EP2938927B1 - Gas turbine burner assembly equipped with a helmholtz resonator - Google Patents
Gas turbine burner assembly equipped with a helmholtz resonator Download PDFInfo
- Publication number
- EP2938927B1 EP2938927B1 EP13831874.6A EP13831874A EP2938927B1 EP 2938927 B1 EP2938927 B1 EP 2938927B1 EP 13831874 A EP13831874 A EP 13831874A EP 2938927 B1 EP2938927 B1 EP 2938927B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- outer body
- resonant chamber
- burner assembly
- assembly
- 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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Links
- 238000002485 combustion reaction Methods 0.000 claims description 26
- 230000000712 assembly Effects 0.000 claims description 10
- 238000000429 assembly Methods 0.000 claims description 10
- 210000003739 neck Anatomy 0.000 claims description 10
- 238000013016 damping Methods 0.000 claims description 6
- 238000001816 cooling Methods 0.000 description 7
- 239000000446 fuel Substances 0.000 description 7
- 230000010355 oscillation Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 239000012530 fluid Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000003491 array Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000009420 retrofitting Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 239000003517 fume Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- 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 turbine burner assembly equipped with a Helmholtz resonator.
- thermoacoustic oscillations which may cause flame instability and a significant degradation in the quality of combustion, needs be solved in large-sized gas turbines, in particular those used in plants for the production of electricity. Therefore, machine performance in terms of power and efficiency, and plant flexibility are highly penalized. Emissions may degrade as well.
- a solution which is becoming popular includes the use of Helmholtz resonators, which have the effect of damping acoustic oscillations in given frequency bands.
- a Helmholtz resonator comprises a resonant chamber placed in fluidic communication with the outside, in particular with the combustion chamber, through fluidic openings or channels. The volume of the resonant chamber and the features of the fluidic channels determine the frequency band in which the resonator is effective.
- the known resonators are generally installed about the combustion chamber either on the burner inserts or directly on the burners.
- the resonators are fixed to the outer wall of the combustion chamber and communicate with the inside through the side wall itself.
- This solution allows to make high-volume resonators but on the other hand has many disadvantages.
- the combustion chamber needs to be specifically modified for the purpose of accommodating the resonators.
- the presence of the resonators affects the step of cooling and results in a large weight bearing on the structure.
- the resonators installed aboard the inserts are simple to be applied, but allow to obtain only modest volumes given the small available space.
- the resonators installed aboard the burner are arranged so that the resonant chamber is directly in fluidic continuity with the inside of the burner, in particular with the air and fluid mixing channels.
- the connection is generally obtained by an opening downstream of the fluid injection nozzles. This solution is critical because it acts directly on the pressure oscillations which propagate from the combustion zone into the mixing channels. The pressure oscillations may not be adequately damped, or could even be amplified, if the resonator is not perfectly tuned to the frequency to be damped.
- a turbine burner assembly comprises a main burner and a Helmholtz resonator.
- the main burner extends about an axis and comprises an inner body and an outer body with a frustoconical wall and a diagonal swirler arranged therebetween.
- An inlet of the swirler being located at a larger base of the frustoconical wall of the outer body.
- the Helmholtz resonator has a resonant chamber and passages for fluidic connection of the resonant chamber to the outside.
- a turbine burner assembly is provided as defined in claim 1.
- a gas turbine system for the production of electricity is indicated as a whole by reference numeral 1 and comprises a compressor 2, a combustion chamber 3 and a turbine 5.
- Compressor 2 combustion chamber 3 and turbine 5 form a turbine assembly which may be fed with fluid fuels of various type, in particular, but not only, natural gas, syngas, diesel.
- Compressor 2 and turbine 5 are mounted to the same shaft in order to form a rotor 7, which is accommodated in a casing 8 and extends along an axis A.
- rotor 7 is provided with a plurality of compressor rotor blades 10 and turbine rotor blades 11, organized in annular arrays, which are arranged in sequence along axis A of the rotor 7 itself.
- Arrays of compressor stator blades 12 and turbine stator blades 13 are fixed to casing 8 and spaced apart between the compressor rotor blade 10 and the turbine rotor blades 11, respectively.
- the combustion chamber 3 is of the toroidal type and arranged about rotor 7 between compressor 2 and turbine 5.
- this must not be considered limitative, because the invention may be advantageously used also with combustion chambers of different type, in particular of the silo type.
- the combustion chamber 3 comprises a plurality of burner assemblies 15, which are arranged on a circumference and are evenly angularly spaced apart.
- the burner assemblies 15 are mounted to respective burner seats 16 of the combustion chamber by respective burner inserts 17.
- FIG. 2 shows in detail one of the burner assemblies 15 used for feeding fuel, in particular a gas, to the combustion chamber 3.
- the burner assembly 15 extends along an axis B and comprises a main peripheral burner 20, a central pilot burner 21, coaxial to the main burner 20, and a Helmholtz resonator 22.
- the main burner 20 is of the premixing type, arranged about the pilot burner 21 and fixed to the respective burner insert 17. More in detail, the main burner 20 extends through a central opening 17a of the burner insert 17, so that the outlet of the main burner 20 is within the combustion chamber 3.
- the main burner 20 is provided with a vortex or turbulence- generating device, referred to as diagonal swirler, and indicated by reference numeral 23.
- the diagonal swirler 23 extends about axis B and is radially defined between an inner body 25 and an outer body 26 of the main burner 20.
- the inner body 25 has a cylindrical axial cavity in which the pilot burner 21 is accommodated and is substantially frustoconical in shape towards the outside.
- the outer body 26 is axially hollow and comprises a frustoconical wall 26a and a cylindrical wall 26b, connected to each other by a joining portion 26c.
- the frustoconical wall 26a accommodates the inner body 25, so that a substantially annular space forming a passage for feeding the air-fuel mixture is defined between the frustoconical wall 26a of the outer body 26 and the inner body 25.
- the diagonal swirler 23 further comprises an array of blades 28 which extend in the space between the inner body 25 and the outer body 26 and define respective mixing channels 30 to convey a mixture of combustion supporting air and fuel towards the combustion chamber 3 with a diagonal pattern with respect to axis B.
- the blades 28 are fixed to the outer body 16 by specific nuts 29a arranged through respective holes 29b made in the frustoconical wall 26a along a circumference.
- the seals 29c ensure the fluidic decoupling between the volume of resonator 22 and the premixing channel 30.
- the inlet 31 of the mixing channels 30 is defined at a larger base of the frustoconical wall 26a of the outer body 26 and allows the introduction of an air flow from compressor 2.
- Nozzles 32 arranged close to the inlet 31 of the mixing channels 30, are connected to a premix feeding line (not shown) and allow the injection of a controlled fuel flow rate inside the mixing channels 30 themselves.
- the nozzles 32 are arranged on the blades 28. The air from compressor 2 and the injected fuel through nozzles 32 admix in the mixing channels 30. The air-fuel mixture flow thus produced develops towards the cylindrical wall 26b, which leads into the combustion chamber 3.
- the Helmholtz resonator 22 comprises a resonant chamber 35 and necks 36 for fluidly connecting the resonant chamber 35 to the outside.
- the resonant chamber 35 is substantially annular in shape and arranged about the frustoconical wall 26a of the-outer body 26, between the inlet 31 of the diagonal swirler 23 and the burner insert 17. According to the invention, the resonant chamber 35 is placed in one edge of the outer body 26 adjacent to the inlet 31 of the diagonal swirler 23. More in detail, the resonant chamber 35 is delimited internally by the frustoconical wall 26a of the outer body 26 and externally by, an annular closing wall 38. In axial direction, the annular closing wall 38 extends on the side of compressor 2 to one edge of the outer body 26 corresponding to the inlet 31 of the mixing channel 30.
- the annular closing wall 38 is delimited by a connection ring 39 of the outer body 26, by which the burner assembly 15 is coupled to the burner insert 17 itself.
- the annular closing wall 38 is reversibly coupled to the frustoconical wall 26a of the outer body 26, e.g. by screw fastening means (not shown).
- the annular closing wall 38 may be welded to or made integrally in one piece with the frustoconical wall 26a.
- the annular closing wall 38 has a plurality of connection holes 37, which are arranged along a circumference and define passages to allow the introduction of an air flow from compressor 2 into the resonant chamber 35.
- the connection ring 39 ( figure 3 ) has a T-shaped crosswise section, and a first portion 39a and a second portion 39b.
- the first portion 39a which is planar and defines a leg of the T-shaped section, substantially extends on a plane perpendicular to axis B of the burner assembly 15 and delimits the resonant chamber 35 in axial direction on the side towards the burner insert 17 and the combustion chamber 3.
- the second portion 39b of the connection ring 39 is substantially cylindrical and extends perpendicular to the first portion 39a on opposite sides thereof.
- the second portion 39a of the connection ring 39 is in contact with the annular closing wall 38, while an outer side surface is coupled to the burner insert 17.
- the second portion 39b has cooling passages 40, defined by grooves made on an outer face along a circumference and extending in axial direction.
- the cooling passages 40 put the delivery air of compressor 2 into communication with the combustion chamber 3, thus cooling the burner insert 17.
- the inlet of the cooling passages 40 is on the side towards compressor 2 with respect to the first portion 39a of the connection ring 39.
- the cooling passages 40 ensure a continuous cooling of the burner insert 17 independently of the assembly uncertainties and of the effects of thermal expansion.
- the necks 36 of the Helmholtz resonator 22 run on the outer surface of the frustoconical wall 26 and extend through the connection ring 39 and the burner insert 17.
- the resonant chamber 35 and the openings of necks 36 are on opposite sides with respect to the burner insert 17.
- the necks 36 are thus arranged to put the resonant chamber 35 into fluidic communication with the outside through the connection ring 39 and the burner insert 17.
- the resonant chamber 35 is free from direct fluidic connections with the mixing channels 30 of the diagonal swirler 23.
- the separation of the two environments is ensured by the frustoconical wall 26a and by the seals 29c between the frustoconical wall 26a and the nuts 29a, which prevent leakages through the holes 29b.
- the resonant chamber 35 is fluidly coupled only to the combustion chamber 3 through the necks 36.
- connection holes 37 in the annular closing wall 38 have a three-fold effect: they allow to maintain an air flow from compressor 2 to combustion chamber 3 through the resonant chamber 35, thus avoiding backflows of hot fumes towards the resonant chamber 35 itself; they allow to maintain the thermodynamic properties inside the resonant chamber 35 approximately constant; and they expand the resonance band of the dynamic pressure fluctuations in combustion chamber 3.
- the Helmholtz resonators 22 may be fitted either on all the burner assemblies 15 or only on some, as needed. Furthermore, the Helmholtz resonators 22 may be mutually different. The band features of each Helmholtz resonator 22 are indeed determined by the geometry of resonant chamber 35, necks 36 and connection holes 37. In order to optimize the thermoacoustic oscillation damping effect on the most critical frequency bands, the Helmholtz resonators 22 may be tuned to respective frequencies by selecting, for each one, the volume and shape of the resonant chamber 35, the number, length and cross section (area and profile) of the necks 36 and the number, position and diameter of the connection holes 37. In one embodiment, for example, each Helmholtz resonator 22 has a respective damping band, and the damping bands of Helmholtz resonators of different burner assemblies do not coincide, although they may be partially overlapping.
- the burner assemblies of the described type have various advantages. Firstly, large volume resonant chambers may be obtained without major modifications to the combustion chamber (also for retrofitting interventions) and without significantly bearing on the structure. Indeed, on one hand, the available space about the main burner up to the inlet of the swirler is wide, and thus Helmholtz resonators of relatively large, volume can be manufactured. On the other hand, the resonant chamber is partially delimited by structural elements which belong to the main burner. The addition of the annular closing wall only allows to complete the resonant chamber without noticeable changes to the burner assembly and without a significant increase of weight. Minor adaptations are thus sufficient to accommodate the necks of the Helmholtz resonator. Furthermore, the described solution allows to select the most appropriate geometries for the Helmholtz resonator, with a wide margin of flexibility.
- a further advantage is that the burner assemblies, in particular the inlet region of the diagonal swirlers, are easily accessible. The maintenance or retrofitting interventions may thus be carried out easily.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Gas Burners (AREA)
- Cyclones (AREA)
Description
- The present invention relates to a turbine burner assembly equipped with a Helmholtz resonator.
- As known, the problem of thermoacoustic oscillations, which may cause flame instability and a significant degradation in the quality of combustion, needs be solved in large-sized gas turbines, in particular those used in plants for the production of electricity. Therefore, machine performance in terms of power and efficiency, and plant flexibility are highly penalized. Emissions may degrade as well.
- A solution which is becoming popular includes the use of Helmholtz resonators, which have the effect of damping acoustic oscillations in given frequency bands. A Helmholtz resonator comprises a resonant chamber placed in fluidic communication with the outside, in particular with the combustion chamber, through fluidic openings or channels. The volume of the resonant chamber and the features of the fluidic channels determine the frequency band in which the resonator is effective.
- The known resonators are generally installed about the combustion chamber either on the burner inserts or directly on the burners.
- In the first case, the resonators are fixed to the outer wall of the combustion chamber and communicate with the inside through the side wall itself. This solution allows to make high-volume resonators but on the other hand has many disadvantages. Firstly, the combustion chamber needs to be specifically modified for the purpose of accommodating the resonators. Furthermore, the presence of the resonators affects the step of cooling and results in a large weight bearing on the structure.
- The resonators installed aboard the inserts are simple to be applied, but allow to obtain only modest volumes given the small available space.
- The resonators installed aboard the burner are arranged so that the resonant chamber is directly in fluidic continuity with the inside of the burner, in particular with the air and fluid mixing channels. The connection is generally obtained by an opening downstream of the fluid injection nozzles. This solution is critical because it acts directly on the pressure oscillations which propagate from the combustion zone into the mixing channels. The pressure oscillations may not be adequately damped, or could even be amplified, if the resonator is not perfectly tuned to the frequency to be damped.
- According to
EP 1 342 953 A1 , a turbine burner assembly comprises a main burner and a Helmholtz resonator. The main burner extends about an axis and comprises an inner body and an outer body with a frustoconical wall and a diagonal swirler arranged therebetween. An inlet of the swirler being located at a larger base of the frustoconical wall of the outer body. The Helmholtz resonator has a resonant chamber and passages for fluidic connection of the resonant chamber to the outside. - Other examples of known burner assemblies are disclosed in
EP 2 187 125 A1US 5 644 918 A - Therefore, it is the object of the present invention to provide a burner for a turbine which allows to overcome the described constraints.
- According to the present invention, a turbine burner assembly is provided as defined in claim 1.
- The present invention will now be described with reference to the accompanying drawings, which show some non-limitative embodiments thereof, in which:
-
figure 1 is a side view, taken along a longitudinal plane, of a portion of a gas turbine system; -
figure 2 is a side view, taken along a longitudinal plane, of a burner assembly in accordance with an embodiment of the present invention incorporated in the system infigure 1 ; -
figure 3 is a perspective view, taken along a different longitudinal plane and with parts removed for clarity, of an enlarged detail of the burner assembly infigure 2 ; and -
figure 4 is a different perspective view of the detail infigure 3 , with parts removed for clarity. - With reference to
figure 1 , a gas turbine system for the production of electricity is indicated as a whole by reference numeral 1 and comprises acompressor 2, acombustion chamber 3 and aturbine 5. -
Compressor 2,combustion chamber 3 andturbine 5 form a turbine assembly which may be fed with fluid fuels of various type, in particular, but not only, natural gas, syngas, diesel. -
Compressor 2 andturbine 5 are mounted to the same shaft in order to form a rotor 7, which is accommodated in acasing 8 and extends along an axis A. - More in detail, rotor 7 is provided with a plurality of
compressor rotor blades 10 andturbine rotor blades 11, organized in annular arrays, which are arranged in sequence along axis A of the rotor 7 itself. - Arrays of
compressor stator blades 12 andturbine stator blades 13 are fixed tocasing 8 and spaced apart between thecompressor rotor blade 10 and theturbine rotor blades 11, respectively. - In the embodiment described herein, the
combustion chamber 3 is of the toroidal type and arranged about rotor 7 betweencompressor 2 andturbine 5. However, this must not be considered limitative, because the invention may be advantageously used also with combustion chambers of different type, in particular of the silo type. - The
combustion chamber 3 comprises a plurality ofburner assemblies 15, which are arranged on a circumference and are evenly angularly spaced apart. Theburner assemblies 15 are mounted torespective burner seats 16 of the combustion chamber by respective burner inserts 17. -
Figure 2 shows in detail one of theburner assemblies 15 used for feeding fuel, in particular a gas, to thecombustion chamber 3. Theburner assembly 15 extends along an axis B and comprises a mainperipheral burner 20, acentral pilot burner 21, coaxial to themain burner 20, and aHelmholtz resonator 22. - The
main burner 20 is of the premixing type, arranged about thepilot burner 21 and fixed to therespective burner insert 17. More in detail, themain burner 20 extends through acentral opening 17a of theburner insert 17, so that the outlet of themain burner 20 is within thecombustion chamber 3. - The
main burner 20 is provided with a vortex or turbulence- generating device, referred to as diagonal swirler, and indicated byreference numeral 23. - The
diagonal swirler 23 extends about axis B and is radially defined between aninner body 25 and anouter body 26 of themain burner 20. Theinner body 25 has a cylindrical axial cavity in which thepilot burner 21 is accommodated and is substantially frustoconical in shape towards the outside. Theouter body 26 is axially hollow and comprises afrustoconical wall 26a and acylindrical wall 26b, connected to each other by a joiningportion 26c. Thefrustoconical wall 26a accommodates theinner body 25, so that a substantially annular space forming a passage for feeding the air-fuel mixture is defined between thefrustoconical wall 26a of theouter body 26 and theinner body 25. - The
diagonal swirler 23 further comprises an array ofblades 28 which extend in the space between theinner body 25 and theouter body 26 and definerespective mixing channels 30 to convey a mixture of combustion supporting air and fuel towards thecombustion chamber 3 with a diagonal pattern with respect to axis B. Theblades 28 are fixed to theouter body 16 byspecific nuts 29a arranged throughrespective holes 29b made in thefrustoconical wall 26a along a circumference. Theseals 29c ensure the fluidic decoupling between the volume ofresonator 22 and thepremixing channel 30. Theinlet 31 of the mixingchannels 30 is defined at a larger base of thefrustoconical wall 26a of theouter body 26 and allows the introduction of an air flow fromcompressor 2.Nozzles 32, arranged close to theinlet 31 of the mixingchannels 30, are connected to a premix feeding line (not shown) and allow the injection of a controlled fuel flow rate inside the mixingchannels 30 themselves. In an embodiment, thenozzles 32 are arranged on theblades 28. The air fromcompressor 2 and the injected fuel throughnozzles 32 admix in the mixingchannels 30. The air-fuel mixture flow thus produced develops towards thecylindrical wall 26b, which leads into thecombustion chamber 3. - The
Helmholtz resonator 22 comprises aresonant chamber 35 andnecks 36 for fluidly connecting theresonant chamber 35 to the outside. - The
resonant chamber 35 is substantially annular in shape and arranged about thefrustoconical wall 26a of the-outer body 26, between theinlet 31 of thediagonal swirler 23 and theburner insert 17. According to the invention, theresonant chamber 35 is placed in one edge of theouter body 26 adjacent to theinlet 31 of thediagonal swirler 23. More in detail, theresonant chamber 35 is delimited internally by thefrustoconical wall 26a of theouter body 26 and externally by, anannular closing wall 38. In axial direction, theannular closing wall 38 extends on the side ofcompressor 2 to one edge of theouter body 26 corresponding to theinlet 31 of themixing channel 30. Towards theburner insert 17, instead, theannular closing wall 38 is delimited by aconnection ring 39 of theouter body 26, by which theburner assembly 15 is coupled to theburner insert 17 itself. In one embodiment, theannular closing wall 38 is reversibly coupled to thefrustoconical wall 26a of theouter body 26, e.g. by screw fastening means (not shown). Alternatively, theannular closing wall 38 may be welded to or made integrally in one piece with thefrustoconical wall 26a. Theannular closing wall 38 has a plurality of connection holes 37, which are arranged along a circumference and define passages to allow the introduction of an air flow fromcompressor 2 into theresonant chamber 35. - The connection ring 39 (
figure 3 ) has a T-shaped crosswise section, and afirst portion 39a and asecond portion 39b. Thefirst portion 39a, which is planar and defines a leg of the T-shaped section, substantially extends on a plane perpendicular to axis B of theburner assembly 15 and delimits theresonant chamber 35 in axial direction on the side towards theburner insert 17 and thecombustion chamber 3. Thesecond portion 39b of theconnection ring 39 is substantially cylindrical and extends perpendicular to thefirst portion 39a on opposite sides thereof. On the compressor side, thesecond portion 39a of theconnection ring 39 is in contact with theannular closing wall 38, while an outer side surface is coupled to theburner insert 17. - The
second portion 39b has coolingpassages 40, defined by grooves made on an outer face along a circumference and extending in axial direction. Thecooling passages 40 put the delivery air ofcompressor 2 into communication with thecombustion chamber 3, thus cooling theburner insert 17. In particular, the inlet of thecooling passages 40 is on the side towardscompressor 2 with respect to thefirst portion 39a of theconnection ring 39. Thecooling passages 40 ensure a continuous cooling of theburner insert 17 independently of the assembly uncertainties and of the effects of thermal expansion. - The
necks 36 of theHelmholtz resonator 22 run on the outer surface of thefrustoconical wall 26 and extend through theconnection ring 39 and theburner insert 17. Theresonant chamber 35 and the openings ofnecks 36 are on opposite sides with respect to theburner insert 17. Thenecks 36 are thus arranged to put theresonant chamber 35 into fluidic communication with the outside through theconnection ring 39 and theburner insert 17. - The
resonant chamber 35 is free from direct fluidic connections with the mixingchannels 30 of thediagonal swirler 23. The separation of the two environments is ensured by thefrustoconical wall 26a and by theseals 29c between thefrustoconical wall 26a and the nuts 29a, which prevent leakages through theholes 29b. - The
resonant chamber 35 is fluidly coupled only to thecombustion chamber 3 through thenecks 36. - The connection holes 37 in the
annular closing wall 38 have a three-fold effect: they allow to maintain an air flow fromcompressor 2 tocombustion chamber 3 through theresonant chamber 35, thus avoiding backflows of hot fumes towards theresonant chamber 35 itself; they allow to maintain the thermodynamic properties inside theresonant chamber 35 approximately constant; and they expand the resonance band of the dynamic pressure fluctuations incombustion chamber 3. - In system 1, the
Helmholtz resonators 22 may be fitted either on all theburner assemblies 15 or only on some, as needed. Furthermore, theHelmholtz resonators 22 may be mutually different. The band features of eachHelmholtz resonator 22 are indeed determined by the geometry ofresonant chamber 35,necks 36 and connection holes 37. In order to optimize the thermoacoustic oscillation damping effect on the most critical frequency bands, theHelmholtz resonators 22 may be tuned to respective frequencies by selecting, for each one, the volume and shape of theresonant chamber 35, the number, length and cross section (area and profile) of thenecks 36 and the number, position and diameter of the connection holes 37. In one embodiment, for example, eachHelmholtz resonator 22 has a respective damping band, and the damping bands of Helmholtz resonators of different burner assemblies do not coincide, although they may be partially overlapping. - The burner assemblies of the described type have various advantages. Firstly, large volume resonant chambers may be obtained without major modifications to the combustion chamber (also for retrofitting interventions) and without significantly bearing on the structure. Indeed, on one hand, the available space about the main burner up to the inlet of the swirler is wide, and thus Helmholtz resonators of relatively large, volume can be manufactured. On the other hand, the resonant chamber is partially delimited by structural elements which belong to the main burner. The addition of the annular closing wall only allows to complete the resonant chamber without noticeable changes to the burner assembly and without a significant increase of weight. Minor adaptations are thus sufficient to accommodate the necks of the Helmholtz resonator. Furthermore, the described solution allows to select the most appropriate geometries for the Helmholtz resonator, with a wide margin of flexibility.
- A further advantage is that the burner assemblies, in particular the inlet region of the diagonal swirlers, are easily accessible. The maintenance or retrofitting interventions may thus be carried out easily.
Claims (14)
- A turbine burner assembly comprising:a main burner (20) extending about an axis (B); anda Helmholtz resonator (22) having a resonant chamber (35) and passages (36, 37) for fluidic connection of the resonant chamber (35) to the outside;wherein the main burner (20) comprises:an inner body (25) and an outer body (26), which extend about the axis (B), wherein the outer body (26) has a frustoconical wall (26a); anda diagonal swirler (23) arranged between the inner body (25) and the outer body (26) and defining mixing channels (30), an inlet (31) of the swirler (23) being located at a larger base of the frustoconical wall (26a) of the outer body (26);characterized in that the resonant chamber (35) extends about one edge of the outer body (26) adjacent to the inlet (31) of the swirler (23); and in that the outer body (26) delimits a portion of the resonant chamber (35) and is shaped so as to prevent direct fluidic connections between the Helmholtz resonator (22) and the mixing channels (30).
- A burner assembly as claimed in Claim 1, wherein the resonant chamber (35) is substantially annular.
- A burner assembly as claimed in any one of the foregoing Claims, comprising an annular closing wall (38) which externally delimits the resonant chamber (35).
- A burner assembly as claimed in Claim 3, wherein the passages (36, 37) comprise connection holes (37) in the annular closing wall (38).
- A burner assembly as claimed in any one of the foregoing Claims, comprising a burner insert (17) for connection to a burner seat (17a) of a gas turbine combustion chamber (3); and wherein the resonant chamber (35) extends about the outer body (26), between the inlet (31) of the swirler (23) and the burner insert (17).
- A burner assembly as claimed in Claim 5, wherein the passages (36) comprise necks (36) arranged to fluidly couple the resonant chamber (35) to the outside through the burner insert (17).
- A burner assembly as claimed in Claim 6, wherein the necks (36) extend through the burner insert (17).
- A burner assembly as claimed in Claim 3 and any one of Claims 6 to 8, wherein the outer body (26) comprises a connecting ring (39) by which the outer body (26) is connected to the burner insert (17); and wherein the annular closing wall (38) extends about the outer body (26), between the inlet (31) of the swirler (23) and the connecting ring (39).
- A burner assembly as claimed in one of the foregoing Claims, wherein the frustoconical wall (26a) has fastening holes (29b) for the blades (28) of the swirler (23); and the frustoconical wall (26a) and seals (29c) in the fastening holes (29b) fluidly separate the resonant chamber (35) from the mixing channels (30).
- A burner assembly as claimed in any one of the foregoing Claims, wherein the resonant chamber (35) is fluidly coupled to the outside exclusively through the passages (36, 37).
- A burner assembly as claimed in any one of the foregoing Claims, wherein the resonant chamber (35) has no fluidic connections to the swirler (23) through the outer body (26).
- A burner assembly as claimed in any one of the foregoing Claims, comprising a pilot burner (21) coaxial with the main burner (20).
- A turbine assembly comprising a combustion chamber (3); and a plurality of burner assemblies (15) as claimed in any one of the foregoing Claims, fitted to respective burner seats (16) of the combustion chamber (3).
- A turbine assembly as claimed in Claim 13, wherein each Helmholtz resonator has a respective damping band, and the damping bands of Helmholtz resonators of separate burner assemblies (15) are not coincident.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT002265A ITMI20122265A1 (en) | 2012-12-28 | 2012-12-28 | BURNER GROUP FOR A GAS TURBINE PROVIDED WITH A HELMHOLTZ RESONATOR |
PCT/IB2013/061378 WO2014102749A1 (en) | 2012-12-28 | 2013-12-27 | Gas turbine burner assembly equipped with a helmholtz resonator |
Publications (2)
Publication Number | Publication Date |
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EP2938927A1 EP2938927A1 (en) | 2015-11-04 |
EP2938927B1 true EP2938927B1 (en) | 2019-02-06 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP13831874.6A Active EP2938927B1 (en) | 2012-12-28 | 2013-12-27 | Gas turbine burner assembly equipped with a helmholtz resonator |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP2938927B1 (en) |
KR (1) | KR20150103032A (en) |
CN (1) | CN105121961B (en) |
IT (1) | ITMI20122265A1 (en) |
WO (1) | WO2014102749A1 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150362189A1 (en) * | 2014-06-13 | 2015-12-17 | Siemens Aktiengesellschaft | Burner system with resonator |
US20190093562A1 (en) * | 2017-09-28 | 2019-03-28 | Solar Turbines Incorporated | Scroll for fuel injector assemblies in gas turbine engines |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5644918A (en) * | 1994-11-14 | 1997-07-08 | General Electric Company | Dynamics free low emissions gas turbine combustor |
DE19839085C2 (en) * | 1998-08-27 | 2000-06-08 | Siemens Ag | Burner arrangement with primary and secondary pilot burner |
DE19851636A1 (en) * | 1998-11-10 | 2000-05-11 | Asea Brown Boveri | Damping device for reducing vibration amplitude of acoustic waves for burner for internal combustion engine operation is preferably for driving gas turbo-group, with mixture area for air and fuel |
EP1476699B1 (en) * | 2002-01-16 | 2013-11-13 | Alstom Technology Ltd | Combustion chamber and damper arrangement for reduction of combustion chamber pulsations in a gas turbine plant |
EP1342953A1 (en) * | 2002-03-07 | 2003-09-10 | Siemens Aktiengesellschaft | Gas turbine |
EP1342952A1 (en) * | 2002-03-07 | 2003-09-10 | Siemens Aktiengesellschaft | Burner, process for operating a burner and gas turbine |
US8127546B2 (en) * | 2007-05-31 | 2012-03-06 | Solar Turbines Inc. | Turbine engine fuel injector with helmholtz resonators |
EP2187125A1 (en) * | 2008-09-24 | 2010-05-19 | Siemens Aktiengesellschaft | Method and device for damping combustion oscillation |
US20110165527A1 (en) * | 2010-01-06 | 2011-07-07 | General Electric Company | Method and Apparatus of Combustor Dynamics Mitigation |
US9341375B2 (en) * | 2011-07-22 | 2016-05-17 | General Electric Company | System for damping oscillations in a turbine combustor |
-
2012
- 2012-12-28 IT IT002265A patent/ITMI20122265A1/en unknown
-
2013
- 2013-12-27 CN CN201380068658.XA patent/CN105121961B/en active Active
- 2013-12-27 KR KR1020157017809A patent/KR20150103032A/en not_active Application Discontinuation
- 2013-12-27 EP EP13831874.6A patent/EP2938927B1/en active Active
- 2013-12-27 WO PCT/IB2013/061378 patent/WO2014102749A1/en active Application Filing
Non-Patent Citations (1)
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None * |
Also Published As
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WO2014102749A1 (en) | 2014-07-03 |
ITMI20122265A1 (en) | 2014-06-29 |
CN105121961A (en) | 2015-12-02 |
EP2938927A1 (en) | 2015-11-04 |
KR20150103032A (en) | 2015-09-09 |
CN105121961B (en) | 2017-05-31 |
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