EP3637000A1 - Brûleur de turbine à gaz pour carburants réactifs - Google Patents
Brûleur de turbine à gaz pour carburants réactifs Download PDFInfo
- Publication number
- EP3637000A1 EP3637000A1 EP18199840.2A EP18199840A EP3637000A1 EP 3637000 A1 EP3637000 A1 EP 3637000A1 EP 18199840 A EP18199840 A EP 18199840A EP 3637000 A1 EP3637000 A1 EP 3637000A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- jet pipes
- fuel
- premix jet
- premix
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 68
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 23
- 238000005452 bending Methods 0.000 claims abstract description 9
- 238000002485 combustion reaction Methods 0.000 description 12
- 239000007789 gas Substances 0.000 description 12
- 206010016754 Flashback Diseases 0.000 description 5
- 239000001257 hydrogen Substances 0.000 description 5
- 229910052739 hydrogen Inorganic materials 0.000 description 5
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 4
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007800 oxidant agent Substances 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
-
- 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
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
Definitions
- the present invention relates to a gas turbine burner for reactive fuels, in particular for annular combustors.
- a working fluid like air
- a compressor section where combustion of a mixture of the working fluid and a fuel occurs.
- the resulting combustion gas drives a turbine through the expansion and deflection of the gas through the turbine of the gas turbine engine.
- the turbine work or a part thereof is transferred to the compressor through an interconnecting shaft.
- the compressor discharge temperature in modern gas turbine engines may be well above 420°C.
- the gas turbine engine is operated with highly reactive fuels, like hydrogen, auto-ignition of a hydrogen/air mixture may occur with these temperatures. Since the burner is situated after the compressor it may have surface temperatures like the temperature of the compressor discharge. Thus, a risk for flashbacks may be disadvantageously enhanced.
- the oxidizer e.g. air
- the oxidizer e.g. air
- the flame speed is limited by the rate of diffusion with relatively high emissions.
- Premix combustion is a combustion process intended to be used for low exhaust pollution. Fuel and air are mixed before entering a combustion chamber. As an example, fuel is introduced by a jet in crossflow arrangement where the fuel is injected perpendicular to the airstream passing through the burner. Unfortunately, near these fuel jets there are always low speed zones, where the fuel concentration is sufficiently high to be ignited by the hot burner geometry. Consequently, it is currently avoided to use highly reactive fuels in this kind of combustion system.
- the present invention provides a burner for a gas turbine with a supply zone for supplying fuel and air and a subsequent mixing zone for premixing fuel and air, the mixing zone having an upstream end and a downstream end and comprising a plurality of premix jet pipes for mixing air and fuel, each with an inlet and an outlet, arranged around a central burner axis and extending between the upstream end and the downstream end, wherein closer to the upstream end the premix jet pipes are straight and parallel to each other and wherein closer to the downstream end the premix jet pipes are bent away from the central burner axis wherein a bending of the premix jet pipes increases with the distance between premix jet pipe and central burner axis, wherein a diameter of the premix jet pipes is between 0.5 mm and 10 mm.
- the multiple premix jet pipes premixing main fuel with air offer an opportunity to operate with up to 100% hydrogen in the fuel. This is enabled by the fact that the relatively small diameter of the tubes prevents the flame to protrude upstream into the burner, so called flashback. The risk for flashback is also reduced by the fact that there is low or no swirl in the tubes.
- the stability of the combustion system is maintained by outer recirculation zones created by the plug flow created by the bundle of the premixed jets combined with sudden expansion outside the burner.
- the bending of the premix jet pipes is not limited to the radial direction but also has a tangential component, thereby creating a collective gross swirl of the exiting flow, if needed.
- Preferably inlets of premix jet pipes at the upstream end of the mixing zone are connected to an air plenum.
- air can be supplied to all premix jet pipes commonly avoiding the need to connect individually to a relatively large number of premix jet pipes. Further, the air flow is balanced, and assembly is easy.
- downstream end of the burner is formed by a convex end cover with evenly distributed openings, wherein premix jet pipe outlets are aligned with the openings of the end cover.
- the plurality of premix jet pipes is surrounded by a shell extending between the air plenum and the end cover such that a space is formed in which the premix jet pipes extend, the space being closed at the downstream end and having an annular gap at its upstream end between the shell and the air plenum. Fuel fed through this gap to this space is equally distributed therein and enters the premix jet pipes through lateral openings arranged in the premix jet pipes. Under operating conditions, the premix jet pipes are surrounded by main fuel, cooling the burner body and tip.
- the burner comprises a pilot fuel cavity arranged in the shell and extending in circumferential direction and from which pilot fuel channels branch off and extend parallel to the premix jet pipes in the direction to the downstream end.
- the stability and the start-up ability of the burner are further enhanced by the outer pilot adding pilot fuel in the outer recirculation zones.
- the burner comprises a fuel stem with hollow struts connecting the fuel stem mechanically to the shell, and fluidly to the space and the pilot fuel cavity for providing fuel. It also enables combustion air to reach the air plenum and the premix pipes with low pressure drop without swirl. This construction finally allows for a simple and safe provision of fuel and air to the mixing zone.
- This burner type can be adapted to many types of combustion systems but is especially suited for an annular gas turbine combustor characterized by a plurality of burners, combustor backwall, outer wall and inner wall.
- FIG 1 shows a burner 1 for a gas turbine according to the invention in a sectional view.
- Said burner 1 comprises a supply zone 2 for supplying fuel and air and a subsequent mixing zone 3 for premixing fuel and air, the mixing zone 3 having an upstream end 4 and a downstream end 5.
- the mixing zone 3 comprises a plurality of premix jet pipes 6 for mixing air and fuel, each with an inlet 7 and an outlet 8, arranged around a central burner axis 9 and extending between the upstream end 4 and the downstream end 5. It can be seen from FIG 1 that closer to the upstream end 4 the premix jet pipes 6 are straight and parallel to each other and closer to the downstream end 5 the premix jet pipes 6 are bent away from the central burner axis 9 wherein a bending of the premix jet pipes 6 increases with the distance between premix jet pipe 6 and central burner axis 9.
- the pipe bending shown in Fig 1 is indicated only in the radial direction. However, bending of pipes is not limited to this direction, also tangential bending is possible.
- the diameter 11 of the premix jet pipes 6 is between 0.5 mm and 10 mm to prevent the flame to protrude upstream into the burner 1, so called flashback.
- Inlets 7 of the premix jet pipes 6 at the upstream end 4 of the mixing zone 3 are connected to an air plenum 12.
- the downstream end 5 of the mixing zone 3 is formed by a convex end cover 13 with evenly distributed openings 14, and premix jet pipe outlets 8 are aligned with the openings 14 of the end cover 13.
- the plurality of premix jet pipes 6 is surrounded by a shell 15 extending between the air plenum 12 and the end cover 13 such that a space 16 is formed in which the premix jet pipes 6 extend, the space 16 being closed at the downstream end 5 and having an annular gap 17 at its upstream end 4 between the shell 15 and the air plenum 12.
- Lateral openings 18 are arranged in the premix jet pipes 6.
- a pilot fuel cavity 19 is arranged in the shell 15 and extending in circumferential direction and from which pilot fuel channels 20 branch off and extend parallel to the premix jet pipes 6 in the direction to the downstream end 5.
- the burner 1 is built on a traditional fuel stem 21 bringing fuel from outside the gas turbine.
- Hollow struts 22 connect the fuel stem 21 mechanically to the shell 15, and fluidly to the space 16 and the pilot fuel cavity 19 for providing fuel.
- the main fuel 25 and the pilot fuel 26 are led in channels 23 inside the struts 22 and are transported to the premix jet pipes 6, which are surrounded by main fuel, cooling the burner body and tip, and the pilot fuel cavity 19.
- the pilot fuel 26 is tangentially distributed in the pilot fuel cavity 19 and then distributed to the pilot fuel nozzles 24.
- This open structure defined by the struts 22 enables combustion air 27 to reach the premix jet pipes 6 with low pressure drop without swirl.
- FIG 2 shows a close-up view of the premix jet pipes 6 with a part of the air plenum 12 as well as the pilot fuel cavity 19 of the burner 1 of FIG 1 .
- the pilot fuel cavity 19 is arranged in the shell 15 and extends in circumferential direction. Pilot fuel channels 20 branch off the pilot fuel cavity 19 and extend parallel to the premix jet pipes 6 in the direction to the downstream end 5.
- FIG 2 shows quite clearly the lateral openings 18 which are arranged in the premix jet pipes 6 as well as the detailed structure of the premix jet pipes 6 themselves with their inlets 7 on the left of FIG 2 to the air plenum 12 as well as their outlets 8 on the right of FIG 2 to the combustion chamber 28 through openings 14 in the convex end cover 13.
- FIG 3 shows a view of the burner of FIG 1 from the upstream side at the position of the fuel stem 21, which is positioned on the central burner axis 9. From the fuel stem 21 struts 22 branch off in downstream direction outwardly in order to connect to the shell 15 surrounding the evenly in a circle distributed premix jet pipes 6, which are also shown in FIG 3 unless hidden by the stem 21 and the struts 22 in this view.
- FIG 4 shows a view from the downstream side in upstream direction of an example of a plurality of burners 1 in an annular combustor.
- Each burner 1 shows an inner circle with premix jet pipe 6 outlets 8 surrounded by a ring with evenly distributed pilot fuel nozzles 24.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP18199840.2A EP3637000A1 (fr) | 2018-10-11 | 2018-10-11 | Brûleur de turbine à gaz pour carburants réactifs |
| PCT/EP2019/074935 WO2020074224A1 (fr) | 2018-10-11 | 2019-09-18 | Brûleur à turbine à gaz pour carburants réactifs |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP18199840.2A EP3637000A1 (fr) | 2018-10-11 | 2018-10-11 | Brûleur de turbine à gaz pour carburants réactifs |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| EP3637000A1 true EP3637000A1 (fr) | 2020-04-15 |
Family
ID=63833899
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP18199840.2A Withdrawn EP3637000A1 (fr) | 2018-10-11 | 2018-10-11 | Brûleur de turbine à gaz pour carburants réactifs |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP3637000A1 (fr) |
| WO (1) | WO2020074224A1 (fr) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4571193A1 (fr) * | 2023-12-15 | 2025-06-18 | Doosan Enerbility Co., Ltd. | Buse de chambre de combustion, chambre de combustion et turbine à gaz comprenant celle-ci |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2216599A2 (fr) * | 2009-02-04 | 2010-08-11 | General Electric Company | Buse de prémélange pour injection directe |
| US20100287942A1 (en) * | 2009-05-14 | 2010-11-18 | General Electric Company | Dry Low NOx Combustion System with Pre-Mixed Direct-Injection Secondary Fuel Nozzle |
| US20120006030A1 (en) * | 2010-07-08 | 2012-01-12 | General Electric Company | Injection nozzle for a turbomachine |
| EP3067625A1 (fr) * | 2013-11-05 | 2016-09-14 | Mitsubishi Hitachi Power Systems, Ltd. | Foyer de turbine à gaz |
| CN106687747A (zh) * | 2014-10-06 | 2017-05-17 | 三菱日立电力系统株式会社 | 燃烧器、燃气轮机 |
| US20170248318A1 (en) * | 2016-02-26 | 2017-08-31 | General Electric Company | Pilot nozzles in gas turbine combustors |
-
2018
- 2018-10-11 EP EP18199840.2A patent/EP3637000A1/fr not_active Withdrawn
-
2019
- 2019-09-18 WO PCT/EP2019/074935 patent/WO2020074224A1/fr not_active Ceased
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2216599A2 (fr) * | 2009-02-04 | 2010-08-11 | General Electric Company | Buse de prémélange pour injection directe |
| US20100287942A1 (en) * | 2009-05-14 | 2010-11-18 | General Electric Company | Dry Low NOx Combustion System with Pre-Mixed Direct-Injection Secondary Fuel Nozzle |
| US20120006030A1 (en) * | 2010-07-08 | 2012-01-12 | General Electric Company | Injection nozzle for a turbomachine |
| EP3067625A1 (fr) * | 2013-11-05 | 2016-09-14 | Mitsubishi Hitachi Power Systems, Ltd. | Foyer de turbine à gaz |
| CN106687747A (zh) * | 2014-10-06 | 2017-05-17 | 三菱日立电力系统株式会社 | 燃烧器、燃气轮机 |
| US20170248318A1 (en) * | 2016-02-26 | 2017-08-31 | General Electric Company | Pilot nozzles in gas turbine combustors |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4571193A1 (fr) * | 2023-12-15 | 2025-06-18 | Doosan Enerbility Co., Ltd. | Buse de chambre de combustion, chambre de combustion et turbine à gaz comprenant celle-ci |
| US12359815B2 (en) | 2023-12-15 | 2025-07-15 | Doosan Enerbility Co., Ltd. | Combustor nozzle, combustor, and gas turbine including same |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2020074224A1 (fr) | 2020-04-16 |
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| 18D | Application deemed to be withdrawn |
Effective date: 20201016 |