CN113719861B - Combustion chamber and gas turbine with same - Google Patents
Combustion chamber and gas turbine with same Download PDFInfo
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- CN113719861B CN113719861B CN202111062504.2A CN202111062504A CN113719861B CN 113719861 B CN113719861 B CN 113719861B CN 202111062504 A CN202111062504 A CN 202111062504A CN 113719861 B CN113719861 B CN 113719861B
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- cavity
- hole
- fuel
- peripheral wall
- chamber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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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
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
Abstract
The invention discloses a combustion chamber and a gas turbine with the same, wherein the combustion chamber comprises: a flame tube, a resonating chamber, and a fuel nozzle. The flame tube comprises a tube wall and a flame cavity defined by the tube wall, the tube wall comprises an installation area, and the installation area is provided with a plurality of first through holes penetrating through the tube wall; the resonant chamber is provided with a resonant cavity, the resonant chamber is arranged on the mounting area, the first through hole is communicated with the resonant cavity and the flame cavity, and the resonant cavity is communicated with the outside; the fuel nozzle is provided with a fuel cavity, a spray hole and a fuel inlet, the spray hole is communicated with the flame cavity and the fuel cavity, and the fuel inlet is communicated with the fuel cavity and the outside. The combustion chamber has the advantages of small volume and good combustion performance.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustion chamber and a gas turbine with the same.
Background
The gas turbine is an internal combustion type power machine which takes continuously flowing gas as a working medium to drive an impeller to rotate at a high speed and converts the energy of fuel into useful work. Among them, the gas turbine has a simple structure, and the gas turbine has a series of advantages of small volume, light weight, quick start, little or no cooling water, etc., so the gas turbine has wide use in various fields. When the combustion chamber of the gas turbine works under the lean-burn condition, the thermo-acoustic instability phenomenon is easy to occur, and further the combustion performance of the gas turbine has great influence. Therefore, in the related art, the provision of the resonator in the combustion chamber can suppress the thermo-acoustic instability phenomenon. However, in the related art, since the fuel nozzle and the resonator are separately provided in the combustion chamber, it is necessary to provide a gas supply device for each of the fuel nozzle and the resonator, and to increase the volume of the combustion chamber.
Disclosure of Invention
The present invention is based on the discovery and recognition by the inventors of the following facts and problems:
the installation of a resonant cavity in a combustion chamber is a means for controlling thermoacoustic, wherein an ideal resonant cavity can eliminate sound waves with specific frequency, so that the transmission loss of the sound waves is infinite, and the characteristic of the common resonant cavity in the combustion chamber is used for reducing high-frequency oscillation to achieve the purpose of inhibiting thermoacoustic oscillation. In the related art, the fuel nozzle in the combustion chamber is designed separately from the resonance cavity, and thus the volume of the combustion chamber space is large.
The present invention is directed to solving, at least in part, one of the technical problems in the related art. To this end, embodiments of the present invention propose a combustion chamber having an advantage of good combustion performance.
Embodiments of the present invention provide a gas turbine having an advantage of good combustion performance.
A combustion chamber according to an embodiment of the present invention is characterized by comprising:
the flame tube comprises a tube wall and a flame cavity enclosed by the tube wall, the tube wall comprises an installation area, and the installation area is provided with a plurality of first through holes penetrating through the tube wall;
the resonant chamber is provided with a resonant cavity, the resonant chamber is arranged on the mounting area, the first through hole is communicated with the resonant cavity and the flame cavity, and the resonant cavity is communicated with the outside;
the fuel nozzle is partially positioned in the resonant cavity and provided with a fuel cavity, a spray hole and a fuel inlet, the fuel cavity comprises a first end and a second end, the first end and the second end are opposite to each other in the length direction of the fuel nozzle, the spray hole is formed in the first end of the fuel cavity, the fuel inlet is formed in the second end of the fuel cavity, the spray hole is communicated with the flame cavity and the fuel cavity, and the fuel inlet is communicated with the fuel cavity and the outside.
The combustion chamber according to the embodiment of the invention arranges a part of the fuel nozzle in the resonance chamber, and then designs the resonance chamber and the fuel nozzle in combination. Furthermore, cooling gas enters the flame cavity from the first through hole of the mounting area, so that fuel sprayed into the flame cavity from the fuel nozzle is fully mixed with fuel gas in the flame cavity, and the combustion performance of the combustion chamber is improved. In addition, the fuel nozzle is combined with the resonance chamber, so that the space of the combustion chamber of the embodiment of the invention is saved.
Therefore, the combustion chamber has the advantages of good combustion performance and small volume.
In some embodiments, the resonance chamber includes a peripheral wall and an end cap, the peripheral wall includes a third end and a fourth end, the third end and the fourth end are opposite to each other in an axial direction of the peripheral wall, the third end of the peripheral wall is disposed on the mounting region, the end cap is disposed on the fourth end of the peripheral wall, so that the peripheral wall, the mounting region and the end cap enclose the resonance cavity, and the end cap is provided with a plurality of second through holes, and the second through holes communicate the resonance cavity and the outside.
In some embodiments, the resonant chamber further includes a partition plate disposed in the resonant cavity, the resonant cavity includes a first cavity and a second cavity separated by the partition plate, the partition plate is provided with a plurality of third through holes, and the third through holes communicate the first cavity and the second cavity.
In some embodiments, the fuel nozzle length direction coincides with an axial direction of the peripheral wall, which coincides with a radial direction of the combustor basket.
In some embodiments, the mounting area is provided with a first through hole, the partition plate is provided with a second through hole, the end cap is provided with a third through hole, the first through hole, the second through hole, and the third through hole are opposed in an axial direction of the peripheral wall, and the fuel nozzle passes through the first through hole, the second through hole, and the third through hole.
In some embodiments, a centerline of the first via coincides with a centerline of the perimeter wall; or the first through hole is positioned on one side of the center line of the peripheral wall in the axial direction of the flame tube; alternatively, the first through hole is located on the other side of the center line of the peripheral wall in the axial direction of the flame tube.
In some embodiments, the resonance chamber further includes an air duct, the air duct includes a fifth end and a sixth end, the fifth end and the sixth end are opposite to each other in a length direction of the air duct, the length direction of the air duct is in accordance with an axial direction of the peripheral wall, the fifth end of the air duct is disposed in the first through hole, and the air duct is sleeved on the fuel nozzle.
In some embodiments, the sixth end of the air duct is located within the first cavity; or, the sixth end of the air duct is located in the second cavity; or the sixth end of the air duct is arranged in the third through hole.
In some embodiments, the resonating chamber further comprises a swirler disposed over the fuel nozzle, and the air duct is disposed over the swirler.
A gas turbine according to an embodiment of the present invention includes the combustor described in any one of the above embodiments.
Drawings
Fig. 1 is a schematic structural view of a combustor of an embodiment of the present invention.
Fig. 2 is a schematic structural view of a combustor of an embodiment of the present invention.
Fig. 3 is a schematic structural view of a combustion chamber of an embodiment of the present invention.
Fig. 4 is a schematic structural view of a combustor of an embodiment of the present invention.
Fig. 5 is a schematic structural view of a combustion chamber of an embodiment of the present invention.
Fig. 6 is a schematic structural view of a combustion chamber of an embodiment of the present invention.
Fig. 7 is a schematic structural view of a combustion chamber of an embodiment of the present invention.
Fig. 8 is a schematic structural view of a combustor of an embodiment of the present invention.
Reference numerals:
a flame tube 1; a flame chamber 11; a barrel wall 12; a mounting area 13; a first through hole 131; first via 132
A resonance chamber 2; a peripheral wall 21; a third end 211; a fourth end 212; an end cap 22; a second through hole 221; a partition plate 23; a third through hole 231; a second via 232; a third via 222; a resonant cavity 24; a first cavity 241; a second cavity 242;
a fuel nozzle 3; a fuel inlet 31; a nozzle hole 32; a fuel chamber 33; a first end 331; a second end 332;
an air duct 4; a fifth end 41; a sixth end 42; a first gap 5; a swirler 6; cooling gas 7; 8, fuel gas; and (9) fuel.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
The combustion chamber of the embodiment of the present invention is described below with reference to the drawings. As shown in fig. 1, the combustion chamber according to the embodiment of the present invention includes a liner 1, a resonance chamber 2, and a fuel nozzle 3.
The flame tube 1 comprises a tube wall 12 and a flame chamber 11 enclosed by the tube wall 12. Specifically, the area enclosed by the inner circumferential surface of the cylindrical wall 12 of the combustor basket 1 is the flame chamber 11, wherein the axial direction of the combustor basket 1 is arranged along the left-right direction, that is, the axial direction of the cylindrical wall 12 is the left-right direction.
The cylinder wall 12 comprises a mounting area 13, the mounting area 13 being provided with a plurality of first through holes 131 extending through the cylinder wall 12. That is, a partial region on the outer circumferential surface of the cylinder wall 12 for mounting the resonance chamber 2 forms the mounting region 13, and the first through hole 131 is opened in the mounting region 13. Specifically, the first through holes 131 are multiple, wherein the axial direction of the first through holes 131 is parallel to the radial direction of the cylinder wall 12, the multiple first through holes 131 are uniformly arranged, and two adjacent first through holes 131 are arranged at intervals.
The mounting area 13 is plural, wherein the mounting areas 13 are located on the outer circumferential surface of the cylinder wall 12, and the mounting areas 13 are arranged at intervals along the circumferential direction of the combustor basket 1.
The resonance chamber 2 has a resonance chamber 24, and the resonance chamber 2 is provided on the mounting area 13. The first through hole 131 communicates the resonant cavity 24 with the flame cavity 11, and the resonant cavity 24 communicates with the outside. Specifically, the resonance chamber 2 is mounted on the mounting area 13 of the cylinder wall 12, and the flame chamber 11 and the resonance chamber 24 communicate through a first through hole 131 in the mounting area 13. In a region where the outer peripheral surface of the cylindrical wall 12 coincides with the resonant cavity 24, the first through holes 131 are arranged at intervals in the left-right direction and in the circumferential direction of the cylindrical wall 12, that is, the first through holes 131 are arranged in a matrix.
The resonance chambers 2 are multiple, wherein the multiple resonance chambers 2 are arranged on the cylinder wall 12 at intervals along the circumferential direction of the flame tube 1.
Further, the resonant cavity 24 is in communication with the outside, which means that the resonant cavity 24 can be filled with cooling gas, for example, as shown in fig. 1, the cooling gas 7 can enter the resonant cavity 24 from the outside of the resonant chamber 2. Thereby enabling the cooling gas 7 to enter the flame chamber 11 from the first through hole 131 of the mounting area 13.
It will be appreciated that thermoacoustic waves are generated when the fuel 9 and the gas 8 are combusted in the flame chamber 11. The high frequency thermal acoustic waves generated by the combustion propagate into the resonant cavity 24 where they can be reflected within the resonant cavity 24. Furthermore, the wave crest of the reflected high-frequency thermal sound wave is superposed with the wave trough of the high-frequency thermal sound wave generated by combustion, so that the amplitude of the superposed thermal sound wave is weakened; or the wave trough of the reflected high-frequency thermal sound wave is superposed with the wave crest of the high-frequency thermal sound wave generated by combustion, so that the amplitude of the superposed thermal sound wave is weakened. Therefore, the resonant cavity 24 can weaken high-frequency thermo-acoustic oscillation in the combustion chamber during combustion, inhibit thermo-acoustic instability, and further improve the combustion performance of the combustion chamber.
Part of the fuel nozzle 3 is located within the resonant cavity 24, the fuel nozzle 3 having a fuel cavity 33, a nozzle hole 32 and a fuel inlet 31. The fuel cavity 33 includes a first end 331 and a second end 332, the first end 331 and the second end 332 being opposite in a length direction of the fuel nozzle 3. The spray holes 32 are arranged at the first end 331 of the fuel cavity 33, the fuel inlet 31 is arranged at the second end 332 of the fuel cavity 33, the spray holes 32 are communicated with the flame cavity 11 and the fuel cavity 33, and the fuel inlet 31 is communicated with the fuel cavity 33 and the outside.
Specifically, the longitudinal direction of the fuel nozzle 3 coincides with the radial direction of the cylindrical wall 12. That is, the fuel nozzle 3 may be provided at any position in the circumferential direction of the cylindrical wall 12, and the longitudinal direction of the fuel nozzle 3 is perpendicular to the axial direction of the cylindrical wall 12.
As shown in fig. 1, the injection holes 32 are provided on the first end 331, the fuel inlet 31 is provided on the second end 332, and the area enclosed by the inner peripheral surface of the fuel nozzle 3 is the fuel chamber 33.
Further, the fuel nozzle 3 is inserted into the resonance chamber 2 in the radial direction of the cylindrical wall 12. Specifically, a part of the fuel nozzle 3 is located in the resonance chamber 2, one end of the fuel nozzle 3 penetrates through the cylinder wall 12 of the mounting area 13, and the other end of the fuel nozzle 3 penetrates through the end cover, wherein one end of the fuel nozzle 3 corresponds to the first end 331 of the fuel cavity 33, and the other end of the fuel nozzle 3 corresponds to the second end 332 of the fuel cavity 33. Therefore, the first end 331 of the fuel cavity 33 is located inside the flame cavity 11, so that the flame cavity 11 is communicated with the fuel cavity 33, that is, the nozzle hole 32 is located inside the flame cavity 11, so that the fuel 9 in the fuel nozzle 3 can enter the flame cavity 11 through the nozzle, and the second end 332 of the fuel cavity 33 is located outside the resonance chamber 2, that is, the fuel inlet 31 is located outside the resonance chamber 2, so that the fuel 9 can enter the fuel cavity 33 from the outside through the fuel inlet 31.
The combustion chamber according to the embodiment of the present invention disposes a portion of the fuel nozzle 3 inside the resonance chamber 2, and thus designs the resonance chamber 2 in combination with the fuel nozzle 3. Further, the cooling gas 7 enters the flame chamber 11 from the first through hole 131 of the mounting area 13, so that the fuel 9 sprayed into the flame chamber 11 from the fuel nozzle 3 is fully mixed with the fuel gas in the flame chamber 11, and the combustion performance of the combustion chamber of the embodiment of the invention is further improved. In addition, the fuel nozzle 3 is designed in combination with the resonance chamber 2, thereby saving the space of the combustion chamber of the embodiment of the present invention.
Therefore, the combustion chamber has the advantages of being good in combustion performance and small in size.
In some embodiments, the resonance chamber 2 comprises a peripheral wall 21 and an end cap 22, the peripheral wall 21 comprising a third end 211 and a fourth end 212, the third end 211 and the fourth end 212 being opposite in the axial direction of the peripheral wall 21, the third end 211 of the peripheral wall 21 being provided on the mounting area 13. The longitudinal direction of the fuel nozzle 3 coincides with the axial direction of the peripheral wall 21, and the axial direction of the peripheral wall 21 coincides with the radial direction of the combustor basket 1
Specifically, the axial direction of the peripheral wall 21 of the resonance chamber 2 coincides with the radial direction of the outer peripheral surface of the cylinder wall 12. Further, the third end 211 of the peripheral wall 21 is disposed on the mounting area 13 of the cylinder wall 12, and the third end 211 of the peripheral wall 21 is in contact with the cylinder wall 12, so that the peripheral wall 21 of the resonance chamber 2 is disposed on the mounting area 13.
Further, the end cap 22 is disposed on the fourth end 212 of the peripheral wall 21 of the resonance chamber 2, so that the peripheral wall 21, the mounting region 13 and the end cap 22 enclose the resonance cavity 24, and a plurality of second through holes 221 are disposed on the end cap 22, and the second through holes 221 communicate the resonance cavity 24 with the outside. Specifically, the axial direction of the outer peripheral surface of the end cap 22 coincides with the axial direction of the peripheral wall 21 of the resonance chamber 2, the end cap 22 is disposed at the fourth end 212 of the peripheral wall 21 of the resonance chamber 2, and the end cap 22 is in contact with the fourth end 212 of the peripheral wall 21, so that the end cap 22, the peripheral wall 21, and the mounting region 13 enclose the resonance cavity 24.
Further, as shown in fig. 1, the resonant chamber 2 further includes a partition 23, the partition 23 is disposed in the resonant cavity 24, and the resonant cavity 24 includes a first cavity 241 and a second cavity 242 separated by the partition 23.
Specifically, the partition 23 is located between the end cover 22 and the mounting area 13 in the radial direction of the cylinder wall 12 of the flame tube 1, the axial direction of the outer peripheral surface of the partition 23 is parallel to the axial direction of the peripheral wall 21 of the resonance chamber 2, and the outer peripheral surface of the partition 23 is in contact with the inner peripheral surface of the peripheral wall 21 of the resonance chamber 2, so that the partition 23 partitions the resonance cavity 24 into the first cavity 241 and the second cavity 242.
Further, the partition 23 is provided with a plurality of third through holes 231, and the third through holes 231 communicate the first cavity 241 and the second cavity 242. Specifically, the axial direction of the inner peripheral surface of the third through hole 231 is parallel to the radial direction of the cylindrical wall 12 of the combustor 1, a plurality of third through holes 231 are provided on the partition plate 23 in the axial direction of the cylindrical wall 12 of the combustor 1, and two adjacent third through holes 231 are provided at intervals.
Specifically, when the combustion chamber is operated, the cooling gas 7 is delivered to the resonance chamber 2 from the outside of the resonance chamber 2, the cooling gas 7 enters the first cavity 241 of the resonance cavity 24 through the second through hole 221 on the end cover 22, and the cooling gas 7 cools the first cavity 241 in the first cavity 241. The cooling gas 7 in the first cavity 241 enters the second cavity 242 through the third through hole 231 of the partition 23, and the cooling gas 7 cools the second cavity 242 in the second cavity 242. The cooling gas 7 in the second cavity 242 is discharged into the flame chamber 11 through the first through-hole 131 of the mounting region 13.
It can be understood that the cooling gas 7 is introduced into the resonance chamber 2 to cool the resonance chamber 2, and the introduction of the cooling gas 7 into the resonance chamber 2 can reduce the hot gas generated by the combustion of the flame tube 1 from entering the resonant cavity 24. And the cooling gas 7 introduced into the fuel nozzle 3 can increase the flow rate of the fuel 9 introduced into the fuel nozzle 3, thereby enhancing the depth of the fuel 9 entering the liner 1, and thus enabling the fuel 9 to be sufficiently burned. In addition, the introduced cooling gas 7 can promote the flow of the fuel gas 8 in the flame tube 1, so that the fuel gas 8 in the flame tube 1 can be fully mixed with the fuel 9 and the combustion-supporting gas 8, and the combustion effect of the fuel gas 8 is improved.
Therefore, the combustion chamber provided by the embodiment of the invention has the advantage of good combustion performance.
In some embodiments, as shown in fig. 2, the mounting area 13 is provided with a first via 132, the partition 23 is provided with a second via 232, and the end cap 22 is provided with a third via 222.
Specifically, the axial direction of the inner peripheral surface of the first through hole 132 coincides with the radial direction of the cylindrical wall 12 of the combustor can 1, the first through hole 132 penetrates the cylindrical wall 12 in the axial direction of the peripheral wall 21 of the resonance chamber 2, and the radial dimension of the inner peripheral surface of the first through hole 132 is equal to the radial dimension of the outer peripheral surface of the fuel nozzle 3. The axial direction of the inner peripheral surface of the second through hole 232 is parallel to the axial direction of the peripheral wall 21, the second through hole 232 penetrates the partition plate 23 in the axial direction of the peripheral wall 21, and the radial dimension of the inner peripheral surface of the second through hole 232 is equal to the radial dimension of the outer peripheral surface of the fuel nozzle 3. The axial direction of the inner peripheral surface of the third through hole 222 is parallel to the axial direction of the peripheral wall 21, the third through hole 222 penetrates the end cover 22 in the axial direction of the peripheral wall 21, and the radial dimension of the inner peripheral surface of the third through hole 222 is equal to the radial dimension of the outer peripheral surface of the fuel nozzle 3.
Further, the first through hole 132, the second through hole 232, and the third through hole 222 are opposed in the axial direction of the peripheral wall 21 of the resonance chamber 2, and the fuel nozzle 3 passes through the first through hole 132, the second through hole 232, and the third through hole 222. Specifically, the fuel nozzle 3 passes through the first, second, and third through holes 132, 232, and 222 in the length direction, and thus, the fuel nozzle 3 can be pierced on the resonance chamber 2.
That is, one end of the fuel nozzle 3 passes through the first through hole 132, the other end of the fuel nozzle 3 passes through the third through hole 222, and the middle of the fuel nozzle 3 is fitted with the second through hole 232. Therefore, the first end 331 of the fuel cavity 33 is located inside the flame cavity 11, so that the flame cavity 11 is communicated with the fuel cavity 33, that is, the nozzle hole 32 is located inside the flame cavity 11, so that the fuel 9 in the fuel nozzle 3 can enter the flame cavity 11 through the nozzle, and the second end 332 of the fuel cavity 33 is located outside the resonance chamber 2, that is, the fuel inlet 31 is located outside the resonance chamber 2, so that the fuel 9 can enter the fuel cavity 33 from the outside through the fuel inlet 31. Therefore, according to the combustor provided by the embodiment of the invention, the fuel nozzle 3 and the resonance chamber 2 are combined, and the fuel 9 sprayed into the flame cavity 11 by the fuel nozzle 3 can be fully mixed with the fuel gas in the flame cavity 11, so that the combustion performance of the combustor provided by the embodiment of the invention is improved, and the space of the combustor provided by the embodiment of the invention can be saved.
In some embodiments, as shown in fig. 1-4, the centre line of the first via coincides with the centre line of the circumferential wall of the resonance chamber 2; or the first through hole is positioned on one side of the center line of the peripheral wall in the axial direction of the flame tube; alternatively, the first through hole is located on the other side of the center line of the peripheral wall in the axial direction of the flame tube.
That is, the fuel nozzle 3 is disposed coaxially with the resonance chamber 2; alternatively, the fuel nozzle 3 is located to the left of the resonance chamber 2 and part of the fuel nozzle 3 is located within the resonance chamber 24; alternatively, the fuel nozzle 3 is located on the right side of the resonance chamber 2 and a portion of the fuel nozzle 3 is located within the resonance chamber 24.
Specifically, as shown in fig. 1 to 2, the center line of the first via hole 132 coincides with the center line of the peripheral wall 21 of the resonance chamber 2. The central axis of the first through hole 132 coincides with the central axis of the peripheral wall 21 of the resonance chamber 2, and the central axis of the second through hole 232 coincides with the central axis of the peripheral wall 21 of the resonance chamber 2, and the central axis of the third through hole 222 coincides with the central axis of the peripheral wall 21 of the resonance chamber 2. Further, the fuel nozzle 3 passes through the first through hole 132, the second through hole 232, and the third through hole 222, so the axial direction of the fuel nozzle 3 coincides with the center line of the peripheral wall 21.
It will be appreciated that in operation of the combustion chamber, fuel 9 enters the flame chamber 11 from the nozzle of the fuel nozzle 3, and cooling gas 7 enters the resonant cavity 24 from the second through-hole 221 in the end cover 22 and enters the flame chamber 11 through the first through-hole 131 in the mounting region 13. The axial direction of the fuel nozzle 3 is coincident with the central line of the peripheral wall 21, so that the cooling gas 7 enhances the circumferential airflow fluidity of the fuel nozzle 3, and the uniformity of the circumferential flow field and the mixing field of the fuel nozzle 3 is increased, thereby improving the combustion performance of the combustion chamber.
As shown in fig. 3, the first through hole 132 is located on one side of the center line of the peripheral wall 21 of the resonance chamber 2 in the axial direction of the combustor basket 1. Specifically, in the axial direction of the flame tube 1, the center axis of the first through hole 132 is located on the left side of the center axis of the peripheral wall 21 of the resonance chamber 2, and the center axis of the second through hole 232 is located on the left side of the center axis of the peripheral wall 21 of the resonance chamber 2, and the center axis of the third through hole 222 is located on the left side of the center axis of the peripheral wall 21 of the resonance chamber 2. Further, the fuel nozzle 3 passes through the first through hole 132, the second through hole 232, and the third through hole 222, and thus the center axis of the fuel nozzle 3 is located on the left side of the center line of the peripheral wall 21.
It will be appreciated that in operation of the combustion chamber, fuel 9 enters the flame chamber 11 from the nozzle of the fuel nozzle 3, and cooling gas 7 enters the resonant cavity 24 from the second through-hole 221 in the end cover 22 and enters the flame chamber 11 through the first through-hole 131 in the mounting region 13. The central axis of the fuel nozzle 3 is positioned on the left side of the central line of the peripheral wall 21 of the resonance chamber 2, so that the cooling gas 7 enhances the fluidity of the gas flow on the right side of the fuel nozzle 3, and the uniformity of the flow field and the mixing field on the right side of the fuel nozzle 3 is increased, thereby improving the combustion performance of the combustion chamber.
As shown in fig. 4, the first through hole 132 is located on the other side of the center line of the peripheral wall 21 of the resonance chamber 2 in the axial direction of the combustor basket 1. Specifically, in the axial direction of the flame tube 1, the center axis of the first through hole 132 is located on the right side of the center axis of the peripheral wall 21 of the resonance chamber 2, and the center axis of the second through hole 232 is located on the right side of the center axis of the peripheral wall 21 of the resonance chamber 2, and the center axis of the third through hole 222 is located on the right side of the center axis of the peripheral wall 21 of the resonance chamber 2. Further, the fuel nozzle 3 passes through the first through hole 132, the second through hole 232, and the third through hole 222, and thus the center axis of the fuel nozzle 3 is located on the right side of the center line of the peripheral wall 21.
It will be appreciated that in operation of the combustion chamber, fuel 9 enters the flame chamber 11 from the nozzle of the fuel nozzle 3, and cooling gas 7 enters the resonant cavity 24 from the second through-hole 221 in the end cover 22 and enters the flame chamber 11 through the first through-hole 131 in the mounting region 13. The central axis of the fuel nozzle 3 is positioned on the right side of the central line of the peripheral wall 21 of the resonance chamber 2, so that the cooling gas 7 enhances the fluidity of the gas flow on the left side of the fuel nozzle 3, and the uniformity of the flow field and the mixing field on the left side of the fuel nozzle 3 is increased, thereby improving the combustion performance of the combustion chamber.
In some embodiments, as shown in fig. 4, the resonant chamber 2 further includes an air duct 4, the air duct 4 includes a fifth end 41 and a sixth end 42, the fifth end 41 and the sixth end 42 are opposite to each other in a length direction of the air duct 4, the length direction of the air duct 4 is in accordance with an axial direction of the peripheral wall 21, the fifth end 41 of the air duct 4 is disposed in the first through hole 132, and the air duct 4 is sleeved on the fuel nozzle 3.
Specifically, the central axis of the air duct 4 and the central axis of the peripheral wall 21 of the resonant chamber 2 are parallel to each other, wherein the radial dimension of the outer peripheral surface of the air duct 4 is equal to the radial dimension of the inner peripheral surfaces of the second through hole 232 and the third through hole 222, so that the air duct 4 passes through the second through hole 232 and the third through hole 222 and is disposed in the resonant cavity 24. The fifth end 41 of the air duct 4 is located in the first through hole 132. The fuel nozzle 3 is arranged in the area enclosed by the inner circumferential surface of the air duct 4, namely the air duct 4 is sleeved on the fuel nozzle 3. And the radial dimension of the inner peripheral surface of the air duct 4 is larger than the radial dimension of the outer peripheral surface of the fuel nozzle 3, and a first gap 5 is formed between the inner peripheral surface of the air duct 4 and the outer peripheral surface of the fuel nozzle 3.
It will be appreciated that, in operation of the combustion chamber, cooling gas can enter the flame chamber 11 through the first gap 5, wherein the cooling gas 7 entering the flame chamber 11 from the first gap 5 is more concentrated, thereby enhancing the depth of entry of the fuel 9 into the flame tube 1 and thus enabling sufficient combustion of the fuel 9. In addition, the introduced cooling gas 7 can promote the flow of the fuel gas 8 in the flame tube 1, so that the fuel gas 8 in the flame tube 1 can be fully mixed with the fuel 9 and the combustion-supporting gas 8, and the combustion effect of the fuel gas 8 is improved.
Therefore, the combustion chamber provided by the embodiment of the invention has the advantage of good combustion performance.
In some embodiments, as shown in fig. 6, the sixth end 42 of the air duct 4 is located in the first cavity 241, that is, in the radial direction of the cylinder wall 12 of the flame tube 1, the axial dimension of the air duct 4 is smaller than the distance separating the cylinder wall 12 of the flame tube 1 from the partition 23.
Alternatively, as shown in fig. 6, the sixth end 42 of the air duct 4 is located in the second cavity 242, that is, in the radial direction of the wall 12 of the flame tube 1, the axial dimension of the air duct 4 is smaller than the distance between the wall 12 of the flame tube 1 and the end cover 22, and the axial dimension of the air duct 4 is larger than the distance between the wall 12 of the flame tube 1 and the partition 23.
Or, as shown in fig. 4, the sixth end 42 of the air duct 4 is disposed in the third through hole 222, that is, in the radial direction of the cylinder wall 12 of the flame tube 1, the axial dimension of the air duct 4 is equal to the spacing distance between the cylinder wall 12 of the flame tube 1 and the end cover 22.
According to the combustion chamber disclosed by the embodiment of the invention, the axial size of the air duct 4 is changed, so that the frequency of the thermo-acoustic wave which can be inhibited by the resonant cavity 24 is adjusted.
In some embodiments, as shown in fig. 8, the resonance chamber 2 further comprises a swirler 6, the swirler 6 is sleeved on the fuel nozzle 3, and the air duct 4 is sleeved on the swirler 6.
Specifically, the swirler 6 is disposed in the first gap 5 between the fuel nozzle 3 and the air duct 4, wherein the swirler 6 is fitted over the outer circumferential surface of the fuel nozzle 3. It can be understood that, when the combustion chamber is operated, the cyclone 6 is started, the cyclone 6 can enable the cooling gas 7 which is introduced into the first gap 5 to form a cyclone to enter the flame cavity 11, and the cyclone formed by the cooling gas 7 can fully mix the fuel gas 8 and the fuel 9 in the flame cavity 11, so that the combustion effect of the combustion chamber is enhanced.
It will be appreciated that in some embodiments, the swirler 6 has a plurality of swirl vanes, and the plurality of swirl vanes are arranged at intervals along the circumference of the wind barrel 4, so that the cooling gas 7 introduced into the first gap 5 can form a cyclone after passing through the swirler 6, thereby sufficiently mixing the fuel gas 8 and the fuel 9 in the flame chamber 11, and thus enhancing the combustion effect of the combustion chamber.
In other embodiments, the swirler 6 is free to rotate. It can be understood that the cooling gas 7 passes through the swirler 6, and the cooling gas 7 can provide a force to the vanes of the swirler 6, so that the swirler 6 can rotate under the action of the cooling gas 7, and therefore, the cooling gas 7 introduced into the first gap 5 can form a cyclone after passing through the swirler 6, so that the fuel gas 8 and the fuel 9 in the flame chamber 11 are sufficiently mixed, and the combustion effect of the combustion chamber is enhanced.
A gas turbine according to an embodiment of the invention comprises a combustor according to any of the embodiments described above.
Specifically, the gas turbine of the embodiment of the invention further comprises a compressor and a turbine. Wherein the compressor presses combustion gas 8 into the combustion chamber of any of the above embodiments, where it is mixed with fuel 9 and burned, and further, the turbine is operated by the energy generated by the combustion in the combustion chamber. The combustion chamber of the embodiment of the invention is provided with the resonance chamber 2, so that the thermo-acoustic instability during combustion in the combustion chamber is inhibited, the combustion performance of the fuel 9 in the combustion chamber is improved, and the resonance chamber 2 and the nozzle of the fuel 9 are combined, so that the space of the fuel 9 chamber is saved.
Therefore, the gas turbine provided by the embodiment of the invention has the advantage of good combustion performance.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In the present invention, unless otherwise explicitly stated or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly, e.g., as being permanently connected, detachably connected, or integral; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the second feature or the first and second features may be indirectly contacting each other through intervening media. Also, a first feature "on," "above," and "over" a second feature may be directly on or obliquely above the second feature, or simply mean that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples" and the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (9)
1. A combustor, comprising:
the flame tube comprises a tube wall and a flame cavity defined by the tube wall, the tube wall comprises a mounting area, and the mounting area is provided with a plurality of first through holes penetrating through the tube wall;
the resonant chamber is provided with a resonant cavity, the resonant chamber is arranged on the mounting area, the first through hole is communicated with the resonant cavity and the flame cavity, and the resonant cavity is communicated with the outside; and
the fuel nozzle is partially positioned in the resonant cavity and provided with a fuel cavity, a spray hole and a fuel inlet, the fuel cavity comprises a first end and a second end, the first end and the second end are opposite to each other in the length direction of the fuel nozzle, the spray hole is formed in the first end of the fuel cavity, the fuel inlet is formed in the second end of the fuel cavity, the spray hole is communicated with the flame cavity and the fuel cavity, and the fuel inlet is communicated with the fuel cavity and the outside;
the resonant chamber comprises a peripheral wall and an end cover, the peripheral wall comprises a third end and a fourth end, the third end and the fourth end are opposite in the axial direction of the peripheral wall, the third end of the peripheral wall is arranged on the mounting area, the end cover is arranged on the fourth end of the peripheral wall, so that the peripheral wall, the mounting area and the end cover surround to form the resonant cavity, a plurality of second through holes are formed in the end cover, and the second through holes are communicated with the resonant cavity and the outside.
2. The combustion chamber of claim 1 wherein the resonance chamber further comprises a baffle disposed within the resonance chamber, the resonance chamber including a first cavity and a second cavity separated by the baffle, the baffle being provided with a plurality of third through holes, the third through holes communicating the first cavity with the second cavity.
3. The combustor of claim 2, wherein the fuel nozzle length direction coincides with an axial direction of the peripheral wall, which coincides with a radial direction of the combustor basket.
4. The combustor of claim 2, wherein said mounting area is provided with a first through hole, said partition is provided with a second through hole, said end cap is provided with a third through hole, said first through hole, said second through hole and said third through hole are opposed in an axial direction of said peripheral wall, and said fuel nozzle passes through said first through hole, said second through hole and said third through hole.
5. The combustion chamber of claim 4 wherein a centerline of the first via coincides with a centerline of the peripheral wall; or the first through hole is positioned on one side of the center line of the peripheral wall in the axial direction of the flame tube; alternatively, the first through hole is located on the other side of the center line of the peripheral wall in the axial direction of the flame tube.
6. The combustor of claim 4, wherein said resonant chamber further comprises an air duct, said air duct comprising a fifth end and a sixth end, said fifth end and said sixth end being opposite to each other in a length direction of said air duct, said length direction of said air duct being in axial alignment with said peripheral wall, said fifth end of said air duct being disposed in said first through hole, said air duct being fitted over said fuel nozzle.
7. The combustion chamber of claim 6 wherein said sixth end of said air duct is located within said first cavity; or the sixth end of the air duct is located in the second cavity; or the sixth end of the air duct is arranged in the third through hole.
8. The combustor of claim 7, wherein said resonating chamber further comprises a swirler disposed over said fuel injector and over said air duct disposed over said swirler.
9. A gas turbine, characterized in that it comprises a combustion chamber according to any one of claims 1 to 8.
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| DE19504610C2 (en) * | 1995-02-13 | 2003-06-18 | Alstom | Device for damping thermoacoustic pressure vibrations |
| DE10055408A1 (en) * | 2000-11-09 | 2002-05-23 | Alstom Switzerland Ltd | Process for fuel injection into a burner |
| US6792747B2 (en) * | 2001-02-07 | 2004-09-21 | James R. Schierbaum | Turbo shaft engine with acoustical compression flow amplifying ramjet |
| US8789372B2 (en) * | 2009-07-08 | 2014-07-29 | General Electric Company | Injector with integrated resonator |
| CN101852444B (en) * | 2010-05-26 | 2012-06-13 | 白野 | Microwave plasma ignition device |
| US9310072B2 (en) * | 2012-07-06 | 2016-04-12 | Hamilton Sundstrand Corporation | Non-symmetric arrangement of fuel nozzles in a combustor |
| US8684130B1 (en) * | 2012-09-10 | 2014-04-01 | Alstom Technology Ltd. | Damping system for combustor |
| US10088165B2 (en) * | 2015-04-07 | 2018-10-02 | General Electric Company | System and method for tuning resonators |
| 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 |
| JP6483510B2 (en) * | 2015-04-14 | 2019-03-13 | 三菱日立パワーシステムズ株式会社 | Gas turbine manufacturing method |
| KR101985081B1 (en) * | 2017-07-14 | 2019-05-31 | 두산중공업 주식회사 | Combustion apparatus and gas turbine including the same |
| EP3438540A1 (en) * | 2017-07-31 | 2019-02-06 | Siemens Aktiengesellschaft | A burner including an acoustic damper |
| JP2020056542A (en) * | 2018-10-02 | 2020-04-09 | 川崎重工業株式会社 | Annular type gas turbine combustor for aircraft |
| CN111174232A (en) * | 2018-11-12 | 2020-05-19 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and micro-mixing nozzle thereof |
| CN112984559A (en) * | 2021-03-19 | 2021-06-18 | 中国联合重型燃气轮机技术有限公司 | Flame tube, combustion chamber, and gas turbine |
| CN113137630B (en) * | 2021-04-19 | 2022-05-31 | 杭州汽轮动力集团有限公司 | Gas turbine combustion chamber for dual suppression of thermoacoustic oscillation |
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