Sound dissipation device for combustion chamber of gas turbine
By adding elastic damping components to the acoustic lining structure of the gas turbine combustion chamber, acoustic energy is converted into mechanical energy and dissipated, solving the combustion instability problem caused by the large size of traditional acoustic lining devices, and realizing the stability of the combustion system and the protection of acoustic frequencies.
Patent Information
- Application Number
- CN202511297702.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-11
- Publication Date
- 2025-12-09
AI Technical Summary
The acoustic lining devices of existing gas turbine combustors may change the inherent acoustic frequency of the combustion system when they are enlarged, leading to combustion instability. Traditional silencers cannot effectively suppress thermoacoustic oscillations.
An acoustic lining structure is installed on the outer wall of the flame tube in the combustion chamber, and an elastic damping structure is added therein. The elastic damping element undergoes elastic deformation under pressure changes, converting acoustic energy into mechanical energy for dissipation. The energy is actively dissipated through turbulent pulsation and the compression-release process of the elastic damping element.
It significantly reduces the amplitude of combustion pressure pulsation, reduces the volume of the sound dissipation device, prevents changes in acoustic frequency, stabilizes the combustion system, and avoids combustion instability.
Smart Images
Figure CN121089087A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The embodiment of the present disclosure belongs to the technical field of gas turbines, and particularly relates to a gas turbine combustion chamber sound dissipation device. BACKGROUND
[0002] Most of the heavy-duty gas turbines in service adopt diffusion combustion (pilot flame) plus lean premixed combustion mode to ensure that the pollutant emissions meet the environmental protection requirements. The lean premixed combustion is usually close to the combustion stability boundary, and is prone to strong thermoacoustic oscillation, which will seriously damage the combustion chamber components. In view of the problem of thermoacoustic oscillation of the combustion chamber, the method of adding a muffler is often used in engineering, such as adding a Helmholtz resonator, a 1 / 4 wavelength tube or a sound lining device at a specific position of the combustion chamber, to increase the dissipation of sound energy and weaken the feedback loop between the sound pressure disturbance and the heat release disturbance. Among them, the sound lining device has good inhibitory effect on the wideband combustion pressure fluctuation of the gas turbine, and itself participates in the overall acoustic response of the gas turbine combustion chamber. When the inlet area of the sound lining device is large enough and its volume accounts for a large part of the volume of the combustion chamber, it will change the original inherent acoustic frequency of the combustion system, the sound damping effect of the sound lining device is inhibited, and even the combustion instability is more serious, which is particularly obvious when a plurality of sound lining devices are used in a stacked manner and the volume is doubled.
[0003] In view of the above problems, it is necessary to provide a gas turbine combustion chamber sound dissipation device which is reasonable in design and effective in solving the above problems. SUMMARY
[0004] The embodiment of the present disclosure aims to at least solve one of the technical problems existing in the prior art, and provides a gas turbine combustion chamber sound dissipation device.
[0005] The embodiment of the present disclosure provides a gas turbine combustion chamber sound dissipation device, which comprises a flame tube and at least one sound lining structure arranged on the outer sidewall of the flame tube.
[0006] The sidewall of the flame tube is provided with a plurality of first air holes, wherein the high-temperature gas in the combustion chamber enters the sound lining structure through the first air holes, so that the pressure in the sound lining structure changes.
[0007] A plurality of elastic damping members are arranged in the sound lining structure, wherein the elastic damping members can elastically deform under the action of the pressure change in the sound lining structure, so as to convert the sound energy in the combustion chamber into mechanical energy dissipation.
[0008] Illustratively, the elastic damping member is provided with a flow channel, and a plurality of communication holes are arranged on the flow channel.
[0009] Illustratively, the plurality of communication holes are equally spaced.
[0010] Exemplarily, the wall of the sound lining structure is provided with a plurality of second air holes.
[0011] The second air holes are used for air in the combustion cylinder to enter the sound lining structure and interact with high-temperature gas in the combustion chamber to form dynamic pressure fluctuation.
[0012] Exemplarily, the plurality of second air holes are equally spaced.
[0013] Exemplarily, the plurality of first air holes are equally spaced.
[0014] Exemplarily, the elastic damping member is made of high-temperature-resistant elastic material.
[0015] Exemplarily, the elastic damping member includes a spring, a metal bellows or a high-temperature-resistant elastomer.
[0016] Exemplarily, the plurality of elastic damping members in the sound lining structure are equally spaced.
[0017] Exemplarily, the sound lining structure is a plurality of sound lining structures, and the plurality of sound lining structures are sequentially arranged on the outer wall of the flame tube.
[0018] The gas turbine combustion chamber sound dissipation device provided by the embodiment of the present disclosure includes a flame tube and at least one sound lining structure arranged on the outer wall of the flame tube. The side wall of the flame tube is provided with a plurality of first air holes, and high-temperature gas in the combustion chamber enters the sound lining structure through the first air holes to change the pressure in the sound lining structure. The sound lining structure is provided with a plurality of elastic damping members, wherein the elastic damping members can elastically deform under the action of the pressure change in the sound lining structure to convert the sound energy in the combustion chamber into mechanical energy dissipation. The device adds elastic damping members to the traditional sound lining device, and can convert more sound energy into mechanical energy dissipation through the compression and release of the elastic damping members and the turbulent pulsation, thereby significantly reducing the amplitude of the combustion pressure fluctuation compared with the traditional cavity structure, so as to reduce the overall size of the sound dissipation device, reduce the volume, and prevent the volume of the sound dissipation device from being too large to change the original inherent acoustic frequency of the combustion system. BRIEF DESCRIPTION OF DRAWINGS
[0019] Figure 1 FIG. 1 is a structural schematic diagram of a gas turbine combustion chamber sound dissipation device according to an embodiment of the present disclosure;
[0020] Figure 2 FIG. 2 is a structural schematic diagram of an elastic damping member according to another embodiment of the present disclosure;
[0021] Figure 3 FIG. 3 is a structural schematic diagram of a gas turbine combustion chamber sound dissipation device according to another embodiment of the present disclosure. DETAILED DESCRIPTION
[0022] In order for those skilled in the art to better understand the technical solutions of the embodiments of the present disclosure, the embodiments of the present disclosure are further described in detail below with reference to the drawings and specific embodiments.
[0023] As shown in Figure 1 The present embodiment provides a gas turbine combustor sound dissipation device 100, which comprises a flame tube 110 and at least one sound lining structure 120 arranged on the outer sidewall of the flame tube 110. Wherein, the flame tube 110 is the core component of the combustor.
[0024] The sidewall of the flame tube 110 is provided with a plurality of first air holes 111, wherein the high-temperature gas in the combustor enters the sound lining structure 120 through the first air holes 111, so that the pressure in the sound lining structure 120 changes.
[0025] A plurality of elastic damping members 130 are arranged in the sound lining structure 120, wherein the elastic damping members 130 can elastically deform under the action of the pressure change in the sound lining structure 120, so as to convert the sound energy in the combustor into mechanical energy dissipation. Specifically, as shown in Figure 1 In this embodiment, one sound lining structure 120 is arranged on each side of the flame tube 110, and each sound lining structure 120 is provided with three elastic damping members 130.
[0026] It should be noted that the number of sound lining structures 120 and the number of elastic damping members 130 in each sound lining structure 120 are not specifically limited in this embodiment and can be selected according to actual needs.
[0027] It should be further noted that in this embodiment, the plurality of first air holes 111 can be equally spaced on the sidewall of the flame tube 110, so that the high-temperature gas in the combustor enters the sound lining structure 120 more uniformly, so as to better change the pressure in the sound lining structure 120. Wherein, the number of first air holes 111 can match the number of elastic damping members 130 in the sound lining structure 120. For example, the number of elastic damping members 130 in the sound lining structure 120 is 3, and correspondingly, the number of first air holes 111 is also 3. In this embodiment, the number and distribution position of the first air holes 111 are not specifically limited and can be selected according to actual needs.
[0028] Specifically, the high-temperature gas in the combustion chamber enters the acoustic lining structure 120 through the first air holes 111, and the fluid entering and exiting the acoustic lining structure 120 generates energy dissipation due to turbulent friction, and the fluid entering and exiting the acoustic lining structure 120 forms a dynamic pressure change in the acoustic lining structure 120. The pressure change in the acoustic lining structure 120 acts on the plurality of elastic dampers 130, so that the elastic dampers 130 are repeatedly compressed and released, thereby converting the acoustic energy in the combustion chamber into mechanical energy dissipation, and greatly reducing the amplitude of the combustion pressure pulsation. The thermoacoustic oscillation (pressure pulsation) in the combustion chamber is greatly weakened, avoiding the combustion instability caused by the coupling of acoustic pressure disturbance and combustion heat release.
[0029] The gas turbine combustion chamber acoustic dissipation device of the embodiment of the present disclosure comprises a flame tube and at least one acoustic lining structure arranged on the outer sidewall of the flame tube; the sidewall of the flame tube is provided with a plurality of first air holes, and the high-temperature gas in the combustion chamber enters the acoustic lining structure through the first air holes to cause a pressure change in the acoustic lining structure; and the acoustic lining structure is provided with a plurality of elastic dampers, wherein the elastic dampers can be elastically deformed under the action of the pressure change in the acoustic lining structure, so as to convert the acoustic energy in the combustion chamber into mechanical energy dissipation. The device adds elastic dampers to the traditional acoustic lining device, and can convert more acoustic energy into mechanical energy dissipation through turbulent pulsation and compression and release of the elastic dampers themselves, thereby significantly reducing the amplitude of the combustion pressure pulsation compared with the traditional cavity structure, so as to reduce the overall size of the acoustic dissipation device, reduce the volume, and prevent the acoustic dissipation device from changing the original inherent acoustic frequency of the combustion system due to the excessively large volume. The gas turbine combustion chamber acoustic dissipation device of the embodiment of the present disclosure suppresses oscillation through "active energy dissipation" rather than "passive reflection", which is the core innovation that distinguishes it from the traditional acoustic lining device.
[0030] It should be noted that the compression-release motion of the elastic dampers 130 is matched with the pressure pulsation frequency in the combustion chamber to maximize the acoustic energy-mechanical energy conversion efficiency.
[0031] For example, as shown in FIG. 2, the elastic dampers 130 are arranged in the acoustic lining structure 120. Figure 2
[0032] Specifically, the flow channel of the elastic damper 130 is connected to the outside through the communication holes 132, so that the fluid in the acoustic lining structure 120 enters and exits the flow channel 131 of the elastic damer 130, further increasing the dissipation of acoustic energy and mechanical energy. The flow channel 131 can be a spiral flow channel to lengthen the airflow path and enhance turbulent dissipation.
[0033] Preferably, in the embodiment, the plurality of communication holes 132 are equally spaced, so that the fluid in the acoustic lining structure 120 enters and exits the flow channel 131 of the elastic damper 130 more uniformly, thereby better increasing the dissipation of acoustic energy and mechanical energy.
[0034] As shown in Figure 1 The wall of the acoustic lining structure 120 is provided with a plurality of second air holes 121, which are used to make the air in the combustion cylinder enter the acoustic lining structure 120 and interact with the high-temperature gas in the combustion chamber to form dynamic pressure fluctuation.
[0035] Specifically, the air in the combustion cylinder and the high-temperature gas in the combustion chamber enter the acoustic lining structure 120 through the second air holes 121 of the acoustic lining structure 120 and the first air holes 111 of the flame tube 110 respectively, and energy dissipation is generated in the process of fluid entering and exiting. At the same time, the entering and exiting of the fluid causes the pressure in the acoustic lining structure 120 to change continuously, and the change of the pressure acts on the elastic damping member 130, so that the elastic damping member 130 is continuously compressed and released, thereby converting the acoustic energy in the combustion chamber into mechanical energy dissipation and greatly reducing the amplitude of the combustion pressure fluctuation.
[0036] Preferably, in the embodiment, the plurality of second air holes 121 can be distributed at equal intervals. In the embodiment, the number of the second air holes 121 matches the number of the elastic damping members 130 in the acoustic lining structure 120.
[0037] Specifically, as shown in Figure 1 In the embodiment, the number of the second air holes 121 matches the number of the elastic damping members 130 in the acoustic lining structure 120, and the number of the second air holes 121 is also 3. The number and distribution position of the second air holes 121 are not limited in the embodiment and can be selected according to actual needs.
[0038] In the embodiment, the elastic damping member 130 can be made of a high-temperature-resistant elastic material. In the high-temperature, high-pressure and corrosive environment of the combustion chamber of the gas turbine, the material of the elastic damping member 130 needs to meet the requirements of high-temperature resistance (usually > 800℃), oxidation resistance, creep resistance and good elasticity. For example, the material of the elastic damping member 130 can be a nickel-based alloy. The specific material of the elastic damping member 130 is not limited in the embodiment and can be selected according to actual needs, as long as it can meet the requirements of high-temperature resistance, oxidation resistance, creep resistance and good elasticity.
[0039] In the embodiment, the elastic damping member 130 can include a spring, a metal bellows or a high-temperature-resistant elastic body, which can convert acoustic energy into mechanical energy dissipation through compression-release movement. The specific structure of the elastic damping member 130 is not limited in the embodiment and can be selected according to actual needs.
[0040] In the embodiment, the elastic damping member 130 can include a spring, a metal bellows or a high-temperature-resistant elastic body, which can convert acoustic energy into mechanical energy dissipation through compression-release movement. The specific structure of the elastic damping member 130 is not limited in the embodiment and can be selected according to actual needs. Figure 1As shown, in this embodiment, the plurality of elastic dampers 130 are evenly distributed in the acoustic lining structure 120. In this way, when the pressure change in the acoustic lining structure 120 acts on the plurality of elastic dampers 130, the plurality of elastic dampers 130 can be more evenly compressed and released repeatedly, thereby converting the acoustic energy in the combustion chamber into mechanical energy dissipation
[0041] For example, in another embodiment, as shown in FIG. 2, the acoustic lining structure 120 is provided on the outer wall of the flame tube 110. Figure 3 As shown, the acoustic lining structure 120 is provided on the outer wall of the flame tube 110. Figure 3 As shown, in this embodiment, the acoustic lining structure 120 is provided on the outer wall of the flame tube 110.
[0042] It should be noted that the number of acoustic lining structures 120 and the number of elastic dampers 130 in the acoustic lining structure 120 are not specifically limited and can be selected according to the actual operating conditions of the gas turbine.
[0043] It should be further noted that the volume of the acoustic lining structure 120 and the stiffness of the elastic dampers 130 can be adjusted to adapt to the acoustic characteristics of different combustion systems.
[0044] It should be understood that the above embodiments are only exemplary embodiments adopted to illustrate the principles of the disclosed embodiments, and the disclosed embodiments are not limited thereto. Various modifications and improvements can be made by those of ordinary skill in the art without departing from the spirit and essence of the disclosed embodiments, and these modifications and improvements are also considered within the protection scope of the disclosed embodiments.
Claims
1. A combustion chamber acoustic dissipation device for a gas turbine engine, characterized by, The flame tube and at least one sound lining structure arranged on the outer wall of the flame tube; The side wall of the flame tube is provided with a plurality of first air holes, wherein high-temperature gas in the combustion chamber enters the sound lining structure through the first air holes, so that the pressure in the sound lining structure changes; The sound lining structure is provided with a plurality of elastic damping members, wherein the elastic damping members can elastically deform under the action of the pressure change in the sound lining structure, so as to convert the sound energy in the combustion chamber into mechanical energy and dissipate it.
2. The apparatus of claim 1, wherein, The elastic damping member is provided with a flow channel, and a plurality of communication holes are arranged on the flow channel.
3. The apparatus of claim 2, wherein, The plurality of communication holes are equally spaced.
4. The device of any one of claims 1 to 3, wherein, The wall surface of the sound lining structure is provided with a plurality of second air holes; The second air holes are used to make the air in the combustion chamber enter the sound lining structure and interact with the high-temperature gas in the combustion chamber to form dynamic pressure fluctuation.
5. The apparatus of claim 4, wherein, The plurality of second air holes are equally spaced.
6. The device of any one of claims 1 to 3, wherein, The plurality of first air holes are equally spaced.
7. The device of any one of claims 1 to 3, wherein, The elastic damping member is made of high-temperature-resistant elastic material.
8. The device of any one of claims 1 to 3, wherein, The elastic damping member includes a spring, a metal bellows or a high-temperature-resistant elastomer.
9. The device of any one of claims 1 to 3, wherein, The plurality of elastic damping members in the sound lining structure are equally spaced.
10. The device of any one of claims 1 to 3, wherein, The number of the sound lining structures is multiple, and the plurality of sound lining structures are arranged on the outer wall of the flame tube in sequence.