CN114909675B - Combustion chamber for a gas turbine and gas turbine - Google Patents
Combustion chamber for a gas turbine and gas turbine Download PDFInfo
- Publication number
- CN114909675B CN114909675B CN202210365110.2A CN202210365110A CN114909675B CN 114909675 B CN114909675 B CN 114909675B CN 202210365110 A CN202210365110 A CN 202210365110A CN 114909675 B CN114909675 B CN 114909675B
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- chamber
- lobe
- inner tube
- airflow
- gas turbine
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 118
- 238000001816 cooling Methods 0.000 claims description 19
- 238000004891 communication Methods 0.000 claims description 14
- 238000009434 installation Methods 0.000 claims description 11
- 238000005192 partition Methods 0.000 claims description 6
- 230000002093 peripheral effect Effects 0.000 claims description 5
- 230000010355 oscillation Effects 0.000 abstract description 19
- 230000008901 benefit Effects 0.000 abstract description 12
- 239000007789 gas Substances 0.000 description 59
- 230000000694 effects Effects 0.000 description 11
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 239000000112 cooling gas Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 239000012530 fluid Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000452 restraining effect Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000003028 elevating effect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000009545 invasion Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
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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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/02—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion characterised by the arrangement of the combustion chamber in the chamber in the plant
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- 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
Embodiments of the present invention provide a combustor for a gas turbine and a gas turbine. Wherein a combustion chamber for a gas turbine of an embodiment of the present invention includes a combustion chamber body having an airflow passage, a mixer provided in the airflow passage so as to divide the airflow passage into an inner passage and an outer passage, and a resonance chamber provided on the mixer, the resonance chamber having a resonance cavity, the resonance cavity and at least one of the inner passage and the outer passage being communicable with the outside. Therefore, the combustion chamber for the gas turbine has the advantages of reducing thermoacoustic oscillation in the combustion chamber and avoiding local overtemperature.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustion chamber for a gas turbine and the gas turbine with the combustion chamber for the gas turbine.
Background
The gas turbine mainly comprises three parts, namely a gas compressor, a combustion chamber and a turbine, wherein exhaust gas of the gas compressor is mixed with fuel in the combustion chamber to participate in combustion, and the combustion chamber of the gas turbine works under a lean combustion condition, so that thermoacoustic instability is extremely easy to occur. In addition, especially in the secondary combustion, the front heat source and the rear heat source are more prone to thermoacoustic instability and more prone to thermoacoustic oscillation.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems in the related art to some extent. To this end, an embodiment of the invention proposes a combustion chamber for a gas turbine. The combustion chamber for the gas turbine has the advantages of reducing thermoacoustic oscillations in the combustion chamber and avoiding local overtemperature.
The embodiment of the invention also provides a gas turbine.
The combustor for a gas turbine according to an embodiment of the present invention includes: a combustion chamber body, a mixer and a resonance chamber.
The combustion chamber body has an air flow passage, the mixer is disposed in the air flow passage so as to divide the air flow passage into an inner passage and an outer passage, the resonance chamber is disposed on the mixer, the resonance chamber has a resonance cavity, the resonance cavity communicates with at least one of the inner passage and the outer passage, and the resonance cavity is capable of communicating with the outside.
Compared with the related art, the combustion chamber for the gas turbine, which is provided by the embodiment of the invention, has the advantages that the resonant chamber is arranged in the air flow channel, and the sound wave with specific frequency in the air flow channel can be counteracted by arranging the resonant chamber in the combustion chamber body, so that the coupling between heat release and sound pressure is avoided, and the feedback loop possibly formed by the heat release and the sound pressure is broken. Has the function of improving the specific frequency sound wave range and effect of the inside of the absorption airflow channel. Therefore, the thermoacoustic oscillation in the combustion chamber is reduced, the thermoacoustic oscillation amplitude in the combustion chamber is prevented from being overlarge, and the method has the advantages of stabilizing the structure of the combustion chamber and prolonging the service life of the combustion chamber.
According to the combustion chamber for the gas turbine, provided by the embodiment of the invention, the mixer is arranged in the combustion chamber of the gas turbine, so that the effect of mixing the gas in the combustion chamber is achieved, the uniformity of gas distribution in the combustion chamber is improved, the problem of local overtemperature in the combustion chamber is avoided, and the combustion stability is further improved. At the same time, the placement of the resonating chamber on the mixer may provide a fixation site for the installation of the resonating chamber. Thereby improving the stability and convenience of the fixation of the resonant chamber.
In addition, the cooling gas can inhibit fluctuation generated by heat release through the communication of the resonance chamber with the outside, and further break the coupling between heat release and sound pressure. Thereby further suppressing the occurrence of thermo-acoustic oscillations of the combustion chamber.
Thus, the combustion chamber for the gas turbine has the advantages of reducing thermoacoustic oscillation inside the combustion chamber and avoiding local overtemperature. In addition, the stability and convenience of resonance chamber fixed have still been promoted to this combustion chamber.
In some embodiments, the mixer has an airflow chamber inside, the airflow chamber being in communication with the resonant cavity, the airflow chamber being capable of communicating with the outside.
In some embodiments, the airflow chamber and the airflow channel communicate.
In some embodiments, the mixer includes an inner tube and an outer tube, the inner tube and the outer tube forming the airflow chamber therebetween.
In some embodiments, each of the outer tube and the inner tube is lobe-shaped, the inner tube comprising an inner tube lobe peak, an inner tube lobe trough, and an inner tube lobe sidewall connecting the inner tube lobe peak and the inner tube lobe trough; the outer tube includes an outer tube lobe peak, an outer tube lobe trough, and an outer tube lobe sidewall connecting the outer tube lobe peak and the outer tube lobe trough, the inner tube lobe peak is disposed corresponding to the outer tube lobe peak, the inner tube lobe trough is disposed corresponding to the outer tube lobe trough, and the inner tube lobe sidewall is disposed corresponding to the outer tube lobe sidewall so as to make the formed airflow cavity be in a lobe shape.
In some embodiments, the distance from the inner tube lobe peak to the inner tube lobe trough is progressively deeper from the front end to the back end of the mixer, and the distance from the outer tube lobe peak to the outer tube lobe trough is progressively deeper from the front end to the back end of the mixer.
In some embodiments, the resonant chamber has an opening, a plurality of first through holes are formed in a wall surface of the resonant chamber, a mounting area is formed in the inner tube and/or the outer tube, a plurality of second through holes are formed in the mounting area, and one end of the resonant chamber having the opening is connected with the mounting area, so that one of the inner channel and the outer channel is sequentially communicated with the first through holes, the resonant cavity, the second through holes and the airflow cavity.
In some embodiments, the first through hole is provided at a bottom wall and/or a peripheral wall of the resonance chamber.
In some embodiments, the mounting area is a plurality of the resonant chambers, and the resonant chambers are arranged on the mounting area of the outer tube and/or the inner tube at intervals.
In some embodiments, the combustion chamber for a gas turbine further comprises a cooling channel, one end of which is in communication with the airflow cavity, and the other end of which is capable of communicating with the outside.
In some embodiments, the combustor for a gas turbine further comprises a support bracket, one end of the support bracket is connected to the mixer, and the other end of the support bracket is connected to the combustor body.
In some embodiments, the support frame has a hollow inner lumen, the inner lumen being the cooling channel, one end of the support frame is connected to the outer tube and the inner lumen is in communication with the airflow chamber, the other end of the support frame is connected to the combustion chamber body and the inner lumen is capable of communicating with the outside.
In some embodiments, the inner tube includes a first tube body and a first flange portion, the first tube body extends along an axial direction of the combustion chamber body, the first flange portion extends along a radial direction of the combustion chamber body, and the first flange portion is disposed at a front end of the first tube body, the outer tube includes a second tube body and a second flange portion, the second tube body extends along the axial direction of the combustion chamber body, the second flange portion extends along the radial direction of the combustion chamber body, and the second flange portion is disposed at the front end of the second tube body, a connecting plate is disposed between the first flange portion and the second flange portion, and an air guide hole is disposed on the connecting plate and is communicated with the inner tube cavity.
In some embodiments, the combustion chamber for a gas turbine further comprises a partition disposed within the airflow chamber so as to divide the airflow chamber into a plurality of airflow subchambers, the support bracket being provided in plurality, the plurality of support brackets being disposed at intervals along a circumference of the outer passage, the airflow subchambers being correspondingly in communication with the inner tube chamber.
The gas turbine provided by the embodiment of the invention comprises the combustion chamber for the gas turbine.
Drawings
FIG. 1 is an isometric view of a combustion chamber according to one embodiment of the invention.
Fig. 2 is an enlarged view of fig. 1 at a.
FIG. 3 is a schematic view of the arrangement of a combustion chamber according to an embodiment of the present invention.
Fig. 4 is an enlarged view of fig. 3 at B.
Reference numerals:
a combustion chamber 100;
a combustion chamber body 1; an air flow passage 11; an inner channel 111; an outer channel 112;
a mixer 2; an inner tube 21; a first tube 211; an inner tube lobe peak 2111; inner tube lobe trough 2112; inner tube lobe sidewall 2113; a first burring part 212;
an outer tube 22; a second pipe body 221; an outer tube lobe peak 2211; outer tube lobe trough 2212; an outer tube lobe side wall 2213; a second burring part 222;
a second through hole 23; an airflow chamber 24; a connection plate 25;
a resonance chamber 3; a resonant cavity 31; a first through hole 32; an opening 33;
a support frame 4; an inner lumen 41;
and a cooling channel 5.
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 by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
A combustor 100 for a gas turbine according to an embodiment of the present invention is described below with reference to fig. 1-4.
The combustion chamber 100 for a gas turbine of an embodiment of the present invention includes a combustion chamber body 1, a mixer 2, and a resonance chamber 3.
The combustion chamber body 1 has an air flow passage 11, and the mixer 2 is disposed in the air flow passage 11 so as to divide the air flow passage 11 into an inner passage 111 and an outer passage 112. The resonance chamber 3 is provided on the mixer 2, the resonance chamber 3 has a resonance chamber 31, the resonance chamber 31 communicates with at least one of the inner passage 111 and the outer passage 112, and the resonance chamber 31 can communicate with the outside.
In other words, the resonance chamber 3 is provided inside the airflow passage 11, and the resonance chamber 31 communicates with the inner passage 111. Alternatively, the resonant cavity 31 communicates with the outer channel 112. Alternatively, the resonant cavity 31 communicates with each of the inner passage 111 and the outer passage 112. Specifically, by communicating the resonant cavity 31 with the outside, intrusion of hot air located in the at least one of the inner passage 111 and the outer passage 112 into the resonant cavity 31 can be avoided, thereby making the resonant cavity 31 function as a feedback loop for breaking heat release and sound pressure formation.
In the related art, the resonance chamber is disposed on the outer wall of the flame tube, or on the stepped end face of the flame tube of the primary combustion chamber and the secondary combustion chamber, or on the cap before the primary combustion chamber, so as to suppress thermo-acoustic oscillations in the combustion chamber.
By disposing the resonance chamber 3 inside the gas flow passage 11, the combustion chamber 100 for a gas turbine of the embodiment of the present invention can cancel out sound waves of a specific frequency inside the gas flow passage 11 by disposing the resonance chamber 3 inside the combustion chamber body 1, and avoid coupling between heat release and sound pressure, thereby breaking a feedback loop that may be formed by the heat release and sound pressure, compared to the related art. Has the effect of elevating the range and effect of absorbing the specific frequency sound waves of the inside of the airflow passage 11. Therefore, the thermoacoustic oscillation in the combustion chamber 100 is reduced, the thermoacoustic oscillation amplitude in the combustion chamber 100 is prevented from being overlarge, and the method has the advantages of stabilizing the structure of the combustion chamber 100 and prolonging the service life of the combustion chamber 100.
According to the combustion chamber 100 for the gas turbine, provided by the embodiment of the invention, the mixer 2 is arranged in the combustion chamber 100 of the gas turbine, so that the effect of mixing the gas in the combustion chamber 100 is achieved, the uniformity of gas distribution in the combustion chamber 100 is improved, the problem of local overtemperature in the combustion chamber 100 is avoided, and the combustion stability is further improved. At the same time, the placement of the resonance chamber 3 on the mixer 2 may provide a fixation site for the installation of the resonance chamber 3. Thereby improving the stability and convenience of the fixation of the resonance chamber 3.
In addition, by communicating the resonance chamber 3 with the outside, cooling gas (for example, fuel and/or air) can be made to enter the resonance chamber 3, and the cooling gas can suppress fluctuation generated by heat release, further breaking the coupling between heat release and sound pressure. Thereby further suppressing occurrence of thermo-acoustic oscillations of the combustion chamber 100.
Thus, the combustor 100 for a gas turbine of an embodiment of the present invention has the advantage of reducing thermo-acoustic oscillations inside the combustor 100, avoiding the occurrence of localized overtemperatures. In addition, the combustion chamber 100 has the advantage of improving the stability and convenience of the fixation of the resonance chamber 3.
As shown in fig. 1 and 3, the mixer 2 has an airflow chamber 24 inside, the airflow chamber 24 communicates with a resonance chamber 31, and the airflow chamber 24 can communicate with the outside. In other words, the airflow chamber 24 communicates with the outside communication and the resonant chamber 31. It will be appreciated that the outside, airflow chamber 24, and resonant chamber 31 communicate with the internal passage 111. Or the outside, the airflow chamber 24, and the resonant chamber 31 communicate with the outer passage 112. Alternatively, the outside, the airflow chamber 24, the resonant chamber 31 may communicate with each of the inner passage 111 and the outer passage 112.
The airflow chamber 24 is provided on the mixer 2, and the mixer 2 itself is provided with the airflow chamber 24.
The combustion chamber 100 for a gas turbine according to the embodiment of the present invention widens the range of suppressing the thermo-acoustic oscillation frequency by providing the airflow chamber 24 on the mixer 2 and communicating the airflow chamber 24 with the resonance chamber 31, which corresponds to the resonance chamber 31 forming a double-chamber with the airflow chamber 24 of the mixer 2. Therefore, the problems of low service life of the combustion chamber 100 and poor structural stability of the combustion chamber 100 caused by overlarge intensity of thermoacoustic oscillation of the combustion chamber 100 are avoided.
As shown in fig. 1 and 3, the airflow chamber 24 communicates with the airflow passage 11.
According to the combustion chamber 100 for the gas turbine, the air flow cavity 24 is communicated with the air flow channel 11, so that external cooling air can enter the air flow cavity 24 and then flow into the air flow channel 11, and further new cooling air can continuously enter the air flow cavity 24, so that the air flow cavity 24 has continuous cooling air, and the effect of restraining thermoacoustic oscillation by the resonant cavity 31 and the resonant cavity 31 of the double cavities formed by the air flow cavity 24 of the mixer 2 is improved. In addition, outside air and/or fuel may be injected into the airflow passage 11 through the airflow chamber 24, enhancing the combustion effect in the combustion chamber 100.
As shown in fig. 1 and 3, the mixer 2 includes an inner tube 21 and an outer tube 22, with an airflow chamber 24 formed between the inner tube 21 and the outer tube 22.
The combustion chamber 100 for a gas turbine of the embodiment of the present invention is divided into an inner tube 21 and an outer tube 22 by a mixer 2, and an airflow chamber 24 is formed between the inner tube 21 and the outer tube 22. By forming the airflow cavity 24 between the inner tube 21 and the outer tube 22, the direct invasion of the hot air in the combustion chamber 100 into the airflow cavity 24 can be reduced, and the effect of restraining the thermoacoustic oscillation by the resonant cavity 31 and the resonant cavity 31 formed into a double cavity by the airflow cavity 24 of the mixer 2 is further improved. Simultaneously, the inner tube 21 and the outer tube 22 are arranged, and the device has the advantages of simple structure and good stability.
Optionally, the inner tube 21 and the outer tube 22 are arranged spaced apart so as to form an airflow chamber 24.
As shown in fig. 1 and 2, each of the outer tube 22 and the inner tube 21 is lobe-shaped, the inner tube 21 including an inner tube lobe peak 2111, an inner tube lobe trough 2112, and an inner tube lobe sidewall 2113 connecting the inner tube lobe peak 2111 and the inner tube lobe trough 2112; the outer tube 22 includes an outer tube lobe peak 2211, an outer tube lobe trough 2212, and an outer tube lobe side wall 2213 connecting the outer tube lobe peak 2211 and the outer tube lobe trough 2212.
The inner tube lobe peak 2111 is provided corresponding to the outer tube lobe peak 2211, the inner tube lobe trough 2112 is provided corresponding to the outer tube lobe trough 2212, and the inner tube lobe side wall 2113 is provided corresponding to the outer tube lobe side wall 2213 so as to make the formed airflow chamber 24 into a lobe shape.
According to the combustion chamber 100 for the gas turbine, provided by the embodiment of the invention, the outer tube 22 and the inner tube 21 are arranged in the lobe shape, so that the gas mixing capability of the combustion chamber 100 can be greatly improved, and the combustion stability and the uniformity of the temperature distribution in the combustion chamber 100 are further improved. Thereby, combustion sufficiency and flame stability of the high-velocity fluid in the combustion chamber 100 are improved.
Optionally, the distance from the inner tube lobe peak 2111 to the inner tube lobe trough 2112 increases gradually from the front end to the rear end of the mixer 2, and the distance from the outer tube lobe peak 2211 to the outer tube lobe trough 2212 increases from the front end to the rear end of the mixer 2 (the front end refers to the upstream of the airflow direction, the rear end refers to the downstream of the airflow direction, for example, the front end of the mixer 2 is on the left side in fig. 3, and the rear end of the mixer 2 is on the right side in fig. 3). This can further improve the flame stability of the high-velocity fluid in the combustion chamber 100.
For example, the combustion chamber 100 of the embodiment of the present invention may be a secondary combustion chamber of a gas turbine, wherein the front end of the mixer 2 is connected to the primary combustion chamber, the rear end of the mixer 2 is connected to a transition section, and the transition section is connected to a turbine chamber, wherein the gas flows sequentially pass through the primary combustion chamber, the secondary combustion chamber and the turbine chamber.
Alternatively, as shown in fig. 1, the resonating chambers 3 are plural, and the plural resonating chambers 3 may be provided on at least one of the outer tube lobe peak 2211, the outer tube lobe trough 2212, and the outer tube lobe side wall 2213. Because the outer tube lobe peak 2211, outer tube lobe trough 2212, and outer tube lobe side wall 2213 are relatively gentle, there is an advantage in that the resonating chamber 3 is easily installed.
Alternatively, the resonating chamber 3 may be a rectangular resonating chamber 3 or a cylindrical resonating chamber 3.
As shown in fig. 1 and 2, the resonating chambers 3 have openings 33, a plurality of first through holes 32 are provided on the wall surface of each resonating chamber 3, a mounting area is provided on at least one of the inner tube 21 and the outer tube 22, a plurality of second through holes 23 are provided on the mounting area, and one end of the resonating chamber 3 having the opening 33 is connected to the mounting area so that at least one of the inner passage 111 and the outer passage 112 is in communication with the first through holes 32, the resonating chamber 31, the second through holes 23, and the airflow chamber 24 in order. In other words, the resonance chamber 3 is provided on the inner tube 21, or the resonance chamber 3 is provided on the outer tube 22, and the resonance chamber 3 is provided on the inner tube 21 and the outer tube 22.
The combustion chamber 100 for a gas turbine according to the embodiment of the present invention, through the plurality of first through holes 32 provided on the wall surface of the resonant chamber 3, can ensure that the resonant chamber 3 is communicated with at least one of the inner channel 111 and the outer channel 112, thereby suppressing the thermo-acoustic oscillation of the combustion chamber 100. The provision of the plurality of first through holes 32 can uniformly disperse the hot air entering at least one of the inner channel 111 and the outer channel 112 into the resonant chamber 3, thereby avoiding the problem of failure of the resonant cavity due to local overhigh temperature. This further improves the effect of suppressing thermoacoustic noise.
Optionally, the first through hole 32 is provided in the bottom wall and/or the peripheral wall of the resonance chamber 3. In other words, the first through hole 32 may be provided on the bottom wall of the resonance chamber 3. The first through hole 32 may also be provided on the peripheral wall of the resonance chamber 3. The first through hole 32 may also be provided on the bottom wall and the peripheral wall of the resonance chamber 3.
Alternatively, the number of the installation areas is plural, the number of the resonance chambers 3 is plural, and the plural resonance chambers 3 are provided on the installation areas of the outer tube 22 and/or the inner tube 21 at intervals.
According to the combustion chamber 100 for the gas turbine, provided by the embodiment of the invention, the effect of suppressing the thermoacoustic vibration can be further improved by arranging the plurality of resonant chambers 3.
As shown in fig. 1, the combustion chamber 100 for a gas turbine further includes a cooling passage 5, one end of the cooling passage 5 communicates with the airflow chamber 24, and the other end of the cooling passage 5 can communicate with the outside.
In other words, the outside, the cooling passage 5, the airflow chamber 24, and the resonance chamber 31 communicate in this order.
The combustion chamber 100 for a gas turbine according to the embodiment of the present invention introduces external gas into the airflow chamber 24 through the cooling passage 5, so that communication between the cooling passage 5, the airflow chamber 24 and the resonance chamber 31 is facilitated.
As shown in fig. 1 and 3, the combustion chamber 100 for a gas turbine further includes a support frame 4, one end of the support frame 4 is connected to the mixer 2, and the other end of the support frame 4 is connected to the combustion chamber body 1.
The combustor 100 for a gas turbine according to the embodiment of the present invention can improve the stability of the installation of the mixer 2 by providing the support frame 4.
As shown in fig. 1 and 3, the support frame 4 has a hollow inner tube cavity 41, the inner tube cavity 41 is a cooling channel 5, one end of the support frame 4 is connected to the outer tube 22 and the inner tube cavity 41 is communicated with the air flow cavity 24, the other end of the support frame 4 is connected to the combustion chamber body 1 and the inner tube cavity 41 can be communicated with the outside. In other words, the cooling channel 5 is provided in the support frame 4.
The combustion chamber 100 for the gas turbine in the embodiment of the invention is arranged in the support frame 4 through the cooling channel 5, so that the support frame 4 not only can play a role in fixing the mixer 2, but also can pass through the outside air in the interior, and has the effect of simplifying the parts and installation of the combustion chamber 100.
Optionally, the inner tube 21 includes a first tube body 211 and a first flanging portion 212, the first tube body 211 extends along the axial direction of the combustion chamber body 1, the first flanging portion 212 extends along the radial direction of the combustion chamber body 1, the first flanging portion 212 is disposed at the front end of the first tube body 211, the outer tube 22 includes a second tube body 221 and a second flanging portion 222, the second tube body 221 extends along the axial direction of the combustion chamber body 1, the second flanging portion 222 extends along the radial direction of the combustion chamber body 1, the second flanging portion 222 is disposed at the front end of the second tube body 221, a connecting plate 25 is disposed between the first flanging portion 212 and the second flanging portion 222, and an air hole is disposed on the connecting plate 25 and is communicated with the inner tube cavity 41.
The combustion chamber 100 for a gas turbine according to the embodiment of the present invention can improve the stability of the connection between the inner tube 21 and the outer tube 22 by providing the first flange portion 212 and the second flange portion 222 extending in the radial direction of the combustion chamber body 1 and providing the connection plate 25 between the first flange portion 212 and the second flange portion 222, and at the same time, provide a corresponding site for the installation of the support frame 4, thereby ensuring the communication between the inner tube cavity 41 (cooling passage 5) and the air flow cavity 24. Has the advantages of simple structure and convenient installation.
The combustion chamber 100 for the gas turbine further includes a partition plate (not shown) provided in the airflow chamber 24 so as to partition the airflow chamber 24 into a plurality of airflow sub-chambers, the support frame 4 being provided in plurality, the plurality of support frames 4 being provided at intervals in the circumferential direction of the outer passage 112, the airflow sub-chambers being respectively communicated with the inner tube chamber 41. In other words, the cooling passages 5 are provided at intervals in the circumferential direction of the outer passage 112, and the plurality of support frames 4 are correspondingly communicated with the airflow sub-chambers.
The combustion chamber 100 for a gas turbine according to the embodiment of the present invention can further enhance the frequency and range of the suppression of the thermoacoustic oscillations by the airflow chamber 24 and the resonance chamber 31 by providing a partition inside to divide the airflow chamber 24 into a plurality of airflow sub-chambers. Furthermore, the provision of a plurality of support brackets 4 can also promote the stability of the installation of the mixer 2.
Alternatively, a partition may be provided in the region of the inner tube lobe trough 2112 corresponding to the outer tube lobe trough 2212, as shown in fig. 1, the airflow chamber 24 is divided into 6 airflow sub-chambers, and a plurality of resonance chambers 3 are provided on each of the airflow sub-chambers. A part of the resonance chamber 3 is arranged on the outer tube lobe 2211, which part of the resonance chamber 3 is arranged at a distance along the extension direction of the combustion chamber body 1. Another part of the resonance chamber 3 is arranged on the outer tube lobe side wall 2213, which part of the resonance chamber 3 is arranged at a distance along the extension direction of the combustion chamber body 1. A further part of the resonance chamber 3 is arranged in the outer tube lobe 2212, which part of the resonance chamber 3 is arranged at a distance along the extension of the combustion chamber body 1.
The gas turbine of an embodiment of the invention comprises a combustion chamber 100 for a gas turbine according to any of the embodiments described above.
The gas turbine of the embodiment of the present invention has the advantage of reducing thermo-acoustic oscillations within the combustor 100 and avoiding localized overtemperature.
Alternatively, the combustor 100 for a gas turbine may be applied to the primary combustor 100 or the secondary combustor 100 of the gas turbine.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., 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 invention. In this specification, schematic representations of the above terms are not necessarily directed 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, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.
Claims (10)
1. A combustor for a gas turbine, comprising:
a combustion chamber body having an airflow passage;
a mixer disposed within the airflow passage so as to divide the airflow passage into an inner passage and an outer passage;
a resonance chamber provided on the mixer, the resonance chamber having a resonance cavity, the resonance cavity being in communication with at least one of the inner and outer channels, the resonance cavity being capable of communicating with the outside;
the interior of the mixer is provided with an airflow cavity which is communicated with the resonant cavity and can be communicated with the outside; the mixer comprises an inner pipe and an outer pipe, wherein the airflow cavity is formed between the inner pipe and the outer pipe;
each of the outer tube and the inner tube is lobe-shaped, the inner tube including an inner tube lobe peak, an inner tube lobe trough, and an inner tube lobe sidewall connecting the inner tube lobe peak and the inner tube lobe trough; the outer tube includes an outer tube lobe peak, an outer tube lobe trough, and an outer tube lobe sidewall connecting the outer tube lobe peak and the outer tube lobe trough.
2. The combustion chamber for a gas turbine of claim 1, the airflow cavity and the airflow passage communicating.
3. A combustor for a gas turbine as claimed in claim 1,
the inner tube lobe peaks and the outer tube lobe peaks are arranged correspondingly, the inner tube lobe troughs and the outer tube lobe troughs are arranged correspondingly, and the inner tube lobe side walls and the outer tube lobe side walls are arranged correspondingly so that the formed airflow cavity takes a lobe shape.
4. A combustor for a gas turbine as claimed in claim 1,
the distance from the peak of the inner tube lobe to the trough of the inner tube lobe gradually deepens from the front end to the rear end of the mixer, and the distance from the peak of the outer tube lobe to the trough of the outer tube lobe deepens from the front end to the rear end of the mixer.
5. The combustor for a gas turbine according to claim 1, wherein the resonating chamber has an opening, a plurality of first through holes are provided on a wall surface of the resonating chamber, a mounting area is provided on the inner tube and/or the outer tube, a plurality of second through holes are provided on the mounting area, and one end of the resonating chamber having the opening is connected to the mounting area so that at least one of the inner passage and the outer passage is in communication with the first through holes, the resonating cavity, the second through holes, and the airflow cavity in order;
the first through hole is arranged at the bottom wall and/or the peripheral wall of the resonant chamber;
the installation area is a plurality of, the resonance chamber is a plurality of, and a plurality of resonance chambers are arranged on the installation area of the outer pipe and/or the inner pipe at intervals.
6. The combustor for a gas turbine according to claim 4 or 5, further comprising a cooling passage, one end of which communicates with the airflow chamber, and the other end of which is communicable with the outside.
7. The combustor for a gas turbine of claim 6, further comprising a support bracket having one end connected to said mixer and another end connected to said combustor body.
8. The combustor for a gas turbine according to claim 7, wherein the support frame has a hollow inner tube cavity, the inner tube cavity being the cooling passage, one end of the support frame being connected to the outer tube and the inner tube cavity being in communication with the airflow cavity, the other end of the support frame being connected to the combustor body and the inner tube cavity being capable of communicating with the outside;
the inner tube includes first body and first turn-ups portion, first body is followed the axial extension of combustion chamber body, first turn-ups portion is followed the radial extension of combustion chamber body, just first turn-ups portion sets up the front end of first body, the outer tube includes second body and second turn-ups portion, the second body is followed the axial extension of combustion chamber body, second turn-ups portion is followed the radial extension of combustion chamber body, just second turn-ups portion sets up the front end of second body, set up the connecting plate between first turn-ups portion and the second turn-ups portion, be equipped with the air vent on the connecting plate, the air vent with the inner tube cavity intercommunication.
9. The combustor for a gas turbine according to claim 8, further comprising a partition plate provided in the airflow chamber so as to divide the airflow chamber into a plurality of airflow subchambers, the support frame being provided in plurality, the plurality of support frames being provided at intervals in a circumferential direction of the outer passage, the airflow subchambers being correspondingly communicated with the inner tube chamber.
10. A gas turbine comprising a combustion chamber for a gas turbine according to any one of claims 1-9.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210365110.2A CN114909675B (en) | 2022-04-07 | 2022-04-07 | Combustion chamber for a gas turbine and gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210365110.2A CN114909675B (en) | 2022-04-07 | 2022-04-07 | Combustion chamber for a gas turbine and gas turbine |
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| CN114909675B true CN114909675B (en) | 2024-03-01 |
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|---|---|
| CN114909675A (en) | 2022-08-16 |
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