EP3189275A1 - Système d'amortissement acoustique pour une chambre de combustion d'une turbine à gaz - Google Patents

Système d'amortissement acoustique pour une chambre de combustion d'une turbine à gaz

Info

Publication number
EP3189275A1
EP3189275A1 EP14767242.2A EP14767242A EP3189275A1 EP 3189275 A1 EP3189275 A1 EP 3189275A1 EP 14767242 A EP14767242 A EP 14767242A EP 3189275 A1 EP3189275 A1 EP 3189275A1
Authority
EP
European Patent Office
Prior art keywords
resonator
orifices
acoustic damping
chamber
housing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP14767242.2A
Other languages
German (de)
English (en)
Inventor
Matthias Hase
Sachin TERDALKAR
Rajesh Rajaram
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP3189275A1 publication Critical patent/EP3189275A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the present invention relates in general to gas turbine engines and, more particularly, to acoustic damping systems for damping dynamics in combustors in gas turbine engines.
  • Gas turbine engines typically include a plurality of combustor baskets positioned downstream from a compressor and upstream from a turbine assembly.
  • longitudinal mode dynamics often occurs in the combustor baskets.
  • the longitudinal mode dynamics usually originates at the inlet of the air flow path in a combustor basket and travels downstream to the turbine inlet.
  • the dynamics restrict the tuning flexibility of the gas turbine engine in order to operate at lower emissions, which is an ever increasing requirement for newer gas turbines.
  • Resonators have been incorporated into combustors to damp the longitudinal mode dynamics.
  • the resonators have been sized and configured to address specific acoustic tunes. Resonators with various configurations have been employed.
  • the resonators are positioned within the combustors in the area of highest heat release to be most effective. It is in this position where the resonators are exposed to significant temperatures and thermal gradients.
  • Other solutions have been used with limited success because of cracking and significant repair costs. Thus, a need exists for a more efficient, less costly solution to damp longitudinal mode dynamics.
  • the acoustic damping resonator system may be formed from one or more resonators formed from a resonator housing positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor.
  • the resonator housing may include one or more resonator chambers that provide enhanced cooling with reduced risk of cracking and other damage.
  • the resonator housing may include resonator exhaust orifices that are positioned closer to an area of maximum temperature within the combustor, thereby enabling the resonator to reduce the temperature gradient within the combustor.
  • the resonator housing may be sized and configured to reduce stress found in conventional systems by increasing distances between resonator exhaust orifices and between resonator inlet impingement orifices, among others.
  • the acoustic damping resonator system for a combustor of a turbine engine may include one or more resonator housings defining one or more inner channels with an inner surface and an outer surface on an opposite side of the resonator housing from the inner surface.
  • the acoustic damping resonator system may include one or more resonator chambers extending radially outward from the resonator housing.
  • the resonator chamber may include one or more resonator inlet impingement orifices in an outer wall of the resonator chamber and one or more resonator exhaust orifices extending through the resonator housing.
  • the resonator exhaust orifice extending through the resonator housing may be offset axially upstream to place the resonator exhaust orifice closer to an area of maximum temperature within the combustor.
  • the resonator exhaust orifice may include a plurality of resonator exhaust orifices that are positioned closer to an upstream wall of the resonator chamber than a downstream wall of the resonator chamber.
  • the plurality of resonator exhaust orifices may be separated from each other a distance equal to at least one and one half times a diameter of a smallest diameter of the plurality of resonator exhaust orifices.
  • the plurality of resonator exhaust orifices may be separated from each other a distance equal to at least two times a diameter of a smallest diameter of the plurality of resonator exhaust orifices.
  • the plurality of resonator exhaust orifices may be collected into a pattern of an inverted triangle with a point of the triangle pointed downstream. In another embodiment, the plurality of resonator exhaust orifices are collected into a pattern of a rectangle.
  • the resonator inlet impingement orifice may include a plurality of resonator inlet impingement orifices that are offset from the plurality of resonator exhaust orifices such that one or more of the plurality of resonator inlet impingement orifices are radially aligned with the resonator housing in which the plurality of resonator exhaust orifices are positioned such that cooling fluids flowing into the resonator chamber impinge on the resonator housing.
  • the plurality of resonator inlet impingement orifices may form half as many rows as rows formed by the plurality of resonator exhaust orifices.
  • the rows formed by the plurality of resonator inlet impingement orifices may extend circumferentially and may be aligned radially between rows of the plurality of resonator exhaust orifices beginning with a first upstream row of resonator exhaust orifices and moving downstream.
  • the plurality of resonator inlet impingement orifices may form a first row that has one fewer orifices than a first row of resonator exhaust orifices.
  • the plurality of resonator inlet impingement orifices may form a second row downstream from the first row of resonator inlet impingement orifices, whereby the second row of resonator inlet impingement orifices may have two fewer orifices than a second row of resonator exhaust orifices.
  • the second row of inlet impingement orifices may skip a position in a middle of the second row of resonator exhaust orifices.
  • the plurality of inlet impingement orifices may be separated from each other a distance equal to at least one and one half times a diameter of a smallest diameter of the plurality of inlet impingement orifices.
  • the plurality of inlet impingement orifices may be separated from each other a distance equal to at least two times a diameter of a smallest diameter of the plurality of inlet impingement orifices.
  • a ratio of distance between the outer wall of the resonator chamber and the resonator housing and a diameter of the resonator inlet impingement orifice may be between about seven and about four.
  • the outer wall may be sized in thickness such that a ratio of a length of the at least one resonator inlet impingement orifice extending radially inward to a diameter of the at least one resonator inlet impingement orifice is greater than one.
  • an acoustic damping resonator system for a combustor of a turbine engine may include one or more resonator housings defining at least one inner channel with an inner surface and an outer surface on an opposite side of the resonator housing from the inner surface.
  • the an acoustic damping resonator system may include one or more resonator chambers extending radially outward from the resonator housing, whereby the resonator chamber includes at least one resonator inlet impingement orifice in an outer wall of the resonator chamber and resonator exhaust orifice extending through the resonator housing.
  • the acoustic damping resonator system may include a ratio of distance between the outer wall of the resonator chamber and the resonator housing to a diameter of the resonator inlet impingement orifice between about seven and about four. As such, the footprint of the resonator chamber is expanded.
  • a maximum internal resonator dimension extending linearly within the at least one resonator chamber may be increased less than 12 percent while a footprint of the resonator chamber has been enlarged by between 40 percent and 100 percent relative to a resonator chamber having a ratio of greater than eight of a distance between the outer wall of a resonator chamber and a resonator housing to a diameter of a resonator inlet impingement orifice.
  • the acoustic damping resonator system may include resonator chambers having numerous different shapes configured to prevent a maximum internal resonator dimension extending linearly within the resonator chamber from being enlarged beyond a point at which the resonator chamber has a target cutoff frequency that is greater than an actual damping frequency.
  • a cross-sectional shape of outer sidewalls forming the resonator chamber forms a modified parallelogram in which a longest diagonal direction has been reduced via truncated intersections.
  • the truncated intersections of the modified parallelogram may be formed with a first corner side at a first intersection and a second corner side at a second intersection, whereby the first corner side may extend between first and second sidewalls forming the modified parallelogram and wherein the second corner side may extend between third and fourth sidewalls forming the modified parallelogram.
  • a cross-sectional shape of outer sidewalls forming the resonator chamber may form a modified triangle in which at least two corners have been truncated with corner sides.
  • each corner of the modified triangle may have been truncated with at least one corner side such that a first corner side may extend between first and second sidewalls, a second corner side may extend between second and third sidewalls and a third corner side may extend between first and third sidewalls.
  • a cross-sectional shape of outer sidewalls forming the resonator chamber may form a modified rectangle in which at least two corners have been truncated with corner sides. At least two corners of the modified rectangle may have been truncated with at least one corner side. Each corner of the modified rectangle may have been truncated with at least one corner side such that a first corner side may extend between first and second sidewalls, a second corner side may extend between second and third sidewalls, a third corner side may extend between third and fourth sidewalls and a fourth corner side may extend between first and fourth sidewalls.
  • at least one corner on at least one sidewall forming the resonator chamber may be curved.
  • Figure 1 is partial cross-sectional side view of a combustors positioned within gas turbine engines.
  • Figure 2 is a cross-sectional side view of a combustor in the gas turbine engine taken as section line 2-2 in Figure 1 .
  • Figure 3 is a perspective view of a combustor liner with an acoustic damping resonator system.
  • Figure 4 is a schematic diagram of a combustor in the gas turbine engine with a conventional resonator.
  • Figure 5 is a cross-sectional side view of a resonator of the acoustic damping resonator system shown together with a conventional resonator with a larger height taken along section line 5-5 in Figure 3.
  • Figure 6 is a perspective, cross-sectional view of resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 7 is a perspective, cross-sectional view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 8 is a cross-sectional side view of resonator chamber of the acoustic damping resonator system showing a reduced sized recirculation zone adjacent to and downstream of a resonator chamber, whereby a high heat transfer starting at a reattachment point is positioned closer to the resonator than in conventional systems taken along section line 5-5 in Figure 3.
  • Figure 9 is a cross-sectional side view of a conventional resonator chamber.
  • Figure 10 is a cross-sectional side view of a resonator chamber of the acoustic damping resonator system taken along section line 5-5 in Figure 3.
  • Figure 1 1 is a cross-sectional side view of a conventional resonator chamber.
  • Figure 12 is a cross-sectional side view of a resonator chamber of the acoustic damping resonator system taken along section line 5-5 in Figure 3.
  • Figure 13 is a cross-sectional side view of another embodiment of a resonator chamber of the acoustic damping resonator system taken along section line 5-5 in Figure 3.
  • Figure 14 is a cross-sectional side view of yet another embodiment of a resonator chamber of the acoustic damping resonator system taken along section line 5-5 in Figure 3.
  • Figure 15 is a cross-sectional top view of a conventional resonator chamber.
  • Figure 16 is a cross-sectional top view of an embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 17 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 18 is a cross-sectional top view of an embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 19 is a cross-sectional top view of a conventional resonator chamber.
  • Figure 20 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 21 is a cross-sectional top view of yet another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 22 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 23 is a cross-sectional top view of still another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 24 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 25 is a cross-sectional top view of a conventional resonator chamber.
  • Figure 26 is a cross-sectional top view of another conventional resonator chamber.
  • Figure 27 is a cross-sectional top view of an embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 28 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 29 is a cross-sectional top view of yet another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 30 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 31 is a cross-sectional top view of still another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 32 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • Figure 33 is a cross-sectional top view of another embodiment of the resonator chamber of the acoustic damping resonator system taken along section line 6-6 in Figure 3.
  • an acoustically dampened gas turbine engine 10 having a gas turbine engine combustor 12 with an acoustic damping resonator system 14 is disclosed.
  • the acoustic damping resonator system 14 may be formed from one or more resonators 16 formed from a resonator housing 18 positioned within the gas turbine engine combustor 12 at an outer housing 20 forming a combustor basket 22 and extending circumferentially within the combustor 12.
  • the resonator housing 18 may include one or more resonator chambers 24 that provide enhanced cooling with reduced risk of cracking and other damage.
  • the resonator housing 18 may include resonator exhaust orifices 26 that may be positioned closer to an area of maximum temperature 28 within the combustor 12, thereby enabling the resonator 16 to reduce the temperature gradient within the combustor 12.
  • the resonator housing 18 may be sized and configured to reduce stress found in conventional systems by increasing distances between resonator exhaust orifices 26 and between resonator inlet impingement orifices 30, among others.
  • the acoustic damping resonator system 14 for a combustor 12 of a turbine engine 10 may include one or more resonator housings 18.
  • the resonator housing 18 may extend for a portion of or entire around a combustor 12, as shown in Figures 2 and 3.
  • the resonator housing 18 may define one or more inner channels 32, as shown in Figures 2, 3 and 5, with an inner surface 34 and an outer surface 36 on an opposite side of the resonator housing 18 from the inner surface 34.
  • the resonator housing 18 may be generally cylindrical, thereby forming a ring with a single inner channel 32 therein.
  • the acoustic damping resonator system 14 may include one or more resonator chambers 24 extending radially outward from the resonator housing 18.
  • the resonator chamber 24 may have any appropriate shape. In at least one embodiment, as shown in Figures 16-18, 22-24, 27, 32 and 33, the resonator chamber 24 may be shaped as a quadrilateral with a somewhat triangular shape, a rectangular shape, as shown in Figures 20-21 and 31 , or other appropriate shape. As shown in Figures 12-14, the resonator chamber 24 may be formed from an outer wall 38 that may be supported by one or more sidewalls 40, such as upstream sidewall 42 and downstream sidewall 44.
  • the resonator chamber 24 may include one or more resonator inlet impingement orifices 30 in the outer wall 38 of the resonator chamber 24 and one or more resonator exhaust orifices 26 extending through the resonator housing 18.
  • the resonator exhaust orifice 26 extending through the resonator housing 18 may be offset axially upstream to place the resonator exhaust orifice 26 closer to an area of maximum temperature within the combustor 12.
  • the resonator 16 may be shifted further in the upstream direction relative to the resonator housing 18 such that the resonator 16 is closer to an area of maximum temperature within the combustor 12.
  • the acoustic damping resonator system 14 may include a plurality of resonator exhaust orifices 26 that are positioned closer to an upstream wall 42 of the resonator chamber 24 than a downstream wall 44 of the resonator chamber 24.
  • the resonator exhaust orifices 26 may be spaced further apart from each other than in conventional systems, as shown in Figures 15 and 19 to reduce the likelihood of cracking in the resonator housing 18.
  • the plurality of resonator exhaust orifices 26 may be separated from each other a distance equal to at least one and one half times a diameter of a smallest diameter of the plurality of resonator exhaust orifices 26.
  • the resonator exhaust orifices 26 may be separated from each other a distance equal to at least two times a diameter of a smallest diameter of the resonator exhaust orifices 26.
  • the resonator exhaust orifices 26 may be collected into a pattern having a shape of a quadrilateral with a somewhat triangular shape as shown in Figures 16-18 and 22- 24, which may also be described as being an inverted triangle with a point of the triangle pointed downstream, a rectangular shape, as shown in Figures 20-21 , or other appropriate shape.
  • the acoustic damping resonator system 14 may include one or more resonator inlet impingement orifices 30 that are offset from the plurality of resonator exhaust orifices 26 such that at least one of the plurality of resonator inlet impingement orifices 30 is radially aligned with the resonator housing 16 in which the plurality of resonator exhaust orifices 26 are positioned such that cooling fluids flowing into the resonator chamber 24 impinge on the resonator housing 16.
  • the resonator inlet impingement orifices 30 may form fewer rows 46 as rows 48 formed by the plurality of resonator exhaust orifices 26.
  • the resonator inlet impingement orifices 30 may form half as many rows 46 as rows 48 formed by the plurality of resonator exhaust orifices 26.
  • the rows 46 formed by the plurality of resonator inlet impingement orifices 30 may extend circumferentially and may be aligned radially between rows 48 of the plurality of resonator exhaust orifices 26 beginning with a first upstream row 50 of resonator exhaust orifices 26 and moving downstream.
  • the rows 46 formed by the plurality of resonator inlet impingement orifices 30 may be positioned closer to an upstream sidewall 42 than a downstream sidewall 44 to increase efficiency.
  • the plurality of resonator inlet impingement orifices 30 may form a first row 52 that has one fewer orifices 30 than a first row 50 of resonator exhaust orifices 50.
  • the plurality of resonator inlet impingement orifices 30 may form a second row 54 downstream from the first row 52 of resonator inlet impingement orifices 30, whereby the second row 54 of resonator inlet impingement orifices 30 has at least two fewer orifices 30 than a second row 56 of resonator exhaust orifices 26.
  • the second row 54 of inlet impingement orifices 30 may skip a position in a middle of the second row 56 of resonator exhaust orifices 26.
  • the plurality of resonator inlet impingement orifices 30 may form a second row 54 downstream from the first row 52 of resonator inlet impingement orifices 30, whereby the second row 54 of resonator inlet impingement orifices 30 has at least one additional orifice 30 than a first row 52 of resonator inlet impingement orifices 30.
  • the second row 56 of resonator exhaust orifices 26 may also include at least one additional resonator exhaust orifice 26 compared to a first row 50 of resonator exhaust orifices 26.
  • a third row 58 of the resonator inlet impingement orifices 30 may have at least one less orifice 30 than a second row 54 of resonator inlet impingement orifices 30.
  • a third row 59 of the resonator exhaust orifices 26 may have at least one less orifice 26 than a second row 56 of resonator exhaust orifices 26. The remaining rows of resonator inlet impingement orifices 30 and resonator exhaust orifices 26 may reduce in number moving downstream towards the downstream sidewall 44.
  • the plurality of inlet impingement orifices 30 may be separated from each other a distance equal to at least one and one half times a diameter of a smallest diameter of the plurality of inlet impingement orifices 30. In another embodiment, the plurality of inlet impingement orifices 30 may be separated from each other a distance equal to at least two times a diameter of a smallest diameter of the plurality of inlet impingement orifices 30.
  • the resonator chamber 24 may be configured to increase cooling of the resonator housing 18 and the combustor 12 without increasing the amount of cooling air needed.
  • the resonator chamber 24 may be reconfigured to extend for a larger distance axially with a smaller radial height, thereby keeping the volume within the resonator chamber 24 relatively unchanged in comparison to conventional systems but exposing a larger amount of surface area of the resonator housing 18 to cooling fluids.
  • the resonator chamber 24 may extend further radially upstream than conventional systems, which enables the upstream sidewall 42 of the resonator chamber 24, resonator exhaust orifices 26 or resonator inlet impingement orifices 30, or any combination thereof, to be shifted upstream and closer to an area of maximum temperature 28 within the combustor 12.
  • a ratio of distance between the outer wall 38 of the resonator chamber 24 and the resonator housing 18 to a diameter of the resonator inlet impingement orifice 30 may be between about seven and about four.
  • the ratio of distance between the outer wall 38 of the resonator chamber 24 and the resonator housing 18 to the diameter of the resonator inlet impingement orifice 30 is about 6.5 in the middle of the resonator 16.
  • the outer wall 38 of the resonator chamber 24 may be configured to enhance the flow of cooling fluids through the resonator inlet impingement orifices 30 and enhance the impingement of cooling fluids on the resonator housing 18 within the resonator chamber 24.
  • the outer wall 38 of the resonator chamber 24 may be thicker than conventional systems, as shown in Figure 9, to increase the effectiveness of the resonator inlet impingement orifices 30.
  • the outer wall 38 may be sized in thickness such that a ratio of a length of the at least one resonator inlet impingement orifice 30 extending radially inward to a diameter of the resonator inlet impingement orifice 30 is greater than about 0.75. In another embodiment, the outer wall 38 may be sized in thickness such that a ratio of a length of the at least one resonator inlet
  • impingement orifice 30 extending radially inward to a diameter of the resonator inlet impingement orifice 30 is greater than about one.
  • the acoustic damping resonator system 14 may be configured such that the footprint of the resonator chamber 24 may be enlarged relative to conventional resonators, yet prevent a maximum internal resonator dimension 60 extending linearly within the resonator chamber 24 from being enlarged beyond a point at which the resonator chamber 24 has a target cutoff frequency that is greater than an actual damping frequency.
  • the shape of the resonator 16 may be adapted such that the maximum internal resonator dimension 60 is not increased in the same relation as the resonator footprint.
  • the acoustic damping resonator system 14 may be formed from a resonator housing 18 with a one or more resonator chambers 24 as described above.
  • a ratio of a distance between the outer wall 38 of the resonator chamber 24 and the resonator housing 18 to a diameter of the resonator inlet impingement orifice 30 may be between about seven and about four.
  • a maximum internal resonator dimension 60 extending linearly within the resonator chamber 24 may be increased less than 12 percent while a footprint of the resonator chamber 24 on the resonator housing 18 may have been enlarged by between 40 percent and 100 percent relative to a resonator chamber 24 having a ratio of greater than eight of a distance between the outer wall 38 of a resonator chamber 24 and a resonator housing 18 to a diameter of a resonator inlet impingement orifice 30.
  • the resonator chamber 24 may have been enlarged and sized, as set forth above.
  • the acoustic damping resonator system 14 may include resonator chambers 24 having numerous different shapes configured to prevent a maximum internal resonator dimension 60 extending linearly within the resonator chamber 24 from being enlarged beyond a point at which the resonator chamber 24 has a target cutoff frequency that is greater than an actual damping frequency.
  • a cross-sectional shape of outer sidewalls 40 forming the resonator chamber 24 may form a modified parallelogram 66, as shown in Figure 30, in which a maximum internal resonator dimension 60 has been reduced via truncated intersections 64.
  • the truncated intersections 64 of the modified parallelogram 66 may be formed with a first corner side 68 at a first intersection 70 and a second corner side 72 at a second intersection 74.
  • the first corner side 68 may extend between first and second sidewalls 76, 78 forming the modified parallelogram 66.
  • the second corner side 72 may extend between third and fourth sidewalls 80, 82 forming the modified parallelogram 66.
  • a cross-sectional shape of outer sidewalls 40 forming the resonator chamber 24 may form a modified triangle 84 in which at least two corners 86 have been truncated with corner sides 88.
  • each corner of the modified triangle 84 may be truncated with at least one corner side 88 such that a first corner side 68 may extend between first and second sidewalls 76, 78, a second corner side 72 may extend between second and third sidewalls 78, 80 and a third corner side 90 may extend between first and third sidewalls 76, 80.
  • a cross-sectional shape of outer sidewalls 40 forming the resonator chamber 24 may form a modified rectangle 92 in which at least two corners 86 have been truncated with corner sides 88. At least two corners 86 of the modified rectangle 92 may have been truncated with one or more corner sides 88.
  • each corner 86 of the modified rectangle 92 may have been truncated with at least one corner side 88 such that a first corner side 68 may extend between first and second sidewalls 76, 78, a second corner side 72 may extend between second and third sidewalls 78, 80, a third corner side 90 may extend between third and fourth sidewalls 80, 82 and a fourth corner side 94 may extend between first and fourth sidewalls 76, 82.
  • the modified rectangle 92 may have equal length sides and be a square.
  • one or more corners 86 on one or more sidewalls 40 forming the resonator chamber 24 may be curved.
  • each corner 86 on each sidewall 40 forming the resonator chamber 24 may be curved.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)

Abstract

L'invention porte sur une turbine à gaz à amortissement acoustique, laquelle turbine a une chambre de combustion de turbine à gaz (12) munie d'un système de résonateur d'amortissement acoustique (10). Le système de résonateur d'amortissement acoustique (10) peut être constitué d'un ou de plusieurs résonateurs (16) formés à partir d'un boîtier de résonateur (18) positionné à l'intérieur de la chambre de combustion de turbine à gaz (12) au niveau d'un boîtier externe (20) constituant un panier de chambre de combustion (22) et s'étendant de façon périphérique à l'intérieur de la chambre de combustion (12). Dans un mode de réalisation, le boîtier de résonateur (18) peut comprendre une ou plusieurs chambres de résonateur (24) qui produisent un refroidissement amélioré avec un risque réduit de fissuration et d'autres détériorations. Le boîtier de résonateur (18) peut comprendre des orifices d'échappement de résonateur (26) qui sont positionnés plus près d'une zone de température maximale à l'intérieur de la chambre de combustion (12), de façon à permettre ainsi au résonateur (16) de réduire le gradient de température à l'intérieur de la chambre de combustion (12). Le boîtier de résonateur (18) peut être dimensionné et configuré de façon à réduire une contrainte existant dans les systèmes classiques par l'accroissement des distances entre les orifices d'échappement de résonateur (26) et entre les orifices d'impact d'entrée de résonateur (30), entre autres.
EP14767242.2A 2014-09-05 2014-09-05 Système d'amortissement acoustique pour une chambre de combustion d'une turbine à gaz Withdrawn EP3189275A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2014/054179 WO2016036380A1 (fr) 2014-09-05 2014-09-05 Système d'amortissement acoustique pour une chambre de combustion d'une turbine à gaz

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EP3189275A1 true EP3189275A1 (fr) 2017-07-12

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US (1) US20180224123A1 (fr)
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020200568A1 (fr) 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Carreau d'écran thermique à fonction d'amortissement

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10359194B2 (en) * 2014-08-26 2019-07-23 Siemens Energy, Inc. Film cooling hole arrangement for acoustic resonators in gas turbine engines
EP3465008B1 (fr) 2016-07-25 2021-08-25 Siemens Energy Global GmbH & Co. KG Anneaux de résonateur pour turbine à gaz

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4168348A (en) * 1974-12-13 1979-09-18 Rolls-Royce Limited Perforated laminated material
US4084366A (en) * 1975-11-14 1978-04-18 Haworth Mfg., Inc. Sound absorbing panel
US6530221B1 (en) * 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
JP2005076982A (ja) * 2003-08-29 2005-03-24 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
US7219498B2 (en) * 2004-09-10 2007-05-22 Honeywell International, Inc. Waffled impingement effusion method
US8146364B2 (en) * 2007-09-14 2012-04-03 Siemens Energy, Inc. Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber
US20100236245A1 (en) * 2009-03-19 2010-09-23 Johnson Clifford E Gas Turbine Combustion System
US8413443B2 (en) * 2009-12-15 2013-04-09 Siemens Energy, Inc. Flow control through a resonator system of gas turbine combustor
US9546558B2 (en) * 2010-07-08 2017-01-17 Siemens Energy, Inc. Damping resonator with impingement cooling
US20150082794A1 (en) * 2013-09-26 2015-03-26 Reinhard Schilp Apparatus for acoustic damping and operational control of damping, cooling, and emissions in a gas turbine engine

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2016036380A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020200568A1 (fr) 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Carreau d'écran thermique à fonction d'amortissement

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