An annular combustion device for studying thermoacoustic oscillations and their active control

Abstract

The present invention belongs to the field of thermoacoustic oscillation of aircraft engines and industrial gas turbines, and specifically relates to an annular combustion device for studying thermoacoustic oscillation and its active control, aiming to solve the problem that the prior art is limited to a single frequency of a specific combustion chamber, has a long development cycle, and is expensive. The present invention includes: the combustion chamber is coaxially fixed with the upper plate of the burner, the upper plate of the burner is coaxially fixed with the support frame, one end of a plurality of annular arrays of burner straight pipes is mounted on the upper plate of the burner, and the other end of the burner straight pipe is detachably fixedly connected with a fastener; a nozzle core that can move along the burner is coaxially arranged in the burner straight pipe, the inner surface of one end of the nozzle core is detachably fixedly connected with a secondary nozzle, the secondary nozzle is used to spray the gas source flowing through the nozzle core, and the other end of the nozzle core is connected to an external gas source; the burner straight pipe is sealed and connected with a diverter ring mechanism, and the diverter ring mechanism is used to introduce premixed gas. The present invention has a simple structure, reduces costs, and can adapt to a variety of frequencies.

Description

Technical Field

[0001] The invention belongs to the field of thermoacoustic oscillation of aircraft engines and industrial gas turbines, and in particular relates to an annular combustion device for studying thermoacoustic oscillation and active control thereof. Background Art

[0002] Thermoacoustic oscillation is caused by the in-phase coupling of non-steady-state pressure pulsation and heat release rate. When thermoacoustic oscillation occurs, the pressure in the combustion chamber presents a high-amplitude limit cycle oscillation. This pressure oscillation will cause periodic heat load on the combustion chamber wall and induce mechanical vibration, resulting in reduced engine performance and possible damage to gas turbine hardware, which seriously restricts the development of advanced engine combustion chambers.

[0003] The mechanism of thermoacoustic oscillation will change due to different combustion chamber structures and working conditions. The commonly accepted ones are equivalence ratio pulsation and velocity pulsation. Equivalence ratio pulsation is caused by uneven equivalence ratio, that is, uneven mixing of fuel and oxidant, which is directly related to the intake method of premixed gas. Velocity pulsation is uneven velocity, which is also closely related to the intake method of premixed gas. Therefore, whether the intake method of premixed gas can be improved will have an important impact on the occurrence of thermoacoustic oscillation.

[0004] There are two main methods for suppressing thermoacoustic oscillations: passive suppression and active control. Passive suppression methods include acoustic cavities and baffles, but this method is often limited to a single frequency in a specific combustion chamber, and has a long development cycle and is expensive. The core of the active control method is to break the coupling relationship between pressure pulsation and heat release rate, which needs to be achieved through solenoid valves and algorithms, and requires a high degree of rapid response from these actuators.

[0005] In order to enable gas turbines to overcome the problem of thermoacoustic oscillation, it is necessary to first develop a test device that can generate thermoacoustic oscillations, so that the generation mechanism of thermoacoustic oscillations can be studied in detail; secondly, it is necessary to develop a simple active control system for thermoacoustic oscillations, which can reduce the pressure oscillation amplitude of thermoacoustic oscillations to an industrially acceptable level through simple control. The above aspects have become problems that need to be solved urgently in the existing technology.

[0006] Based on this, the present invention proposes an annular combustion device for studying thermoacoustic oscillation and its active control. Summary of the invention

[0007] In order to solve the above problems in the prior art, that is, the prior art is limited to a single frequency of a specific combustion chamber, has a long development cycle, and is expensive, the present invention provides an annular combustion device for studying thermoacoustic oscillation and its active control, including a combustion chamber, a burner upper plate, a support frame, a nozzle core, a burner straight pipe, a secondary nozzle, a swirler, and a honeycomb;

[0008] The combustion chamber is coaxially fixed to the burner upper plate, the burner upper plate is coaxially fixed to the support frame, the support frame is fixed to the external optical platform, one end of a plurality of annular arrays of burner straight tubes is mounted on the burner upper plate, and the other end of the burner straight tube is detachably fixedly connected to a fastener;

[0009] A nozzle core that can move along the burner straight tube is coaxially arranged inside the burner straight tube, the inner surface of one end of the nozzle core is detachably fixedly connected to a secondary nozzle, the secondary nozzle is used to spray the gas source flowing through the nozzle core, and the other end of the nozzle core is connected to an external gas source;

[0010] The burner straight pipe is sealed and connected to the diverter ring mechanism, and the diverter ring mechanism is used to introduce premixed gas;

[0011] The outer surface of one end of the nozzle inner core is threadedly connected to the swirler, and a plurality of blades are arranged on the swirler. A honeycomb is installed between the outer surface of the nozzle inner core and the inner surface of the burner straight pipe, and the honeycomb is used to increase the smoothness of the premixed gas intake.

[0012] In some preferred embodiments, the fastener includes a fastening bolt and a fastening nut;

[0013] The other end of the burner straight tube is coaxially fixed with the fastening bolt, and the fastening bolt is threadedly connected with the fastening nut.

[0014] In some preferred embodiments, a plurality of spray holes are evenly and axially formed on the upper surface of the secondary nozzle, and the spray holes are used to spray the gas source into the combustion chamber.

[0015] In some preferred embodiments, an igniter hole is provided on the upper plate of the burner, and the igniter hole is used for an external igniter.

[0016] In some preferred embodiments, a pressure sensor mounting hole is provided on the upper plate of the burner, and the pressure sensor mounting hole is used for connecting an external high-frequency pressure sensor.

[0017] In some preferred embodiments, a plurality of burner straight tube air inlet holes are provided on the burner straight tube along its circumferential direction, and the burner straight tube air inlet holes are used to allow the premixed gas to flow into the burner straight tube.

[0018] In some preferred embodiments, the diverter ring mechanism includes at least two connected diverter rings, which are coaxially fixed with the diverter ring nut, and the diverter ring nut is threadedly connected to the outer surface of the burner straight pipe. The lowermost diverter ring is connected to a diverter ring joint, and the uppermost diverter ring covers the air inlet hole of the burner straight pipe, and the diverter ring joint is used to connect to a premixed gas source.

[0019] In some preferred embodiments, the other end of the nozzle inner core is detachably fixed to a nozzle inner core joint, and the nozzle inner core joint is connected to an external air source.

[0020] In some preferred embodiments, the combustion chamber is a quartz glass combustion chamber.

[0021] Beneficial effects of the present invention:

[0022] The present invention can generate thermoacoustic oscillations during the thermal test process, so that the mechanism of thermoacoustic oscillation generation can be studied. The use of a quartz glass combustion chamber facilitates optical visualization observation, and a high-frequency pressure sensor can collect pressure pulsation data, which can be used for modal judgment of thermoacoustic oscillations.

[0023] The present invention has a high degree of modularization and can carry out parametric research on thermoacoustic oscillations. In terms of structural parameters, the secondary nozzle and the swirler are threadedly installed with the inner core of the nozzle, so it is easy to replace, and the influence of different swirl angles and secondary nozzle spray hole angles on thermoacoustic oscillations can be studied. By adjusting the tightness of the fastening nut, the axial movement of the inner core of the nozzle can be achieved, so that the retraction distance can be changed, and the influence of different retraction distances on thermoacoustic oscillations can be studied. In terms of operating parameters, the flow rate of each nozzle is controlled separately, so the influence of different equivalence ratios, different propellant spatial distributions, different swirler flow rates, and different secondary nozzle flow rates on thermoacoustic oscillations can be studied. The diverter ring interface is externally connected to the premixed methane / air gas, and the nozzle inner core joint is externally connected to the gas source, which can be methane, air, hydrogen, nitrogen, etc., and the influence of fuel composition on thermoacoustic oscillations can be studied.

[0024] Finally, in terms of combustion form, the combustion device can realize two different combustion forms. When the diverter ring interface is connected to a premixed gas, it is premixed combustion. When the secondary nozzle is removed, the diverter ring interface is connected to one gas and the nozzle inner core joint is connected to another gas, which is non-premixed combustion. Therefore, the influence of combustion form on thermoacoustic oscillation can be studied. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings:

[0026] Figure 1 It is an axonometric diagram of an annular combustion device for studying thermoacoustic oscillation and its active control according to the present invention;

[0027] Figure 2 It is a schematic diagram of the internal structure of an annular combustion device for studying thermoacoustic oscillation and its active control according to the present invention;

[0028] Figure 3It is a top view of an annular combustion device for studying thermoacoustic oscillation and active control thereof according to the present invention;

[0029] Figure 4 It is a structural schematic diagram of a secondary nozzle of an annular combustion device for studying thermoacoustic oscillation and active control thereof according to the present invention;

[0030] Figure 5 It is a structural schematic diagram of a straight tube of a burner of an annular combustion device for studying thermoacoustic oscillation and active control thereof according to the present invention;

[0031] Figure 6 It is a structural schematic diagram of a first diverter ring of an annular combustion device for studying thermoacoustic oscillation and active control thereof according to the present invention;

[0032] Figure 7 It is a structural schematic diagram of a second diverter ring of an annular combustion device for studying thermoacoustic oscillation and active control thereof according to the present invention;

[0033] Figure 8 It is a structural schematic diagram of the third diverter ring of an annular combustion device for studying thermoacoustic oscillation and active control thereof according to the present invention. DETAILED DESCRIPTION

[0034] The present application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant invention, rather than to limit the invention. It is also necessary to explain that, for ease of description, only the parts related to the relevant invention are shown in the accompanying drawings.

[0035] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0036] like Figure 1-Figure 8 As shown, see Figure 1 and Figure 2 , the present invention provides an annular combustion device for studying thermoacoustic oscillation and its active control, comprising a combustion chamber 1, a burner upper plate 2, a support frame 3, a nozzle inner core 4, a burner straight pipe 5 and a secondary nozzle 9;

[0037] The combustion chamber 1 is coaxially fixed to the burner upper plate 2, the burner upper plate 2 is coaxially fixed to the support frame 3, one end of a plurality of annular array burner straight tubes 5 are mounted on the burner upper plate 2, and the other end of the burner straight tube 5 is detachably fixedly connected with a fastener;

[0038] A nozzle core 4 is coaxially arranged in the burner straight tube 5 and can move along the nozzle core 4. The inner surface of one end of the nozzle core 4 is detachably fixedly connected to a secondary nozzle 9. The secondary nozzle 9 is used to spray the gas source flowing through the nozzle core 4. The other end of the nozzle core 4 is connected to an external gas source.

[0039] The burner straight pipe 5 is in sealed communication with a diverter ring mechanism, and the diverter ring mechanism is used for introducing premixed gas.

[0040] The combustion chamber 1 in this embodiment is preferably a quartz glass combustion chamber.

[0041] The burner upper plate 2 and the support frame 3 are coaxially fixed and installed by bolts.

[0042] Among them, in this embodiment, a burner upper plate mounting hole 21 is opened in the center of the burner upper plate 2, and with the burner upper plate 2 as the center, multiple burner upper plate mounting holes 21 are evenly opened in the circumferential direction thereof, preferably 6 holes, and each burner upper plate mounting hole 21 is used for welding and installation with the burner straight pipe 5.

[0043] The number of the burner upper plate mounting holes 21 is consistent with the number of the burner straight tubes 5 .

[0044] In this embodiment, there are seven burner straight tubes 5 in total, each of which is provided with a nozzle core 4. Accordingly, seven fasteners and secondary nozzles 9 are also provided.

[0045] In this embodiment, the seven burner straight tubes 5 are distributed as follows: one is set at the center of the burner upper plate 2, and six are evenly distributed in the circumferential direction with the center of the burner upper plate 2 as the center of the circle.

[0046] The secondary nozzle 9 is provided with a secondary nozzle thread 92 for detachably fixing to the nozzle inner core 4 .

[0047] The burner upper plate 2 is a stepped circular ring, the outer surface of the upper stepped circular ring is coaxially fixed to the inner surface of the combustion chamber 1 , and the lower stepped circular ring is fixed to the support frame 3 .

[0048] For further explanation of the present invention, see Figure 2 , the fastener comprises a fastening bolt 6 and a fastening nut 7;

[0049] The other end of the burner straight tube 5 is coaxially fixed to the fastening bolt 6 , and the fastening bolt 6 is threadedly connected to the fastening nut 7 .

[0050] The method of “the other end of the burner straight tube 5 is coaxially fixed with the fastening bolt 6” is preferably welding fixation.

[0051] In the present invention, when the fastening nut 7 is not tightened, the nozzle core 4 can move up and down along the combustion chamber straight pipe 5 in the axial direction, so that the retraction distance can be adjusted; when the fastening nut 7 is tightened, the nozzle core 4 cannot move.

[0052] For further explanation of the present invention, see Figure 2 The outer surface of one end of the nozzle inner core 4 is threadedly connected to the swirler 10, and the swirler 10 is provided with a plurality of blades.

[0053] There are 7 swirlers 10, and the angle between the blades of the swirler 10 and the axial direction of the combustion chamber 1 is preferably 45°.

[0054] The combustion device includes 7 swirlers 10 and 7 secondary nozzles 9, and the flow rate of each secondary nozzle 9 is individually controlled, so the influence of different equivalence ratios, different propellant spatial distributions, different swirler 10 flow rates, and different secondary nozzle 9 flow rates on thermoacoustic oscillations can be studied.

[0055] As a further explanation of the present invention, a honeycomb 11 is installed between the outer surface of the nozzle inner core 4 and the inner surface of the burner straight tube 5, and the honeycomb 11 is used to increase the smoothness of the premixed gas intake.

[0056] Among them, the honeycomb devices 11 are correspondingly provided in 7 numbers.

[0057] For further explanation of the present invention, see Figure 2 and Figure 4 A plurality of spray holes 91 are evenly and axially formed on the upper surface of the secondary nozzle 9 , and the spray holes 91 are used to spray the gas source into the combustion chamber 1 .

[0058] Among them, a plurality of secondary nozzle spray holes 91 are evenly distributed in the circumferential direction inside the secondary nozzle 9, and the angle between the direction of the secondary nozzle spray holes 91 and the axial direction of the combustion chamber 1 can be 30°, 45° and 60°. The number of the secondary nozzle spray holes 91 is not specifically limited, and any number is acceptable, but in the present embodiment, 8 are preferred.

[0059] For further explanation of the present invention, see Figure 3 An igniter hole 22 is provided on the burner upper plate 2, and the igniter hole 22 is used for an external igniter for test ignition.

[0060] For further explanation of the present invention, see Figure 3 A pressure sensor mounting hole 23 is provided on the burner upper plate 2, and the pressure sensor mounting hole 23 is used for connecting an external high-frequency pressure sensor to measure the pressure pulsation signal during the test.

[0061] For further explanation of the present invention, see Figure 5 The burner straight tube 5 is provided with a plurality of burner straight tube air inlet holes 51 along its circumferential direction, and the burner straight tube air inlet holes 51 are used to allow the premixed gas to flow into the burner straight tube 5 .

[0062] There are eight air inlet holes 51 evenly arranged along the circumferential direction of the burner straight tube 5 .

[0063] For further explanation of the present invention, see Figure 6-Figure 8 The diverter ring mechanism includes at least two connected diverter rings, which are coaxially fixed with the diverter ring nut 15, and the diverter ring nut 15 is threadedly connected to the outer surface of the burner straight pipe 5. The bottom diverter ring is externally connected to a diverter ring joint 16, and the top diverter ring covers the burner straight pipe air inlet hole 51, and the diverter ring joint 16 is used to connect the premixed gas source.

[0064] In this embodiment, the number of the diverter rings is preferably three, namely a first diverter ring 14, a second diverter ring 13 and a third diverter ring 12;

[0065] The first diverter ring 14, the second diverter ring 13 and the third diverter ring 12 are coaxially arranged and coaxially fixed with the diverter ring nut 15. Specifically:

[0066] The first splitter ring 14 is provided with a first air inlet 141, a first positioning hole 142, a first radial sealing groove 143 and a first axial sealing groove 144;

[0067] The second flow dividing ring 13 is provided with a first air outlet hole 131, a second positioning hole 132, a second air inlet hole 133 and a second radial sealing groove 134;

[0068] The third flow dividing ring 12 is provided with a third air inlet hole 121 and a third positioning hole 122;

[0069] The splitter ring joint 16 is connected to the first splitter ring 14, and the premixed gas source enters the first splitter ring 14 through the splitter ring joint 16, flows into the second splitter ring 13 through the first air inlet 141 and the second air inlet hole 133, and then flows into the third splitter ring 12 through the first air outlet 131 and the third air inlet hole 121, so that the premixed gas flows into the burner straight pipe 5 through the burner straight pipe air inlet hole 51;

[0070] The third diverter ring 12 covers the burner straight pipe air inlet hole 51, the first positioning hole 142, the second positioning hole 132, and the third positioning hole 122 are coaxially arranged, and the first radial sealing groove 143, the first axial sealing groove 144 and the second radial sealing groove 134 are used for sealing connection with the burner straight pipe 5.

[0071] As a further explanation of the present invention, the other end of the nozzle inner core 4 is detachably fixed to the nozzle inner core joint 8, and the nozzle inner core joint 8 is connected to an external air source.

[0072] The nozzle core joint 8 is connected to an external gas source, the interior of the nozzle core 4 is a gas source flow channel, and then the gas enters the combustion chamber 1 through the secondary nozzle spray hole 91.

[0073] Among them, the first diverter ring 14, the second diverter ring 13, the third diverter ring 12, the diverter ring nut 15, the diverter ring joint 16 and the nozzle core joint 8 are consistent in number with the nozzle core 4 and the burner straight pipe 5 and are installed in corresponding positions.

[0074] The present invention adopts a combination of a diverter ring and a honeycomb 11, which can make the mixing, air intake and axial velocity of the premixed gas more uniform and stable. The premixed gas enters the first diverter ring 14, and enters the second diverter ring 13 from the two first air inlets 141 on the circumference of the first diverter ring 14; after the premixed gas enters the second diverter ring 13, it enters the third diverter ring 12 from the four second air inlet holes 133 on the circumference of the diverter ring, and then enters the burner straight tube 5 through 8 burner straight tube air inlet holes 51 evenly distributed on the circumference. This design can ensure that the premixed gas can enter the burner straight tube 5 more evenly, and the presence of the honeycomb 11 in the burner straight tube 5 can make the premixed gas obtain a uniform axial velocity distribution.

[0075] The present invention can realize active control of thermoacoustic oscillations in three forms. First, the premixed gas enters the combustion chamber 1 to produce tangential combustion instability. The first way is to spray 1% of the total flow of premixed gas into the combustion chamber 1 through the secondary nozzle 9. Methane and hydrogen realize active control of thermoacoustic oscillations; the second way is to remove the secondary nozzle 9 and directly spray 1% of the total flow of premixed gas into the combustion chamber from the nozzle core 4 to realize active control of thermoacoustic oscillations. The working principle of these two methods is: breaking the strong coupling relationship between the pressure pulsation and the heat release rate of the combustion chamber by adding an injection device. Specifically, the area where the secondary nozzle 9 and the nozzle core 4 are sprayed is located at the head of the combustion chamber 1. This area is considered to be the most likely location for strong coupling between pressure and heat release; secondly, the heat release rate of the combustion chamber 1 is related to the spatiotemporal distribution of the flame structure, and the flame structure is strongly dependent on the flow conditions at the inlet of the combustion chamber 1, which means that any slight change may produce heat release that is out of phase with the pressure oscillation, thereby realizing active control of thermoacoustic oscillations. The combustion chamber 1 has seven secondary nozzles 9 distributed in the center and on the circumference. The third method is to increase the flow rate of a secondary nozzle 9 on the circumference to act as an artificial baffle to reduce the pressure amplitude of the thermoacoustic oscillation. In engineering, baffles are used to suppress thermoacoustic oscillations. When thermoacoustic oscillations occur, the pressure wave rotates along the combustion chamber. The baffle can block the propagation of the pressure wave and thus suppress the combustion oscillation. Therefore, the third method of the present invention adjusts the flow rate of a single secondary nozzle 9. The secondary nozzle 9 produces a greater axial velocity and a higher flame structure, which is similar to an artificial baffle, thereby reducing the degree of thermoacoustic oscillation. The test results show that the first two methods can suppress thermoacoustic oscillations, and the third method can reduce thermoacoustic oscillations. Therefore, the present invention can achieve active control of thermoacoustic oscillations in three forms.

[0076] The present invention can conduct parametric research on active control of thermoacoustic oscillations, as described above, and will not be elaborated here.

[0077] The active control system of the present invention has a simple structure, is easy to operate and has good reliability. The implementation forms of the above three methods do not require high-precision, fast-response control valves, but only require a simple gas mass flow controller. The specific implementation method is: when thermoacoustic oscillations appear in the combustion chamber, the gas mass flow controller of the secondary nozzle 9, the nozzle core 4 or a single nozzle pipeline on the circumference is adjusted, and the thermoacoustic oscillation can be suppressed or weakened by inputting a changed flow rate. Therefore, the active control system has good effect, high reliability and is very simple, which is convenient for engineering implementation.

[0078] In the description of the present invention, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings, which are only for the convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0079] In addition, it should be noted that in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0080] The term "comprise" or any other similar term is intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus / device that includes a list of elements includes not only those elements but also other elements not expressly listed, or also includes elements inherent to such process, method, article, or apparatus / device.

[0081] So far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is easy for those skilled in the art to understand that the protection scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

Claims

1. An annular combustion device for studying thermoacoustic oscillation and its active control, characterized in that: It comprises a combustion chamber (1), a burner upper plate (2), a support frame (3), a nozzle inner core (4), a burner straight pipe (5), a secondary nozzle (9), a swirler (10) and a honeycomb (11); The combustion chamber (1) is coaxially fixed to the burner upper plate (2), the burner upper plate (2) and the support frame (3) are coaxially fixed, the support frame (3) is fixed to the external optical platform, one end of a plurality of annular arrays of burner straight tubes (5) are mounted on the burner upper plate (2), and the other end of the burner straight tube (5) is detachably fixedly connected to a fastener; A nozzle core (4) is coaxially arranged inside the burner straight tube (5) and is movable along the nozzle core (4); the inner surface of one end of the nozzle core (4) is detachably fixedly connected to a secondary nozzle (9); the secondary nozzle (9) is used to spray an air source flowing through the nozzle core (4); and the other end of the nozzle core (4) is connected to an external air source; The burner straight pipe (5) is in sealed communication with a diverter ring mechanism, and the diverter ring mechanism is used to introduce premixed gas; The outer surface of one end of the nozzle inner core (4) is threadedly connected to the swirler (10), and the swirler (10) is provided with a plurality of blades. A honeycomb (11) is installed between the outer surface of the nozzle inner core (4) and the inner surface of the burner straight pipe (5), and the honeycomb (11) is used to increase the smoothness of the premixed gas intake.

2. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: The fastener comprises a fastening bolt (6) and a fastening nut (7); The other end of the burner straight tube (5) is coaxially fixed to the fastening bolt (6), and the fastening bolt (6) is threadedly connected to the fastening nut (7).

3. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: A plurality of spray holes (91) are evenly and axially formed on the upper surface of the secondary nozzle (9), and the spray holes (91) are used to spray a gas source into the combustion chamber (1).

4. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: An igniter hole (22) is provided on the burner upper plate (2), and the igniter hole (22) is used for an external igniter.

5. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: A pressure sensor mounting hole (23) is provided on the burner upper plate (2), and the pressure sensor mounting hole (23) is used for externally connecting a high-frequency pressure sensor.

6. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: The burner straight tube (5) is provided with a plurality of burner straight tube air inlet holes (51) along its circumferential direction, and the burner straight tube air inlet holes (51) are used to allow the premixed gas to flow into the burner straight tube (5).

7. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 6, characterized in that: The diverter ring mechanism comprises at least three connected diverter rings, wherein the diverter rings are coaxially fixed to the diverter ring nuts (15), the diverter ring nuts (15) are threadedly connected to the outer surface of the burner straight pipe (5), the bottom diverter ring is externally connected to a diverter ring joint (16), the top diverter ring covers the burner straight pipe air inlet hole (51), and the diverter ring joint (16) is used to connect to a premixed gas source.

8. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: The other end of the nozzle inner core (4) is detachably fixed to the nozzle inner core joint (8), and the nozzle inner core joint (8) is connected to an external air source.

9. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: A plurality of the burner straight tubes (5) are evenly arranged at the center of the burner upper plate (2) and in the circumferential direction of the burner upper plate (2).

10. The annular combustion device for studying thermoacoustic oscillation and its active control according to claim 1, characterized in that: The combustion chamber (1) is a quartz glass combustion chamber.

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