EP3821174B1 - Gas turbine burner with pilot fuel-air mixing - Google Patents
Gas turbine burner with pilot fuel-air mixing Download PDFInfo
- Publication number
- EP3821174B1 EP3821174B1 EP19769056.3A EP19769056A EP3821174B1 EP 3821174 B1 EP3821174 B1 EP 3821174B1 EP 19769056 A EP19769056 A EP 19769056A EP 3821174 B1 EP3821174 B1 EP 3821174B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- pilot
- burner
- mixing
- fuel
- mixing tube
- 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.)
- Active
Links
- 238000002156 mixing Methods 0.000 title claims description 98
- 239000000446 fuel Substances 0.000 claims description 42
- 238000002485 combustion reaction Methods 0.000 claims description 17
- 238000011144 upstream manufacturing Methods 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 9
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 230000006641 stabilisation Effects 0.000 description 4
- 238000011105 stabilization Methods 0.000 description 4
- 238000009792 diffusion process Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
Images
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
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
- F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
- F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
- F23D11/103—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
- F23D11/402—Mixing chambers downstream of the nozzle
-
- 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
- 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
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
-
- 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
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2203/00—Gaseous fuel burners
- F23D2203/007—Mixing tubes, air supply regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing
-
- 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
- F23R2900/03343—Pilot burners operating in premixed mode
Definitions
- the invention relates to a burner according to the features of the preamble of claim 1.
- Such burners are preferably used for firing the combustion chamber of a gas turbine.
- Such burners are known from EP 1 389 713 B1 and comprise a swirl generator and a downstream mixing tube.
- the burner head is provided with a pilot burner system to support the main flame.
- the pilot burner system comprises a mixing cavity for mixing pilot fuel and assist air.
- the mixing cavity of the known burner is of a pure circumferential shape. Since such a design bears the risk for the pilot flame to burn inside the mixing cavity
- EP 2 268 975 B1 proposes a solution with swirler wings being arranged in the vicinity of the pilot fuel/air mix outlet nozzles. A further example with such a solution is shown in EP 3290804 A1 , on which the two-part-form of claim 1 is based.
- pilot flame is an external air assisted diffusion like flame that has inherent flame stability but can also create high NO x emission due to this diffusion mode combustion.
- combustor dump locations contribute to flame stabilization as will be shown in Figure 3 .
- the object of the present invention is to improve a burner of the above type in such a way that NO x emission is reduced.
- the present invention solves the above problem by providing a burner with a burner head comprising a main mixing tube for premixing combustion air and fuel, wherein the main mixing tube is provided with a pilot burner system in its downstream part, wherein the pilot burner system comprises an annular mixing cavity with an entrance for air in its upstream end, with an entrance for pilot fuel and with an outlet nozzle in its downstream end, wherein a pilot mixing tube extends inside the mixing cavity between the entrance for air and the outlet nozzle with a pilot mixing tube length exceeding a distance between the upstream and the downstream ends of the mixing cavity.
- the non-premixed behavior of the pilot flame is one of the major sources of NO x .
- the extended mixing path inside the mixing cavity of the inventive burner improves fuel and air mixing and reduces the formation of NO x . Further premixing of the pilot stage is possible when the pilot flame has an additional flame stabilization point.
- the present invention is intended to increase the pilot fuel mixing and inherently to reduce the NO x without affecting the flame stability.
- the mixing cavity comprises a conical front surface facing away from the burner axis and the outlet nozzle is arranged in that conical front surface with an injection angle perpendicular to the front surface.
- a cooling channel is arranged in at least a part of a radially outer wall and the downstream end of the mixing cavity.
- Yet another preferred embodiment of the present invention is characterized in that the cooling channel opens out at the conical front surface at an inner position compared to the outlet nozzle as seen in a radial direction of the burner.
- the cooling channel begins at an upstream part of the mixing cavity.
- pilot mixing tube is a spiral tubing arrangement.
- the pilot mixing tube comprises secondary tubes that merge before opening out into the outlet nozzle.
- the pilot mixing tube comprises steps.
- pilot mixing tube is fully integrated with the mixing cavity, especially when the pilot burner system is additively manufactured.
- the present invention additionally relates to an annular combustion chamber of a gas turbine, which is characterized in that at least two, preferably at least 10 burners as described above are arranged within the combustion chamber.
- the mixing of fuel and air can be improved by introducing additively manufactured pilot fueling arrangement with additional mixing length.
- mixing at the pilot burner stage exit can be controlled more efficiently.
- the overall fuel-air mixing is improved.
- the enhanced mixing can produce lower NO x emission without affecting the combustion stability.
- a variable mixing length is possible for different fuels. Variable location fuel injection possibility can widen the fuel flexibility of the pilot stage combustion.
- Figure 1 shows a pilot fuel-air mixing arrangement in prior art design according to EP 2 268 975 B1 .
- Pilot fuel 19 is provided through a gas channel 16.
- the gas channel 16 emerges into a mixing cavity 17.
- Assist air 20 for burning the pilot fuel 19 is led into the mixing cavity 17 through air channels (not shown) and is deflected by swirler vanes 18.
- fuel and air mixing is mainly due to a tangential interaction of fuel and air streams. Due to a relatively short mixing length, the mixing is limited, and a center rich pilot jet is directed toward the combustion chamber.
- Figure 2 shows a burner arrangement in an annular combustion chamber 15 with pilot injection holes 21 arranged in a conical front surface 9 of a downstream part of the respective burner 1.
- Figure 3 shows a pilot flame stabilization process due to dump plane in a double cone burner 1.
- Fuel and air enter the main mixing tube 2 through tangential slots 22 of a swirler prior entering the combustion chamber 15. Due to the broadening a main recirculation zone 23 of the main flame 26 forms with a forward stagnation point 24 at the entry level of the combustion chamber 15. Pilot fuel 19 and air are added to the combustion chamber 15 radially outwardly with respect to the main air and fuel, the pilot fuel 19 and air forming external recirculation zones 25 with opposite direction of rotation compared to the main recirculation zone 23.
- Figure 4 shows a cut through of a prior art double cone burner 1 with a burner head comprising a main mixing tube 2 for premixing combustion air and fuel, wherein the main mixing tube 2 is provided with a pilot burner system 3 in its downstream part.
- the pilot burner system 3 is highlighted by a rectangular box and shows the prior art design that has already been presented in Figure 1 .
- the relatively small partially premixed pilot arrangement of the prior art can be replaced with a cavity filled with fuel and tube arrangements according to the invention.
- pilot burner system 3 comprising an annular mixing cavity 4 with an entrance 5 for air in its upstream end, with an entrance 6 for pilot fuel and with an outlet nozzle 7 in its downstream end.
- a pilot mixing tube 8 extends inside the mixing cavity 4 between the entrance 5 for air and the outlet nozzle 7.
- the pilot mixing tube 8 length exceeds a distance between the upstream and the downstream ends of the mixing cavity 4 which is achieved by a meandering pilot mixing tube 8.
- the pilot mixing tube 8 is fully integrated with the mixing cavity 4 and given the geometry is suitable for being additively manufactured.
- the mixing cavity 4 comprises a conical front surface 9 facing away from the burner axis 10 (see figure 3 ).
- the outlet nozzle 7 is arranged in that conical front surface 9 with an injection angle perpendicular to the front surface 9.
- pilot fuel 19 is provided through a channel 27 arranged in the wall of the main mixing tube 2 which is also the radially inner wall of the mixing cavity 4 and enters the mixing cavity 4 at its downstream part where it travels in the opposite direction and enters the pilot mixing tube 8 in its upstream part so that the pilot mixing tube 8 carries the air and the fuel.
- the fuel supply is indicated by lines and arrows in figure 5 .
- the fuel injection holes at the entrance 11 for pilot fuel of the pilot mixing tube 8 can be of different cross section like oval/triangular or circular to get the penetration. Additionally, swirl can also be introduced in the fuel holes if required.
- Figure 6 shows a cut through an alternative embodiment of the annular mixing cavity 4 for supplying fuel and air in the pilot burner system 3 with more safety features or film air to protect the metal.
- Figure 6 shows a cooling channel 12 arranged in at least a part of a radially outer wall 13 and the downstream end of the mixing cavity 4 for a small stream of air.
- the cooling channel 12 opens out at the conical front surface 9 at an inner position compared to the outlet nozzle 7 as seen in a radial direction of the burner 1.
- the cooling channel 12 begins at an upstream part of the mixing cavity 4. Further, the front surface 9 is cooled by the fuel which is then introduced inside the mixing cavity 4 for mixing.
- Figure 7 shows the pilot mixing tube 8 realized as a spiral tubing arrangement inside the mixing cavity 4.
- Figure 8 shows a multiple pilot tube arrangement where the pilot mixing tubes 8 comprise steps.
- the step type tubing can be in X-Y or X-Z plane.
- the X-Z plane which is parallel to the burner outer surface, opens many possibilities to place the pilot mixing tube bundles.
- Figure 9 shows a pilot fuel arrangement where secondary tubes 14 combine inside the mixing cavity 4 before opening out into the outlet nozzle 7.
- pilot mixing tube 8 arrangements can be incorporated based on design requirements.
- the location of the entrance for pilot fuel of the mixing cavity 4 can be varied to achieve a specific degree of mixing of fuel and air.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Description
- The invention relates to a burner according to the features of the preamble of claim 1.
- Such burners are preferably used for firing the combustion chamber of a gas turbine. Such burners are known from
EP 1 389 713 B1 and comprise a swirl generator and a downstream mixing tube. The burner head is provided with a pilot burner system to support the main flame. The pilot burner system comprises a mixing cavity for mixing pilot fuel and assist air. The mixing cavity of the known burner is of a pure circumferential shape. Since such a design bears the risk for the pilot flame to burn inside the mixingcavity EP 2 268 975 B1 proposes a solution with swirler wings being arranged in the vicinity of the pilot fuel/air mix outlet nozzles. A further example with such a solution is shown inEP 3290804 A1 , on which the two-part-form of claim 1 is based. The mixing of fuel and air is mainly due to the tangential interaction of fuel and air streams. But still the pilot fuel-air mixing is limited, and fuel rich pockets are directed towards the combustion chamber. Therefore, the pilot flame is an external air assisted diffusion like flame that has inherent flame stability but can also create high NOx emission due to this diffusion mode combustion. - Further, the combustor dump locations contribute to flame stabilization as will be shown in
Figure 3 . - The object of the present invention is to improve a burner of the above type in such a way that NOx emission is reduced.
- The present invention solves the above problem by providing a burner with a burner head comprising a main mixing tube for premixing combustion air and fuel, wherein the main mixing tube is provided with a pilot burner system in its downstream part, wherein the pilot burner system comprises an annular mixing cavity with an entrance for air in its upstream end, with an entrance for pilot fuel and with an outlet nozzle in its downstream end, wherein a pilot mixing tube extends inside the mixing cavity between the entrance for air and the outlet nozzle with a pilot mixing tube length exceeding a distance between the upstream and the downstream ends of the mixing cavity.
- The non-premixed behavior of the pilot flame is one of the major sources of NOx. The extended mixing path inside the mixing cavity of the inventive burner improves fuel and air mixing and reduces the formation of NOx. Further premixing of the pilot stage is possible when the pilot flame has an additional flame stabilization point. The present invention is intended to increase the pilot fuel mixing and inherently to reduce the NOx without affecting the flame stability.
- According to a preferred embodiment of the invention the mixing cavity comprises a conical front surface facing away from the burner axis and the outlet nozzle is arranged in that conical front surface with an injection angle perpendicular to the front surface.
- It is particularly advantageous when the entrance for pilot fuel of the mixing cavity is in its downstream part and the entrance for pilot fuel of the pilot mixing tube is in its upstream part.
- According to a preferred embodiment, a cooling channel is arranged in at least a part of a radially outer wall and the downstream end of the mixing cavity.
- Yet another preferred embodiment of the present invention is characterized in that the cooling channel opens out at the conical front surface at an inner position compared to the outlet nozzle as seen in a radial direction of the burner.
- According to another preferred embodiment of the invention, the cooling channel begins at an upstream part of the mixing cavity.
- According to a further embodiment of the invention the pilot mixing tube is a spiral tubing arrangement.
- Alternatively, the pilot mixing tube comprises secondary tubes that merge before opening out into the outlet nozzle.
- In another alternative embodiment, the pilot mixing tube comprises steps.
- It is advantageous, when the pilot mixing tube is fully integrated with the mixing cavity, especially when the pilot burner system is additively manufactured.
- The present invention additionally relates to an annular combustion chamber of a gas turbine, which is characterized in that at least two, preferably at least 10 burners as described above are arranged within the combustion chamber.
- To sum up, the mixing of fuel and air can be improved by introducing additively manufactured pilot fueling arrangement with additional mixing length. With the invention mixing at the pilot burner stage exit can be controlled more efficiently. The overall fuel-air mixing is improved. The enhanced mixing can produce lower NOx emission without affecting the combustion stability. A variable mixing length is possible for different fuels. Variable location fuel injection possibility can widen the fuel flexibility of the pilot stage combustion.
- Embodiments of the invention are now described, by way of example only, with reference to the accompanying drawings, of which:
- Figure 1
- shows a pilot fuel-air mixing arrangement in prior art design;
- Figure 2
- shows a burner arrangement with pilot injection holes;
- Figure 3
- shows a pilot flame stabilization process due to dump plane;
- Figure 4
- shows a cut through of a double cone burner with mixing tube in prior art design indicating the position of the pilot burner system in its downstream part highlighted by the rectangular box;
- Figure 5
- shows a cut through a simplified sketch of the annular mixing cavity according to the invention;
- Figure 6
- shows a cut through an alternative embodiment of the annular mixing cavity with more safety features or film air to protect the metal;
- Figure 7
- shows a spiral tubing arrangement possible inside the mixing cavity;
- Figure 8
- shows a multiple pilot tube arrangement and
- Figure 9
- shows a pilot fuel arrangement where secondary tubes combine inside the mixing cavity.
- The illustration in the drawings is in schematic form. It is noted that in different figures, similar or identical elements may be provided with the same reference signs.
-
Figure 1 shows a pilot fuel-air mixing arrangement in prior art design according toEP 2 268 975 B1Pilot fuel 19 is provided through agas channel 16. Thegas channel 16 emerges into amixing cavity 17. Assistair 20 for burning thepilot fuel 19 is led into themixing cavity 17 through air channels (not shown) and is deflected byswirler vanes 18. As can be seen fuel and air mixing is mainly due to a tangential interaction of fuel and air streams. Due to a relatively short mixing length, the mixing is limited, and a center rich pilot jet is directed toward the combustion chamber. -
Figure 2 shows a burner arrangement in anannular combustion chamber 15 with pilot injection holes 21 arranged in a conical front surface 9 of a downstream part of the respective burner 1. -
Figure 3 shows a pilot flame stabilization process due to dump plane in a double cone burner 1. Fuel and air enter themain mixing tube 2 throughtangential slots 22 of a swirler prior entering thecombustion chamber 15. Due to the broadening amain recirculation zone 23 of themain flame 26 forms with aforward stagnation point 24 at the entry level of thecombustion chamber 15.Pilot fuel 19 and air are added to thecombustion chamber 15 radially outwardly with respect to the main air and fuel, thepilot fuel 19 and air formingexternal recirculation zones 25 with opposite direction of rotation compared to themain recirculation zone 23. -
Figure 4 shows a cut through of a prior art double cone burner 1 with a burner head comprising amain mixing tube 2 for premixing combustion air and fuel, wherein themain mixing tube 2 is provided with apilot burner system 3 in its downstream part. Thepilot burner system 3 is highlighted by a rectangular box and shows the prior art design that has already been presented inFigure 1 . - The relatively small partially premixed pilot arrangement of the prior art can be replaced with a cavity filled with fuel and tube arrangements according to the invention.
- The invention is explained in
Figure 5 showing a cut through a simplified sketch of the mixingcavity 4 of thepilot burner system 3, thepilot burner system 3 comprising anannular mixing cavity 4 with an entrance 5 for air in its upstream end, with anentrance 6 for pilot fuel and with anoutlet nozzle 7 in its downstream end. Apilot mixing tube 8 extends inside the mixingcavity 4 between the entrance 5 for air and theoutlet nozzle 7. Thepilot mixing tube 8 length exceeds a distance between the upstream and the downstream ends of the mixingcavity 4 which is achieved by a meanderingpilot mixing tube 8. Further, thepilot mixing tube 8 is fully integrated with the mixingcavity 4 and given the geometry is suitable for being additively manufactured. - The mixing
cavity 4 comprises a conical front surface 9 facing away from the burner axis 10 (seefigure 3 ). Theoutlet nozzle 7 is arranged in that conical front surface 9 with an injection angle perpendicular to the front surface 9. - Under operating
conditions pilot fuel 19 is provided through achannel 27 arranged in the wall of themain mixing tube 2 which is also the radially inner wall of the mixingcavity 4 and enters the mixingcavity 4 at its downstream part where it travels in the opposite direction and enters thepilot mixing tube 8 in its upstream part so that thepilot mixing tube 8 carries the air and the fuel. The fuel supply is indicated by lines and arrows infigure 5 . The fuel injection holes at theentrance 11 for pilot fuel of thepilot mixing tube 8 can be of different cross section like oval/triangular or circular to get the penetration. Additionally, swirl can also be introduced in the fuel holes if required. -
Figure 6 shows a cut through an alternative embodiment of theannular mixing cavity 4 for supplying fuel and air in thepilot burner system 3 with more safety features or film air to protect the metal.Figure 6 shows a coolingchannel 12 arranged in at least a part of a radiallyouter wall 13 and the downstream end of the mixingcavity 4 for a small stream of air. The coolingchannel 12 opens out at the conical front surface 9 at an inner position compared to theoutlet nozzle 7 as seen in a radial direction of the burner 1. The coolingchannel 12 begins at an upstream part of the mixingcavity 4. Further, the front surface 9 is cooled by the fuel which is then introduced inside the mixingcavity 4 for mixing. - Different tubing arrangements for increasing the fuel-air mixing are possible inside the mixing
cavity 4.Figure 7 shows thepilot mixing tube 8 realized as a spiral tubing arrangement inside the mixingcavity 4. -
Figure 8 shows a multiple pilot tube arrangement where thepilot mixing tubes 8 comprise steps. The step type tubing can be in X-Y or X-Z plane. The X-Z plane, which is parallel to the burner outer surface, opens many possibilities to place the pilot mixing tube bundles. -
Figure 9 shows a pilot fuel arrangement wheresecondary tubes 14 combine inside the mixingcavity 4 before opening out into theoutlet nozzle 7. - From the examples shown in
Figures 7 to 9 it becomes clear that single or multiplepilot mixing tube 8 arrangements can be incorporated based on design requirements. The location of the entrance for pilot fuel of the mixingcavity 4 can be varied to achieve a specific degree of mixing of fuel and air. - Although the present invention has been described in detail with reference to the preferred embodiment, it is to be understood that the present invention is not limited by the disclosed examples, and that numerous additional modifications and variations could be made thereto by a person skilled in the art without departing from the scope of the invention as defined in the appended claims.
Claims (12)
- A burner (1) with a burner head comprising a main mixing tube (2) for premixing combustion air and fuel, wherein the main mixing tube (2) is provided with a pilot burner system (3) in its downstream part, wherein the pilot burner system (3) comprises an annular mixing cavity (4) with an entrance (5) for air in its upstream end, with an entrance (6) for pilot fuel and with an outlet nozzle (7) in its downstream end, characterized in that a pilot mixing tube (8) extends inside the mixing cavity (4) between the entrance (5) for air and the outlet nozzle (7) with a pilot mixing tube (8) length exceeding a distance between the upstream and the downstream ends of the mixing cavity (4) .
- The burner (1) according to claim 1, wherein the mixing cavity (4) comprises a conical front surface (9) facing away from a burner axis (10) and wherein the outlet nozzle (7) is arranged in that conical front surface (9) with an injection angle perpendicular to the front surface (9).
- The burner (1) according to claim 1 or claim 2, wherein the entrance (6) for pilot fuel of the mixing cavity (4) is in its downstream part and a entrance (11) for pilot fuel of the pilot mixing tube (8) is in its upstream part.
- The burner (1) according to claims 1 to 3, wherein a cooling channel (12) is arranged in at least a part of a radially outer wall (13) and the downstream end of the mixing cavity (4).
- The burner (1) according to claim 4, wherein the cooling channel (12) opens out at the conical front surface (9) at an inner position compared to the outlet nozzle (7) as seen in a radial direction of the burner (1).
- The burner (1) according to claims 4 or 5, wherein the cooling channel (12) begins at an upstream part of the mixing cavity (4).
- The burner (1) according to one of the preceding claims, wherein the pilot mixing tube (8) is a spiral tubing arrangement.
- The burner (1) according to one of claims 1 to 6, wherein the pilot mixing tube (8) comprises secondary tubes (14) that merge before opening out into the outlet nozzle (7).
- The burner (1) according to one of claims 1 to 6, wherein the pilot mixing tube (8) comprises steps.
- The burner (1) according to one of the preceding claims, wherein the pilot mixing tube (8) is fully integrated with the mixing cavity (4).
- The burner (1) according to one of the preceding claims, wherein the pilot burner system (3) is additively manufactured.
- Annular combustion chamber (15) of a gas turbine, characterized in that at least two, preferably at least 10 burners (1) according to the preceding claims are arranged within the combustion chamber (15).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18193084.3A EP3620718A1 (en) | 2018-09-07 | 2018-09-07 | Gas turbine burner with pilot fuel-air mixing |
PCT/EP2019/073185 WO2020048880A1 (en) | 2018-09-07 | 2019-08-30 | Gas turbine burner with pilot fuel-air mixing |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3821174A1 EP3821174A1 (en) | 2021-05-19 |
EP3821174B1 true EP3821174B1 (en) | 2023-08-23 |
Family
ID=63528543
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18193084.3A Withdrawn EP3620718A1 (en) | 2018-09-07 | 2018-09-07 | Gas turbine burner with pilot fuel-air mixing |
EP19769056.3A Active EP3821174B1 (en) | 2018-09-07 | 2019-08-30 | Gas turbine burner with pilot fuel-air mixing |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18193084.3A Withdrawn EP3620718A1 (en) | 2018-09-07 | 2018-09-07 | Gas turbine burner with pilot fuel-air mixing |
Country Status (2)
Country | Link |
---|---|
EP (2) | EP3620718A1 (en) |
WO (1) | WO2020048880A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113440978A (en) * | 2021-07-08 | 2021-09-28 | 山东红石环保科技有限公司 | Industrial waste gas treatment device and method |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1389713A1 (en) | 2002-08-12 | 2004-02-18 | ALSTOM (Switzerland) Ltd | Premixed exit ring pilot burner |
EP2110601A1 (en) | 2008-04-15 | 2009-10-21 | Siemens Aktiengesellschaft | Burner |
EP3290804A1 (en) * | 2016-08-31 | 2018-03-07 | Siemens Aktiengesellschaft | A burner with fuel and air supply incorporated in a wall of the burner |
-
2018
- 2018-09-07 EP EP18193084.3A patent/EP3620718A1/en not_active Withdrawn
-
2019
- 2019-08-30 WO PCT/EP2019/073185 patent/WO2020048880A1/en unknown
- 2019-08-30 EP EP19769056.3A patent/EP3821174B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
EP3821174A1 (en) | 2021-05-19 |
EP3620718A1 (en) | 2020-03-11 |
WO2020048880A1 (en) | 2020-03-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4271674A (en) | Premix combustor assembly | |
EP2496880B1 (en) | Reheat burner injection system | |
EP1278013B1 (en) | Pilot burner, premixing combustor, and gas turbine | |
US8910481B2 (en) | Advanced quench pattern combustor | |
US8057224B2 (en) | Premix burner with mixing section | |
US8555646B2 (en) | Annular fuel and air co-flow premixer | |
EP2496885B1 (en) | Burner with a cooling system allowing an increased gas turbine efficiency | |
US10072846B2 (en) | Trapped vortex cavity staging in a combustor | |
CN1263983C (en) | Burner for synthesis gas | |
EP0728989B1 (en) | Gas turbine engine combustor | |
EP2436979A1 (en) | Burner for a gas turbine | |
CN107270328B (en) | Closed trapped vortex cavity pilot for gas turbine engine amplifier | |
KR101774630B1 (en) | Tangential annular combustor with premixed fuel and air for use on gas turbine engines | |
WO2009084587A1 (en) | Combustor of gas turbine | |
CN109642730B (en) | Burner with combined fuel and air supply in the wall of the burner | |
KR102165972B1 (en) | Burner assembly, combustor, and gas turbine | |
EP3220055A1 (en) | Axially staged fuel injector assembly | |
EP3472518B1 (en) | Fuel oil axial stage combustion for improved turbine combustor performance | |
EP3821174B1 (en) | Gas turbine burner with pilot fuel-air mixing | |
EP3438539B1 (en) | Gas turbine combustor | |
EP3403028B1 (en) | Combustor for a gas turbine | |
EP3465009B1 (en) | Fuel nozzle for a gas turbine with radial swirler and axial swirler and gas turbine | |
JP2016023916A (en) | Gas turbine combustor | |
WO2023140180A1 (en) | Combustor and gas turbine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: UNKNOWN |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20210212 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20230323 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602019035663 Country of ref document: DE |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 20230902 Year of fee payment: 5 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230828 Year of fee payment: 5 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20230823 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1602993 Country of ref document: AT Kind code of ref document: T Effective date: 20230823 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231124 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231223 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231226 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231123 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231223 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231124 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20230830 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20230830 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20230831 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20230823 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |