A Combustion Chamber Thermoacoustic Vibration Suppression System and Adjustment Method

Abstract

This invention proposes a combustion chamber thermoacoustic oscillation suppression system and debugging method. In the system, a first acoustic liner is detachably fixed to a flow guide bushing. The method includes: installing a first acoustic liner without a first channel onto the flow guide bushing; obtaining initial thermoacoustic oscillation parameters of the combustion chamber; based on the initial thermoacoustic oscillation parameters, replacing at least a portion of the first acoustic liner without a first channel with a first acoustic liner having a first channel; obtaining subsequent thermoacoustic oscillation parameters of the combustion chamber; based on the subsequent thermoacoustic oscillation parameters of the combustion chamber, determining whether the subsequent thermoacoustic oscillation parameters meet the design target; if the design target is met, debugging ends; if the design target is not met, the first acoustic liner is adjusted. Applying this invention not only allows the first chamber to suppress thermoacoustic oscillations but also enables precise control of the combustion chamber's vibration suppression capability by replacing the first acoustic liner.

Description

Technical Field

[0001] This invention relates to the field of gas turbine combustion stability and fault diagnosis technology, specifically to a combustion chamber thermoacoustic oscillation suppression system and debugging method. Background Technology

[0002] During operation, gas turbine combustors frequently experience thermoacoustic oscillations due to the coupling of flame heat release rate and pressure fluctuations. Strong thermoacoustic oscillations can lead to combustion instability, high-cycle fatigue of components, and seriously threaten the safe operation of the engine. Currently, one of the mainstream methods for suppressing thermoacoustic oscillations is to create acoustic lining holes in the combustor wall (such as the shroud and flame tube) to form a Helmholtz resonator, using acoustic damping to dissipate oscillation energy. However, this type of traditional acoustic lining structure has the following shortcomings: the hole diameter, hole depth, and back cavity volume cannot be changed after processing, and the resonant frequency is fixed, making it impossible to adapt to the oscillation frequency adjustment of the combustor under different operating conditions, fuels, or environmental conditions. The research and development cycle is long and costly; during the engine or single-tube prototype development stage, the frequency and intensity of thermoacoustic oscillations are often difficult to predict accurately in advance. To solve the thermoacoustic problems, it is necessary to manufacture multiple guide bushings with different acoustic lining schemes (different hole diameters and opening ratios) for repeated testing. Each replacement requires disassembling the entire combustor, resulting in a huge workload and high manufacturing costs for individual bushings, severely slowing down the research and development progress. Due to its poor flexibility, an engine with a fixed acoustic liner design cannot adapt to new thermoacoustic vibration risks brought about by changes in fuel characteristics and expanded operating conditions. Acoustic liner structures requiring specific designs may fail once placed in the combustion chamber environment due to issues such as operating condition adjustments and hot gas backflow, thus failing to achieve acoustic suppression effects. Traditional acoustic liner designs are typically limited to a thin cavity within the combustion chamber wall itself, with a limited back cavity volume, offering almost no attenuation effect for low-frequency, high-wavelength oscillations within certain specific ranges.

[0003] To address the aforementioned technical problems, existing technologies, such as CN113776088A, propose a flame tube. The tube has a combustion section extending along its length, and the outer wall of the combustion section has a protrusion. A resonator is connected to the side of the protrusion away from the tube, and the resonator has a chamber. One end of the chamber communicates with the interior of the tube, and the other end is adapted to connect to the outside. The combustion section has multiple cooling holes penetrating the tube wall, connecting the chamber to the interior of the tube. The resonator has multiple through holes connecting the chamber to the outside.

[0004] However, existing technologies cannot completely solve the above-mentioned technical problems. Summary of the Invention

[0005] The purpose of this invention is to solve the above-mentioned technical problems.

[0006] To achieve the above objectives, the first aspect of the present invention provides a combustion chamber thermoacoustic oscillation suppression system. The combustion chamber includes a combustion cylinder, a flow guide bushing, and a flame tube. The flow guide bushing is located radially inside the combustion cylinder, and the flame tube is located radially inside the flow guide bushing. The inner wall of the combustion cylinder and the outer wall of the flow guide bushing form a first chamber, and the inner wall of the flow guide bushing and the outer wall of the flame tube form a second chamber. The combustion chamber further includes two or more first acoustic linings, which are detachably fixed to the flow guide bushing along its circumference. At least a portion of the first acoustic linings is provided with a first channel, and the first chamber and the second chamber are connected through the first channel. The first chamber is connected to the interior of the flame tube.

[0007] Furthermore, the first acoustic liner is detachably fixed to the head region of the flow guide bushing. The head region refers to the area in the flow guide bushing whose length from the end of the flow guide bushing near the nozzle is less than 1 / 2 of the axial length of the flow guide bushing.

[0008] Furthermore, in the first acoustic liner provided with the first channel, at least a portion of the first acoustic liner has a different length and / or diameter of the first channel.

[0009] Furthermore, the flow guide bushing includes two or more base holes, which are arranged circumferentially in the head region of the flow guide bushing, and the first acoustic liner is detachably fixed to the flow guide bushing through the base holes.

[0010] Furthermore, the first acoustic liner is fixed to the base hole by threads.

[0011] To achieve the above objectives, a second aspect of the present invention provides a debugging method for a combustion chamber thermoacoustic oscillation suppression system, used in the combustion chamber thermoacoustic oscillation suppression system, comprising: installing a first acoustic liner without a first channel onto a flow guide bushing; acquiring initial thermoacoustic oscillation parameters of the combustion chamber; based on the initial thermoacoustic oscillation parameters, replacing at least a portion of the first acoustic liner without a first channel with a first acoustic liner having a first channel; acquiring subsequent thermoacoustic oscillation parameters of the combustion chamber; based on the subsequent thermoacoustic oscillation parameters of the combustion chamber, determining whether the subsequent thermoacoustic oscillation parameters meet the design target; if the design target is met, ending the debugging; if the design target is not met, adjusting the first acoustic liner.

[0012] Furthermore, installing the first acoustic liner without a first channel in front of the flow guide bushing also includes determining whether the combustion chamber has a characteristic frequency of thermoacoustic oscillation; if not, the debugging ends; if so, the position distribution of the first acoustic liner in the head region of the flow guide bushing is determined based on the characteristic frequency.

[0013] Further, determining the positional distribution of the first acoustic liner in the flow guide bushing based on the characteristic frequency includes: acquiring a pressure cloud field map when the combustion chamber undergoes thermoacoustic oscillation at the characteristic frequency; and determining the positional distribution of the first acoustic liner in the head region of the flow guide bushing based on the pressure cloud field map.

[0014] Furthermore, the characteristic frequency is the frequency corresponding to the first mode when the combustion chamber undergoes thermoacoustic oscillation.

[0015] Furthermore, the initial thermoacoustic oscillation parameters include an initial frequency and an initial amplitude; the subsequent thermoacoustic oscillation parameters include a subsequent frequency and a subsequent amplitude.

[0016] Furthermore, the calculation relationship between the initial frequency and the subsequent frequency is as follows: ; In the formula: This refers to either the initial frequency or a subsequent frequency. S is the speed of sound; S is the minimum flow area of ​​the first channel; V is the volume of the first chamber; L is the effective length of the neck, which is determined at least based on the axial length and radius of the first channel.

[0017] Further, determining whether the subsequent thermoacoustic oscillation parameters have reached the design target includes: if the decrease in the subsequent amplitude compared to the initial amplitude reaches an amplitude threshold, then the design target has been reached; if the decrease in the subsequent amplitude compared to the initial amplitude is less than the amplitude threshold, then the design target has not been reached.

[0018] Further, adjusting the first acoustic liner includes: adjusting the position, quantity, and specifications of the first acoustic liner installed in the flow guide bushing and having the first channel, wherein the specifications of the first acoustic liner are determined by the size of the first channel.

[0019] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. The present invention proposes a combustion chamber thermoacoustic oscillation suppression system, which suppresses thermoacoustic oscillations through a first chamber formed by the inner wall of the combustion cylinder and the outer wall of the flow guide bushing, thereby improving the ability to suppress combustion chamber thermoacoustic oscillations.

[0020] 2. The present invention proposes a combustion chamber thermoacoustic oscillation suppression system, wherein the first acoustic liner is detachably fixed to the flow guide bushing and at least part of the first acoustic liner is provided with a first channel, and the vibration suppression capability of the first chamber can be adjusted by replacing the first acoustic liner.

[0021] 3. The present invention proposes a method for adjusting a combustion chamber thermoacoustic oscillation suppression system. According to the vibration suppression requirements of the combustion chamber, the vibration suppression capability of the combustion chamber can be precisely controlled by replacing the first acoustic liner.

[0022] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0023] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 A schematic diagram of a combustion chamber thermoacoustic oscillation suppression system is shown in one embodiment; Figure 2 A schematic diagram of the flow guide bushing in one embodiment is shown; Figure 3 A cross-sectional schematic diagram of a first acoustic liner having a first channel is shown in one embodiment. Figure 4 A cross-sectional schematic diagram of a first acoustic liner without a first channel is shown in one embodiment. Figure 5 A cross-sectional schematic diagram of another embodiment of the first acoustic liner is shown. Figure 6 A cross-sectional schematic diagram of the first acoustic liner in another embodiment is shown. Figure 7 A cross-sectional schematic diagram of the first acoustic liner in another embodiment is shown. Figure 8 A flowchart of the debugging method of the combustion chamber thermoacoustic oscillation suppression system in one embodiment is presented.

[0024] Reference numerals: 1. Combustion cylinder; 2. First acoustic liner; 21. First channel; 22. Throat; 3. Guide bushing; 4. Flame tube; 5. Combustion zone inside the flame tube; 6. First chamber; 7. Second chamber; 8. Base hole. Detailed Implementation

[0025] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0026] The present invention will be further described in detail below with reference to specific embodiments, which should not be construed as limiting the scope of protection claimed by the present invention.

[0027] Example

[0028] According to one aspect of the present invention, a combustion chamber thermoacoustic oscillation suppression system is proposed, such as... Figure 1-7 As shown, the combustion chamber includes a combustion cylinder 1, a flow guide bushing 3, and a flame tube 4. The flow guide bushing 3 is located radially inside the combustion cylinder 1, and the flame tube 4 is located radially inside the flow guide bushing 3. The inner wall of the combustion cylinder 1 and the outer wall of the flow guide bushing 3 form a first chamber 6, and the inner wall of the flow guide bushing 3 and the outer wall of the flame tube 4 form a second chamber 7. The combustion chamber also includes two or more first acoustic linings 2, which are detachably fixed to the flow guide bushing 3 along its circumference. At least a portion of the first acoustic linings 2 are provided with a first channel 21. The first chamber 6 and the second chamber 7 are connected through the first channel 21, and the first chamber 6 is connected to the interior of the flame tube 4. Specifically, the first chamber 6 is connected to the combustion zone 5 inside the flame tube.

[0029] The first acoustic liner 2 is detachably fixed to the head region of the flow guide bushing 3. The head region refers to the area in the flow guide bushing 3 where the length from the end of the flow guide bushing 3 near the nozzle is less than 1 / 2 of the axial length of the flow guide bushing 3.

[0030] The flow guide bushing 3 includes two or more base holes 8, which are arranged circumferentially in the head region of the flow guide bushing 3. The first acoustic liner 2 is detachably fixed to the flow guide bushing 3 through the base holes 8. The first acoustic liner 2 is fixed to the base holes 8 by threads. Specifically, as shown... Figure 3-7 As shown, the first acoustic liner 2 is a bolt, and the extension direction of the first channel 21 is the same as the extension direction of the bolt. The base holes 8 are not uniformly distributed on the flow guide bushing 3, and are densely arranged in the antinode region of the pressure of the flow guide bushing 3, and sparsely or sporadically arranged in the nodal region of the pressure of the flow guide bushing 3. The antinode region refers to the position near the point of maximum pressure, and the nodal region refers to the region near the point of minimum pressure.

[0031] In the first acoustic liner 2 provided with the first channel 21, at least some of the first acoustic liner 2 have different diameters and / or lengths of the first channel 21. Specifically, in this embodiment, Figure 3 and Figure 5 The diameter of the first channel 21 of the first acoustic liner 2 shown is different; Figure 3 and Figure 6The length of the first channel 21 of the first acoustic liner 2 shown is different; Figure 5 and Figure 6 The length and diameter of the first channel 21 of the first acoustic liner 2 shown are different. Figure 7 The first acoustic liner 2 shown also includes a throat 22, which is disposed in the first channel 21, and the diameter of the throat 22 is smaller than the diameter of the first channel 21.

[0032] Optionally, the diameter of the first channel 21 can be 2mm, 5mm or 10mm.

[0033] According to another aspect of the present invention, a method for debugging a combustion chamber thermoacoustic oscillation suppression system is provided, for use in the aforementioned combustion chamber thermoacoustic oscillation suppression system, such as... Figure 8 As shown, it includes: S1, the first acoustic liner 2 without the first channel 21 is installed on the flow guide bushing 3.

[0034] Further, determine whether the combustion chamber has a characteristic frequency of thermoacoustic oscillation; if not, end the debugging; if it does, determine the position distribution of the first acoustic liner 2 in the head region of the flow guide bushing 3 based on the characteristic frequency.

[0035] It should be noted here that the characteristic frequency refers to the main frequency corresponding to the oscillation amplitude of the combustion chamber exceeding the set threshold.

[0036] Specifically, in this embodiment, the characteristic frequency is the frequency corresponding to the first mode when the combustion chamber experiences thermoacoustic oscillation. Numerical simulation is used to pre-determine whether the combustion chamber exhibits a characteristic frequency of thermoacoustic oscillation. In other embodiments, the presence of a characteristic frequency of thermoacoustic oscillation in the combustion chamber can also be determined through theoretical analysis.

[0037] It should also be noted that the combustion chamber oscillations are axial, tangential, and radial modes, respectively. The axial mode is a low-frequency oscillation that oscillates along the airflow direction; the tangential mode is a mid-to-high-frequency oscillation that oscillates along a direction tangential to the circumference of the flame tube; and the radial mode is a mid-to-high-frequency oscillation that oscillates radially along the flame tube. Specifically, the first mode includes at least one of the first axial mode, the first tangential mode, and the first radial mode.

[0038] More specifically, in this embodiment, the characteristic frequency is the frequency corresponding to the first tangential mode when the combustion chamber experiences thermoacoustic oscillation. Preferably, if the frequency corresponding to the first tangential mode of the combustion chamber vibration is within the range of 100 Hz to 180 Hz, then this frequency is considered the characteristic frequency of the thermoacoustic oscillation, and the relevant size requirements of the resonant cavity need to be redesigned and changed; if the frequency corresponding to the first tangential mode of the combustion chamber vibration is not within the range of 100 Hz to 180 Hz, then the thermoacoustic oscillation of the combustion chamber under this operating condition is considered insignificant, and subsequent design can disregard this frequency band.

[0039] In other embodiments, the characteristic frequency may also be a second mode, a third mode, and a fourth mode, etc.

[0040] Furthermore, determining the positional distribution of the first acoustic liner 2 in the flow guide bushing 3 based on the characteristic frequency includes: acquiring a pressure cloud field map when the combustion chamber undergoes thermoacoustic oscillation at the characteristic frequency; and determining the positional distribution of the first acoustic liner 2 in the head region of the flow guide bushing 3 based on the pressure cloud field map. Specifically, in this embodiment, pressure antinodes and pressure nodal regions are determined according to the pressure cloud field map. The antinodes refer to the region near the point of maximum pressure, and the nodal regions refer to the region near the point of minimum pressure. The pre-holes 8 are densely arranged in the pressure antinodes and sparsely arranged in the pressure nodal regions. After the pre-holes 8 are installed, the first acoustic liner 2 without the first channel 21 is installed according to the distribution of the pre-holes 8.

[0041] S2, obtain the initial thermoacoustic oscillation parameters of the combustion chamber.

[0042] It should be noted here that the initial thermoacoustic oscillation parameter refers to the parameter that measures the inherent thermoacoustic oscillation characteristics of the combustion chamber before acoustic lining suppression. Specifically, in this embodiment, the initial thermoacoustic oscillation parameters refer to the thermoacoustic oscillation parameters of the combustion chamber obtained after installing the first acoustic liner 2 without the first channel 21. The initial thermoacoustic oscillation parameters include an initial frequency and an initial amplitude. In some embodiments, the initial thermoacoustic oscillation parameters consist of an initial frequency and an initial amplitude.

[0043] Optionally, the initial thermoacoustic oscillation parameters are obtained experimentally.

[0044] More specifically, the initial frequency is calculated using the following formula: ; In the formula: The initial frequency; S is the speed of sound; S is the minimum flow area of ​​the first channel; V is the volume of the first chamber; L is the effective length of the neck, which is determined at least based on the axial length and radius of the first channel.

[0045] Specifically, the effective length of the neck is the sum of the axial length of the first channel and the radius of the modified first channel, wherein the radius of the modified first channel is 0.3-0.8 times the radius of the first channel. In this embodiment, the radius of the modified first channel is 0.5 times the radius of the first channel. In other embodiments, the radius of the modified first channel may also be 0.3, 0.4, 0.6, 0.7, and 0.8 times the radius of the first channel, etc.

[0046] As can be seen from the above formula, due to the extremely large volume of the first chamber 6, even with a large minimum flow area in the first channel, a very low frequency can still be obtained. This is precisely the theoretical basis for the present invention's ability to effectively suppress low-frequency oscillations.

[0047] S3, based on the initial thermoacoustic oscillation parameters, at least part of the first acoustic liner 2 without the first channel 21 is replaced with the first acoustic liner 2 with the first channel 21.

[0048] Specifically, the total flow area of ​​the first channel is calculated based on the initial thermoacoustic oscillation parameters, the initial frequency calculation formula in step S2, and the target suppression frequency. Then, the position, quantity, and specifications of the first acoustic liner 2 with the first channel 21 are determined. The specifications of the first acoustic liner 2 are determined by the size of the first channel 21.

[0049] S4, obtain the subsequent thermoacoustic oscillation parameters of the combustion chamber.

[0050] It should be noted here that the subsequent thermoacoustic oscillation parameters refer to the parameters used to measure the thermoacoustic oscillation characteristics of the combustion chamber after acoustic lining suppression. Specifically, in this embodiment, the subsequent thermoacoustic oscillation parameters refer to the thermoacoustic oscillation parameters of the combustion chamber obtained after replacing at least a portion of the first acoustic lining 2 without the first channel 21 with the first acoustic lining 2 having the first channel 21. The subsequent thermoacoustic oscillation parameters include subsequent frequency and subsequent amplitude. In some embodiments, the subsequent thermoacoustic oscillation parameters consist of subsequent amplitude and subsequent frequency.

[0051] Specifically, the calculation formula for the subsequent thermoacoustic oscillation parameters is the same as the calculation formula for the initial frequency.

[0052] S5, based on the subsequent thermoacoustic oscillation parameters of the combustion chamber, determine whether the subsequent thermoacoustic oscillation parameters have reached the design target; if the design target has been reached, end the debugging; if the design target has not been reached, adjust the first acoustic liner 2.

[0053] Further, determining whether the subsequent thermoacoustic oscillation parameters have reached the design target includes: if the decrease in the subsequent amplitude compared to the initial amplitude reaches an amplitude threshold, then the design target has been reached; if the decrease in the subsequent amplitude compared to the initial amplitude is less than the amplitude threshold, then the design target has not been reached.

[0054] It should be noted that the amplitude threshold refers to the proportion of the decrease in amplitude of subsequent amplitudes compared to the initial amplitude. The amplitude threshold ranges from 10% to 100%, and in this embodiment, the amplitude threshold is 30%. In other embodiments, the amplitude threshold may also be 10%, 20%, 40%, 50%, 60%, 70%, 80%, 90%, or 100%, etc.

[0055] Furthermore, adjusting the first acoustic liner includes: adjusting the position, quantity, and specifications of the first acoustic liner installed in the flow guide bushing and having the first channel, wherein the specifications of the first acoustic liner are determined by the size of the first channel.

[0056] To demonstrate the technical effectiveness of the aforementioned combustion chamber thermoacoustic oscillation suppression system debugging method, the following calculations were performed using a single-tube test of a certain type of gas turbine as an example: First, numerical simulations revealed that the frequency corresponding to the first mode of the combustion chamber under a certain operating condition is 150 Hz. This frequency falls within the range of 100 Hz to 180 Hz, thus confirming that the combustion chamber exhibits a characteristic frequency of thermoacoustic oscillation, meaning that the combustion chamber will experience thermoacoustic oscillations under this operating condition. Subsequently, pressure cloud field diagrams were obtained from the numerical simulations when thermoacoustic oscillations occur at this frequency, and the pressure antinodes and nodes were determined based on these diagrams.

[0057] Second, the antinodes of the flow guide bushing 3 are densely machined with internal threads and M20 specification base holes, while no base holes are machined in the nodal areas.

[0058] Third, a first acoustic liner 2 without a first channel 21 is installed in all the foundation holes 8. The gas turbine is then ignited and operated; the measured initial frequency is 155 Hz, which basically matches the characteristic frequency predicted by numerical simulation.

[0059] Fourth, in order to suppress thermoacoustic oscillations at 155 Hz, according to the initial frequency and calculation formula, the first acoustic liner 2 without the first channel 21 is replaced with a first acoustic liner 2 with a diameter of 10 mm and equipped with the first channel 21 in each of the 10 base holes in the two antinode regions of 90° and 270°.

[0060] Fifth, the subsequent amplitude measured at 155Hz was less than 10 kPa. Compared to the initial amplitude of 30 kPa, the decrease was more than 60% of the initial amplitude, exceeding the amplitude threshold, indicating successful vibration suppression. If vibration suppression is unsuccessful, the first acoustic liner 2 with a larger diameter can be replaced with the first channel 21, or the number of first acoustic liner 2s with the first channel 21 can be increased.

[0061] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. The present invention proposes a combustion chamber thermoacoustic oscillation suppression system, which suppresses thermoacoustic oscillations through a first chamber formed by the inner wall of the combustion cylinder and the outer wall of the flow guide bushing, thereby improving the ability to suppress combustion chamber thermoacoustic oscillations.

[0062] 2. The present invention proposes a combustion chamber thermoacoustic oscillation suppression system, wherein the first acoustic liner is detachably fixed to the flow guide bushing and at least part of the first acoustic liner is provided with a first channel, and the vibration suppression capability of the first chamber can be adjusted by replacing the first acoustic liner.

[0063] 3. The present invention proposes a method for adjusting a combustion chamber thermoacoustic oscillation suppression system. According to the vibration suppression requirements of the combustion chamber, the vibration suppression capability of the combustion chamber can be precisely controlled by replacing the first acoustic liner.

[0064] The above are merely several specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

[0065] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0066] It should be noted that, in the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

Claims

1. A combustion chamber thermoacoustic vibration suppression system, wherein the combustion chamber includes a combustion cylinder (1), a flow guide bushing (3), and a flame tube (4), wherein the flow guide bushing (3) is located radially inside the combustion cylinder (1), and the flame tube (4) is located radially inside the flow guide bushing (3), wherein the inner wall of the combustion cylinder (1) and the outer wall of the flow guide bushing (3) form a first chamber (6), and the inner wall of the flow guide bushing (3) and the outer wall of the flame tube (4) form a second chamber (7), characterized in that, The combustion chamber further includes two or more first acoustic liner parts (2), which are detachably fixed to the flow guide bushing (3) along the circumference of the flow guide bushing (3). At least a portion of the first acoustic liner parts (2) are provided with a first channel (21). The first chamber (6) and the second chamber (7) are connected through the first channel (21). The first chamber (6) is connected to the interior of the flame tube (4).

2. The combustion chamber thermoacoustic vibration suppression system according to claim 1, characterized in that, The first acoustic liner (2) is detachably fixed to the head region of the flow guide bushing (3). The head region refers to the area in the flow guide bushing (3) whose length from the end of the flow guide bushing (3) near the nozzle is less than 1 / 2 of the axial length of the flow guide bushing (3).

3. The combustion chamber thermoacoustic vibration suppression system according to claim 1, characterized in that, In the first acoustic liner (2) provided with the first channel (21), at least some of the first acoustic liner (2) have different lengths and / or diameters of the first channel (21).

4. The combustion chamber thermoacoustic vibration suppression system according to claim 2, characterized in that, The flow guide bushing (3) includes two or more base holes (8), which are arranged in the head region of the flow guide bushing (3) along the circumference of the flow guide bushing (3). The first acoustic liner (2) is detachably fixed to the flow guide bushing (3) through the base holes (8).

5. The combustion chamber thermoacoustic oscillation suppression system according to claim 4, characterized in that, The first acoustic liner (2) is fixed to the base hole (8) by threads.

6. A method for debugging a combustion chamber thermoacoustic oscillation suppression system, used in the combustion chamber thermoacoustic oscillation suppression system according to any one of claims 1-5, characterized in that, include: The first acoustic liner (2) without the first channel (21) is installed on the flow guide bushing (3); Obtain the initial thermoacoustic oscillation parameters of the combustion chamber; Based on the initial thermoacoustic oscillation parameters, at least part of the first acoustic liner (2) without the first channel (21) is replaced with the first acoustic liner (2) with the first channel (21). Obtain the subsequent thermoacoustic oscillation parameters of the combustion chamber; Based on the subsequent thermoacoustic oscillation parameters of the combustion chamber, determine whether the subsequent thermoacoustic oscillation parameters have reached the design target; If the design goal is achieved, the debugging is terminated; if the design goal is not achieved, the first acoustic liner (2) is adjusted.

7. The method for debugging the combustion chamber thermoacoustic oscillation suppression system according to claim 6, characterized in that, The first acoustic liner (2), which does not have a first channel (21), is installed in front of the flow guide bushing (3), and also includes, Determine whether the combustion chamber has a characteristic frequency of thermoacoustic oscillation; If it does not exist, end debugging; If present, the positional distribution of the first acoustic liner (2) in the head region of the flow guide bushing (3) is determined based on the characteristic frequency.

8. The method for debugging the combustion chamber thermoacoustic oscillation suppression system according to claim 7, characterized in that, Determining the positional distribution of the first acoustic liner (2) in the flow guide bushing (3) based on the characteristic frequency includes: Obtain the pressure cloud field diagram of the combustion chamber when thermoacoustic oscillation occurs at the characteristic frequency; The position distribution of the first acoustic liner (2) in the head region of the flow guide bushing (3) is determined based on the pressure cloud field diagram.

9. The method for debugging the combustion chamber thermoacoustic oscillation suppression system according to claim 8, characterized in that, The characteristic frequency is the frequency corresponding to the first mode when the combustion chamber undergoes thermoacoustic oscillation.

10. The method for debugging the combustion chamber thermoacoustic oscillation suppression system according to claim 6, characterized in that, The initial thermoacoustic oscillation parameters include the initial frequency and the initial amplitude; the subsequent thermoacoustic oscillation parameters include the subsequent frequency and the subsequent amplitude.

11. The method for debugging the combustion chamber thermoacoustic vibration suppression system according to claim 10, characterized in that, The calculation relationship between the initial frequency and the subsequent frequency is as follows: ； In the formula: This refers to either the initial frequency or a subsequent frequency. S is the speed of sound; S is the minimum flow area of ​​the first channel; V is the volume of the first chamber; L is the effective length of the neck, which is determined at least based on the axial length and radius of the first channel.

12. The method for debugging the combustion chamber thermoacoustic vibration suppression system according to claim 10, characterized in that, Determining whether the subsequent thermoacoustic oscillation parameters meet the design target includes: If the decrease in subsequent amplitude compared to the initial amplitude reaches an amplitude threshold, the design goal is achieved; if the decrease in subsequent amplitude compared to the initial amplitude is less than the amplitude threshold, the design goal is not achieved.

13. The method for debugging the combustion chamber thermoacoustic oscillation suppression system according to claim 6, characterized in that, Adjusting the first acoustic liner (2) includes: Adjust the position, quantity, and specifications of the first acoustic liner (2) installed in the flow guide bushing and having the first channel (21). The specifications of the first acoustic liner (2) are determined by the size of the first channel (21).

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