low-pressure turbine 7 comprises a plurality of stages, or rows, of rotor blades 15 arranged in series in the main flow direction. Such stages of blades 15 are interposed by stages of stator vanes 16.
  • the rotor blades 15 are connected to the rotor 8 whereas the stator vanes 16 are connected to a vane carrier 17 that is a concentric casing surrounding the low-pressure turbine 7.
  • FIG. 2 is a schematic view of a second example of a gas turbine 20 comprising a sequential combustor wherein the first burner with a pilot can be provided with the pilot fuel lines according to the present invention.
  • figure 2 discloses a gas turbine 20 provided with a compressor 29, one turbine 21 and a sequential combustor 22.
  • the sequential combustor 22 of figure 2 comprises a plurality of so-called can combustors, i.e. a plurality of cylindrical casings wherein each can combustor houses a plurality of first burners 24, for instance four first burners 24, a first combustion chamber 25, a second burner 26, and a second combustion chamber 27.
  • an air mixer (not represented) may be provided configured for adding air in the hot gas leaving the first combustion chamber 25.
  • the sequential combustor arrangement is at least in part housed in an outer casing 28 supporting the plurality of can combustor 22 arranged as a ring around the turbine axis.
  • a first fuel is introduced via a first fuel injector (not shown) into the first burners 24 wherein the fuel is mixed with the compressed gas supplied by the compressor 29.
  • each first burner 24 of this embodiment is a "premix" burner configured for generating a premix flame and a diffusion flame.
  • Each first burner 24 of figure 2 and each first burner 12 of figure 1 is independently operable, i.e.
  • each first burner may be switched off independently on the other first burners and each first burner may be operated independently in terms of ratio between the fuel injected in the diffusion mode and the fuel injected in the premix mode.
  • the hot gas leaving the second combustion chamber 27 expands in the turbine 21 performing work on a rotor 30.
  • FIG. 3 is a schematic view of a can combustor 22 that may be a combustor of the turbine of figure 2 .
  • figure 3 discloses the combustor in two different operation conditions, i.e. with two different flames positions inside the can combustor 22.
  • a diagram is present disclosing how the temperature varies in these two different operation conditions inside the can combustor 22.
  • the can combustor 22 is today preferable because it has significant advantages in terms of both low emissions and fuel flexibility.
  • the first stage premixed burner 24 utilizes aerodynamic structures to stabilize a propagating premix flame providing excellent flame stability and combustion efficiency over an extensive operational range.
  • This flame having a correct distance from the burner nozzles is represented by the reference 34'.
  • the second burner 26 in contrast is a primarily auto-ignition controlled burner.
  • the flame generated by the second burner 26 is represented by the reference 35'.
  • the flames at the first 24 and the second burner 26 move upstream as represented by the references 34 and 35.
  • These movement towards the burners involves some drawbacks, i.e. a high flame residence time (and therefore high NOx generation) and overheating of the burner nozzles.
  • a solution to move downstream the flames 34 35 to a correct position of flames 34' 35' may be reducing the first stage flame temperature (reducing fuel injected in the first stage for passing from line 36 to line 37 in diagram of Figure 3 ).
  • it also accounts for the change in auto-ignition delay time and hence flame location of the second stage whose position for the same flame temperature can be controlled. If, for example, instead of natural gas a more reactive fuel, i.e.
  • the first stage temperature has to be reduced.
  • reducing the first stage temperature alters the ignition delay time of the second stage in the desired way to keep the flame 35 at its design position 35'.
  • a lower second inlet temperature is required.
  • Applicant developed a new solution for allowing the feeding of higly reactive fuels. This solution is to realize hybrid flames obtained by adjusting the distribution of fuel of some active first burners between the diffusion and premixed mode, in particular by providing a high pilot fuel rate. In this way the lean blow out margin (low temperature) of the first stage is extended without any drawback of the prior art practice.
  • the first stage can be operated with highly reactive fuels without injecting diluents while delivering sufficiently lower inlet temperature levels for the second stage combustor.
  • the present invention solves the problem of safely performing the above operating step of feeding the burner with a "high diffusion fuel flow rate". Indeed, a high diffusion fuel flow rate during normal operation requires a high fuel pressure drop (more than 10 bar) and this high fuel pressure drop requires a very high fuel pressure inside the gas fuel line feeding.
  • the premix burner 41 is a burner configured for generating a diffusion flame 42 ( figure 4 ) and a premix flame 43 ( figure 5 ).
  • the fuel is directly injected in the combustion chamber by a pilot lance 44 without any preliminary mixing with the coming compressed air.
  • the premix flame 43 the fuel is mixed with the compressed air before entering the combustion chamber.
  • the mixing may be realized by passing the air in a conical casing 45 configured for generating a swirl wherein this conical casing 45 is also provided with nozzles for injecting fuel in this swirl.
  • the method comprises the step switching off at least one of the first burners (for instance at least a burner for each can combustor) and operating the remaining active first burners for generating hybrid flames as combination of diffusion mode and premix mode.
  • at least one of active first burners is operated so that a significant amount of fuel is burnt in diffusion mode, in particular at least 5% of the fuel fed to this burner.
  • some burners on the first stage may be operated only in premix configuration and others only in diffusion configuration.
  • different burners may be operated simultaneously in premix and in diffusion configuration with different ratios of diffusion/premix mode.
  • the switch-off of some of the first stage burners may be done with a specific pattern in order to optimize the temperature distribution.
  • FIG 6 is a schematic view of fuel lines according to an embodiment of the present invention.
  • the solution proposed is feeding part of the high reactive gas fuel running inside the gas line into the oil line (already present in the burner and usually used only for oil fuel feeding).
  • the burner is provided with a gas fuel nozzle 48 and an oil fuel nozzle 49.
  • the gas fuel nozzle 48 is fed by a gas fuel line 50 connected at the opposite end to a gas fuel source 51.
  • the oil fuel nozzle 49 is fed by a oil fuel line 52 connected at the opposite end to an oil fuel source 53.
  • the burner is also provided with a connection 54 (i.e. at least a duct) fluidly connecting the gas fuel line 50 with oil fuel line 52.
  • connection 54 is provided with a valve 55 configured for selectively feeding part of the gas fuel running in the gas fuel line 50 inside the oil fuel line 52 so that the pressure present in the gas line may be reduced without any detrimental impact on combustion.
  • the burner may comprise a plurality of gas and oil nozzles fed by a plurality of fuel lines.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
EP19160086.5A 2019-02-28 2019-02-28 Procédé de fonctionnement d'une chambre de combustion séquentielle d'une turbine à gaz Active EP3702670B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19160086.5A EP3702670B1 (fr) 2019-02-28 2019-02-28 Procédé de fonctionnement d'une chambre de combustion séquentielle d'une turbine à gaz
CN202010128447.2A CN111623373B (zh) 2019-02-28 2020-02-28 用于燃气涡轮的顺序燃烧器、其运行方法和其整修方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19160086.5A EP3702670B1 (fr) 2019-02-28 2019-02-28 Procédé de fonctionnement d'une chambre de combustion séquentielle d'une turbine à gaz

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EP3702670A1 true EP3702670A1 (fr) 2020-09-02
EP3702670B1 EP3702670B1 (fr) 2021-12-15

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0506069A1 (fr) * 1991-03-29 1992-09-30 Union Carbide Chemicals & Plastics Technology Corporation Fluides supercritiques comme diluants dans la combustion de combustibles liquides et de déchets
EP2090830A1 (fr) * 2008-02-13 2009-08-19 ALSTOM Technology Ltd Agencement d'alimentation en carburant
EP2767699A1 (fr) * 2013-02-19 2014-08-20 Alstom Technology Ltd Turbine à gaz avec commande de composition de carburant

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704829A2 (de) * 2011-04-08 2012-11-15 Alstom Technology Ltd Gasturbogruppe und zugehöriges Betriebsverfahren.
EP2889542B1 (fr) * 2013-12-24 2019-11-13 Ansaldo Energia Switzerland AG Procédé pour le fonctionnement d'une chambre de combustion pour turbine à gaz et chambre de combustion
EP3015772B1 (fr) * 2014-10-31 2020-01-08 Ansaldo Energia Switzerland AG Agencement de chambre de combustion pour une turbine à gaz
EP3029378B1 (fr) * 2014-12-04 2019-08-28 Ansaldo Energia Switzerland AG Brûleur séquentiel pour une turbine à gaz axiale
EP3199781B1 (fr) * 2016-01-27 2019-05-01 Ansaldo Energia IP UK Limited Turbine à gaz et procédé correspondant pour commander un fonctionnement d'une turbine à gaz avec des capteurs de température de sortie de turbine sélectionnés

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0506069A1 (fr) * 1991-03-29 1992-09-30 Union Carbide Chemicals & Plastics Technology Corporation Fluides supercritiques comme diluants dans la combustion de combustibles liquides et de déchets
EP2090830A1 (fr) * 2008-02-13 2009-08-19 ALSTOM Technology Ltd Agencement d'alimentation en carburant
EP2767699A1 (fr) * 2013-02-19 2014-08-20 Alstom Technology Ltd Turbine à gaz avec commande de composition de carburant

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CN111623373B (zh) 2023-05-16
EP3702670B1 (fr) 2021-12-15
CN111623373A (zh) 2020-09-04

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