EP3438530B1 - Sequential combustor assembly for a gas turbine assembly - Google Patents
Sequential combustor assembly for a gas turbine assembly Download PDFInfo
- Publication number
- EP3438530B1 EP3438530B1 EP17184122.4A EP17184122A EP3438530B1 EP 3438530 B1 EP3438530 B1 EP 3438530B1 EP 17184122 A EP17184122 A EP 17184122A EP 3438530 B1 EP3438530 B1 EP 3438530B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- air
- lance
- along
- mixer
- sequential
- 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
- 238000002347 injection Methods 0.000 claims description 33
- 239000007924 injection Substances 0.000 claims description 33
- 238000004891 communication Methods 0.000 claims description 9
- 238000002485 combustion reaction Methods 0.000 description 16
- 239000000446 fuel Substances 0.000 description 10
- 238000009826 distribution Methods 0.000 description 6
- 238000013016 damping Methods 0.000 description 5
- 230000035515 penetration Effects 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000116 mitigating effect Effects 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
- 238000005457 optimization Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
Images
Classifications
-
- 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
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. 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
- 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
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
- F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
- F23C6/042—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with fuel supply in stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03341—Sequential combustion chambers or burners
Definitions
- the present invention relates to a sequential combustor assembly for a gas turbine assembly.
- the present invention relates to a sequential combustor assembly for a gas turbine assembly which is part of a plant for the production of electrical power.
- a sequential combustor assembly comprises a first-stage combustor and a second-stage combustor which is arranged downstream the first-stage combustor along the gas flow.
- a mixer is arranged between the first-stage combustor and the second-stage combustor. In use, dilution air is selectively injected in said mixer.
- EP3015772 which disclose the features of the preamble of claim 1.
- the object of the present invention is therefore to provide a sequential combustor assembly which enables avoiding or at least mitigating the described drawbacks.
- the lance is provided with a plurality of first air outlets circumferentially aligned and evenly distributed along the circumference centered on the main axis. In this way a better uniform temperature distribution can be reached in the mixer.
- the plurality of first air outlets have the same outlet section. In this way the amount of the air flowing into the mixer can be controlled.
- the at least one first air outlet is provided with an insert.
- the lance is provided with a plurality of second air outlets axially spaced from the first air outlet along the middle portion. In this way a better uniform temperature distribution can be reached in the mixer.
- the plurality of second air outlets are circumferentially aligned.
- the first air outlet and the second air outlet are in fluidic communication with the first air channel. In this way the pressure of air injected through the first air outlet and the second air outlet is the same.
- the lance comprises at least one second air channel distinct from the first air channel; the first air outlet being in fluidic communication with the first air channel while the second air outlet being in fluidic communication with the second air channel.
- the sequential combustor assembly comprises a liner; a part of the liner defines the mixer; the liner being provided with at least one first air injection along the mixer.
- the liner is provided with at least one second air injection axially spaced from the first air injection along the mixer. In this way a regulation and an optimization of the damping can be obtained.
- the at least one first air injection is in fluidic communication with a respective liner air plenum; wherein the liner plenum and the first air channel are adapted such that the pressure of the air in the liner plenum may be greater than the pressure of the air in the first air channel of the lance. It is furthermore an object of the present invention to provide a turbine assembly having an improved efficiency. According to the present invention, there is provided a gas turbine assembly as claimed in claim 14.
- reference numeral 1 indicates a gas turbine assembly.
- the gas turbine assembly 1 comprises a compressor section 2, a sequential combustor assembly 3 and a turbine section 5.
- the compressor section 2 and the turbine section 3 extend along a main axis A.
- an airflow compressed in the compressor section 2 is mixed with fuel and is burned in the sequential combustor assembly 3.
- the burned mixture is then expanded to the turbine section 5 and converted in mechanical power.
- the sequential combustor assembly 3 comprises at least one can 6 which extends along a main axis B and comprises a first-stage combustor 8 and a second-stage combustor 9 sequentially arranged along the gas flow direction G.
- the second stage combustor 9 is arranged downstream the first stage combustor 8 along the gas flow.
- the combustor assembly 3 further comprises a mixer 11 arranged between the first stage combustor 8 and the second stage combustor 9.
- the first-stage combustor 8 comprises at least one burner 13 and a first combustion chamber 14.
- the second-stage combustor 9 comprises a second combustion chamber 16.
- the combustor assembly 3 further comprises a transition element 17 arranged downstream the can 6 for coupling the second combustion chamber 16 to the turbine section 5 (not shown) .
- the first combustion chamber 14, the second combustion chamber 16 and the mixer 11 are in fluidic communication and are defined by a liner 18 which extends axially.
- the liner 18 is substantially cylindrical along the first combustion chamber 14, is conical along the mixer 11 and again substantially cylindrical along the second combustion chamber 16.
- the liner 18 converges along the gas flow direction G.
- the combustor assembly 3 further comprises a lance 19, which extends axially through the first combustion chamber 14 of the first-stage combustor 8, through the mixer 11 and discharges in the second combustion chamber 16.
- the lance 19 is arranged along the axis B, i.e. substantially centrally with respect to the liner 18.
- the lance 19 is configured to feed air and at least one fuel.
- the lance 19 comprises at least one fuel channel 20 and at least one air channel 21.
- Air flowing in the air channel 21 comes from a respective lance plenum (not illustrated) wherein air has a determined pressure.
- the lance comprises a further fuel channel.
- the lance comprises a plurality of air channels, in each of which flows air coming from different plena having preferably different air pressure.
- the fuel channel 20 is centrally arranged, while the air channel 21 extends about the fuel channel 20.
- the lance 19 comprises an inlet portion 22 housed in the first combustion chamber 14, a middle portion 23 and an outlet portion 24 housed in the second combustion chamber 16.
- the lance 19 is provided with at least one fuel discharge 26 in the outlet portion 24 in order to provide fuel to the second combustion chamber 16.
- the lance 19 comprises a swirler 27 and one first fuel discharge 26 located at the swirler 27 and at least one second fuel discharge 26 located near the tip of the lance 19.
- the lance 19 is further provided with at least one air outlet 28 along the middle portion 23 housed in the mixer 11.
- the lance 19 is provided with a plurality of air outlets 28 circumferentially aligned.
- the plurality of air outlets 28 are evenly distributed along the circumference.
- the plurality of air outlets are unevenly distributed in order to create zones of air injections substantially separated.
- the plurality of air outlets 28 have the same outlet section.
- the plurality of air outlets can have different outlet sections in order to regulate the air flow rate entering in the mixer 11.
- the at least one air outlet 28 is provided with an insert.
- the insert can be configured to regulate the outlet section and/or to create turbulence and/or to deviate the flow in a desired direction and/or to modify the position of the injection of the air flow inside the mixer.
- the air outlet 28 can be a slot realized on the middle portion 23 of the lance 19.
- the slot is an annular slot.
- the lance 19 is provided with at least one first air outlet 30, at least one second air outlet 31 and, preferably, at least a third air outlet 32.
- the first air outlet 30, the second air outlet 31 and the third air outlet 32 are axially spaced along the middle portion 23.
- air exiting through the first air outlet 30, the second air outlet 31 and the third air outlet 32 comes from the same air channel 21.
- the second air outlet and the third air outlet comes from respective separate air channels supplied with air coming from different plena having different air pressures.
- the lance 19 is provided with a plurality of first air outlets 30, a plurality of second air outlets 31 and, preferably, a plurality of third air outlets 32.
- the plurality of first air outlets 30 are circumferentially aligned
- the plurality of second air outlets 31 are circumferentially aligned
- the plurality of third air outlets 32 are circumferentially aligned.
- the plurality of first air outlets 30, the plurality of second air outlets 31 and the plurality of third air outlets 32 are evenly distributed along the respective circumferences.
- the liner 18 is provided with at least one air injection 35 along the mixer 11.
- the liner 18 is provided with a first air injection 35a, a second air injection 35b and a third air injection 35c.
- the first air injection 35a, the second air injection 35b and the third air injection 35c are axially spaced along the mixer 11.
- the liner 18 is provided with a plurality of first air injections 35a, a plurality of second air injections 35b and a plurality of third air injections 35c.
- air exiting through the air injection 35 or through the air injections 35a, 35b, 35c comes from a respective liner plenum (not illustrated) wherein air has a determined pressure.
- the liner plenum air has a pressure different from the pressure of the air in the lance plenum.
- the liner plenum and the lance plenum can have the same pressure.
- the liner plenum and the lance plenum can coincide. Thanks to the presence of the air injections 35a, 35b, 35c, the air jet penetration required for air outlets 28, 30, 31, 32 in the lance 16 to create a uniform temperature distribution is lower since air is injected from both the liner wall (through air injections 35a, 35b, 35c) and the central lance 16 (through air outlets 28, 30, 31, 32). Consequently the required pressure drop in air outlets 28, 30, 31, 32 is also lower.
- Axial positions of air injections 35a, 35b, 35c and of air outlets 30, 31, 32 can be defined in the designing phase in order to conveniently damp the temperature fluctuations at the inlet of the second-stage combustor 9.
- air injections 35a, 35b, 35c can be designed in order to direct air towards distal zones of the mixer 11 near the wall of the liner 18 while the air outlets 30, 31, 32 can be designed in order to direct air towards proximal zones of the mixer 11 near the lance 16.
- air outlets 30, 31, 32 direct air mainly towards zone of the mixer which are radially proximal with respect to axis B
- air injections 35a, 35b, 35c direct air mainly towards zone of the mixer which are radially distal with respect to axis B.
- the axial position of air injections 35a, 35b, 35c and of air outlets 30, 31, 32 can be selected in order to have a uniform distribution of the air injected from the lance 16 and from the liner 18 or in order to focus the air injection towards one or more zones of the mixer 11 wherein temperature fluctuations are particularly relevant.
- the design and the axial position of air injections 35a, 35b, 35c and of air outlets 30, 31, 32 can be optimized in order to damp different unstable modes affecting the mixer 11.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Nozzles (AREA)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17184122.4A EP3438530B1 (en) | 2017-07-31 | 2017-07-31 | Sequential combustor assembly for a gas turbine assembly |
CN201810845402.XA CN109323286B (zh) | 2017-07-31 | 2018-07-27 | 用于燃气涡轮组件的顺序燃烧器组件 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17184122.4A EP3438530B1 (en) | 2017-07-31 | 2017-07-31 | Sequential combustor assembly for a gas turbine assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3438530A1 EP3438530A1 (en) | 2019-02-06 |
EP3438530B1 true EP3438530B1 (en) | 2020-03-04 |
Family
ID=59501366
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17184122.4A Active EP3438530B1 (en) | 2017-07-31 | 2017-07-31 | Sequential combustor assembly for a gas turbine assembly |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP3438530B1 (zh) |
CN (1) | CN109323286B (zh) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3702669B1 (en) * | 2019-02-28 | 2022-08-03 | Ansaldo Energia Switzerland AG | Method for operating a sequential combustor of a gas turbine and a gas turbine comprising this sequential combustor |
EP3772615B1 (en) * | 2019-08-08 | 2024-03-20 | Ansaldo Energia Switzerland AG | Sequential combustor assembly for a gas turbine assembly and method for operating said sequential combustor assembly |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20120304660A1 (en) * | 2011-06-06 | 2012-12-06 | Kupratis Daniel B | Turbomachine combustors having different flow paths |
EP2966356B1 (en) * | 2014-07-10 | 2020-01-08 | Ansaldo Energia Switzerland AG | Sequential combustor arrangement with a mixer |
EP2993404B1 (en) * | 2014-09-08 | 2019-03-13 | Ansaldo Energia Switzerland AG | Dilution gas or air mixer for a combustor of a gas turbine |
EP3015772B1 (en) * | 2014-10-31 | 2020-01-08 | Ansaldo Energia Switzerland AG | Combustor arrangement for a gas turbine |
EP3015771B1 (en) * | 2014-10-31 | 2020-01-01 | Ansaldo Energia Switzerland AG | Combustor arrangement for a gas turbine |
-
2017
- 2017-07-31 EP EP17184122.4A patent/EP3438530B1/en active Active
-
2018
- 2018-07-27 CN CN201810845402.XA patent/CN109323286B/zh active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
EP3438530A1 (en) | 2019-02-06 |
CN109323286B (zh) | 2022-03-08 |
CN109323286A (zh) | 2019-02-12 |
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