Gas turbine combustion chamber and gas turbine

Abstract

The invention discloses a combustion chamber of a gas turbine and the gas turbine, the combustion chamber of the gas turbine comprises a shell, a flame tube, a cover cap, a resonance device and a flow guide cover, the flame tube and the cover cap are both arranged in the shell; the cover cap is arranged on one side of the flame tube in the axial direction of the cover cap and connected with the flame tube. The resonance device and the flow guide cover are both arranged in the shell and arranged on the side, away from the flame tube, of the cover cap in the axial direction of the cover cap, and the resonance device is provided with a resonance cavity and a through hole communicating with the resonance cavity. According to the combustion chamber of the gas turbine, the resonance device is arranged on the side, away from the flame tube, of the cover cap, the thermo-acoustic oscillation phenomenon outside the flame tube can be restrained through the resonance device, and the thermo-acoustic oscillation restraining effect in the combustion chamber of the gas turbine is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine combustion chamber and a gas turbine. Background Art

[0002] The gas turbine consists of three major components: the compressor, the combustion chamber, and the turbine. The exhaust gas of the compressor is mixed with the fuel in the outer casing and then burned. The generated hot gas is transported to the turbine to do work. Since the combustion chamber of the gas turbine operates under lean combustion conditions, thermoacoustic instability, that is, thermoacoustic oscillation, is very likely to occur. In the related art, a resonance device is set on the side of the flame tube, and the resonance device is connected to the inside of the flame tube. This method can only suppress the thermoacoustic oscillation phenomenon in the flame tube, and the thermoacoustic oscillation suppression effect in the combustion chamber is poor. Summary of the invention

[0003] The present invention provides a gas turbine combustion chamber to improve the thermal acoustic oscillation suppression effect in the combustion chamber.

[0004] The gas turbine combustion chamber of the present invention comprises an outer shell, a flame tube, a cover, a resonance device and a guide cover, wherein the flame tube and the cover are both arranged inside the outer shell, and the cover is arranged on one side of the flame tube in the axial direction and is connected to the flame tube; the resonance device and the guide cover are both arranged inside the outer shell, and are arranged on the side of the cover away from the flame tube in the axial direction of the cover, and the resonance device has a resonance cavity and a through hole connected to the resonance cavity.

[0005] Optionally, the resonance device has a plurality of the resonance cavities.

[0006] Optionally, at least two of the resonant cavities are arranged sequentially along the radial direction of the cap.

[0007] Optionally, at least two of the resonant cavities are arranged sequentially along the circumference of the cap.

[0008] Optionally, the gas turbine combustion chamber further comprises a plurality of swirl nozzles, wherein the swirl nozzles are arranged inside the hood and connected to the hood, and at least a portion of the resonance cavity is arranged between two adjacent swirl nozzles.

[0009] Optionally, the number of the swirl nozzles is at least three, one of which is a central nozzle, and the other swirl nozzles are peripheral nozzles, and a plurality of peripheral nozzles are arranged at intervals around the central nozzle; at least a portion of the resonance cavity is arranged between the central nozzle and the peripheral nozzles, and / or at least a portion of the resonance cavity is arranged between two adjacent peripheral nozzles.

[0010] Optionally, at least a portion of the resonance cavity is provided between any two adjacent swirl nozzles.

[0011] Optionally, the outer edge of the resonance device is flush with the outer edge of the cover cap; or, the outer edge of the resonance device is located inside the outer edge of the cover cap.

[0012] Optionally, the end surface of the resonance device away from the cap is arranged between the end surface of the deflector away from the cap and the end surface of the cap away from the flame tube.

[0013] Optionally, the through hole is arranged toward a side of the resonance device away from the cover cap; or, the through hole is arranged toward a radially outer side or a radially inner side of the cover cap.

[0014] The present invention also provides a gas turbine.

[0015] A gas turbine according to the present invention includes any one of the gas turbine combustors described above.

[0016] The gas turbine combustion chamber of the present invention is provided with a resonance device on the side of the cap away from the flame tube, and the resonance device can be used to suppress the thermoacoustic oscillation phenomenon outside the flame tube, thereby improving the thermoacoustic oscillation suppression effect in the gas turbine combustion chamber. In addition, the cold air flows in the direction indicated by the arrow in the figure, that is, flows in the premixing channel, and then flows back into the nozzle swirl channel at the confluence area of ​​the guide cover close to the cap. The flow of the airflow is slow in the reflow area, and the resonance device is arranged there, which has little effect on the flow of the airflow, and fully utilizes the space inside the shell. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a partial cross-sectional view of a gas turbine combustion chamber according to one embodiment of the present invention.

[0018] Figure 2 yes Figure 1 Enlarged view of point A in the middle.

[0019] Figure 3 It is a partial cross-sectional view of a gas turbine combustion chamber according to another embodiment of the present invention.

[0020] Figure 4 It is a partial cross-sectional view of a gas turbine combustion chamber according to another embodiment of the present invention.

[0021] Figure 5 It is a partial cross-sectional view of a gas turbine combustion chamber according to another embodiment of the present invention.

[0022] Figure 6 yes Figure 5 Enlarged view of point B in the middle.

[0023] Figure 7 It is a partial cross-sectional view of a gas turbine combustion chamber according to another embodiment of the present invention.

[0024] Figure 8 It is a cross-sectional view of a cap and a resonance device in a gas turbine combustion chamber according to another embodiment of the present invention.

[0025] Fig. 9 It is a cross-sectional view of a cap and a resonance device in a gas turbine combustion chamber according to another embodiment of the present invention.

[0026] Fig.10 It is a cross-sectional view of a cap and a resonance device in a gas turbine combustion chamber according to another embodiment of the present invention.

[0027] Reference numerals:

[0028] 1. Shell;

[0029] 2. Flame tube;

[0030] 3. Cover cap; 31. Nozzle mounting hole;

[0031] 4. Resonance device; 41. Resonance cavity; 42. Through hole; 401. First resonant cavity; 402. Second resonant cavity;

[0032] 5. guide cover; 51. guide vane; 52. guide hole;

[0033] 6. Swirl nozzle; 61. Swirl blade. DETAILED DESCRIPTION

[0034] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0035] like Figures 1 to 7 As shown, the gas turbine combustion chamber of the embodiment of the present invention comprises a casing 1, a flame tube 2, a cap 3, a resonance device 4 and a guide cover 5. The flame tube 2 and the cap 3 are both arranged inside the casing 1. The cap 3 is arranged on one side of the flame tube 2 in the axial direction thereof and is connected to the flame tube 2. The resonance device 4 and the guide cover 5 are both arranged inside the casing 1 and are arranged on the side of the cap 3 away from the flame tube 2 in the axial direction of the cap 3. The resonance device 4 has a resonance cavity 41 and a through hole 42 connected to the resonance cavity 41.

[0036] The through hole 42 is used to connect the resonance cavity 41 and the space outside the flame tube 2, for example, the through hole 42 connects the resonance cavity 41 and the premixing channel, or the through hole 42 connects the resonance cavity 41 and the nozzle swirl channel. The premixing channel refers to the space located inside the housing 1, outside the cap 3 and outside the shroud 5, and the nozzle swirl channel refers to the space located inside the shroud 5. The resonance cavity 41 may be a Helmholtz resonance cavity.

[0037] The direction close to the center line n of the cap 3 is inward, and the direction away from the center line n of the cap 3 is outward. Figures 1 to 7 shown.

[0038] The gas turbine combustion chamber of the embodiment of the present invention is provided with a resonance device 4 on the side of the cap 3 away from the flame tube 2. The resonance device 4 can suppress the thermoacoustic oscillation phenomenon outside the flame tube 2 (for example, in the premixing channel or the nozzle swirl channel), thereby improving the thermoacoustic oscillation suppression effect in the gas turbine combustion chamber. Figures 1 to 7 As shown, the cold air flows in the direction indicated by the arrow in the figure, that is, it flows in the premixing channel, and then flows back into the nozzle swirl channel at the confluence area of ​​the guide cover 5 close to the cap 3. The flow of the airflow is slow in the reflow area. The resonance device 4 is set there, which has little effect on the flow of the airflow and makes full use of the space inside the shell 1.

[0039] In some embodiments, the resonance device 4 has a plurality of resonance cavities 41 .

[0040] By providing a plurality of resonance cavities 41 in the resonance device 4, the size and position of the resonance cavity 41 can be set according to the thermoacoustic oscillation conditions outside the flame tube 2, thereby increasing the frequency range of the thermoacoustic oscillations suppressed by the resonance device 4 and further improving the thermoacoustic oscillation suppression effect in the gas turbine combustion chamber.

[0041] Optionally, at least two resonance cavities 41 are arranged in sequence along the radial direction of the cap 3 .

[0042] For example, Figure 5 and Figure 6 As shown, the two resonant cavities 41 are respectively a first resonant cavity 401 and a second resonant cavity 402, and the first resonant cavity 401 is arranged radially outside the second resonant cavity 402. The first resonant cavity 401 and the second resonant cavity 402 are connected through a through hole 42, and the second resonant cavity 402 is connected to the nozzle swirl channel. Therefore, the first resonant cavity 401 and the second resonant cavity 402 are used to suppress the heat oscillation phenomenon in the nozzle swirl channel.

[0043] By arranging at least two resonance cavities 41 in sequence along the radial direction of the cap 3, the frequency range of the thermoacoustic oscillation suppressed by the resonance device 4 can be widened, and the effect of suppressing the thermoacoustic oscillation in the combustion chamber of the gas turbine can be further improved.

[0044] Optionally, at least two resonance cavities 41 are arranged in sequence along the circumference of the cap 3 .

[0045] For example, the two resonant cavities 41 are respectively the third resonant cavity and the fourth resonant cavity, and the third resonant cavity and the fourth resonant cavity are arranged adjacent to each other along the circumference of the cap 3. The third resonant cavity and the fourth resonant cavity are respectively connected to the nozzle swirl channel through the through hole 42. Thus, the third resonant cavity and the fourth resonant cavity are used to suppress the heat oscillation phenomenon in the nozzle swirl channel.

[0046] By arranging at least two resonance cavities 41 in sequence along the circumferential direction of the cap 3, the frequency range of the thermoacoustic oscillation suppressed by the resonance device 4 can be widened, and the effect of suppressing the thermoacoustic oscillation in the combustion chamber of the gas turbine can be further improved.

[0047] In some embodiments, the gas turbine combustion chamber further includes a plurality of swirl nozzles 6, which are disposed inside the cap 3 and connected to the cap 3, and at least a portion of the resonance cavity 41 is disposed between two adjacent swirl nozzles 6. The swirl nozzle 6 includes a swirl blade 61, which is disposed inside the cap 3.

[0048] For example, Figures 8 to 10 As shown, the cap 3 is provided with seven nozzle mounting holes 31. Each nozzle mounting hole 31 is used to mount a swirl nozzle 6, that is, the gas turbine combustion chamber includes seven swirl nozzles 6.

[0049] By arranging at least a portion of the resonance cavity 41 between two adjacent swirl nozzles 6, the resonance device 4 can be used to suppress the thermoacoustic oscillation phenomenon in the nozzle swirl channel, thereby improving the thermoacoustic oscillation suppression effect in the gas turbine combustion chamber.

[0050] Optionally, the number of the swirl nozzles 6 is at least three, one of which is a central nozzle, and the other swirl nozzles 6 are peripheral nozzles, and the plurality of peripheral nozzles are arranged at intervals around the central nozzle. At least a portion of the resonance cavity 41 is disposed between the central nozzle and the peripheral nozzles, and / or at least a portion of the resonance cavity 41 is disposed between two adjacent peripheral nozzles.

[0051] For example, Figures 8 to 10 As shown, among the seven nozzle mounting holes 31, one nozzle mounting hole 31 is a central mounting hole, and the remaining six nozzle mounting holes 31 are outer mounting holes, and the six outer mounting holes are evenly spaced around the central mounting hole. Among them, the swirl nozzle 6 installed in the central mounting hole is the central nozzle, and the swirl nozzle 6 installed in the outer mounting hole is the peripheral nozzle.

[0052] By disposing at least a portion of the resonance cavity 41 between the central nozzle and the peripheral nozzle, and / or disposing at least a portion of the resonance cavity 41 between two adjacent peripheral nozzles, the area selection of the resonance cavity 41 can be increased, the frequency range of the thermoacoustic oscillations suppressed by the resonance device 4 can be broadened, and the effect of suppressing the thermoacoustic oscillations in the gas turbine combustion chamber can be further improved.

[0053] Optionally, at least a portion of the resonance cavity 41 is provided between any two adjacent swirl nozzles 6 .

[0054] By providing at least a portion of the resonance cavity 41 between any two adjacent swirl nozzles 6, the frequency range of the thermoacoustic oscillations suppressed by the resonance device 4 can be more effectively broadened, further improving the effect of suppressing the thermoacoustic oscillations in the combustion chamber of the gas turbine.

[0055] In some embodiments, Figures 1 to 7 As shown, the outer edge of the resonance device 4 is flush with the outer edge of the cap 3 .

[0056] For example, Figures 1 to 7 As shown, the outer edge of the resonance device 4 is flush with the outer edge of the cap 3, thereby preventing the resonance device 4 from occupying additional internal space of the housing 1 in the radial direction of the cap 3 and affecting the flow of the airflow in the premixing channel of the housing 1.

[0057] By setting the outer edge of the resonance device 4 to be flush with the outer edge of the cover 3, the space inside the outer shell 1 can be more fully utilized when the resonance device 4 has little effect on the flow of the airflow, thereby increasing the area selection of the resonance cavity 41, broadening the frequency range of the thermoacoustic oscillations suppressed by the resonance device 4, and further improving the effect of suppressing the thermoacoustic oscillations in the gas turbine combustion chamber.

[0058] In other embodiments, the outer edge of the resonance device 4 is located inside the outer edge of the cap 3 .

[0059] By arranging the outer edge of the resonance device 4 to be located inside the outer edge of the cap 3, the influence of the resonance device 4 on the flow of the airflow can be reduced, thereby improving the performance of the gas turbine combustion chamber.

[0060] In some embodiments, Figures 1 to 7 As shown, the end surface of the resonance device 4 away from the cap 3 is arranged between the end surface of the deflector 5 away from the cap 3 and the end surface of the cap 3 away from the flame tube 2.

[0061] For example, Figures 1 to 7 As shown, the guide cover 5 includes a guide vane 51 and a guide hole 52. The guide cover 5 is used to guide the airflow in the combustion chamber of the gas turbine.

[0062] By arranging the end face of the resonance device 4 away from the cap 3 between the end face of the deflector 5 away from the cap 3 and the end face of the cap 3 away from the flame tube 2, the resonance device 4 can be located as a whole in the reflow zone, reducing the impact on the airflow flow and more effectively utilizing the space inside the outer shell 1.

[0063] Optionally, the resonance device 4 is welded to the air deflector 5. In other embodiments, the resonance device 4 and the air deflector 5 may also be connected by fasteners, which may be bolts, screws, rivets, and the like.

[0064] Optionally, the resonance device 4 is welded to the cap 3. In other embodiments, the resonance device 4 and the cap 3 may also be connected by a fastener, which may be a bolt, a screw, a rivet, or the like.

[0065] In some embodiments, Figure 1 and Figure 2 As shown, the through hole 42 is arranged toward a side of the resonator 4 away from the cap 3 .

[0066] By arranging the through hole 42 toward the side of the resonance device 4 away from the cap 3 , the premixing channel and the resonance cavity 41 are connected by the through hole 42 , thereby suppressing the oscillation mode that may occur in the premixing channel.

[0067] In some embodiments, Figure 3 As shown, the through hole 42 is arranged toward the radial outside or the radial inside of the cap 3 .

[0068] By arranging the through hole 42 toward the radial outer side of the cap 3, the premixing channel and the resonance cavity 41 are connected by the through hole 42, and the oscillation mode that may occur in the premixing channel is suppressed. By arranging the through hole 42 toward the radial inner side of the cap 3, the nozzle swirl channel and the resonance cavity 41 are connected by the through hole 42, and the oscillation mode that may occur in the nozzle swirl channel is suppressed.

[0069] The shapes of the resonance device 4 and the resonance cavity 41 can be selected as needed, in order to reduce the flow loss of the airflow while complying with the flow direction of the airflow and ensure the effect of suppressing the thermoacoustic oscillation in the combustion chamber of the gas turbine. Figures 8 to 10 shown.

[0070] The gas turbine combustion chamber of the embodiment of the present invention can make full use of the dead zone of the gas flow (the area where the air flow is slow) inside the gas turbine combustion chamber by setting the resonance device 4 on the side of the cap 3 away from the flame tube 2, thereby improving the suppression effect of the thermoacoustic oscillation in the gas turbine combustion chamber. The space between the swirl nozzles 6 is fully utilized, the area of ​​the resonance cavity 41 is increased, and the thermoacoustic oscillation of the flow field at the cold end of the gas turbine combustion chamber is effectively suppressed. In addition, the resonance cavity 41 has a variety of shapes and can be used for a variety of frequencies, especially a large volume to be used for low-frequency oscillations; the position of the through hole 42 connected to the resonance cavity 41 can be varied, which can suppress the acoustic oscillation of the premixing channel and the nozzle swirl channel.

[0071] The gas turbine combustion chamber of the embodiment of the present invention breaks away from the shackles of the traditional resonance cavity position, fully utilizes other spaces inside the gas turbine combustion chamber, suppresses the thermoacoustic oscillation mode of the gas turbine combustion chamber by suppressing the acoustic oscillation of the premixing channel, and enhances the thermoacoustic oscillation suppression capability of the gas turbine combustion chamber on the basis of fully utilizing the internal space of the gas turbine combustion chamber.

[0072] Optionally, a resonance device is arranged inside the cap 3 , and the resonance device is used to suppress the thermoacoustic oscillation phenomenon inside the flame tube 2 .

[0073] The gas turbine of the embodiment of the present invention includes the gas turbine combustion chamber described in any one of the above embodiments.

[0074] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those of ordinary skill in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine combustion chamber, characterized in that: include: shell; A flame tube and a cover cap, wherein the flame tube and the cover cap are both arranged inside the shell, and the cover cap is arranged on one side of the flame tube in the axial direction and connected to the flame tube; A resonance device and a deflector, wherein the resonance device and the deflector are both arranged inside the shell and on a side of the cap away from the flame tube in the axial direction of the cap, and the resonance device has a resonance cavity and a through hole connected to the resonance cavity.

2. The gas turbine combustor according to claim 1, characterized in that: The resonant device has a plurality of the resonant cavities.

3. The gas turbine combustor according to claim 2, characterized in that: At least two of the resonant cavities are arranged in sequence along the radial direction of the cap.

4. The gas turbine combustor according to claim 2, characterized in that: At least two of the resonant cavities are arranged in sequence along the circumference of the cap.

5. The gas turbine combustor according to claim 1, characterized in that: The gas turbine combustion chamber further comprises a plurality of swirl nozzles, wherein the swirl nozzles are arranged inside the cap and connected to the cap, and at least a portion of the resonance cavity is arranged between two adjacent swirl nozzles.

6. The gas turbine combustor according to claim 5, characterized in that: The number of the swirl nozzles is at least three, one of which is a central nozzle, and the other swirl nozzles are peripheral nozzles, and the plurality of peripheral nozzles are arranged at intervals around the central nozzle; At least a portion of the resonance cavity is disposed between the central nozzle and the peripheral nozzle, and / or at least a portion of the resonance cavity is disposed between two adjacent peripheral nozzles.

7. The gas turbine combustor according to claim 6, characterized in that: At least a portion of the resonance cavity is disposed between any two adjacent swirl nozzles.

8. The gas turbine combustor according to claim 1, characterized in that: The outer edge of the resonant device is flush with the outer edge of the cap; or The outer edge of the resonant device is located inside the outer edge of the cover cap.

9. The gas turbine combustor according to claim 1, characterized in that: The end surface of the resonance device away from the cap is arranged between the end surface of the deflector away from the cap and the end surface of the cap away from the flame tube.

10. The gas turbine combustor according to claim 1, characterized in that The through hole is arranged toward a side of the resonant device away from the cap; or The through hole is arranged toward the radial outer side or the radial inner side of the cover cap.

11. A gas turbine, characterized in that: A gas turbine combustion chamber comprising the combustion chamber of any one of claims 1-10.

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