EP4019840A1 - Combustor unit for a gas turbine assembly, gas turbine assembly and method for controlling fuel injection in a combustor unit for a gas turbine assembly - Google Patents
Combustor unit for a gas turbine assembly, gas turbine assembly and method for controlling fuel injection in a combustor unit for a gas turbine assembly Download PDFInfo
- Publication number
- EP4019840A1 EP4019840A1 EP20217211.0A EP20217211A EP4019840A1 EP 4019840 A1 EP4019840 A1 EP 4019840A1 EP 20217211 A EP20217211 A EP 20217211A EP 4019840 A1 EP4019840 A1 EP 4019840A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustor
- injection
- air
- fuel
- injection units
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000002347 injection Methods 0.000 title claims abstract description 118
- 239000007924 injection Substances 0.000 title claims abstract description 118
- 239000000446 fuel Substances 0.000 title claims abstract description 78
- 238000000034 method Methods 0.000 title description 2
- 238000002485 combustion reaction Methods 0.000 claims abstract description 29
- 230000035515 penetration Effects 0.000 claims description 7
- 238000004891 communication Methods 0.000 claims description 6
- 239000003570 air Substances 0.000 description 64
- 230000010349 pulsation Effects 0.000 description 6
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000010355 oscillation Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000007789 gas Substances 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
- 238000009828 non-uniform distribution Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
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- 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
- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00013—Reducing thermo-acoustic vibrations by active means
-
- 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
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
-
- 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 combustor unit for a gas turbine assembly and to a gas turbine assembly, in particular of a power plant.
- the invention further relates to a method for controlling fuel injection in a combustor unit.
- a gas turbine assembly for power plants comprises a compressor, a combustor unit and a turbine.
- the compressor comprises an inlet, supplied with air, and a plurality of blades compressing the passing air.
- the compressed air leaving the compressor flows into a plenum, i.e. a closed volume, and from there into the combustor unit, where the compressed air is mixed with at least one fuel and combusted.
- the resulting hot gas leaves the combustor unit and is expanded in the turbine, producing mechanical work.
- gas turbine assemblies which comprise a combustor unit performing a sequential combustion cycle.
- a sequential combustor unit comprises two combustors in series, wherein each combustor is provided with a respective burner and combustion chamber. Following the main gas flow direction, the upstream combustor is called “premix” combustor and is fed by the compressed air. The downstream combustor is called “sequential” or “reheat” combustor and is fed by the hot gas leaving the first combustion chamber.
- this first configuration includes the compressor, the premix combustor, the high-pressure turbine, the reheat combustor and a low-pressure turbine.
- the premix and the reheat combustor are arranged directly one downstream the other inside a common casing, in particular a can-shaped casing, and no high-pressure turbine is used.
- a plurality of can combustors are provided, which are distributed around the turbine axis.
- Each reheat combustor is preferably provided with a reheat burner and a reheat combustion chamber into which the hot flow coming from the premix is discharged.
- a transition duct is arranged downstream the reheat combustion chamber and guides the hot gas leaving the reheat combustor toward the turbine.
- the reheat burner may include a plurality of identical injection units, which are circumferentially arranged about the reheat combustion chamber and are designed to uniformly inject fuel into the reheat combustion chamber.
- thermoacoustic pulsations which may exceed acceptable pulsation limits and undesirably restrict the gas turbine operational range.
- damping devices are not always effective and require space, not always available in all combustor assemblies.
- a combustor unit for a gas turbine assembly comprising a premix combustor and a reheat combustor, which are arranged in series along the gas flow direction;
- the reheat combustor comprising:
- Figure 1 is a schematic view of a gas turbine assembly 1 for power plants according to the present invention.
- Gas turbine assembly 1 comprises a compressor 2, a combustor assembly 3 and a turbine 4.
- Compressor 2 and turbine 4 have a common axis A and form respective sections of a rotor 5 rotatable about axis A.
- ambient air 6 enters compressor 2 and is compressed.
- Compressed air 7 leaves compressor 2 and enters a plenum 8, i.e. a volume defined by an outer casing 9.
- a plenum 8 i.e. a volume defined by an outer casing 9.
- compressed air 7 enters combustor assembly 3 that comprises a plurality of combustor units 10 annularly arranged around axis A.
- Combustor units 10 are often defined "can combustors". In combustor units 10 at least a fuel is injected, and the air/fuel mixture is ignited, producing hot gas 11 that is conveyed to turbine 4.
- each combustor unit 10 is housed in a respective portal hole of the outer casing 9 and has an axis B.
- Combustor unit 10 comprises, in series along gas flow M, a first or premix combustor 15, a second or reheat combustor 16 and a transition duct 19, which guides the hot gas leaving the reheat combustor 16 toward the turbine 4.
- premix combustor 15 comprises a premix burner 17 and a first combustion chamber 18.
- Reheat combustor 16 comprises a housing 20 defining a combustion chamber 23 and a reheat burner 22.
- the housing 20 is a double wall housing wherein a cooling interspace 24 (better visible in figures 3a-3c , 4a-4c , 5a-5c , 6a-6c ) is formed.
- the cooling interspace 24 is fed with air coming from the plenum 8.
- the housing 20 is arranged inside a casing 25, which substantially surrounds the housing 20 in order to create an air chamber 26, which is fed with the air coming from the plenum 8.
- reheat burner 22 comprises a plurality of injection units collectively referenced 27, and individually referenced 27a, 27b, 27c, 27d, etc.
- the plurality of injection units 27 is arranged around the reheat combustion chamber 23 and is fed with air and fuel.
- the plurality of injection units 27 is arranged circumferentially around the reheat combustion chamber 23.
- Each injection unit 27a, 27b, 27c, 27d, etc. engages a respective through hole 28 made in the housing 20.
- each injection unit 27a, 27b, 27c, 27d comprises a fuel supply line 30 and at least one fuel nozzle 31 in fluidic communication with the fuel supply line 30, an air supply line 29 and at least one air nozzle 32 in fluidic communication with the air supply line 29 and a conveying tube 33, wherein air and fuel coming from the at least one fuel nozzle 31 and air nozzle 32 are mixed.
- the conveying tube 33 extends along an axis C. In the non-limitative example here disclosed and illustrated, the conveying tube 33 extends from an inlet coinciding with the air nozzle 32 to an outlet 35 flowing into the reheat combustion chamber 23.
- the conveying tube 33 is cylindrical and is at least partially housed in the hole 28 of the housing 20
- the air supply line 29 comprises the air chamber 26, which surrounds the housing 20 and supplies all the air nozzles 32.
- the fuel supply line 30 comprises a fuel conduit 37 (schematically represented) and a fuel collector 38, preferably surrounding the inlet portion of the conveying tube 33.
- the fuel supplied to the fuel supply line 30 can be the same fuel supplied to the first combustor 15 or a different fuel.
- each injection unit 27a, 27b, 27c, 27d, 27e comprises a plurality of fuel nozzles 31, which are arranged along a substantially circumferential path extending on a plane orthogonal to axis C.
- At least one injection unit 27a of the plurality of injection units 27 is configured to inject fuel and air differently from the other injection units of the plurality of injection units 27.
- the injection unit 27a is configured to inject fuel and air according to a different equivalence ratio and/or to a different mixing between air and fuel and/or to a different penetration into the reheat combustion chamber 23 with respect to the others injection units 27b, 27c, 27d, 27e of the plurality of injection units 27.
- ⁇ QF / QA QF / QA STOICH as the ratio of the fuel-to-air ratio to the stoichiometric fuel-to-air ratio.
- mixing between air and fuel is intended the way of mixing the fuel and the air supplied to the injection unit (e.g. presence of vortex generators/deflectors and other means for controlling the mixing between fuel and air).
- the jet characteristic of the mixed air/fuel flow is intended the jet characteristic of the mixed air/fuel flow, which is injected into the reheat combustion chamber 23.
- the jet characteristic of the mixed air/fuel flow can depend on the jet momentum, the jet diameter, the jet angle, and the position at which the mixed air/fuel flow coming from the injection unit is injected in the reheat combustion chamber 23.
- FIGS 3a-3c it is represented a first embodiment of the present invention wherein at least the injection unit 27a has a conveying tube 33a having a tube length La different from the tube lengths Lb, Lc, Ld, Le of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube length is measured along the axis C.
- the tube length La is greater than the tube lengths Lb, Lc, Ld, Le of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube length La is greater than the depth of the housing 20.
- the tube lengths La, Lb, Lc, Ld, Le are different from each other in order to change the penetration depth of each injection unit 27.
- FIGS 4a-4c it is represented a second embodiment of the present invention, wherein at least the injection unit 27a has fuel nozzles 31a having a diameter Da different from the diameter Db, Dc, Dd, De of the fuel nozzles 31b, 31c, 31d, 31e of the other injection units 27b, 27c, 27d, 27e.
- fuel nozzles 31a have a diameter Da greater than the diameters Db, Dc, Dd, De of the fuel nozzles 31b, 31c, 31d of the other injection units 27b, 27c, 27d, 27e.
- the diameters Da, Db, Dc, Dd, De of the fuel nozzles 31a, 31b, 31c, 31d, 31e are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27
- FIG. 5a-5c it is represented a third embodiment of the present invention, wherein at least the injection unit 27a has a conveying tube 33a having a tube width Wa different from the tube widths Wb, Wc, Wd, We of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube width is measured along a direction orthogonal to axis C.
- the tube width Wa is smaller than the tube widths Wb, Wc, Wd, We of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube widths Wa, Wb, Wc, Wd, We are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27 and the penetration into the reheat combustion chamber 23.
- FIG. 6a-6c it is represented a fourth embodiment of the present invention, wherein at least the injection unit 27a has an air nozzle 32a having a passage section Aa different from the passage sections Ab, Ac, Ad, Ae of the air nozzles 32b, 32c, 32d, 32e of the other injection units 27b, 27c, 27d, 27e.
- air nozzle 32a has a passage section Aa smaller from the passage sections Ab, Ac, Ad, Ae of the air nozzles 32b, 32c, 32d, 32e of the other injection units 27b, 27c, 27d, 27e.
- air nozzle 32a is coupled to a metering plate 39 having a hole 40 whose passage section is the desired one Aa.
- the passage sections Aa, Ab, Ac, Ad, Ae of the air nozzles 32a, 32b, 32c, 32d, 32e of the injection units 27a, 27b, 27c, 27d, 27e are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27
- conveying tubes 33a, 33b, 33c, 33d, 33e extend along an axis B which is substantially arranged radially with respect to the axis B of the combustor unit 10.
- At least one of the injection units 27a, 27b, 27c, 27d, 27e is provided with a conveying tube 33a, 33b, 33c, 33d, 33e extending along an axis which is not radially arranged.
- all the conveying tubes 33a, 33b, 33c, 33d, 33e extend along respective axis which are not radially arranged and are inclined differently from each other.
- At least one of the injection units 27a is provided with fuel nozzles 31a having a shape and/or a position different from the shapes and/or the positions of the other fuel nozzles 31b, 31c, 31d, 31e.
- the shapes and/or the positions of fuel nozzles 31a, 31b, 31c, 31d, 31e are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27.
- the supply line 30 can be adjusted in order to supply a different fuel flow rate to at least one injection unit of the plurality of injection units 27.
- the passage section of the fuel conduit 37 of at least one injection unit 27a can be different from the passage section of the fuel conduits 37 of at least one injection units 37b, 37c, 37d, 37e.
- At least one injection unit of the plurality of injection units 27 is provided with a combination of the different features above described for each embodiment.
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Abstract
Description
- The present invention relates to a combustor unit for a gas turbine assembly and to a gas turbine assembly, in particular of a power plant.
- The invention further relates to a method for controlling fuel injection in a combustor unit.
- As is known, a gas turbine assembly for power plants comprises a compressor, a combustor unit and a turbine.
- In particular, the compressor comprises an inlet, supplied with air, and a plurality of blades compressing the passing air. The compressed air leaving the compressor flows into a plenum, i.e. a closed volume, and from there into the combustor unit, where the compressed air is mixed with at least one fuel and combusted. The resulting hot gas leaves the combustor unit and is expanded in the turbine, producing mechanical work.
- In order to achieve a high efficiency, a high turbine inlet temperature is required.
- However, due to this high temperature, high NOx emissions are generated.
- In order to reduce these emissions and to increase operational flexibility, gas turbine assemblies have been developed which comprise a combustor unit performing a sequential combustion cycle.
- In general, a sequential combustor unit comprises two combustors in series, wherein each combustor is provided with a respective burner and combustion chamber. Following the main gas flow direction, the upstream combustor is called "premix" combustor and is fed by the compressed air. The downstream combustor is called "sequential" or "reheat" combustor and is fed by the hot gas leaving the first combustion chamber.
- According to a first known configuration, the two combustors are physically separated by a high pressure turbine. Following the main gas flow, this first configuration includes the compressor, the premix combustor, the high-pressure turbine, the reheat combustor and a low-pressure turbine.
- According to a second known configuration, the premix and the reheat combustor are arranged directly one downstream the other inside a common casing, in particular a can-shaped casing, and no high-pressure turbine is used. According to this kind of sequential gas turbines, a plurality of can combustors are provided, which are distributed around the turbine axis.
- Each reheat combustor is preferably provided with a reheat burner and a reheat combustion chamber into which the hot flow coming from the premix is discharged. A transition duct is arranged downstream the reheat combustion chamber and guides the hot gas leaving the reheat combustor toward the turbine.
- The reheat burner may include a plurality of identical injection units, which are circumferentially arranged about the reheat combustion chamber and are designed to uniformly inject fuel into the reheat combustion chamber.
- The reheat burner flames, in certain operating conditions, generate self-excited thermoacoustic pulsations, which may exceed acceptable pulsation limits and undesirably restrict the gas turbine operational range.
- For this reason, usually, combustor assemblies are provided with damping devices in order to damp these pressure oscillations. However, damping devices are not always effective and require space, not always available in all combustor assemblies.
- Therefore it is primary object of the present invention to provide a combustor unit wherein flame pulsations are reduced in a cost effective way and, at the same time, without affecting NOx emissions.
- This object is attained, according to the present invention, by a combustor unit for a gas turbine assembly comprising a premix combustor and a reheat combustor, which are arranged in series along the gas flow direction;
the reheat combustor comprising: - a housing extending substantially along a longitudinal axis and defining a reheat combustion chamber,
- a plurality of injection units distributed around the reheat combustion chamber and fed with air and fuel;
- at least one first injection unit of the plurality of injection units being configured to inject fuel and air differently with respect to the others injection units.
- It is also another object of the present invention to provide a gas turbine assembly wherein flame pulsations are reduced in a cost effective way and, at the same time, without affecting NOx emissions.
According to these objects the present invention relates to a gas turbine assembly as claimed inclaim 15. - For a better comprehension of the present invention and its advantages, an exemplary embodiment of the invention is described below in conjunction with the accompanying drawings, in which:
-
figure 1 is a schematic view, with parts removed for clarity, of a gas turbine assembly provided with a combustor unit according to the present invention; -
figure 2a is a schematic lateral section view, with parts removed for clarity, of a combustor unit according to the invention; -
figure 2b is an enlarged view of a detail offigure 2a ; -
figures 3a-3c are schematic enlarged section views of details of the combustor unit offigure 2 ; -
figures 4a-4c are schematic enlarged section views of details of the combustor unit offigure 2 according to a first variant of the present invention; -
figures 5a-5c are schematic enlarged section views of details of the combustor unit offigure 2 according to a second variant of the present invention; -
figures 6a-6c are schematic enlarged section views of details of the combustor unit offigure 2 according to a third variant of the present invention. -
Figure 1 is a schematic view of a gas turbine assembly 1 for power plants according to the present invention. - Gas turbine assembly 1 comprises a
compressor 2, acombustor assembly 3 and a turbine 4.Compressor 2 and turbine 4 have a common axis A and form respective sections of arotor 5 rotatable about axis A. - As is known,
ambient air 6 enterscompressor 2 and is compressed. Compressed air 7leaves compressor 2 and enters aplenum 8, i.e. a volume defined by anouter casing 9. Fromplenum 8, compressed air 7 enterscombustor assembly 3 that comprises a plurality ofcombustor units 10 annularly arranged around axisA. Combustor units 10 are often defined "can combustors". Incombustor units 10 at least a fuel is injected, and the air/fuel mixture is ignited, producinghot gas 11 that is conveyed to turbine 4. - As is better shown in
figure 2a , eachcombustor unit 10 is housed in a respective portal hole of theouter casing 9 and has an axisB. Combustor unit 10 comprises, in series along gas flow M, a first orpremix combustor 15, a second or reheatcombustor 16 and a transition duct 19, which guides the hot gas leaving thereheat combustor 16 toward the turbine 4. - In particular,
premix combustor 15 comprises apremix burner 17 and afirst combustion chamber 18. -
Reheat combustor 16 comprises ahousing 20 defining acombustion chamber 23 and areheat burner 22. - Preferably, the
housing 20 is a double wall housing wherein a cooling interspace 24 (better visible infigures 3a-3c ,4a-4c ,5a-5c ,6a-6c ) is formed. Thecooling interspace 24 is fed with air coming from theplenum 8. - The
housing 20 is arranged inside acasing 25, which substantially surrounds thehousing 20 in order to create anair chamber 26, which is fed with the air coming from theplenum 8. - With reference to
figure 2b ,reheat burner 22 comprises a plurality of injection units collectively referenced 27, and individually referenced 27a, 27b, 27c, 27d, etc.... - The plurality of
injection units 27 is arranged around thereheat combustion chamber 23 and is fed with air and fuel. Preferably,, the plurality ofinjection units 27 is arranged circumferentially around thereheat combustion chamber 23. - Each
injection unit hole 28 made in thehousing 20. - With reference to
figures 3a-3c , eachinjection unit fuel supply line 30 and at least onefuel nozzle 31 in fluidic communication with thefuel supply line 30, anair supply line 29 and at least oneair nozzle 32 in fluidic communication with theair supply line 29 and a conveyingtube 33, wherein air and fuel coming from the at least onefuel nozzle 31 andair nozzle 32 are mixed. - The conveying
tube 33 extends along an axis C. In the non-limitative example here disclosed and illustrated, the conveyingtube 33 extends from an inlet coinciding with theair nozzle 32 to an outlet 35 flowing into thereheat combustion chamber 23. - Preferably, the conveying
tube 33 is cylindrical and is at least partially housed in thehole 28 of thehousing 20 - The
air supply line 29 comprises theair chamber 26, which surrounds thehousing 20 and supplies all theair nozzles 32. - The
fuel supply line 30 comprises a fuel conduit 37 (schematically represented) and afuel collector 38, preferably surrounding the inlet portion of the conveyingtube 33. The fuel supplied to thefuel supply line 30 can be the same fuel supplied to thefirst combustor 15 or a different fuel. - In the non-limitative example here disclosed and illustrated, each
injection unit fuel nozzles 31, which are arranged along a substantially circumferential path extending on a plane orthogonal to axis C. - At least one
injection unit 27a of the plurality ofinjection units 27 is configured to inject fuel and air differently from the other injection units of the plurality ofinjection units 27. - With the expression "differently" it is intended that the geometry or the supply control of air and/or fuel is different from the geometry or the supply control of the
other injection units injection units 27. - Preferably, the
injection unit 27a is configured to inject fuel and air according to a different equivalence ratio and/or to a different mixing between air and fuel and/or to a different penetration into thereheat combustion chamber 23 with respect to theothers injection units injection units 27. -
- The advantage of using equivalence ratio over fuel-air ratio is that it takes into account (and is therefore independent of) both mass and molar values for the fuel and air.
- With the expression "mixing between air and fuel" is intended the way of mixing the fuel and the air supplied to the injection unit (e.g. presence of vortex generators/deflectors and other means for controlling the mixing between fuel and air).
- With the expression "penetration into the reheat combustion chamber" is intended the jet characteristic of the mixed air/fuel flow, which is injected into the
reheat combustion chamber 23. In particular, the jet characteristic of the mixed air/fuel flow can depend on the jet momentum, the jet diameter, the jet angle, and the position at which the mixed air/fuel flow coming from the injection unit is injected in thereheat combustion chamber 23. - In this way, in the
reheat combustion chamber 23 at least one non-uniformity is introduced. This leads to an uneven distribution of the flow field and of the hot gas, fuel, air mixing field at the reaction zone (flame) of thereheat combustor 16. The acoustic dynamics are therefore damped and the dangerous increasing of some acoustic oscillations is avoided. - In
figures 3a-3c it is represented a first embodiment of the present invention wherein at least theinjection unit 27a has a conveyingtube 33a having a tube length La different from the tube lengths Lb, Lc, Ld, Le of the conveyingtubes 33b, 33c, 33d, 33e of theother injection units - Preferably, the tube length La is greater than the tube lengths Lb, Lc, Ld, Le of the conveying
tubes 33b, 33c, 33d, 33e of theother injection units - More preferably, the tube length La is greater than the depth of the
housing 20. - According to a variant not shown, the tube lengths La, Lb, Lc, Ld, Le are different from each other in order to change the penetration depth of each
injection unit 27. - In
figures 4a-4c it is represented a second embodiment of the present invention, wherein at least theinjection unit 27a hasfuel nozzles 31a having a diameter Da different from the diameter Db, Dc, Dd, De of thefuel nozzles other injection units - Preferably,
fuel nozzles 31a have a diameter Da greater than the diameters Db, Dc, Dd, De of thefuel nozzles other injection units - According to a variant not shown, the diameters Da, Db, Dc, Dd, De of the
fuel nozzles injection unit 27 - In
figures 5a-5c it is represented a third embodiment of the present invention, wherein at least theinjection unit 27a has a conveyingtube 33a having a tube width Wa different from the tube widths Wb, Wc, Wd, We of the conveyingtubes 33b, 33c, 33d, 33e of theother injection units - Preferably, the tube width Wa is smaller than the tube widths Wb, Wc, Wd, We of the conveying
tubes 33b, 33c, 33d, 33e of theother injection units - According to a variant not shown, the tube widths Wa, Wb, Wc, Wd, We are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each
injection unit 27 and the penetration into thereheat combustion chamber 23. - In
figures 6a-6c it is represented a fourth embodiment of the present invention, wherein at least theinjection unit 27a has anair nozzle 32a having a passage section Aa different from the passage sections Ab, Ac, Ad, Ae of theair nozzles other injection units - Preferably,
air nozzle 32a has a passage section Aa smaller from the passage sections Ab, Ac, Ad, Ae of theair nozzles other injection units - More preferably,
air nozzle 32a is coupled to ametering plate 39 having ahole 40 whose passage section is the desired one Aa. - According to a variant not shown, the passage sections Aa, Ab, Ac, Ad, Ae of the
air nozzles injection units injection unit 27 - In the examples here disclosed and illustrated all the conveying
tubes combustor unit 10. - According to a variant not shown, at least one of the
injection units tube - According to a further variant all the conveying
tubes - According to a variant not shown, at least one of the
injection units 27a is provided withfuel nozzles 31a having a shape and/or a position different from the shapes and/or the positions of theother fuel nozzles - According to a further variant not shown, the shapes and/or the positions of
fuel nozzles injection unit 27. - According to a variant not shown the
supply line 30 can be adjusted in order to supply a different fuel flow rate to at least one injection unit of the plurality ofinjection units 27. For example, the passage section of the fuel conduit 37 of at least oneinjection unit 27a can be different from the passage section of the fuel conduits 37 of at least oneinjection units 37b, 37c, 37d, 37e. - According to a further variant not shown, at least one injection unit of the plurality of
injection units 27 is provided with a combination of the different features above described for each embodiment. - Other variants may be considered and focused on changing further geometrical parameters of the injection units able to modify the equivalence ratio and/or the mixing between air and fuel and/or the penetration into the
reheat combustion chamber 23. - In this way a different behavior of the injection nozzles creates a non-uniformity in the flame front and therefore a disruptive interference of the acoustic oscillations.
- Although the invention has been explained in relation to its preferred embodiments as mentioned above, it is to be understood that many other possible modifications and variations can be made without departing from the scope of the appended claims.
According to a variant, all the injection units of the plurality of injection units are configured to inject fuel and air differently from each other.
According to a variant of the present invention, the at least one first injection unit of the plurality of injection units is configured to inject fuel and air according to a different equivalence ratio and/or to a different mixing between air and fuel and/or to a different penetration into the reheat combustion chamber with respect to the other injection units. According to a further variant of the present invention, the geometry of the at least one first injection unit of the plurality of injection units is different from the geometry of the other injection units of the plurality of injection units.
According to a variant of the present invention, the amount of air and/or fuel fed to the at least one first injection unit of the plurality of injection units is different from the amount of air and/or fuel fed to the other injection units of the plurality of injection units.
According to a variant of the present invention, each injection unit of the plurality of injection units engages a respective hole of the housing.
According to a variant of the present invention, each injection unit of the plurality of injection units comprises a fuel supply line and at least one fuel nozzle in fluidic communication with the fuel supply line; an air supply line and at least one air nozzle in fluidic communication with the air supply line; and a conveying tube extending along an extension axis and provided with an outlet flowing into the reheat combustion chamber; in the conveying tube air and fuel coming from the at least one fuel nozzle and air nozzle are mixed.
According to a further variant of the present invention, the inlet of the conveying tube coincides with the air nozzle.
According to a variant of the present invention, the at least one first injection unit has a conveying tube having a first tube length different from the tube lengths of the conveying tubes of the other injection units.
Preferably, according to an embodiment of the present invention, the at least one first fuel nozzles of the at least one first injection unit has a first diameter different from the diameters of the fuel nozzles of the other injection units.
According to another embodiment of the present invention, the at least one first injection unit has a first conveying tube having a first tube width different from the tube widths of the conveying tubes of the other injection units.
According to another embodiment of the present invention, the at least one first injection unit has a first air nozzle having a passage section different from the passage sections of the air nozzles of the other injection units.
According to another embodiment of the present invention, the first injection unit comprises a metering plate provided with a hole and coupled to the first air nozzle to adjust the passage section of the first air nozzle.
According to another embodiment of the present invention, the at least first injection unit has a first conveying tube extending along an extension axis which is inclined differently from the extension axes of the conveying tubes of the other injection units.
Claims (15)
- A combustor unit (10) for a gas turbine assembly (1) comprising a premix combustor (15) and a reheat combustor (16), which are arranged in series along the gas flow direction (M); the reheat combustor (16) comprising:a housing (20) extending substantially along a longitudinal axis (B) and defining a reheat combustion chamber (23),a plurality of injection units (27) distributed around the reheat combustion chamber (23) and fed with air and fuel;at least one first injection unit (27a) of the plurality of injection units (27) being configured to inject fuel and air differently with respect to the others injection units (27b, 27c, 27d, 27e).
- A combustor unit according to claim 1, wherein all the injection units (27a, 27b, 27c, 27d, 27e) of the plurality of injection units (27) are configured to inject fuel and air differently from each other.
- A combustor unit according to claim 1 or 2, wherein the at least one first injection unit (27a) of the plurality of injection units (27) is configured to inject fuel and air according to a different equivalence ratio and/or to a different mixing between air and fuel and/or to a different penetration into the reheat combustion chamber (23) with respect to the other injection units (27b, 27c, 27d, 27e).
- A combustor unit according to anyone of the foregoing claims, wherein the geometry of the at least one first injection unit (27a) of the plurality of injection units (27) is different from the geometry of the other injection units (27b, 27c, 27d, 27e) of the plurality of injection units (27).
- A combustor unit according to anyone of the foregoing claims, wherein the amount of air and/or fuel fed to the at least one first injection unit (27a) of the plurality of injection units (27) is different from the amount of air and/or fuel fed to the other injection units (27b, 27c, 27d, 27e) of the plurality of injection units (27).
- A combustor unit according to anyone of the foregoing claims, wherein each injection unit (27a, 27b, 27c, 27d) of the plurality of injection units (27) engages a respective hole (28) of the housing (20).
- A combustor unit according to anyone of the foregoing claims, wherein each injection unit (27a, 27b, 27c, 27d) of the plurality of injection units (27) comprises a fuel supply line (30) and at least one fuel nozzle (31) in fluidic communication with the fuel supply line (30); an air supply line (29) and at least one air nozzle (32) in fluidic communication with the air supply line (31); and a conveying tube (33) extending along an extension axis (C) and provided with an outlet (35) flowing into the reheat combustion chamber (23); in the conveying tube (33) air and fuel coming from the at least one fuel nozzle (31) and air nozzle (32) are mixed.
- A combustor unit according to claim 7, wherein the inlet of the conveying tube (33) coincides with the air nozzle (32) .
- A combustor unit according to claim 7 or 8, wherein the at least one first injection unit (27a) has a conveying tube (33a) having a first tube length (La) different from the tube lengths (Lb, Lc, Ld, Le) of the conveying tubes (33b, 33c, 33d, 33e) of the other injection units (27b, 27c, 27d, 27e).
- A combustor unit according to anyone of claims 7-9, wherein at least one first fuel nozzles (31a) of the at least one first injection unit (27a) has a first diameter (Da) different from the diameters (Db, Dc, Dd, De) of the fuel nozzles (31b, 31c, 31d, 31e) of the other injection units (27b, 27c, 27d, 27e).
- A combustor unit according to anyone of claims 7-10, wherein the at least one first injection unit (27a) has a first conveying tube (33a) having a first tube width (Wa) different from the tube widths (Wb, Wc, Wd, We) of the conveying tubes (33b, 33c, 33d, 33e) of the other injection units (27b, 27c, 27d, 27e).
- A combustor unit according to anyone of claims 7-11, wherein the at least one first injection unit (27a) has a first air nozzle (32a) having a passage section (Aa) different from the passage sections (Ab, Ac, Ad, Ae) of the air nozzles (32b, 32c, 32d, 32e) of the other injection units (27b, 27c, 27d, 27e).
- A combustor unit according to claim 12, wherein the first injection unit (27a) comprises a metering plate (39) provided with a hole (40) and coupled to the first air nozzle (32a) to adjust the passage section (Aa) of the first air nozzle (32a).
- A combustor unit according to anyone of claims 7-13, wherein the at least first injection unit (27a) has a first conveying tube (33a) extending along an extension axis (C) which is inclined differently from the extension axes (C) of the conveying tubes (33a, 33b, 33c, 33d, 33e) of the other injection units (27b, 27c, 27d, 27e).
- Gas turbine assembly comprising:
a compressor (2), a turbine (4) and a combustor assembly (3); the combustor assembly (3) comprising at least one combustor unit (10) as claimed in anyone of the foregoing claims.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP20217211.0A EP4019840B1 (en) | 2020-12-24 | 2020-12-24 | Combustor unit for a gas turbine assembly |
CN202111561357.3A CN114754377A (en) | 2020-12-24 | 2021-12-20 | Combustor unit, gas turbine assembly and method for controlling fuel injection |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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EP20217211.0A EP4019840B1 (en) | 2020-12-24 | 2020-12-24 | Combustor unit for a gas turbine assembly |
Publications (2)
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EP4019840A1 true EP4019840A1 (en) | 2022-06-29 |
EP4019840B1 EP4019840B1 (en) | 2024-04-03 |
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EP20217211.0A Active EP4019840B1 (en) | 2020-12-24 | 2020-12-24 | Combustor unit for a gas turbine assembly |
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WO2009078891A2 (en) * | 2007-09-14 | 2009-06-25 | Siemens Energy, Inc. | Secondary fuel delivery system |
WO2013022367A1 (en) * | 2011-08-11 | 2013-02-14 | General Electric Company | System for injecting fuel in a gas turbine engine |
EP2835516A1 (en) * | 2013-08-08 | 2015-02-11 | Alstom Technology Ltd | Gas turbine with improved part load emissions behavior |
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EP3369995A1 (en) * | 2017-03-02 | 2018-09-05 | Ansaldo Energia Switzerland AG | Mixer |
EP3486568A1 (en) * | 2017-11-20 | 2019-05-22 | Ansaldo Energia Switzerland AG | Method of controlling fuel injection in a reheat combustor for a cambustor assembly of a gas turbine and associated reheat combustor |
US20200378604A1 (en) * | 2019-05-30 | 2020-12-03 | Doosan Heavy Industries & Construction Co., Ltd. | Combustor with axial fuel staging system and gas turbine having the same |
-
2020
- 2020-12-24 EP EP20217211.0A patent/EP4019840B1/en active Active
-
2021
- 2021-12-20 CN CN202111561357.3A patent/CN114754377A/en active Pending
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WO2009078891A2 (en) * | 2007-09-14 | 2009-06-25 | Siemens Energy, Inc. | Secondary fuel delivery system |
WO2013022367A1 (en) * | 2011-08-11 | 2013-02-14 | General Electric Company | System for injecting fuel in a gas turbine engine |
EP2835516A1 (en) * | 2013-08-08 | 2015-02-11 | Alstom Technology Ltd | Gas turbine with improved part load emissions behavior |
US20160305337A1 (en) * | 2015-04-15 | 2016-10-20 | General Electric Company | Systems and methods for control of combustion dynamics in combustion system |
EP3369995A1 (en) * | 2017-03-02 | 2018-09-05 | Ansaldo Energia Switzerland AG | Mixer |
EP3486568A1 (en) * | 2017-11-20 | 2019-05-22 | Ansaldo Energia Switzerland AG | Method of controlling fuel injection in a reheat combustor for a cambustor assembly of a gas turbine and associated reheat combustor |
US20200378604A1 (en) * | 2019-05-30 | 2020-12-03 | Doosan Heavy Industries & Construction Co., Ltd. | Combustor with axial fuel staging system and gas turbine having the same |
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CN114754377A (en) | 2022-07-15 |
EP4019840B1 (en) | 2024-04-03 |
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