Noise suppression system and method covering full working rotating speed range of marine gas turbine

Abstract

The invention relates to the technical field of marine gas turbines, in particular to a noise suppression system and method covering the full working rotating speed range of a marine gas turbine. A combustion noise suppression module, a mechanical noise suppression module and an aerodynamic noise suppression module are adopted for noise control in a starting and idling area, a middle power area and a high power area respectively, and all the modules drive a loudspeaker array arranged on the inner side of a sound insulation cover to generate reverse sound waves with the phase opposite to that of original noise. Precise suppression of main noise sources such as a combustion chamber, a gas compressor and an exhaust assembly is achieved.

Description

Technical Field

[0001] This invention relates to the field of marine gas turbine technology, specifically to a noise suppression system and method covering the entire operating speed range of marine gas turbines. Background Technology

[0002] As the core component of a ship's propulsion system, the noise control of marine gas turbines directly impacts the ship's stealth, crew comfort, and equipment reliability. The primary noise generation mechanisms and characteristics of gas turbines differ significantly across different operating speed ranges, creating a complex and time-varying sound field. During startup and idling (typically 0%-40% of rated speed), gas turbine noise primarily originates from the instability of the combustion process. At this point, the pulsations of fuel injection, mixing, and combustion generate predominantly low-frequency combustion noise, exhibiting a wide-bandwidth spectral characteristic and relatively low sound pressure level, but significantly interfering with the cabin environment. As the intermediate power range (40%-80% of rated speed) is entered, mechanical noise becomes prominent. Imbalance in the rotor system, periodic bearing impacts, and mechanical excitations such as gear meshing become the main noise sources, displaying discrete line spectra related to speed (such as rotational frequency, gear meshing frequency, and their harmonics). Simultaneously, the blade pass frequency (BPF) noise from the compressor and turbine also begins to emerge. In the high-power range (80%-100% of rated speed), aerodynamic noise becomes absolutely dominant. In particular, the jet noise generated by the high-speed combustion gas ejected from the exhaust system mixing with the surrounding medium has extremely high sound pressure level and wide frequency characteristics. At the same time, the aerodynamic noise of rotating parts is also significantly enhanced, causing the overall noise level to reach its peak in this stage.

[0003] For the complex noise spectrum characteristics of marine gas turbines, existing noise reduction technologies have revealed numerous limitations in practical applications, especially when covering the entire operating speed range. Currently widely used technologies mainly rely on passive noise reduction methods, such as installing soundproof enclosures around the gas turbine and mufflers in the intake and exhaust pipes. These methods have a good suppression effect on mid-to-high frequency noise, but their noise reduction performance largely depends on the properties of the materials and the structural design. Furthermore, they are often ineffective against low-frequency noise (such as combustion noise in the start-up and idling range) and may lead to an increase in equipment size and weight. In addition, once traditional passive noise reduction measures are designed, their performance remains fixed and cannot be adaptively adjusted according to the changing operating conditions of the gas turbine. This means that a well-optimized sound insulation or silencing design in one speed range may be significantly less effective in another operating condition, making it difficult to achieve optimal noise reduction across the entire operating range. Summary of the Invention

[0004] To achieve the above objectives, the present invention provides an intelligent, adaptive noise suppression system that can cover the entire operating speed range of marine gas turbines. The system can identify the operating status and noise characteristics of the gas turbine in real time and dynamically adjust the noise reduction strategy.

[0005] This invention discloses a noise suppression system covering the entire operating speed range of a marine gas turbine, comprising a combustion noise suppression module, an aerodynamic noise suppression module, and a mechanical noise suppression module. The marine gas turbine is externally equipped with a soundproof enclosure, on which multiple speaker arrays are mounted. A speed sensor detects the current operating speed range of the marine gas turbine. During the start-up and idling speed ranges of the marine gas turbine, the combustion noise suppression module controls the speaker arrays to generate reverse sound waves to suppress noise in the combustion chamber. In the intermediate power range of the marine gas turbine, the mechanical noise suppression module controls the speaker arrays to generate reverse sound waves to suppress noise in the turbine itself. In the high power range of the marine gas turbine, the aerodynamic noise suppression module controls the speaker arrays to generate reverse sound waves to suppress noise in the compressor and exhaust components. Furthermore, the combustion noise suppression module performs the following steps: Step S101: The operating status parameters, acoustic parameters and thermal parameters of the marine gas turbine in the start-up and idling range are collected in real time through a distributed sensor network, and the synchronization of the collected parameters is ensured through time synchronization. Step S102: Identify and verify the operating conditions of the marine gas turbine. Based on the speed signal N, confirm that the gas turbine is in the start-up and idling range, and check the fuel flow rate. and combustion chamber pressure Verify the accuracy of operating condition identification; if abnormal operating conditions are detected, activate the safety protection mechanism and issue an alarm. Step S103: Extract combustion noise features, perform 1 / 3 octave band spectrum analysis on the acquired acoustic signal; calculate the sound field phase distribution, analyze signal coherence, and evaluate the quality of the reference signal.

[0006] Furthermore, the thermal parameters include the inlet air temperature. Combustion chamber temperature Exhaust temperature The acoustic parameters include sound pressure spectrum and sound field phase; the operating status parameters include rotor speed N and fuel mass flow rate. Combustion chamber pressure air-fuel ratio .

[0007] Furthermore, the combustion noise suppression module calculates the sound power level of the current combustion noise according to the following formula: ,in The sound power level of combustion noise. This represents the fluctuation in the combustion heat release rate. Let be the average density of the combustion gas in the combustion zone, and c be the sound velocity of the combustion gas in the combustion zone. For reference sound pressure level, K is an empirical constant for burner structure. This is a working condition correction factor; The combustion noise suppression module 2 estimates the peak frequency using the following formula. ,in The peak frequency of combustion noise. The geometry factor of the combustion chamber. For laminar flame velocity, For the thickness of the flame, This represents the actual fuel mass flow rate. This is the rated fuel mass flow rate.

[0008] Furthermore, the mechanical noise suppression module performs the following steps: Step S201: Monitor the gas turbine speed N to confirm that it is in the intermediate power range, i.e., 40%-80% of the rated speed; detect the load power to help judge the stability of the operating conditions, verify the accuracy of the speed signal, and ensure reliable identification of the operating conditions. Step S202: Detect vibration signals using an accelerometer, including detecting bearing characteristic frequency vibration, gear meshing frequency vibration, and structural propagation vibration, to obtain a mechanical excitation reference signal; Step S203: Acoustic signals are acquired through a microphone array, the sound pressure spectrum is analyzed to identify the main noise components, and the sound field phase signal is measured. Step S204: Perform noise characteristic analysis and modeling, calculate the blade passing frequency, gear meshing frequency, and rotor rotation frequency, estimate the sound pressure level of each frequency component, and then calculate the total sound pressure level.

[0009] Furthermore, the blades are controlled by frequency. Where N is the rotor speed and B is the number of blades; the gear meshing frequency Where Z is the number of gear teeth; the rotor rotation frequency .

[0010] Furthermore, the estimated sound pressure level for each frequency component is calculated using the following formula: , in, For the sound pressure level estimated in a specific frequency band, k is an empirical coefficient related to the machine structure and mass, N is the engine speed when it is running, f is the calculated center frequency term, and C is a correction constant; The calculation of the total sound pressure level includes, ,in, Total sound pressure level, Let be the sound pressure level of the i-th noise component, and n be the number of noise components.

[0011] Furthermore, the aerodynamic noise suppression module performs the following steps: Step S301: Detect operating status parameters, monitor the gas turbine speed N in real time to confirm it is in the high-power range, i.e., 80%-100% of rated speed; detect the exhaust temperature. and exhaust flow _ex, monitor load power and verify high-power operation status; Step S302, acoustic signal detection: Acoustic signals are acquired through a high-frequency microphone array; the sound pressure spectrum is analyzed and the broadband characteristics of the jet noise are identified; the sound field phase information is measured. Step S303: Thermal parameter detection, detecting ambient temperature, pressure, and humidity to calculate air density and sound speed, providing environmental parameters for sound wave propagation model correction; Step S304: Calculate the jet noise sound power level and jet noise characteristic frequency based on the detection parameters; calculate the noise of the rotating component, calculate the sound pressure level based on the calculated blade passing frequency, and finally calculate the total sound pressure level.

[0012] Furthermore, the jet noise sound power level is calculated using the following method: , in, The jet noise sound power level, Let v be the jet density, v be the jet velocity, and D be the nozzle diameter. For ambient air density, For ambient sound speed, This is an empirical constant for jet noise.

[0013] The characteristic frequency of the jet noise ,in Here, denoted as the Strojal number, and v is the jet velocity.

[0014] Furthermore, the calculation of the sound pressure level based on the frequency of the blade is specifically performed using the following formula: in Let S be the sound pressure level at the frequency through which the blade passes, k be an empirical coefficient, and S be the characteristic area of ​​the blade. The number of blades involved in generating noise. This is a correction constant.

[0015] The beneficial effects of this invention are as follows: Most existing technologies employ single passive sound insulation or fixed-parameter active noise reduction schemes, which are insufficient to address the challenge of drastic changes in the noise spectrum and dominant sound sources of gas turbines under different operating speeds. Compared with existing technologies, the marine gas turbine noise suppression system of this invention can cover the entire operating speed range of the gas turbine. Through an intelligent architecture integrating speed sensing and multi-module collaboration, it achieves precise matching between noise reduction strategies and operating conditions: In the start-up and idling range, the system mainly targets low-frequency noise dominated by combustion instability; in the intermediate power range, the system mainly suppresses mechanical vibrations and noise generated by rotor, bearing, and gear meshing; in the high power range, the system mainly addresses high-intensity aerodynamic noise represented by jet noise and blade passing frequency noise. The noise suppression system of this invention ensures that, from low to high speeds, the system can effectively suppress the most significant noise sources, thereby solving the technical problem of performance degradation under varying operating conditions in traditional methods. It achieves optimal and stable noise reduction effects over a wide speed range, improving the cabin noise reduction performance of ships. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the marine gas turbine of the present invention; Figure 2 This is a cross-sectional view of the noise suppression system covering the entire operating speed range of marine gas turbines according to the present invention. Figure 3 This is a front view of the noise suppression system of the present invention; Figure 4 This is a physical architecture diagram of the noise suppression system of the present invention; Figure 5 This is a schematic diagram of the control unit of the present invention; Figure 6 This is a flowchart of the noise suppression method covering the entire operating speed range of marine gas turbines according to the present invention; Figure 7 This is a flowchart illustrating the operation of the combustion noise suppression module under startup and idling conditions of the present invention. Figure 8 This is a flowchart illustrating the operation of the intermediate power region mechanical noise suppression module of the present invention. Figure 9 This is a flowchart illustrating the operation of the high-power region aerodynamic noise suppression module of the present invention. In the picture: Marine gas turbine 1, compressor 11, combustion chamber 12, turbine 13, exhaust assembly 14; Soundproof enclosure 20, speaker array 21-23; Combustion noise suppression module 2, aerodynamic noise suppression module 3, and mechanical noise suppression module 4; Detailed Implementation The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0017] The present invention will now be described in detail with reference to the accompanying drawings. The noise suppression system of the present invention, covering the entire operating speed range of a marine gas turbine, includes a combustion noise suppression module 2, an aerodynamic noise suppression module 3, and a mechanical noise suppression module 4. A soundproof enclosure 20 is provided externally to the marine gas turbine 1, and multiple speaker arrays 21-23 are mounted on the soundproof enclosure 20. The current operating speed range of the marine gas turbine 1 is detected by a speed sensor. In the start-up and idling speed range of the marine gas turbine 1, the combustion noise suppression module 2 controls the speaker arrays to generate reverse sound waves to suppress noise in the combustion chamber 12 of the marine gas turbine 1. In the intermediate power range of the marine gas turbine 1, the mechanical noise suppression module 4 controls the speaker arrays to generate reverse sound waves to suppress noise in the marine gas turbine 1. In the high power range of the marine gas turbine 1, the aerodynamic noise suppression module 3 controls the speaker arrays to generate reverse sound waves to suppress noise in the compressor 11 and exhaust assembly 14 of the marine gas turbine 1.

[0018] Marine gas turbines have a wide operating speed range, and the frequency of their internal excitation forces varies greatly, such as rotor imbalance and blade passing frequency. The noise suppression system of this invention can cover the entire operating speed range of marine gas turbines.

[0019] Example 1 In the starting and idling range of marine gas turbines, i.e. 0% to 40% of rated speed, the noise characteristics are dominated by low-frequency combustion noise. The noise in this stage is mainly caused by the unsteady heat release during the fuel combustion process in the combustion chamber, which manifests as a wide-band low-frequency roaring sound.

[0020] Specifically, the controller acquires the current thermal parameters, combustion parameters, and operating status parameters of the marine gas turbine 1, and sends these parameters to the combustion noise suppression module 2. The thermal parameters include the inlet air temperature. Combustion chamber temperature Exhaust temperature The acoustic parameters include sound pressure spectrum and sound field phase; the operating status parameters include rotor speed N and fuel mass flow rate. Combustion chamber pressure air-fuel ratio .

[0021] The combustion noise suppression module 2 performs the following steps: The operating status parameters, acoustic parameters, and thermal parameters of the marine gas turbine 1 in the start-up and idling ranges are collected in real time through a distributed sensor network; time synchronization technology is used to ensure the synchronization of the collected parameters, providing accurate time-aligned data for subsequent analysis; The operating conditions of marine gas turbine 1 are identified and verified. Based on the speed signal N, it is confirmed that the gas turbine is in the start-up and idling range, i.e., whether it is 0%-40% of the rated speed, by measuring the fuel flow rate. and combustion chamber pressure Verify the accuracy of operating condition identification; if abnormal operating conditions are detected, activate the safety protection mechanism and issue an alarm. Combustion noise features were extracted, and 1 / 3 octave band spectrum analysis was performed on the collected acoustic signals, with a focus on the low-frequency band of 20-500Hz. The phase distribution of the sound field was calculated to provide a phase reference for the synthesis of reverse sound waves. The signal coherence was analyzed, and the quality of the reference signal was evaluated. Calculate the fluctuation of combustion heat release rate based on the detection parameters. , ,in This is the combustion efficiency fluctuation coefficient, typically ranging from 0.1 to 0.01. This represents the actual fuel mass flow rate. The lower calorific value of the fuel is the heat released when a unit mass of fuel is completely burned; calculate the sound velocity c of the combustion gas in the combustion zone. ,in The specific heat ratio of the gas. The specific gas constant of the fuel gas. Given the absolute temperature of the combustion gases within the combustion zone; calculate the combustion noise sound power level. and peak frequency .

[0022] The combustion noise suppression module 2 calculates the sound power level of the current combustion noise according to the following formula: ,in The sound power level of combustion noise. This represents the fluctuation in the combustion heat release rate. Let be the average density of the combustion gas in the combustion zone, and c be the sound velocity of the combustion gas in the combustion zone. For reference sound pressure, it is usually taken as Pa and K are empirical constants for burner structure, typically ranging from 120 to 140 dB. It is a condition correction factor, which is related to air-fuel ratio and combustion stability.

[0023] The combustion noise spectrum exhibits broadband characteristics. The combustion noise suppression module 2 estimates the peak frequency using the following formula: ,in The peak frequency of combustion noise. The geometry factor of the combustion chamber. For laminar flame velocity, For the thickness of the flame, This represents the actual fuel mass flow rate. This is the rated fuel mass flow rate.

[0024] Example 2 When the marine gas turbine 1 is in the intermediate power range, typically 40% to 80% of the rated speed, its operating state tends to be stable. Under this operating condition, the noise source of the gas turbine exhibits a composite characteristic of mechanical noise, aerodynamic noise, and combustion noise superimposed on each other. However, mechanical noise begins to appear and becomes one of the main contradictions that need to be suppressed.

[0025] Specifically, the mechanical noise suppression module 4 performs the following steps: Monitor the gas turbine speed N to confirm that it is in the intermediate power range, i.e., 40%-80% of the rated speed; detect the load power to help judge the stability of the operating conditions, verify the accuracy of the speed signal, and ensure reliable identification of the operating conditions. Vibration signals are detected by accelerometers, including vibrations at bearing characteristic frequencies, gear meshing frequencies, and structural propagation vibrations, to obtain mechanical excitation reference signals. Acoustic signals are acquired by a microphone array, the sound pressure spectrum is analyzed to identify the main noise components, and the sound field phase information is measured to provide a phase reference for the reverse sound wave. Noise characteristic analysis and modeling are performed, the blade passing frequency, gear meshing frequency, and rotor rotation frequency are calculated, the sound pressure level of each frequency component is estimated, and then the total sound pressure level is calculated.

[0026] Specifically, the blade passes through frequency Where N is the rotor speed and B is the number of blades; the gear meshing frequency Where Z is the number of gear teeth; the rotor rotation frequency Rotor imbalance excitation will also generate a frequency of Harmonic noise; The sound pressure level of each frequency component is specifically calculated using the following formula. , in, For the sound pressure level estimated in a specific frequency band, k is an empirical coefficient related to the machine structure and mass, N is the engine speed when it is running, f is the calculated center frequency term, and C is a correction constant; The calculation of the total sound pressure level includes, ,in, Total sound pressure level, Let be the sound pressure level of the i-th noise component, and n be the number of noise components.

[0027] Example 3 When the marine gas turbine 1 is in the high-power range, typically 80% to 100% of its rated speed, its noise characteristics differ significantly from those in the start-up / idle and intermediate-power ranges. Under this condition, the aerodynamic noise of the marine gas turbine 1 becomes the dominant sound source, with its intensity far exceeding that of other noise components.

[0028] Specifically, jet noise dominates the aerodynamic noise. The high-speed exhaust gas discharged from the exhaust assembly 14 of the marine gas turbine 1 mixes violently with the relatively still surrounding air, generating large-scale turbulence and forming extremely strong broadband noise. This noise has a wide frequency spectrum and extremely high sound pressure level, making it the most significant noise source of the gas turbine at high power, and directly determining the far-field noise level of the equipment.

[0029] In addition, the aerodynamic noise of rotating components is enhanced. When the compressor and turbine blades rotate at high speed, the interaction between the blades and the airflow generates strong blade passage frequencies and their harmonic noise. These discrete tones are superimposed on the broadband noise background, further increasing the complexity of the noise.

[0030] Although combustion noise and mechanical noise still exist, they are usually masked by strong aerodynamic noise in the high-power range and become secondary noise components.

[0031] Specifically, the aerodynamic noise suppression module 3 performs the following steps: Operating status parameters are monitored, including real-time monitoring of the gas turbine speed N to confirm it is in the high-power range, i.e., 80%-100% of rated speed; exhaust temperature is also monitored. and exhaust flow _ex provides key input for jet noise calculation; monitors load power and verifies high-power operation. Acoustic signal detection involves acquiring acoustic signals using a high-frequency microphone array, with a focus on high sound pressure level environments; analyzing the sound pressure spectrum to identify the broadband characteristics of jet noise; and measuring the sound field phase information to provide a reference for high-precision reverse acoustic wave synthesis. Thermal parameters are detected, including ambient temperature, pressure, and humidity, to calculate air density and sound speed, providing environmental parameters for the correction of sound wave propagation models; The jet noise sound power level and characteristic frequency are calculated based on the detection parameters; the noise of the rotating components is calculated, the sound pressure level is calculated based on the calculated blade passing frequency, and finally the total sound pressure level is calculated.

[0032] Specifically, the jet noise sound power level is calculated using the following method: , in, The jet noise sound power level, ρ is the jet density, which is related to the exhaust temperature and gas composition; v is the jet velocity, which is the most critical parameter affecting jet noise; and D is the nozzle diameter. For ambient air density, For ambient sound speed, This is an empirical constant for jet noise, typically ranging from -100 to -80 dB, and is related to jet temperature and turbulence characteristics.

[0033] The characteristic frequency of the jet noise ,in denoted as the Storohal number, typically taken as 0.15-0.2, where v is the jet velocity and D is the nozzle diameter.

[0034] The blade passes through frequency Where N is the rotor speed and B is the number of blades; the sound pressure level at the blade passing frequency is calculated using the following formula. in Let S be the sound pressure level at the frequency at which the blade passes through, k be an empirical coefficient related to the blade cascade design, and S be the characteristic area of ​​the blade. The number of blades involved in generating noise. This is the BPF noise correction constant.

[0035] The calculation of the total sound pressure level includes, ,in, Total sound pressure level, Let be the sound pressure level of the i-th noise component, and n be the number of noise components.

[0036] Furthermore, the control of the loudspeaker array to generate reverse sound waves specifically includes synthesizing reverse sound wave signals based on the acquired noise spectrum characteristics of the marine gas turbine 1 at different operating speed ranges. Where y(t) is the time-domain signal of the reverse acoustic wave. Let be the amplitude of the i-th frequency component, which is equal to the corresponding noise amplitude. The i-th frequency component is taken from the main components of the noise spectrum. Let be the phase of the i-th frequency component, obtained through real-time analysis, and M be the number of frequency components considered.

[0037] The multiple speaker arrays 21-23 on the soundproof enclosure 20 are coordinated and controlled in the following manner. , in, This is the speaker drive signal vector. The transfer function matrix describes the acoustic path from each loudspeaker to each control point. Let be the desired control sound field vector, and be the negative value of the detected noise.

[0038] Finally, the performance of the noise suppression system of the present invention, which covers the entire operating speed range of marine gas turbines, compared to the active noise reduction system is evaluated by the following indicators. , , Where NR is the noise reduction amount. Sound pressure level before noise reduction. The sound pressure level after noise reduction. For noise reduction efficiency.

[0039] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A noise suppression system covering the entire operating speed range of a marine gas turbine, comprising a combustion noise suppression module (2), an aerodynamic noise suppression module (3), and a mechanical noise suppression module (4), characterized in that: The marine gas turbine (1) is provided with a soundproof enclosure (20) on its exterior, and the soundproof enclosure (20) is provided with a plurality of speaker arrays (21-23). The current operating speed range of the marine gas turbine (1) is detected by the speed sensor. During the start-up and idling speed range of the marine gas turbine (1), the combustion noise suppression module (2) controls the speaker array to generate reverse sound waves to suppress the noise in the combustion chamber (12) of the marine gas turbine (1). In the intermediate power range of the marine gas turbine (1), the mechanical noise suppression module (4) controls the speaker array to generate reverse sound waves to suppress noise in the marine gas turbine (1). In the high-power region of the marine gas turbine (1), the aerodynamic noise suppression module (3) controls the speaker array to generate reverse sound waves to suppress noise from the compressor (11) and exhaust assembly (14) of the marine gas turbine (1).

2. The noise suppression system according to claim 1, characterized in that, The combustion noise suppression module (2) performs the following steps: Step S101: The operating status parameters, acoustic parameters and thermal parameters of the marine gas turbine (1) in the starting and idling range are collected in real time through a distributed sensor network, and the synchronization of the collected parameters is ensured through time synchronization. Step S102: Identify and verify the operating conditions of the marine gas turbine (1). Based on the speed signal N, confirm that the gas turbine is in the start-up and idling range, and check the fuel flow rate. and combustion chamber pressure Verify the accuracy of operating condition identification; if abnormal operating conditions are detected, activate the safety protection mechanism and issue an alarm. Step S103: Extract combustion noise features, perform 1 / 3 octave band spectrum analysis on the acquired acoustic signal; calculate the sound field phase distribution, analyze signal coherence, and evaluate the quality of the reference signal.

3. The noise suppression system according to claim 2, characterized in that: The thermal parameters include the inlet air temperature. Combustion chamber temperature Exhaust temperature The acoustic parameters include sound pressure spectrum and sound field phase; the operating status parameters include rotor speed N and fuel mass flow rate. Combustion chamber pressure air-fuel ratio .

4. The noise suppression system according to claim 2, characterized in that: The combustion noise suppression module (2) calculates the sound power level of the current combustion noise according to the following formula: ,in The sound power level of combustion noise. This represents the fluctuation in the combustion heat release rate. Let be the average density of the combustion gas in the combustion zone, and c be the sound velocity of the combustion gas in the combustion zone. For reference sound pressure level, K is an empirical constant for burner structure. This is a working condition correction factor; The combustion noise suppression module 2 estimates the peak frequency using the following formula. ,in The peak frequency of combustion noise. The geometry factor of the combustion chamber. For laminar flame velocity, For the thickness of the flame, This represents the actual fuel mass flow rate. This is the rated fuel mass flow rate.

5. The noise suppression system according to claim 1, characterized in that, The mechanical noise suppression module (4) performs the following steps: Step S201: Monitor the gas turbine speed N to confirm that it is in the intermediate power range, i.e., 40%-80% of the rated speed; detect the load power to help judge the stability of the operating conditions, verify the accuracy of the speed signal, and ensure reliable identification of the operating conditions. Step S202: Detect vibration signals using an accelerometer, including detecting bearing characteristic frequency vibration, gear meshing frequency vibration, and structural propagation vibration, to obtain a mechanical excitation reference signal; Step S203: Acoustic signals are acquired through a microphone array, the sound pressure spectrum is analyzed to identify the main noise components, and the sound field phase signal is measured. Step S204: Perform noise characteristic analysis and modeling, calculate the blade passing frequency, gear meshing frequency, and rotor rotation frequency, estimate the sound pressure level of each frequency component, and then calculate the total sound pressure level.

6. The noise suppression system according to claim 5, characterized in that, The blade passes through frequency Where N is the rotor speed and B is the number of blades; the gear meshing frequency Where Z is the number of gear teeth; the rotor rotation frequency .

7. The noise suppression system according to claim 6, characterized in that, The estimated sound pressure level for each frequency component is calculated using the following formula. ， in, For the sound pressure level estimated in a specific frequency band, k is an empirical coefficient related to the machine structure and mass, N is the engine speed when it is running, f is the calculated center frequency term, and C is a correction constant; The calculation of the total sound pressure level includes, ,in, Total sound pressure level, Let be the sound pressure level of the i-th noise component, and n be the number of noise components.

8. The noise suppression system according to claim 1, characterized in that, The aerodynamic noise suppression module (3) performs the following steps: Step S301: Detect operating status parameters, monitor the gas turbine speed N in real time to confirm it is in the high-power range, i.e., 80%-100% of rated speed; detect the exhaust temperature. and exhaust flow _ex, monitor load power and verify high-power operation status; Step S302, acoustic signal detection: Acoustic signals are acquired through a high-frequency microphone array; the sound pressure spectrum is analyzed and the broadband characteristics of the jet noise are identified; the sound field phase information is measured. Step S303: Thermal parameter detection, detecting ambient temperature, pressure, and humidity to calculate air density and sound speed, providing environmental parameters for sound wave propagation model correction; Step S304: Calculate the jet noise sound power level and jet noise characteristic frequency based on the detection parameters; The noise of the rotating component is calculated by calculating the sound pressure level based on the frequency at which the blades pass through, and finally calculating the total sound pressure level.

9. The noise suppression system according to claim 8, characterized in that, The jet noise sound power level is calculated using the following method. ， in, The jet noise sound power level, Let v be the jet density, v be the jet velocity, and D be the nozzle diameter. For ambient air density, For ambient sound speed, This is an empirical constant for jet noise. The characteristic frequency of the jet noise ,in Here, denoted as the Strojal number, and v is the jet velocity.

10. The noise suppression system according to claim 9, characterized in that, The sound pressure level is calculated based on the frequency at which the blade passes through, specifically using the following formula. in Let S be the sound pressure level at the frequency through which the blade passes, k be an empirical coefficient, and S be the characteristic area of ​​the blade. The number of blades involved in generating noise. This is a correction constant.

Images