WO2026027101A1 - Tube de brûleur à combustible pour un brûleur pour combustibles gazeux hautement réactifs - Google Patents

Tube de brûleur à combustible pour un brûleur pour combustibles gazeux hautement réactifs

Info

Publication number
WO2026027101A1
WO2026027101A1 PCT/EP2025/064979 EP2025064979W WO2026027101A1 WO 2026027101 A1 WO2026027101 A1 WO 2026027101A1 EP 2025064979 W EP2025064979 W EP 2025064979W WO 2026027101 A1 WO2026027101 A1 WO 2026027101A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
burner tube
tubular body
fuel burner
premixing
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.)
Pending
Application number
PCT/EP2025/064979
Other languages
English (en)
Inventor
Stefano Gori
Roberto MELONI
Pier Carlo NASSINI
Emanuele Matoni
Alessandro ZUCCA
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.)
Nuovo Pignone Technologie SRL
Original Assignee
Nuovo Pignone Technologie SRL
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 Nuovo Pignone Technologie SRL filed Critical Nuovo Pignone Technologie SRL
Publication of WO2026027101A1 publication Critical patent/WO2026027101A1/fr
Pending legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F23R3/286—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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the present disclosure concerns a fuel burner tube for a burner, for instance a burner of a gas turbine, for the combustion of highly reactive fuels.
  • a single burner has some similarities with the currently proposed geometry, being equipped as a bundle of tubes to form a complete burner.
  • Each tube has radially oriented air holes in the upstream part and a centerbody, which extends to the end of the tube where fuel is injected through jets in crossflow.
  • US10208958B2 discloses a method and apparatus for mixing H2-rich fuels with air in a gas turbine combustion system, wherein a first stream of burner air and a second stream of a H2-rich fuel are provided. All of the fuel is premixed with a portion of the burner air to produce a pre-premixed fuel/air mixture. This pre-premixed fuel/air mixture is injected into the main burner air stream.
  • the subject matter disclosed herein concerns a fuel burner tube for a burner of a combustion chamber.
  • the fuel burner tube comprises a tubular body that extends along a longitudinal axis, having an external surface, an internal surface, a first end, and a second end.
  • the fuel burner tube is capable of emitting a flame at the second end.
  • the tubular body includes a premixing area delimited within the internal surface, where at least one premixing process flow is combined with fuel. Additionally, one or more through holes are radially arranged on the internal surface of the tubular body for injecting a lateral purging flow downstream toward the premixing area.
  • a further aspect of the present disclosure is drawn to a centerbody arranged within the tubular body, extending from the first end of the tubular body up to the premixing area, to allow the introduction of a central purging flow into the premixing area.
  • at least one fuel injection channel is connectable to a fuel injection system for injecting a stream of fuel into the premixing area.
  • This fuel injection channel is arranged downstream of the centerbody, on the internal surface of the tubular body, and in correspondence with the premixing area.
  • a fuel burner tube wherein the centerbody extends from 20% to 60% of the total length of the tubular body. Additionally, the at least one fuel injection channel can be inclined at an angle from 20 to 90 degrees with respect to the internal surface of the tubular body.
  • a further aspect of the present disclosure is drawn to a fuel burner tube comprising one or more oxidant gas passages radially arranged on the internal surface of the tubular body in correspondence with the premixing area. These oxidant gas passages are configured to mix the stream of fuel injected by the fuel injection channel with a stream of oxidant passing through the oxidant gas passages.
  • a fuel burner tube comprising an annular lateral purge surrounding one or more oxidant gas passages. Additionally, the tube may include at least one lateral purge cavity with an outlet on the internal surface of the tubular body. The outlet of this lateral purge cavity is located in correspondence with the premixing area and in proximity to the outlets of the fuel injection channels.
  • a further aspect of the present disclosure is drawn to a fuel burner tube wherein the at least one lateral purge cavity is arranged to direct the lateral purge flow within the tubular body, forming a fluid gap that prevents flame anchoring. Furthermore, the outlet of the lateral purge cavity can be C-shaped, creating a horseshoe lateral purge flow to prevent flame anchoring.
  • a fuel burner tube comprising lateral purge cavities located upstream and/or downstream with respect to the fuel injection channel.
  • the fuel burner tube may also comprise an element, which, with the centerbody, forms a passive damper fluidically coupled to the first end of the tubular body.
  • the passive damper is capable of dampening pressure and/or acoustic pulsations of the flows passing through the fuel burner tube.
  • a further aspect of the present disclosure is drawn to a fuel burner tube wherein the element of the damper includes a vertical wall at its base and at least one hole on the vertical wall, allowing the passage of the mixing process flow inside the passive damper.
  • a dilution slot having a plurality of channels, each one opening into the premixing area.
  • the channels of the dilution slot inject air without fuel or as a lean mixture.
  • the dilution slot is configured to distribute an air jet over the inner terminal surface of the premixing area, to form a protective air layer or sleeve along the inner surface of the premixing area.
  • the fuel burner tube comprises a plurality of injection channels, arranged on the lateral surface of the tubular body and opening into the premixing area.
  • Each injection channel comprises a fuel injection channel, substantially inclined with respect to the in-ternal surface of the tubular body, and a protection channel, substantially circular, arranged around the relevant fuel injection channel, through which air is injected.
  • the air injected through each protection channel serves to pro-tect or sleeve the fuel injection channel to prevent the flame to anchor on the inner surface of the premixing area.
  • a fuel burner tube suitable for use in the combustion chamber of a gas turbine or an Allam-cycle plant.
  • the central and premixing process flows, as well as the central purging and lateral purging flows, can comprise an oxidant, a stream of carbon dioxide, or a mixture containing carbon dioxide.
  • the oxidant flow may consist of air, oxygen, or oxygen mixed with a recycled carbon dioxide flow stream, or air mixed with recycled carbon dioxide.
  • the subject matter disclosed herein concerns a fuel burner wherein the internal surface is smoothed to counteract or diminish the boundary layer growth. This feature reduces turbulence and improves fluid dynamics within the burner.
  • a fuel burner wherein the entire internal surface is smoothed, or alternatively, only the portion of the internal surface closest to the second end of the tubular body is smoothed. This smoothness allows the desired reduction in boundary layer growth, thereby minimizing the risk of backfire.
  • a further aspect of the present disclosure is drawn to a burner comprising a plurality of fuel burner tubes as defined in any of the preceding claims, wherein the fuel burner tubes are arranged together for the combustion of highly reactive fuels, such as hydrogen.
  • Fig. 1 A illustrates a lateral section of a fuel burner tube according to a first embodiment
  • Fig. IB the cross section of Fig. 1A;
  • Fig. 2B the cross section of Fig. 2 A;
  • Fig. 3A illustrates a lateral section of a fuel burner tube, according to a third embodiment
  • Fig. 3B the cross section of Fig. 3 A;
  • Fig. 4A illustrates a lateral section of a fuel burner tube, according to a fourth embodiment
  • Fig. 4B the cross section of Fig. 4 A;
  • Fig. 5A illustrates a lateral section of a fuel burner tube, according to a fifth embodiment
  • Fig. 5B the cross section of Fig. 15 A;
  • Fig. 6A illustrates a lateral section of a fuel burner tube, according to a sixth embodiment
  • Fig. 6B the cross section of Fig. 6 A;
  • Fig. 7 illustrates a burner made of a bundle of fuel burner tubes according to the present disclosure
  • Fig. 8 illustrates first perspective view of a burner having fuel burner tubes according to a further embodiment
  • Fig. 9 illustrates a second perspective of the burner of Fig. 8.
  • Fig. 10 illustrates a front view of the burner of Fig. 8.
  • Fig. 11 illustrates a sectional view along the line A-A of the burner of Fig. 8; and Fig. 12 illustrates a sectional view of a fuel burner tube of Fig. 8.
  • the present subject matter is directed to a fuel burner tube of a burner, such as a gas turbine or an Allam-cycle plant burner, tailored for highly reactive gas fuels.
  • the fuel burner tube is designed to optimize the fuel and oxidant premixing process within a burner before entering the combustor. This optimization aims to enhance emission performance by reducing NO X emissions resulting from the combustion.
  • innovative purging concepts are introduced to mitigate issues such as flame anchoring within the burner premixing section and flashback from the combustion chamber.
  • the fuel burner tube integrates also a passive acoustic damping mechanism within the burner premixing area, to mitigate noise generation.
  • Figures 1 A and IB shows a first embodiment of a fuel burner tube 1 of a burner for a gas turbine (the gas turbine not shown in the figures).
  • the fuel burner tube 1 for a burner of a gas turbine comprises a tubular body 2, which extends along a longitudinal axis L.
  • the tubular body 2 features an external surface 21 and an internal surface 22, with a first end 23 and a second end 24.
  • the flame can be emitted in correspondence with the second end 24 and is generated by spontaneous ignition, after the fuel is mixed with air or any other oxidant gas.
  • a premixing area 25 defined by the internal surface 22, where oxidant gas is premixed with fuel, before the combustion.
  • the tubular body 2 has a cylindrical shape or a troncoconical shape. Also, the tubular body 2 has one or more through holes 3 radially arranged on the internal surface 22. The through holes 3 are designed to inject the oxidant gas downstream of the premixing area 25, between the internal surface 22 of the tubular body 2 and a centerbody 4 (the latter better defined below).
  • the centerbody 4 is arranged within the tubular body 2 and extends from one end of the tubular body 2 up to the premixing area 25. [0031] In some embodiments, the centerbody 4 can extend from 20% to 60% of the total length of the tubular body 2 (from the first end 23 of the tubular body 2), providing both structural support and better flow management within the fuel burner tube 1.
  • the centerbody 4 is indeed a channel, projecting and extending into the tubular body 2.
  • the centerbody 4 is tapered in the direction of the flow passing through it.
  • the centerbody 4 is designed to extend from the first end 23 of the tubular body 2 up to the premixing area 25, ensuring an optimized flow path for a purging flow to be mixed with the oxidant gas and fuel mixture.
  • the centerbody 4 is positioned coaxially within the tubular body 2 and is made of materials capable of withstanding high temperatures and corrosive environments typically encountered in gas turbine operations.
  • the centerbody 4 may include a smooth or contoured surface to facilitate streamlined airflow and minimize turbulence within the premixing area 25.
  • the centerbody 4 ensures a uniform and stable mixture of oxidant gas and fuel, for an efficient combustion and reduced emissions.
  • the centerbody 4 may comprise features to improve the thermal and acoustic performance of the fuel burner tube 1, as better explained below.
  • the main function of the centerbody 4 is that of stabilizing the airflow and support fuel injection. By optimizing the centerbody's 4 length, material, and internal features, the performance of the entire fuel burner tube 1 is improved, contributing to improved combustion efficiency and lower emissions of the gas turbine.
  • the fuel burner tube 1 has at least one fuel injection channel 5, connectable to a fuel injection system (not shown in the figure) for injecting a stream of fuel into the premixing area 25, and is positioned in correspondence with the premixing area 25.
  • the fuel burner tube 1 has a plurality of fuel injection channel 5.
  • the structure of the fuel burner tube 1 described herein, referred to as "tuber" is aimed at optimizing the mixing of air or any other oxidant gas and highly reactive fuel in the premixing section.
  • the centerbody 4 has multiple functions. Specifically, the centerbody 4 is configured with a central purge system that directs the central purging flow axially from the upstream radial holes 3. This forward direction of the central purging flow towards the premixing area 25 ensures that the oxidant gas is effectively channeled, improving the mixing process and stabilizing the combustion.
  • the premixing area 25 of the fuel burner tube 1 is designed, as mentioned, to handle highly reactive fuels efficiently. Fuel is injected into the premixing area 25 via jets in a crossflow configuration. This fuel injection system allows thorough mixing of the fuel with the incoming air or any other oxidant gas, ensuring a uniform and stable mixture.
  • the crossflow injection is particularly beneficial and for highly reactive fuels, as it facilitates rapid mixing and minimizes the risk of flame flashback and anchoring.
  • the burner incorporates a multiple pattern of lateral purging cavities 6 located downstream of each fuel injection channel 5. These purging cavities 6 are adapted to maintain the integrity of the premixing process. They provide additional lateral purging flow flows that create a barrier, preventing the flame from propagating back towards the fuel injection points and the premixing area 25.
  • This configuration helps to mitigate the risks associated with highly reactive fuels, such as, again, flashback and flame anchoring, thereby improving the overall safety and reliability of the fuel burner tube 1.
  • the oxidant gas is introduced into the tubular body 2 through the radially arranged holes 3, ensuring a steady flow downstream of the premixing area 25.
  • the centerbody 4 aids in directing and stabilizing this oxidant gas by the central purging flow.
  • Fuel is then injected through the fuel injection channels 5 into the premixing area 25, where it mixes with the incoming oxidant gas.
  • the specific inclination of the fuel injection channels 5 facilitates efficient mixing.
  • the premixed fuel and oxidant gas then proceed to the combustion zone at the second end 24 of the tubular body 2, where the flame is generated.
  • FIG. 2A and 2B a second embodiment of the fuel burner tube 1 is shown.
  • the fuel injection channels 5 is inclined at an angle a with respect to the external surface 21 of the tubular body 2.
  • the angle a ranges from 20° to 90° degrees with respect to the internal surface 22 of the tubular body 2, optimizing the mixing process, since the fuel enters the flow of the oxidant gas without interfering with it.
  • the fuel burner tube 1 also comprises at least one oxidant lateral purge cavity 6 with an outlet 61 on the internal surface of the tubular body 2.
  • the lateral purging flow from the lateral purge cavity 6 is arranged to direct a flow of oxidant gas within the tubular body 2, forming an air gap that prevents flame anchoring and flame flashback.
  • the outlet 61 of the lateral purging flow coming from the lateral purge cavity 6 is located in correspondence with the premixing area 25, in proximity to the outlets 52 of the fuel injection channels 5, and can be C-shaped to create a horseshoe oxidant gas turbulence, further preventing flame anchoring and flame flashback.
  • these outlets 61 of the lateral purge cavities 6 are designed to create a protective barrier around the fuel injection points.
  • the shape and positioning of the lateral purging cavities 6 ensure that the injected fuel is surrounded by the flow of the lateral purging flow, which serves to prevent the flame from propagating backward towards the premixing area 25, to mitigate the risk of flame flashback and anchoring, which, as mentioned, are common issues when dealing with highly reactive fuels.
  • outlets 61 of the lateral purging cavities 6 shown in the Fig. 2 A are “C- shaped” to generate a horseshoe-like turbulence by the lateral purging flow that improves the stability of the fuel -oxidant gas mixture and prevents the formation of hot spots that could lead to early ignition or flame instability.
  • This design not only improves the safety and reliability of the burner of the gas turbine, but also contributes to a more uniform and efficient combustion process, reducing emissions and enhancing the overall performance of the gas turbine.
  • each of the fuel injection channels 5 defines also a premixing chamber 51, where the stream of fuel is mixed with a stream of oxidant gas already before entering the combustion zone of the gas turbine (not shown).
  • This design ensures thorough mixing, enhancing combustion efficiency and reducing emissions.
  • the design includes a lateral purging cavities 6 positioned both upstream and downstream of each fuel injection channel 5. These lateral purging cavities 6 are located in close proximity to the fuel injection channels 5.
  • the upstream (with respect to the respective fuel injection channels 5) lateral purging cavities 6 help to pre-purge the premixing area 25 , creating a clean and controlled environment for the fuel injection, which prevents any pre-ignition or instability in the premixing section.
  • downstream lateral purging cavities 6 serve to provide the additional lateral purging flow immediately after the fuel injection.
  • This downstream purging flow acts as a barrier, preventing the flame from propagating back towards the fuel injection points and the premixing area 25, still mitigating the risks associated with flame flashback and anchoring, enhancing the overall safety and reliability of the burner.
  • the fuel burner tube 1 of the Fig. 4A has a lateral premixing chamber 51 designed for the injection of highly reactive fuel.
  • the premixing chamber 51 is an intermediate space where the initial mixing of fuel and air takes place before being introduced into the main premixing area 25.
  • the premixing chamber 51 ensures that the highly reactive fuel is thoroughly mixed with oxidant gas, creating a stable and homogenous mixture that enhances combustion efficiency and reduces the risk of flame flashback and anchoring.
  • the premixing chamber 51 is positioned to inject the mixture of oxydant gas and fuel radially into the premixing area 25.
  • This radial injection method allows a uniform distribution of the fuel-oxidant gas mixture across the entire cross-section of the premixing area 25, allowing a more uniform combustion process.
  • the radial orientation of the injection also helps in maintaining a stable flow pattern, which is crucial for efficient and complete combustion.
  • the premixing chamber 51 can be designed to protrude radially inward into the premixing area 25. This inward protrusion enhances the mixing dynamics by creating localized turbulence, which improves the interaction between the oxidant gas and fuel streams.
  • the premixing chamber 51 can be constructed from materials that resist high temperatures and corrosive environments, typical in gas turbine operations.
  • the lateral purging cavities 6 fully encircles the premixing chamber 51, providing a continuous flow of purging flow around the entire circumference of the premixing chamber 51.
  • This design creates a uniform barrier of fluid that helps prevent flame flashback and anchoring by ensuring that any residual combustion products are swept away from the premixing area 25.
  • the lateral purging cavity 6 can be designed to cover only a shorter path around the premixing chamber 51.
  • the lateral purging flow is directed at specific points where it is most needed to stabilize the fuel-oxidant gas mixture and prevent flame-related issues. This more “targeted” approach allows for more efficient use of the purging air and can be applied to address specific combustion problems associated with highly reactive fuels.
  • the premixing chamber 5 litself is designed to protrude radially inward (i.e., (toward the internal volume of the fuel burner tube 1) into the premixing area 25, creating localized turbulence that enhances the mixing of the oxidant gas and fuel.
  • This protrusion helps to break up any laminar flow patterns and ensures a more homogeneous mixture, which is beneficial for stable and efficient combustion.
  • the combination of the radially inward injection from the premixing chamber 51 and the surrounding lateral purging cavity 6 allows an optimal combustion of highly reactive fuels, reducing the risk of premature ignition and ensuring a more controlled combustion process.
  • Materials used in constructing the premixing chambers 51 and lateral purging cavities 6 are selected for their ability to withstand the high temperatures and corrosive conditions.
  • FIG. 6A and 6B a sixth embodiment of a fuel burner tube 1 is shown.
  • the fuel burner tube 1 additionally comprises an element 7, fluidically coupled to the first end 23 of the tubular body 2.
  • the element 7 has an air channel 71, passing through it, for injecting a stream of air through the centerbody 4 into the premixing area 25.
  • the air channel 71 of the element 7 is in fluidic connection with the channel of the centerbody 4 and allows the passage of the central purging flow.
  • the element 7 comprises a vertical wall 72 positioned at its base. To enhance the performance of the element 7, the vertical wall 72 has at least one holes 73 . These holes 73 allow the controlled passage of central purging flow into the element 7.
  • the holes 73 on the vertical wall 72 ensure that air can enter the element 7 in a regulated manner, contributing to the overall effectiveness of the damping system.
  • the center body 4 is coupled with the element 7 forming a passive damper is capable of dampening the pressure and/or acoustic pulsations of the flows passing through fuel burner tube 1.
  • the element 7 is then capable of dampening the pressure and/or acoustic pulsations of the stream of air, contributing to the stability and noise reduction of the burner operation.
  • the lateral purge cavities 6 continuously supplies a lateral purging flow, creating an air gap that acts as a barrier against flame anchoring and flashback.
  • the “C-shaped” outlets 61 of the lateral purge cavities 6 generate a horseshoe flow turbulence that enhances this protective effect.
  • the element 7 at the first end 23 of the tubular body 2 injects an additional stream of center purging flow through the centerbody 4 directly into the premixing area 25, while also dampening pressure and acoustic pulsations, stabilizing the operation of the burner.
  • the purging flows namely the central and the lateral purging flows can be made of air, oxygen (O2), a stream of carbon dioxide (CO2) and oxygen or a mixture comprising carbon dioxide (CO2).
  • the oxidant gas to be mixed with the fuel can be air or any other mixture comprising air.
  • FIG. 7 illustrates a burner 8 for a gas turbine (not shown) that comprises a bundle of fuel burner tube 1 arranged to form a complete burner assembly 81.
  • a frame 82 supports and keeps the burner assembly 81.
  • Each fuel burner tube 1 is equipped with radially oriented air through holes 3 located in the upstream part, facilitating the introduction of air into the burner 8.
  • the lateral purge cavities 6, as mentioned, work to prevent the flame from anchoring within the premixing region, while also mitigating the risk of flashback from the combustion chamber of the gas turbine.
  • the integrated passive acoustic dampers formed by the element 7 and the centerbody 4, reduce noise generation, ensuring a more stable operation.
  • This optimized premixing process improves combustion efficiency and reduces NO X emissions, making the burner suited for use with highly reactive gas fuels.
  • the disclosure introduces new purging concepts aimed at enhancing the stabil- ity and efficiency of the burner by creating purge and dilution zones near the fuel injection chambers 51.
  • the centerbody 4 is integrated with additional element 7 to form with the centerbody 4 a passive acoustic damper.
  • dampers are fluidly coupled with the premixing section and are designed to mitigate pressure pulsations that can occur during combustion.
  • the integration of these dampers within the fuel burner tube 1, formed by the element 7 and the centerbody 4, ensures that they effectively reduce the acoustic disturbances without interfering with the primary airflow and fuel injection processes.
  • the burner 1 may be applied, as mentioned, to the combustion chamber of a gas turbine (not shown in the figures).
  • the burner 1 is designed to efficiently mix fuel and oxidant gases to ensure complete combustion, thereby optimizing the energy output and reducing emissions.
  • the burner 1 may also be applied to the combustion chamber of an expander operating in an Allam-cycle plant (not shown in the figures)
  • the Allam cycle is a power cycle that aims to achieve high efficiency and nearzero emissions. It operates by combusting a fuel (typically natural gas) with an oxidant stream consisting of a variable mixture of oxygen and CO2, rather than air, and utilizes supercritical CO2 as a working fluid to drive a turbine.
  • the cycle integrates the capture of CO2 by producing it at high-pressure, making it particularly suitable for carbon capture and storage (CCS) applications. This process eliminates the need for the expensive CO2 separation equipment and significantly reduces the environmental impact compared to traditional power generation methods.
  • the Allam cycle represents a significant advancement in clean energy technology, combining high performance with reduced carbon emissions.
  • the oxidizer in the Allam cycle is oxygen, which is produced by an air-separation unit (ASU).
  • ASU is a component that separates oxygen from an air-stream, providing the pure oxygen required for the combustion process.
  • This pure oxygen is mixed with carbon oxide CO2 to generate a proper blend used as the oxidant, which is then mixed with fuel in the burner 1, resulting in a high-temperature and high- pressure exhaust gas, which can be expanded through a turbine to generate electricity.
  • the utilization of oxygen as the oxidant in the Allam cycle improves emission containment.
  • the internal surface 22 may be machined to reduce roughness. This reduction in roughness helps to counteract or diminish the boundary layer growth, which in turn reduces backfire.
  • the entire internal surface 22 may undergo machining to achieve this smoothness.
  • the machining may be localized, focusing only on the portion nearest to the second end 24 of the tubular body 2.
  • the fuel burner tubes 1 of the burner 8 include each a dilution slot 9, having a toroidal shape, arranged around the premixing area 25 at the outlet end.
  • the dilution slot 9 allows the formation of a protective air layer or sleeve along the inner surface of the premixing area 25.
  • each fuel burner tube 1, in the embodiment shown in Figures 8, 9, 10, 11, and 12, comprises a plurality of injection channels 10, arranged on the lateral surface of the tubular body 2 and opening into the premixing area 25.
  • the injection channels 10 comprise a fuel injection channel 101, substantially inclined with respect to the internal surface of the tubular body 2, and a protection channel 102, substantially circular, arranged around the fuel injection channel 101, through which air is injected.
  • This air injection serves to protect or sleeve the fuel injection channel 101. This effect allows the cleaning of the recirculation zone, where the flame could potentially anchor on the inner surface of the premixing area 25.
  • the geometry of the dilution slot 9 being toroidal in shape, allows for a more uniform and symmetrical distribution of the injected flows around the central axis.
  • the air injected acts as a diluent for the fuel -rich region adjacent to the wall, thereby forming a leaner fuel-air mixture near the surface.
  • This configuration contributes to a significant reduction in wall heat flux and helps in preventing local hot spots.
  • this design provides enhanced resistance to flashback phenomena, i.e., the upstream propagation of the flame into the premixing zone.
  • flashback phenomena i.e., the upstream propagation of the flame into the premixing zone.
  • the configuration also imply a purge mechanism, which is optimized to reduce the amount of purging required at the wall. This is achieved by effectively managing the local fuel concentration: the air injection ensures that less combustible material accumulates near the surface, minimizing the need for active purging. The result is a reduced purge flow that still achieves the desired effects of dilution and thermal protection.
  • this solution provides multiple technical advantages, including improved flame stability, reduced risk of flashback, and enhanced thermal management near the wall, all of which contribute to a more efficient and reliable combustion system.
  • An advantage of the present invention is that it avoids or limits the possibility of flame anchoring inside the premixing region. This is achieved through innovative purging system combined with an improved fuel injection that ensure a stable and controlled combustion process.
  • Another advantage of the present invention is that it avoids or limits the possibility of the flame propagating back from the combustion chamber toward the premixing region. This enhances overall safety and reliability by mitigating the risk of flame flashback.

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

Abstract

L'invention concerne un tube de brûleur à combustible (1) pour un brûleur de chambre de combustion, qui comprend un corps tubulaire (2) s'étendant le long d'un axe longitudinal ayant des surfaces externe (21) et interne (22). Le corps tubulaire (2) possède une zone de prémélange (25) au sein de la surface interne (22) où un gaz oxydant est prémélangé avec un combustible. Un ou plusieurs trous traversants (3) radialement agencés sur la surface interne (22) injectent un courant de purge latéral en aval vers la zone de prémélange (25). Un corps central (4) au sein du corps tubulaire (2) s'étend d'une première extrémité (23) à la zone de prémélange (25), ce qui permet l'introduction d'un courant de purge central. Au moins un canal d'injection de combustible (5), apte à être raccordé à un système d'injection de combustible, est positionné en aval du corps central (4) sur la surface interne (22) en correspondance avec la zone de prémélange (25) pour injecter un combustible dans la zone de prémélange (25).
PCT/EP2025/064979 2024-08-02 2025-05-30 Tube de brûleur à combustible pour un brûleur pour combustibles gazeux hautement réactifs Pending WO2026027101A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
IT102024000018133 2024-08-02
IT202400018133 2024-08-02
IT202500011191 2025-05-19
IT102025000011191 2025-05-19

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WO2026027101A1 true WO2026027101A1 (fr) 2026-02-05

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Citations (10)

* Cited by examiner, † Cited by third party
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US4969815A (en) * 1985-04-26 1990-11-13 Nippon Kokan Kabushiki Kaisha Burner
US6370879B1 (en) * 1998-11-10 2002-04-16 Alstom Damping device for reducing the vibration amplitude of acoustic waves for a burner
US20070259296A1 (en) * 2004-12-23 2007-11-08 Knoepfel Hans P Premix Burner With Mixing Section
EP2244014A2 (fr) * 2009-04-23 2010-10-27 General Electric Company Brûleur à injection directe stratifié radial
US20100323309A1 (en) * 2008-01-11 2010-12-23 David Barkowski Burner and Method for Reducing Self-Induced Flame Oscillations
US10208958B2 (en) 2009-09-17 2019-02-19 Ansaldo Energia Switzerland AG Method and gas turbine combustion system for safely mixing H2-rich fuels with air
US20200191386A1 (en) * 2018-12-15 2020-06-18 Harper Biotech Llc D/B/A Simbuka Energy, Llc Method for co-production of hyper-efficient electric power and a methane sidestream from high co2 natural gas sources with optional integrated lng production and power storage
EP4056902A1 (fr) * 2021-03-11 2022-09-14 General Electric Company Mélangeur de carburant
EP4202308A1 (fr) * 2021-12-21 2023-06-28 Ansaldo Energia Switzerland AG Brûleur de prémélange pour un ensemble de turbine à gaz de centrale électrique adapté pour être alimenté avec des combustibles communs et très réactifs, son procédé de fonctionnement et ensemble de turbine à gaz de centrale électrique comprenant ce brûleur
US20240183537A1 (en) * 2022-12-02 2024-06-06 Toyota Jidosha Kabushiki Kaisha Combustion nozzle and combustor

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4969815A (en) * 1985-04-26 1990-11-13 Nippon Kokan Kabushiki Kaisha Burner
US6370879B1 (en) * 1998-11-10 2002-04-16 Alstom Damping device for reducing the vibration amplitude of acoustic waves for a burner
US20070259296A1 (en) * 2004-12-23 2007-11-08 Knoepfel Hans P Premix Burner With Mixing Section
US20100323309A1 (en) * 2008-01-11 2010-12-23 David Barkowski Burner and Method for Reducing Self-Induced Flame Oscillations
EP2244014A2 (fr) * 2009-04-23 2010-10-27 General Electric Company Brûleur à injection directe stratifié radial
US10208958B2 (en) 2009-09-17 2019-02-19 Ansaldo Energia Switzerland AG Method and gas turbine combustion system for safely mixing H2-rich fuels with air
US20200191386A1 (en) * 2018-12-15 2020-06-18 Harper Biotech Llc D/B/A Simbuka Energy, Llc Method for co-production of hyper-efficient electric power and a methane sidestream from high co2 natural gas sources with optional integrated lng production and power storage
EP4056902A1 (fr) * 2021-03-11 2022-09-14 General Electric Company Mélangeur de carburant
EP4202308A1 (fr) * 2021-12-21 2023-06-28 Ansaldo Energia Switzerland AG Brûleur de prémélange pour un ensemble de turbine à gaz de centrale électrique adapté pour être alimenté avec des combustibles communs et très réactifs, son procédé de fonctionnement et ensemble de turbine à gaz de centrale électrique comprenant ce brûleur
US20240183537A1 (en) * 2022-12-02 2024-06-06 Toyota Jidosha Kabushiki Kaisha Combustion nozzle and combustor

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