CN117029045A - Structure and method for inhibiting thermoacoustic oscillation of gas turbine combustor - Google Patents
Structure and method for inhibiting thermoacoustic oscillation of gas turbine combustor Download PDFInfo
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- CN117029045A CN117029045A CN202311042467.8A CN202311042467A CN117029045A CN 117029045 A CN117029045 A CN 117029045A CN 202311042467 A CN202311042467 A CN 202311042467A CN 117029045 A CN117029045 A CN 117029045A
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- acoustic
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- layer pipe
- back cavity
- outer layer
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- 230000010355 oscillation Effects 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 19
- 230000002401 inhibitory effect Effects 0.000 title abstract description 4
- 238000001816 cooling Methods 0.000 claims description 27
- 230000000694 effects Effects 0.000 claims description 9
- 238000010521 absorption reaction Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 230000005284 excitation Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 14
- 238000013016 damping Methods 0.000 description 7
- 238000002485 combustion reaction Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000000452 restraining effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
The invention discloses a structure and a method for inhibiting thermoacoustic oscillation of a gas turbine combustor, which relate to the field of inhibiting thermoacoustic oscillation of the gas turbine combustor, and are applied to the combustor, and comprise an outer layer pipe and an inner layer pipe, wherein the inner layer pipe is positioned in the outer layer pipe, and the inner layer pipe and the outer layer pipe are coaxial; a back cavity is formed between the inner layer tube and the outer layer tube; the inner layer pipe is provided with a plurality of acoustic holes, the acoustic holes are communicated with the back cavity, a resonance cavity is arranged in a part of space corresponding to the acoustic holes in the back cavity, and each acoustic hole and the resonance cavity form a resonance system. The invention can effectively inhibit the thermoacoustic oscillation of the gas turbine combustor and reduce the influence of the thermoacoustic oscillation.
Description
Technical Field
The invention relates to the field of suppressing thermoacoustic oscillations of a gas turbine combustor, in particular to a structure and a method for suppressing thermoacoustic oscillations of a gas turbine combustor.
Background
The combustor is one of three core components of the gas turbine, fuel and air are mixed in the combustor and undergo severe combustion chemical reaction to form high-temperature and high-pressure fuel gas, and a power source spring is provided for turbine work. Wherein, thermoacoustic oscillation is a main factor in restricting the progress of the combustor and even the gas turbine to high efficiency, high temperature rise targets. Thermo-acoustic oscillations result from the coupling between flame heat release rate and pressure disturbances that affect the local instantaneous heat release rate, which in turn generates pressure disturbances that are delayed in time (phase) from the initial disturbance, and subsequently the pressure disturbance wave is reflected at the flame tube boundary, eventually forming a closed loop feedback loop.
When the rate of energy supplied to the sound field by the combustion process is greater than the dissipation of acoustic energy, large pressure fluctuations are caused, including circumferential, axial, radial and compound oscillations of different modes, which can cause flashback or flameout, leading to component ablation and even shutdown; when the resonance occurs with the structure, low-cycle or high-cycle fatigue of parts can be aggravated, the service life of the parts is shortened, and even the parts are invalid; the operation of the control system is interfered, and the operation safety of the combustion engine is endangered; therefore, how to suppress the thermo-acoustic oscillations of the gas turbine combustor is a problem that needs to be solved at present.
Disclosure of Invention
The invention aims at: in order to solve the above-mentioned problems, a structure and a method for suppressing thermoacoustic oscillations of a gas turbine combustor are provided, which can effectively suppress thermoacoustic oscillations of the gas turbine combustor and reduce the influence of the thermoacoustic oscillations.
The technical scheme adopted by the invention is as follows: a structure for restraining thermoacoustic oscillation of a gas turbine combustor is applied to the combustor and comprises an outer layer pipe and an inner layer pipe, wherein the inner layer pipe is positioned in the outer layer pipe and is coaxial with the outer layer pipe; a back cavity is formed between the inner layer tube and the outer layer tube; the inner layer pipe is provided with a plurality of acoustic holes, the acoustic holes are communicated with the back cavity, a resonance cavity is arranged in a part of space corresponding to the acoustic holes in the back cavity, and each acoustic hole and the resonance cavity form a resonance system.
Further, both ends of the back cavity are provided with sealing plates, and the sealing plates are fixed between the end parts of the inner layer pipes and the inner walls of the outer layer pipes.
Further, the plurality of acoustic holes are uniformly arranged along the circumferential direction and the axial direction of the inner layer pipe.
Further, a plurality of cooling holes are formed in the outer layer pipe, and the cooling holes are communicated with the back cavity.
Further, the plurality of cooling holes are uniformly arranged along the circumferential direction and the axial direction of the outer layer tube.
A method of suppressing thermoacoustic oscillations of a gas turbine combustor, the structure for suppressing thermoacoustic oscillations of a gas turbine combustor comprising the steps of:
s1: coaxially installing the structure in the flame tube;
s2: incident sound waves generated by the vibration source enter the back cavity through the acoustic holes;
s3: the sound wave resonates at the acoustic port and consumes and absorbs the energy of the sound wave at or near the resonant frequency of the resonant system.
Further, the shape and the position of a system formed by the inner layer tube and the back cavity are changed, so that sound waves generated by different excitation sources can be consumed and absorbed.
Further, the height and length of the back cavity and the aperture and number of the acoustic holes are adjusted, so that sound waves with different frequencies can be consumed and absorbed.
Further, cold flow enters the back cavity from the cooling hole and flows through the acoustic hole to form a bias flow, and the existence of the bias flow enhances the absorption effect on acoustic energy.
Further, cold flow enters the back cavity from the cooling hole to cool the inner layer pipe, and the size change of the inner layer pipe and the acoustic hole is weakened.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
the back cavity is formed by the inner layer pipe and the outer layer pipe, the inner layer pipe is provided with a plurality of acoustic holes, the acoustic holes and the back cavity space at the acoustic holes form a resonance system, the acoustic holes and the whole back cavity form an acoustic damping system, the acoustic damping system is equivalent to a plurality of resonance systems which are connected in parallel, and sound waves can resonate at the acoustic holes of the resonance system, so that the acoustic energy is consumed and absorbed, and the aim of suppressing thermoacoustic oscillation is fulfilled.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
FIG. 1 is a schematic illustration of the structure of the present disclosure;
FIG. 2 is a schematic illustration of a cooling hole circumferential arrangement of the present disclosure;
FIG. 3 is a schematic view of a circumferential arrangement of acoustic holes in accordance with the present invention;
the marks in the figure: 1-an outer layer tube; 11-cooling holes; 2-an inner tube; 21-an acoustic port; 3-back cavity; 31-a resonant cavity; 4-closing plate.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification may be replaced by alternative features serving the same or equivalent purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
Example 1
As shown in fig. 1 to 3, a structure for suppressing thermo-acoustic oscillations of a gas turbine combustor, which is applied to the combustor, is installed in a combustion barrel of the combustor, and comprises an outer layer pipe 1 and an inner layer pipe 2, wherein the inner layer pipe 2 is positioned in the outer layer pipe 1, and the inner layer pipe 2 is coaxial with the outer layer pipe 1; a space exists between the outer wall of the inner layer tube 2 and the inner wall of the outer layer tube 1, and the space is used as a back cavity 3, namely, the back cavity 3 is formed between the inner layer tube 2 and the outer layer tube 1; the inner layer tube 2 is provided with a plurality of acoustic holes 21, the acoustic holes 21 are communicated with the back cavity 3, and each acoustic hole 21 and the back cavity 3 space at the acoustic hole 21 form a resonance system; in fact, the resonance system is composed of a resonance cavity 31 and an acoustic hole 21, wherein the resonance cavity 31 is a part of the space corresponding to the acoustic hole 21 in the back cavity 3, is a part of the space of the back cavity 3, and is positioned at the position of the corresponding acoustic hole 21; the acoustic damping system consisting of the acoustic port 21 and the back cavity 3 is equivalent to a system formed by connecting a plurality of resonance systems in parallel.
In this embodiment, the sound wave enters the back cavity 3 through the acoustic hole 21, if the frequency of the sound wave is the same as the resonance frequency of the resonance system, the sound wave will resonate at the position of the acoustic hole 21, and the sound energy will be consumed and absorbed; the acoustic damping system formed by the acoustic holes 21 and the back cavity 3 is formed by connecting a plurality of resonance systems in parallel, and the frequency of the sound wave which absorbs and consumes energy under the action of the acoustic damping system in the flame tube is wider than that of a single resonance system.
In this embodiment, the method for calculating the resonance frequency of the single resonance system is as follows:
wherein:
c: sound velocity; n: the number of acoustic holes; d: acoustic hole diameter; v: the total volume of the back cavity 3; l (L) eq : resonance equivalent length.
The method for determining the resonance equivalent length is as follows:
L eq ＝t+0.8d
wherein:
t: the thickness of the inner layer tube; d: an acoustic aperture 21; 0.8d: correction amount; since the air near both ends of the air column at the acoustic port 21 also participates in vibration, correction is required, and the correction value is generally 0.8d.
In summary, in this embodiment, the back cavity 3 is formed by the inner layer pipe 2 and the outer layer pipe 1, and the inner layer pipe 2 is provided with the plurality of acoustic holes 21, the acoustic holes 21 and the back cavity 3 space at the acoustic holes 21 form a resonance system, the acoustic holes 21 and the whole back cavity 3 form an acoustic damping system, the acoustic damping system is equivalent to a plurality of resonance systems in parallel, and the acoustic wave can resonate at the acoustic holes 21 of the resonance system, so that the acoustic energy is consumed and absorbed, the purpose of suppressing thermoacoustic oscillation is achieved, and the stability and the safety of the operation of the burner are remarkably improved.
Example 2
Further embodiments are presented which can be implemented on the basis of example 1.
The utility model provides a feasible implementation, the both ends of back chamber 3 all are provided with closure plate 4, and closure plate 4 seals back chamber 3, is fixed in between the inner wall of the tip of inlayer pipe 2 and outer pipe 1 for back chamber 3 is by independent space, effectively avoids the sound wave to get into back chamber 3 from the both ends of back chamber 3 and causes the interference.
In a possible embodiment, the plurality of acoustic holes 21 are uniformly arranged along the circumferential direction and the axial direction of the inner tube 2, so that the pressure loss of the acoustic wave is more uniform.
In a possible embodiment, the acoustic hole 21 may be in the shape of a cylindrical hole, a square hole, etc., and in a preferred manner, the cross-sectional shape of the acoustic hole 21 is tapered, and the small-diameter section of the acoustic hole 21 is close to the back cavity 3; the frequency band in which sound waves can be consumed and absorbed can be increased.
Further, when the acoustic port 21 is tapered, the diameter D of the acoustic port 21 in embodiment 1 may be selected as the diameter of the acoustic port 21.
Example 3
Further embodiments are provided that are possible on the basis of any one of the embodiments 1-2.
One possible implementation mode is that a plurality of cooling holes 11 are formed in the outer layer tube 1, and the cooling holes 11 are communicated with the back cavity 3; the introduction of a cold flow of relatively low temperature through the cooling holes 11 into the back cavity 3 has at least the following advantageous effects in this embodiment.
The cooling flow has the advantages that firstly, the cooling flow can cool the inner layer pipe 2, the heat in the combustion cylinder is reduced, the geometric dimensions of the inner layer pipe 2 and the acoustic holes 21 are changed, the inner layer pipe 2 is ensured to be close to the acoustic holes 21 and kept at the designed dimensions, and the resonance frequency of the resonance system is ensured to be close to the acoustic holes 21 and kept at the designed dimensions, namely, the resonance frequency of the resonance system is ensured because the resonance frequency of the resonance system is related to the aperture of the acoustic holes 21, the thickness of the inner layer pipe 2 and the total volume of the back cavity 3; for sound waves with a certain frequency, the capacity of consuming and absorbing sound energy can be ensured, and further, the effect of restraining thermoacoustic oscillation is ensured.
The beneficial effects are that after cold flow enters the back cavity 3, a bias flow is formed at the acoustic hole 21, and the bias flow can enhance the speed disturbance and the viscosity effect at the acoustic hole 21, so that the conversion of sound energy to vortex energy is accelerated, and the sound absorption effect of a resonance system is enhanced.
The beneficial effects are three, utilize the cold flow of drift, can improve the cooling performance of combustor.
Further, a plurality of cooling air are arrayed along the circumferential direction of the outer layer pipe 1, so that cold flow can uniformly enter the back cavity 3 from the circumferential direction of the outer layer pipe 1, and the aim of uniformly cooling the inner layer pipe 2 in the circumferential direction is fulfilled; the plurality of cooling holes 11 are arrayed along the axis of the outer layer pipe 1, so that cold flow can uniformly enter the back cavity 3 from the axial direction of the outer layer pipe 1, and the aim of axially uniformly cooling the inner layer pipe 2 is fulfilled; the cooling is uniform in the circumferential direction and the axial direction, and the purpose of uniformly cooling the whole body is achieved.
In this embodiment, the cold flow is cooling air, which may be relatively low temperature air.
Example 4
A method for suppressing thermoacoustic oscillations of a gas turbine combustor, using the structure for suppressing thermoacoustic oscillations of a gas turbine combustor of any one of embodiments 1-3, comprising the steps of:
s1: coaxially installing the structure in the flame tube;
s2: the incident sound wave generated by the vibration source enters the back cavity 3 through the acoustic hole 21;
s3: the acoustic wave resonates at the acoustic port 21, and consumes and absorbs the energy of the acoustic wave at or near the resonance frequency of the resonant system.
In this embodiment, the method of acquiring the resonance frequency of the resonance system can be seen from the description in embodiment 1, and will not be described in detail here.
Further, the sound waves generated by different excitation sources can be consumed and absorbed by changing the shape and the position of the system formed by the inner layer tube 2 and the back cavity 3.
Further, the height and length of the back cavity 3 are adjusted, and the aperture, the number and the arrangement positions of the acoustic holes 21 can consume and absorb sound waves with different frequencies; according to the formula in embodiment 1, adjusting the height and length of the back chamber 3 is actually adjusting the total volume of the back chamber 3; the aperture and the number of the acoustic holes 21 are comprehensively adjusted, so that the resonance frequency of the resonance system can be adjusted, and the consumption and the absorption of sound waves with different frequencies are realized.
In this embodiment, the outer layer tube 1 is provided with a cooling hole 11, cold flow enters the back cavity 3 from the cooling hole 11 and flows through the acoustic hole 21 to form a bias current, and the existence of the bias current enhances the absorption effect of acoustic energy, thereby further enhancing the effect of suppressing thermo-acoustic oscillation; and the inner layer pipe 2 is cooled, so that the dimensional change of the inner layer pipe and the acoustic holes 21 is weakened, and the resonance frequency of the resonance system is ensured; for sound waves with a certain frequency, the capacity of consuming and absorbing sound energy can be ensured, and further, the effect of restraining thermoacoustic oscillation is ensured.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Claims (10)
1. A structure for suppressing thermo-acoustic oscillations of a gas turbine combustor, characterized by: the burner comprises an outer layer pipe (1) and an inner layer pipe (2), wherein the inner layer pipe (2) is positioned in the outer layer pipe (1) and the inner layer pipe (2) and the outer layer pipe (1) are coaxial; a back cavity (3) is formed between the inner layer tube (2) and the outer layer tube (1); be provided with a plurality of acoustic hole (21) on inlayer pipe (2), acoustic hole (21) communicate in back of the body chamber (3), and the place space that acoustic hole (21) department corresponds in back of the body chamber (3) is resonant cavity (31), and every acoustic hole (21) and resonant cavity (31) form resonance system.
2. The structure according to claim 1, characterized in that: both ends of the back cavity (3) are provided with sealing plates (4), and the sealing plates (4) are fixed between the end parts of the inner layer tubes (2) and the inner walls of the outer layer tubes (1).
3. The structure according to claim 1, characterized in that: the plurality of acoustic holes (21) are uniformly distributed along the circumferential direction and the axial direction of the inner layer pipe (2).
4. A structure according to any one of claims 1-3, characterized in that: a plurality of cooling holes (11) are formed in the outer layer tube (1), and the cooling holes (11) are communicated with the back cavity (3).
5. The structure according to claim 4, characterized in that: the plurality of cooling holes (11) are uniformly distributed along the circumferential direction and the axial direction of the outer layer tube (1).
6. A method of suppressing thermoacoustic oscillations of a gas turbine combustor, comprising: use of a structure according to any one of claims 1-6 for suppressing thermo-acoustic oscillations of a gas turbine combustor, comprising the steps of:
s1: coaxially installing the structure in the flame tube;
s2: the incident sound wave generated by the vibration source enters the back cavity (3) through the acoustic hole (21);
s3: the sound wave resonates at the acoustic port (21), and consumes and absorbs the sound wave energy at or near the resonance frequency of the resonance system.
7. The method according to claim 6, wherein: the shape and the position of a system formed by the inner layer tube (2) and the back cavity (3) are changed, so that sound waves generated by different excitation sources can be consumed and absorbed.
8. The method according to claim 6, wherein: the height and the length of the back cavity (3) are adjusted, and the aperture and the number of the acoustic holes (21) can consume and absorb sound waves with different frequencies.
9. A method according to any one of claims 6-8, characterized in that: cold flow enters the back cavity (3) from the cooling hole (11) and flows through the acoustic hole (21) to form bias flow, and the existence of the bias flow enhances the absorption effect on acoustic energy.
10. The method according to claim 9, wherein: the cold flow enters the back cavity (3) from the cooling hole (11) to cool the inner layer pipe (2) and weaken the dimensional change of the inner layer pipe (2) and the acoustic hole (21).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311042467.8A CN117029045A (en) | 2023-08-18 | 2023-08-18 | Structure and method for inhibiting thermoacoustic oscillation of gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311042467.8A CN117029045A (en) | 2023-08-18 | 2023-08-18 | Structure and method for inhibiting thermoacoustic oscillation of gas turbine combustor |
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| Publication Number | Publication Date |
|---|---|
| CN117029045A true CN117029045A (en) | 2023-11-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311042467.8A Pending CN117029045A (en) | 2023-08-18 | 2023-08-18 | Structure and method for inhibiting thermoacoustic oscillation of gas turbine combustor |
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| Country | Link |
|---|---|
| CN (1) | CN117029045A (en) |
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2023
- 2023-08-18 CN CN202311042467.8A patent/CN117029045A/en active Pending
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