EP3543610B1 - Gas turbine having a damper - Google Patents
Gas turbine having a damper Download PDFInfo
- Publication number
- EP3543610B1 EP3543610B1 EP18425016.5A EP18425016A EP3543610B1 EP 3543610 B1 EP3543610 B1 EP 3543610B1 EP 18425016 A EP18425016 A EP 18425016A EP 3543610 B1 EP3543610 B1 EP 3543610B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- front plate
- damper
- chamber
- gas turbine
- air flow
- 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.)
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- 238000002485 combustion reaction Methods 0.000 claims description 21
- 238000013016 damping Methods 0.000 description 9
- 230000010349 pulsation Effects 0.000 description 9
- 239000000446 fuel Substances 0.000 description 8
- 238000000034 method Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 3
- 238000009420 retrofitting Methods 0.000 description 3
- 238000007493 shaping process Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005755 formation reaction Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000001902 propagating effect Effects 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
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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
-
- 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
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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
- 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
Definitions
- the present invention relates to a gas turbine and a method for retrofitting same.
- Gas turbines are known to comprise a compressor, a combustion chamber fed with: compressed air supplied from the compressor and with a fuel, in which combustion chamber the fuel is combusted generating a high pressure and high temperature hot gas, and a turbine where the hot gas is expanded to gather mechanical work.
- the compressor is connected to a plenum and the combustion chamber has a combustor with a front plate provided with burners.
- the front plate and the burners are housed in the plenum, such that the compressed air is supplied into the plenum and from the plenum it enters the burners where it is mixed with the fuel and thus passes into the combustor where combustion occurs.
- the combustion process can cause pulsations that, when occurs, should be controlled and damped to prevent mechanical failure of the components of the combustion chamber.
- Helmholtz damper A kind of damper often used in gas turbine applications is the so called: Helmholtz damper; Helmholtz dampers have a chamber: connected via a neck to the environment where pulsations to be damped are generated, such as the combustor of the combustion chamber.
- the frequency at which the pulsations are damped depends on the volume of the chamber and the length of the neck (actually the effective length that is longer than the geometrical length), such that to damp pulsations in the relevant frequency range (e.g. between 50-500 Hz) given proportions between the chamber volume and the neck length are required.
- the efficiency of the Helmholtz damper depends on the volume of the chamber, such that the larger the volume, the higher the damping effect.
- dampers such as half wave or quarter wave dampers; these dampers have similar constrains as the Helmholtz dampers with respect to geometrical proportions and volume. In the following description reference to Helmholtz dampers is made.
- the dampers should be provided at an area of the combustor close to the zone where the flame is anchored during operation, because it is there that the pulsations are generated.
- DE 10 2015 218677 A1 discloses a gas turbine having a compressor, a plenum connected to the compressor, a combustion chamber with a combustor having a front plate and burners connected to the front plate, and at least a damper connected to the front plate and housed in the plenum.
- the front plate and the burners are at least partially housed in the plenum and the damper has a chamber tailored to the space available between adjacent burners.
- Other examples of known gas turbines are disclosed in US 2017/082287 A1 and in US 2013/062425 A1 .
- An aspect of the invention includes providing a gas turbine with a damper that is able to efficiently damp pulsations in the required frequency range and at the same time that is provided at the required position of the combustor close to the area where the flame is anchored.
- FIGS. 1 show a gas turbine 1 having a compressor 2, a combustion chamber 3 and a turbine 4.
- the gas turbine further has a plenum 5-connected to the compressor 2; in the plenum 5 there is housed a front end of the combustion chamber 3.
- the combustion chamber 3 comprises a combustor 7 with a front plate 8 and burners 9 connected to the front plate 8.
- the burners 9 are connected to a fuel supply system (not shown) for fuel feeding.
- the gas turbine 1 comprises one or preferably more than one dampers 10 connected to the front plate 8 and housed in the plenum 5. This way the dampers are connected to an area of the combustion chamber close to the area where the flame is anchored, the combustion process takes place and pulsations can generate. Damping in this area prevents the pulsations from propagating through the combustor and possibly damaging it.
- the combustion chamber 3 is an annular combustion chamber and the burners 9 are provided over the entire circumference of the combustion chamber.
- the circumferential distance between the burners is constant, but it could also vary in particular applications.
- all the burners lay on one circumference ( figures 4 through 6 , 11, 12 ), but embodiments with burners laying on different circumferences, such as concentric circumferences, are also possible ( figure 7 ).
- the dampers 10 have a chamber 11 tailored to the space available between adjacent burners 9. This feature allows an optimized use of the available space, such that the volume of the chambers 11 and therefore the damping efficiency can be optimized, e.g. maximized.
- Preferably tailoring to the space available between adjacent dampers 10 is done in the plane of the front plate 8, as shown for example in figures 4 through 7 .
- Tailoring includes shaping the chamber 11 in the plane of the front plate 8 ( figures 4 through 7 ) for the chamber shape to adapt to the available space between the burners 9.
- the chamber 11 is further tailored to an outer perimeter 13 of the front plate 8.
- Tailoring includes shaping the chamber 11 in the plane of the front plane 8 ( figures 4 through 7 ) for the chamber shape to adapt to the available space delimited by the outer perimeter 13.
- a substantially triangular space can be defined between adjacent burners 9 and the outer perimeter 13 of the front plate 8, and the chamber 11 preferably has a substantially triangular shape and is housed in this space ( figure 4 ).
- the front plate 8 can be annular in shape and the chamber 11 can be further tailored to an inner perimeter 15 of the front plate 8.
- Tailoring includes shaping the chamber 11 in the plane of the front plane 8 ( figures 5 through 7 ) for the chamber shape to adapt to the available space delimited by the inner perimeter 15.
- a substantially triangular space can be defined between adjacent burners 9 and the inner perimeter 15 of the front plate 8, and the chamber 11 has a substantially triangular shape and: is housed in this space ( figure 5 ).
- the chamber 11 can extend between the outer perimeter 13 and the inner perimeter 15 of the annular front plate 8. In this case the use of the available space is further optimized ( figure 6 ).
- the chamber 11 can be tailored to a wall 16 delimiting the plenum 5 ( figures 9, 10 ).
- the damper 10 is a Helmholtz damper and comprises the chamber 11 and a neck 17 that is connected between the chamber 11 and the front plate 8.
- the damper 10 does not substantially affect the air flow through the burners 9, thus neither the total flow through all the burners 9, nor the flow through each burner 9 is substantially affected.
- this feature can promote retrofitting of existing gas turbines; this feature can also be useful in new gas turbines, e.g. for leaving open the possibility of upgrading or to allow the use of existing data on air flow through the dampers and/or formations of the air/fuel mixture and/or combustion during design.
- a first air flow F1 passes through the burner 9 when no dampers 10 are provided connected to the front plate 8
- a second air flow F2 passes through the burner 9 when the dampers 10 (one or more dampers) are connected to the front plate 8.
- the chamber 11 has a given size S in a direction facing away from the front plate 8.
- the given size S is limited so that the second air flow F2 is substantially the same as the first air flow F1.
- the limited size S is limited does not imply that it is less than or equal to the distance between the openings 18 for air entrance into the burners 9 and the front plate 8; the given size S can be less than or equal to or even greater than the distance between the openings 18 for air entrance into the burners 9 and the front plate 8, provided that the air flow into the burners 9 is not substantially counteracted.
- the mass flow distribution through the burners and for each burner is not substantially affected, i.e. it is not substantially changed in case the damper is provided or not.
- the gas turbine can be provided with guides 20 that influence the air flow F2, such that the distribution of the air flow F2 is substantially the same as the distribution of the air flow F1.
- the guides 20 can be defined by the shape of the chamber 11 ( figures 9 , 12 ) and/or neck 17; alternatively or in addition, the guides can also be defined by baffles or steering components provided within the plenum 5 ( figures 10 , 11 ) e.g. connected to the chamber 11 and/or to the neck 17 and/or not connected either to the chamber 11 or to the neck 17 but as separate elements.
- the compressor 2 compresses air and supplies it into the plenum 5. From the plenum 5 the air flow F2 of compressed air enters into the burners 9 via the openings 18, it is mixed with fuel and the mixture is fed into the combustor 7. In the combustor 7 the mixture is burned generating the hot gas that is expanded in the turbine 4.
- Pulsations that are generated into the combustor 7 are damper by the dampers 10. Damping is effective because thanks to the optimization of the use of the available space, the damper can be designed in order to match the frequency range to be damped and the damping efficiency with the requirements. Disclosed herein is also a method for retrofitting a gas turbine.
- the method comprises providing at least a damper 10 connected to the front plate 8 and housed in the plenum 5, the damper 10 having a shape tailored to the space available between adjacent burners 9.
- the damper 10 has a given size S facing away from the front plate 8, and the method comprises limiting the given size S so that the provision of the damper 10 does not affect, e.g. does not substantially causes a reduction of air flow through the burners 10.
- Figure 13 shows an arrangement of a damper 10 (as described before or also of different type) that is connected to the front plate 8.
- This arrangement is useful (but not mandatory) when the damper 10 has to be connected close to the position where the flame is anchored, e.g. the connection can be done to the front plate 8 or elsewhere.
- Figure 13 shows the Helmholtz damper having the chamber 11 and the neck 17 connected to the front plate 8; this figure also shows the burner 9 and a flame 21 generated by the fuel supplied via the burner 9; the flame can either be a premixed flame or a diffusion flame.
- the damper 10 has its terminal portion 23 inserted in an opening 25 of the front plate 8. In particular between the opening 25 and the terminal portion 23 a gap 26 (e.g. annular gap) is defined.
- the terminal portion 23 of the damper 10 facing the front plate 8 is flared.
- the gap 26 and the flared terminal portion 23 are advantageous because they provide an efficient way to cool the terminal portion 23.
- the gap 26 allows air flow through it; such an air flow cools the terminal part 23 of the damper 10.
- the gap 26 constitutes a restricting nozzle for the air- flow (e.g. because of the flared terminal portion 23) the air flow accelerates when passing through the gap 26, further improving the cooling efficiency.
- the flared terminal portion 23 defines a diverging nozzle that injects the air flow away from the neck 17, e.g. over a conical path.
- the vortices 28 at the neck 17 are thus not affected and damping efficiency is consequently not affected.
- this arrangement advantageously allows to cool the neck 17 preventing its damage without affecting its damping efficiency.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Description
- The present invention relates to a gas turbine and a method for retrofitting same.
- Gas turbines are known to comprise a compressor, a combustion chamber fed with: compressed air supplied from the compressor and with a fuel, in which combustion chamber the fuel is combusted generating a high pressure and high temperature hot gas, and a turbine where the hot gas is expanded to gather mechanical work.
- In particular, the compressor is connected to a plenum and the combustion chamber has a combustor with a front plate provided with burners. The front plate and the burners are housed in the plenum, such that the compressed air is supplied into the plenum and from the plenum it enters the burners where it is mixed with the fuel and thus passes into the combustor where combustion occurs.
- The combustion process can cause pulsations that, when occurs, should be controlled and damped to prevent mechanical failure of the components of the combustion chamber.
- A kind of damper often used in gas turbine applications is the so called: Helmholtz damper; Helmholtz dampers have a chamber: connected via a neck to the environment where pulsations to be damped are generated, such as the combustor of the combustion chamber.
- The frequency at which the pulsations are damped depends on the volume of the chamber and the length of the neck (actually the effective length that is longer than the geometrical length), such that to damp pulsations in the relevant frequency range (e.g. between 50-500 Hz) given proportions between the chamber volume and the neck length are required.
- In addition, the efficiency of the Helmholtz damper depends on the volume of the chamber, such that the larger the volume, the higher the damping effect.
- Other kinds of dampers are known, such as half wave or quarter wave dampers; these dampers have similar constrains as the Helmholtz dampers with respect to geometrical proportions and volume. In the following description reference to Helmholtz dampers is made.
- In order to optimize the damping effect, the dampers should be provided at an area of the combustor close to the zone where the flame is anchored during operation, because it is there that the pulsations are generated.
- Nevertheless, because of the constrains imposed by the required geometrical proportions of the damper, the volume of the chamber, and the very few space available in the area of the combustor, it could be difficult or even impossible to provide dampers with the required features and at the required position.
DE 10 2015 218677 A1 discloses a gas turbine having a compressor, a plenum connected to the compressor, a combustion chamber with a combustor having a front plate and burners connected to the front plate, and at least a damper connected to the front plate and housed in the plenum. The front plate and the burners are at least partially housed in the plenum and the damper has a chamber tailored to the space available between adjacent burners. Other examples of known gas turbines are disclosed inUS 2017/082287 A1 and inUS 2013/062425 A1 . - An aspect of the invention includes providing a gas turbine with a damper that is able to efficiently damp pulsations in the required frequency range and at the same time that is provided at the required position of the combustor close to the area where the flame is anchored.
- These and further aspects are attained by providing a gas turbine in accordance with the accompanying claims.
- Further characteristics and advantages will be more apparent from the description of a preferred but non-exclusive embodiment of the gas turbine according to the invention, illustrated by way of non-limiting example in the accompanying drawings, in which:
-
Figure 1 schematically shows a gas turbine; -
Figure 2 shows a portion of a combustion chamber of a gas turbine without dampers; -
Figure 3 shows a portion of a combustion chamber of a gas turbine with dampers; -
Figures 4 through 7 show different examples of a front plate with burners and dampers; -
Figures 8 through 10 show enlarged portions of the front plate and the area around it in different embodiments; -
Figures 11 through 12 show different examples of dampers; -
Figure 13 shows a damper connected to a front plate. - With reference to the figures, these show a
gas turbine 1 having acompressor 2, acombustion chamber 3 and aturbine 4. The gas turbine further has a plenum 5-connected to thecompressor 2; in theplenum 5 there is housed a front end of thecombustion chamber 3. Thecombustion chamber 3 comprises acombustor 7 with afront plate 8 andburners 9 connected to thefront plate 8. Theburners 9 are connected to a fuel supply system (not shown) for fuel feeding. - The
gas turbine 1 comprises one or preferably more than onedampers 10 connected to thefront plate 8 and housed in theplenum 5. This way the dampers are connected to an area of the combustion chamber close to the area where the flame is anchored, the combustion process takes place and pulsations can generate. Damping in this area prevents the pulsations from propagating through the combustor and possibly damaging it. - In a preferred embodiment the
combustion chamber 3 is an annular combustion chamber and theburners 9 are provided over the entire circumference of the combustion chamber. Preferably the circumferential distance between the burners is constant, but it could also vary in particular applications. Preferably all the burners lay on one circumference (figures 4 through 6 ,11, 12 ), but embodiments with burners laying on different circumferences, such as concentric circumferences, are also possible (figure 7 ). - The
dampers 10 have achamber 11 tailored to the space available betweenadjacent burners 9. This feature allows an optimized use of the available space, such that the volume of thechambers 11 and therefore the damping efficiency can be optimized, e.g. maximized. - Preferably tailoring to the space available between
adjacent dampers 10 is done in the plane of thefront plate 8, as shown for example infigures 4 through 7 . - Tailoring includes shaping the
chamber 11 in the plane of the front plate 8 (figures 4 through 7 ) for the chamber shape to adapt to the available space between theburners 9. - Preferably, in order to further optimize the use of the available space, the
chamber 11 is further tailored to anouter perimeter 13 of thefront plate 8. - Tailoring includes shaping the
chamber 11 in the plane of the front plane 8 (figures 4 through 7 ) for the chamber shape to adapt to the available space delimited by theouter perimeter 13. - For example, a substantially triangular space can be defined between
adjacent burners 9 and theouter perimeter 13 of thefront plate 8, and thechamber 11 preferably has a substantially triangular shape and is housed in this space (figure 4 ). - In addition or alternatively, the
front plate 8 can be annular in shape and thechamber 11 can be further tailored to aninner perimeter 15 of thefront plate 8. - Tailoring includes shaping the
chamber 11 in the plane of the front plane 8 (figures 5 through 7 ) for the chamber shape to adapt to the available space delimited by theinner perimeter 15. - For example, a substantially triangular space can be defined between
adjacent burners 9 and theinner perimeter 15 of thefront plate 8, and thechamber 11 has a substantially triangular shape and: is housed in this space (figure 5 ). - In a further example, the
chamber 11 can extend between theouter perimeter 13 and theinner perimeter 15 of theannular front plate 8. In this case the use of the available space is further optimized (figure 6 ). - In addition, in order to even further optimize the use of the available space, the
chamber 11 can be tailored to awall 16 delimiting the plenum 5 (figures 9, 10 ). - The
damper 10 is a Helmholtz damper and comprises thechamber 11 and aneck 17 that is connected between thechamber 11 and thefront plate 8. - In a preferred and advantageous embodiment, the
damper 10 does not substantially affect the air flow through theburners 9, thus neither the total flow through all theburners 9, nor the flow through eachburner 9 is substantially affected. For example this feature can promote retrofitting of existing gas turbines; this feature can also be useful in new gas turbines, e.g. for leaving open the possibility of upgrading or to allow the use of existing data on air flow through the dampers and/or formations of the air/fuel mixture and/or combustion during design. - With reference to
figures 2 and 3 , during operation a first air flow F1 passes through theburner 9 when nodampers 10 are provided connected to thefront plate 8, and a second air flow F2 passes through theburner 9 when the dampers 10 (one or more dampers) are connected to thefront plate 8. - The
chamber 11 has a given size S in a direction facing away from thefront plate 8. Advantageously, the given size S is limited so that the second air flow F2 is substantially the same as the first air flow F1. - The fact that the limited size S is limited does not imply that it is less than or equal to the distance between the
openings 18 for air entrance into theburners 9 and thefront plate 8; the given size S can be less than or equal to or even greater than the distance between theopenings 18 for air entrance into theburners 9 and thefront plate 8, provided that the air flow into theburners 9 is not substantially counteracted. - In addition, in a particularly advantageous embodiment the mass flow distribution through the burners and for each burner is not substantially affected, i.e. it is not substantially changed in case the damper is provided or not.
- In this connection, the gas turbine can be provided with
guides 20 that influence the air flow F2, such that the distribution of the air flow F2 is substantially the same as the distribution of the air flow F1. Theguides 20 can be defined by the shape of the chamber 11 (figures 9 ,12 ) and/orneck 17; alternatively or in addition, the guides can also be defined by baffles or steering components provided within the plenum 5 (figures 10 ,11 ) e.g. connected to thechamber 11 and/or to theneck 17 and/or not connected either to thechamber 11 or to theneck 17 but as separate elements. - The operation of the gas turbine is apparent from that described and illustrated and is substantially the following.
- The
compressor 2 compresses air and supplies it into theplenum 5. From theplenum 5 the air flow F2 of compressed air enters into theburners 9 via theopenings 18, it is mixed with fuel and the mixture is fed into thecombustor 7. In thecombustor 7 the mixture is burned generating the hot gas that is expanded in theturbine 4. - Pulsations that are generated into the
combustor 7 are damper by thedampers 10. Damping is effective because thanks to the optimization of the use of the available space, the damper can be designed in order to match the frequency range to be damped and the damping efficiency with the requirements. Disclosed herein is also a method for retrofitting a gas turbine. - In particular, the method comprises providing at least a
damper 10 connected to thefront plate 8 and housed in theplenum 5, thedamper 10 having a shape tailored to the space available betweenadjacent burners 9. - In a preferred embodiment of the method, the
damper 10 has a given size S facing away from thefront plate 8, and the method comprises limiting the given size S so that the provision of thedamper 10 does not affect, e.g. does not substantially causes a reduction of air flow through theburners 10. -
Figure 13 shows an arrangement of a damper 10 (as described before or also of different type) that is connected to thefront plate 8. - This arrangement is useful (but not mandatory) when the
damper 10 has to be connected close to the position where the flame is anchored, e.g. the connection can be done to thefront plate 8 or elsewhere. -
Figure 13 shows the Helmholtz damper having thechamber 11 and theneck 17 connected to thefront plate 8; this figure also shows theburner 9 and aflame 21 generated by the fuel supplied via theburner 9; the flame can either be a premixed flame or a diffusion flame. - The
damper 10 has itsterminal portion 23 inserted in anopening 25 of thefront plate 8. In particular between theopening 25 and the terminal portion 23 a gap 26 (e.g. annular gap) is defined. Theterminal portion 23 of thedamper 10 facing thefront plate 8 is flared. - The
gap 26 and the flaredterminal portion 23 are advantageous because they provide an efficient way to cool theterminal portion 23. In fact, thegap 26 allows air flow through it; such an air flow cools theterminal part 23 of thedamper 10. - In addition, since the
gap 26 constitutes a restricting nozzle for the air- flow (e.g. because of the flared terminal portion 23) the air flow accelerates when passing through thegap 26, further improving the cooling efficiency. - In addition, notwithstanding the cooling, the operation of the
damper 10 and thus its damping efficiency is not affected. In fact the flaredterminal portion 23 defines a diverging nozzle that injects the air flow away from theneck 17, e.g. over a conical path. Thevortices 28 at the neck 17 (these vortices damp the vibrations) are thus not affected and damping efficiency is consequently not affected. - For example, when the
damper 10 is at a position close to theflame 21, this arrangement advantageously allows to cool theneck 17 preventing its damage without affecting its damping efficiency. - In practice the materials used and the dimensions can be chosen at will according to requirements and to the state of the art.
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- 1
- gas turbine
- 2
- compressor
- 3
- combustion chamber
- 4
- turbine
- 5
- plenum
- 7
- combustor
- 8
- front plate
- 9
- burners
- 10
- damper
- 11
- chamber
- 13
- outer perimeter
- 15
- inner perimeter
- 16
- wall of the plenum
- 17
- neck
- 18
- openings
- 20
- guide
- 21
- flame
- 23
- terminal portion
- 25
- opening
- 26
- gap
- 28
- vortices
- F1
- first air flow
- F2
- second air flow
- S
- size of the damper
Claims (12)
- A gas turbine (1) having a compressor (2), a plenum (5) connected to the compressor (2), a combustion chamber (3) with a combustor (7) having a front plate (8) and burners (9) connected to the front plate (8), and at least a damper (10) connected to the front plate (8) and housed in the plenum (5), the front plate (8) and the burners (9) being at least partially housed in the plenum (5), the damper (10) having a chamber (11) tailored to the space available between adjacent burners (9); characterized in that the damper (10) is a Helmholtz damper and comprises the chamber (11) and a neck (17), the neck (17) being connected between the chamber (11) and the front plate (8).
- The gas turbine (1) according to claim 1, characterized in that the chamber (11) of the damper (10) is further tailored to an outer perimeter (13) of the front plate (8).
- The gas turbine (1) according to claim 2, characterized in that a substantially triangular space is defined between adjacent burners (9) and the outer perimeter (13) of the front plate (8), the chamber (11) having a substantially triangular shape and being housed in this space.
- The gas turbine (1) according to any one of claims 1 through 3, characterized in that the front plate (8) is annular in shape and the chamber (11) is further tailored to an inner perimeter (15) of the front plate (8).
- The gas turbine (1) according to claim 4, characterized in that a substantially triangular space is defined between adjacent burners (9) and the inner perimeter (15) of the front plate (8), the chamber (11) having a substantially triangular shape and being housed in this space.
- The gas turbine (1) according to claim 2 and 4, characterized in that the chamber (11) extends between the outer perimeter (13) and the inner perimeter (15) of the annular front plate (8).
- The gas turbine (1) according to any one of the previous claims, characterized in that the chamber (11) is tailored to a wall delimiting the plenum (5).
- The gas turbine (1) according to any one of the previous claims, characterized in that during operation
a first air flow (F1) passes through the burners (9) when no damper (10) is provided connected to the front plate (8), and
a second air flow (F2) passes through the burners (9) when the damper (10) is provided connected to the front plate (8),
wherein
the chamber (11) has a given size (S) in a direction facing away from the front plate (8), and
the given size (S) is such that the second air flow (F2) is the same as the first air flow (F1). - The gas turbine (1) according to any one of the previous claims, characterized in that during operation
a first air flow (F1) passes through the burners (9) when no damper (10) is provided connected to the front plate (8), and
a second air flow (F2) passes through the burners (9) when the damper (10) is provided connected to the front plate (8),
characterized by being provided with at least a guide that influences the second air flow (F2), such that the distribution of the second air flow (F2) is substantially the same as the distribution of the first air flow (F1). - The gas turbine (1) according to claim 9, characterized in that the at least a guide is defined by the shape of the chamber (11) and/or neck (17), and/or the at least a guide is defined by at least a baffle or steering component provided within the plenum (5).
- The gas turbine (1) according to any one of the previous claims, characterized in that the damper (10) has a terminal portion (23) facing the front plate (8),
the front plate (8) has an opening (25),
the terminal portion (23) is flared,
the terminal portion (23) is inserted into the opening (25),
a gap (26) is defined between the terminal portion (23) and the opening (25),
the gap (26) defines a diverging nozzle for injecting the air flow away from the damper (10). - The gas turbine (1) according to claim 11, characterized in that the gap (26) defines a restricting nozzle that accelerates the air flow passing through it.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18425016.5A EP3543610B1 (en) | 2018-03-23 | 2018-03-23 | Gas turbine having a damper |
RU2019108054A RU2784917C2 (en) | 2018-03-23 | 2019-03-21 | Gas turbine installation and its modernization method |
CN201910221387.6A CN110296440B (en) | 2018-03-23 | 2019-03-22 | Gas turbine and method for improving the same |
Applications Claiming Priority (1)
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EP18425016.5A EP3543610B1 (en) | 2018-03-23 | 2018-03-23 | Gas turbine having a damper |
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EP3543610A1 EP3543610A1 (en) | 2019-09-25 |
EP3543610B1 true EP3543610B1 (en) | 2021-05-05 |
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DE102005062284B4 (en) * | 2005-12-24 | 2019-02-28 | Ansaldo Energia Ip Uk Limited | Combustion chamber for a gas turbine |
US8474265B2 (en) * | 2009-07-29 | 2013-07-02 | General Electric Company | Fuel nozzle for a turbine combustor, and methods of forming same |
EP2397760B1 (en) * | 2010-06-16 | 2020-11-18 | Ansaldo Energia IP UK Limited | Damper Arrangement and Method for Designing Same |
US8443611B2 (en) * | 2011-09-09 | 2013-05-21 | General Electric Company | System and method for damping combustor nozzle vibrations |
EP2642203A1 (en) * | 2012-03-20 | 2013-09-25 | Alstom Technology Ltd | Annular Helmholtz damper |
US9447971B2 (en) * | 2012-05-02 | 2016-09-20 | General Electric Company | Acoustic resonator located at flow sleeve of gas turbine combustor |
EP2762784B1 (en) * | 2012-11-30 | 2016-02-03 | Alstom Technology Ltd | Damping device for a gas turbine combustor |
EP2816288B1 (en) * | 2013-05-24 | 2019-09-04 | Ansaldo Energia IP UK Limited | Combustion chamber for a gas turbine with a vibration damper |
EP2816289B1 (en) * | 2013-05-24 | 2020-10-07 | Ansaldo Energia IP UK Limited | Damper for gas turbine |
WO2015176887A1 (en) * | 2014-05-19 | 2015-11-26 | Siemens Aktiengesellschaft | Burner arrangement with resonator |
CN104595928B (en) * | 2015-01-23 | 2020-02-14 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Acoustic flame tube of diffusion combustion chamber |
DE102015218677A1 (en) * | 2015-09-29 | 2017-03-30 | Siemens Aktiengesellschaft | Burner arrangement with resonator |
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RU2019108054A (en) | 2020-09-22 |
EP3543610A1 (en) | 2019-09-25 |
CN110296440A (en) | 2019-10-01 |
CN110296440B (en) | 2022-07-08 |
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