Four-claw anti-vibration ring device, combustion chamber and gas turbine

Abstract

The invention provides a four-claw anti-vibration ring device, a combustion chamber and a gas turbine, the four-claw anti-vibration ring device is used for the rectangular combustion chamber, the combustion chamber comprises a rotational flow shell, a center body, a swirler and a flame tube, the center body and the swirler are arranged in the rotational flow shell, and under the action of the swirler, a rotational flow flowing ring cavity channel is formed in the inner side of the rotational flow shell; the four-claw anti-vibration ring device is used for communicating a rotational flow flowing ring cavity channel with a flame tube, and comprises a connecting ring, a rotating shaft, a rotating shaft and a rotating shaft, one end of the anti-vibration ring is connected with the connecting ring, and the other end of the anti-vibration ring makes contact with the inner wall of the flame tube so as to eliminate the angular vortex area of the rectangular combustion chamber. According to the four-claw anti-vibration ring device, the combustion chamber and the gas turbine, angular vortexes in the combustion chamber can be eliminated, then heat release pulsation in the combustion chamber is weakened, and combustion oscillation is regulated and controlled.

Description

Technical Field

[0001] The present invention relates to the technical field of combustion chambers, and in particular to a four-claw anti-vibration ring device, a combustion chamber and a gas turbine. Background Art

[0002] Gas turbines are one of the important equipment in today's energy and power field, and are widely used in aviation, navigation and power generation industries. Among them, the gas turbine combustion chamber is the core component and power source of the entire gas turbine. However, with increasingly stringent pollutant emission requirements, in order to reduce pollutant emissions mainly composed of nitrogen oxides (NOx), advanced gas turbine combustion chambers mostly use lean oil premixed combustion technology. The combustion chamber often operates in a working state close to flameout, which is very sensitive to external disturbances and easily affected by external disturbances, resulting in heat release rate pulsation. When the heat release rate pulsation in the burner is coupled with the acoustics of the combustion system, it is easy to cause large heat release rate pulsation and pressure pulsation. The large pressure pulsation and heat release pulsation in the combustion chamber may cause structural damage to the combustion chamber, which may affect the stable operation and safe operation of the combustion chamber and even the gas turbine system. Therefore, overcoming combustion oscillation is an urgent problem to be solved.

[0003] like Figure 1 As shown, the rectangular combustion chamber in the prior art generally includes a swirl shell 10, a center body 20, a swirler 30 and a flame tube 40, wherein the center body 20 and the swirler 30 are arranged in the swirl shell 10, and a swirl flow annular cavity channel 50 is formed on the inner side of the swirl shell 10, and the end wall 60 of the flame tube 40 facing the swirl shell 10 is a flat plate, which may cause the problem of combustion oscillation. In order to solve the problem of combustion oscillation in the combustion chamber of a gas turbine, it is generally divided into active control and passive control. Active control is to use a special signal monitor to monitor the pressure pulsation or heat release pulsation in the combustion chamber, and according to the pressure pulsation and other signals monitored in the combustion chamber, a suitable external excitation (to the inlet air or fuel supply, etc.) is applied through the corresponding actuator to suppress or eliminate the coupling between the heat release rate pulsation and the pressure oscillation (sound wave). However, this type of method requires an additional control system and an actuator, and has high requirements for the control algorithm, which will increase additional costs and has limited applicable scenarios.

[0004] Passive control refers to adding certain fixed devices to the combustion system to suppress or eliminate combustion oscillations. Common types of acoustic components, such as Helmholtz resonators, can suppress combustion oscillations of specific frequencies. The disadvantage is that they are large in size, are only effective for specific frequencies, and require a lot of experiments and debugging. Summary of the invention

[0005] The invention provides a four-claw anti-vibration ring device, a combustion chamber and a gas turbine to overcome the problems in the prior art.

[0006] The present invention provides a four-claw anti-vibration ring device for a rectangular combustion chamber, wherein the rectangular combustion chamber comprises a swirl shell, a center body, a swirler and a flame tube, wherein the center body and the swirler are arranged in the swirl shell, and under the action of the swirler, a swirl flow annular cavity channel is formed on the inner side of the swirl shell, and the swirl flow annular cavity channel is connected with the flame tube; the four-claw anti-vibration ring device is used to connect the swirl flow annular cavity channel and the flame tube, and the four-claw anti-vibration ring device comprises: A connecting ring connected to the cyclone housing; An anti-vibration ring has one end connected to the connecting ring and the other end in contact with the inner wall of the flame tube to eliminate the corner vortex area of ​​the rectangular combustion chamber.

[0007] According to a four-claw anti-vibration ring device provided by the present invention, the central section of the anti-vibration ring adopts a linear expansion form, wherein the expansion angle is α; the axial length of the central section of the anti-vibration ring is L1, and the height of the central section of the anti-vibration ring is h, then , , H and W are the height and width of the flame tube respectively; r is the inner diameter length of the connecting ring; the total length of the expansion section of the anti-vibration ring is L2, ; Among them, 0≤α≤90°, 1≤H / r≤3; 1≤W / r≤3.

[0008] According to a four-claw anti-vibration ring device provided by the present invention, the central section of the anti-vibration ring adopts a curve expansion form, and the central curve is constructed by a reverse Witosinski curve. ,in, is the outlet radius of the curved surface, is the entrance radius of the curved surface, and , L is , where L2 is related to the flame tube height H and the flame tube width W, and satisfies the corresponding relationship: .

[0009] According to a four-claw anti-vibration ring device provided by the present invention, the central section of the anti-vibration ring adopts a curve expansion form, and the central curve is constructed using a bicubic curve.

[0010] According to a four-claw anti-vibration ring device provided by the present invention, the distance from the starting point of the anti-vibration ring to the outlet of the swirl ring cavity channel is P, and 0≤P / L1≤0.5.

[0011] According to a four-claw anti-vibration ring device provided by the present invention, the anti-vibration ring has a tip structure, and the tip structure is located at the corner of the flame tube.

[0012] According to a four-claw anti-vibration ring device provided by the present invention, the anti-vibration ring is a symmetrical structure.

[0013] The present invention also provides a combustion chamber, comprising a swirl shell, a center body, a swirler, a flame tube and the four-claw anti-vibration ring device as described above, wherein the center body and the swirler are arranged in the swirl shell, and under the action of the swirler, a swirl flow annular channel is formed on the inner side of the swirl shell, and the swirl flow annular channel is connected to the flame tube, and the four-claw anti-vibration ring device is used to connect the swirl flow annular channel and the flame tube.

[0014] The present invention also provides a gas turbine, comprising the four-claw anti-vibration ring device as described above or the combustion chamber as described above.

[0015] The present invention also provides a gas turbine, comprising the four-claw anti-vibration ring device as described above or the combustion chamber as described above.

[0016] According to a gas turbine provided by the present invention, the gas turbine includes an aircraft engine or a gas turbine.

[0017] The four-claw anti-vibration ring device provided by the present invention is used for a rectangular combustion chamber, the combustion chamber includes a swirl shell, a center body, a swirler and a flame tube, the center body and the swirler are arranged in the swirl shell, under the action of the swirler, a swirl flow annular cavity channel is formed on the inner side of the swirl shell, and the swirl flow annular cavity channel is connected with the flame tube; used to connect the swirl flow annular cavity channel and the flame tube, the four-claw anti-vibration ring device includes a connecting ring and an anti-vibration ring, the connecting ring is connected to the swirler shell, one end of the anti-vibration ring is connected to the connecting ring, and the other end contacts the inner wall of the flame tube to eliminate the corner vortex area of ​​the rectangular combustion chamber, thereby realizing the regulation of combustion oscillation and enhancing the flame stabilization capability.

[0018] The combustion chamber and gas turbine provided by the present invention have the various advantages as described above because they include the four-claw anti-vibration ring device as described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 It is a structural schematic diagram of a combustion chamber in the prior art.

[0021] Figure 2 It is a structural schematic diagram of the four-claw anti-vibration ring device provided by the present invention installed in the combustion chamber.

[0022] Figure 3It is a structural schematic diagram of a linear expansion embodiment of a four-claw anti-vibration ring device provided by the present invention.

[0023] Figure 4 It is a side view of a linear expansion embodiment of the four-claw anti-vibration ring device provided by the present invention.

[0024] Figure 5 It is a rear view of a linear expansion embodiment of the four-claw anti-vibration ring device provided by the present invention.

[0025] Figure 6 It is a structural schematic diagram of a curve expansion embodiment of a four-claw anti-vibration ring device provided by the present invention.

[0026] Figure 7 It is a side view of a curved expansion embodiment of a four-claw anti-vibration ring device provided by the present invention.

[0027] Figure 8 It is a rear view of a curved expansion embodiment of a four-claw anti-vibration ring device provided by the present invention.

[0028] Fig. 9 It is a side view of the connection between the anti-vibration ring and the cyclone housing provided by the present invention.

[0029] Reference numerals: 1. Swirl shell; 2. Center body; 3. Swirl device; 4. Flame tube; 5. Swirl flow annular cavity channel; 6. Anti-vibration ring device; 61. Connecting ring; 62. Anti-vibration ring. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0031] In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limitations on the embodiments of 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.

[0032] Combine the following Figure 2-9 The four-claw anti-vibration ring device provided by the present invention is described, which is used for a rectangular combustion chamber. The combustion chamber includes a swirl shell 1, a center body 2, a swirler 3 and a flame tube 4. The center body 2 and the swirler 3 are arranged in the swirl shell 1. Under the action of the swirler 3, a swirl flow annular cavity channel 5 is formed on the inner side of the swirl shell 1. The four-claw anti-vibration ring device 6 is used to connect the swirl flow annular cavity channel 5 and the flame tube 4.

[0033] The four-claw anti-vibration ring device 6 is arranged on the end wall of the flame tube 4 close to the swirl flow annular channel 5, and includes a connecting ring 61 and an anti-vibration ring 62. The connecting ring 61 is connected to the swirl outer shell 1. One end of the anti-vibration ring 62 is connected to the connecting ring 61, and the other end is in contact with the inner wall of the flame tube 4. The setting of the anti-vibration ring 62 can completely eliminate the angular vortex area of ​​heat release pulsation in the combustion chamber, thereby realizing the regulation of combustion oscillation and enhancing the flame stabilization ability.

[0034] like Figure 3 , Figure 4 and Figure 5 As shown, in a feasible embodiment of the present invention, the central section of the anti-vibration ring 62 adopts a linear expansion form, wherein the expansion angle is α; the axial length of the central section of the anti-vibration ring is L1, and the height of the central section of the anti-vibration ring is h, then , , H and W are the height and width of the flame tube respectively; r is the inner diameter length of the connecting ring; the total length of the expansion section of the anti-vibration ring is L2, ; Among them, 0≤α≤90°, 1≤H / r≤3; 1≤W / r≤3.

[0035] like Figure 6 , Figure 7 and Figure 8 As shown, in a feasible embodiment of the present invention, the central cross section of the vibration-proof ring 62 adopts a curve expansion form, and the central curve is constructed by adopting a reverse Witosinski curve. ,in, is the outlet radius of the curved surface, is the entrance radius of the curved surface, and , L is , where L2 size is related to the flame tube height and the width of the flame tube Related, and satisfy the corresponding relationship: .

[0036] in, The dimensions are related to the swirl flow at the head of the combustion chamber. Different sizes are used for different flame tube structures. In a feasible embodiment of the present invention, the central cross-section of the anti-vibration ring 62 adopts a curve expansion form, and the central curve is constructed using a bicubic curve and has the same size relationship.

[0037] The present invention achieves complete elimination of corner vortices in the combustion chamber by providing an anti-vibration ring 62 with a protruding tip and combining anti-vibration rings 62 with different central profile curve forms, thereby weakening heat release pulsation in the combustion chamber and achieving the purpose of regulating and weakening combustion oscillations.

[0038] like Fig. 9 As shown, the starting point of the anti-vibration ring 62 can be the outlet of the cyclone and develop downstream, or it can be a starting point at a certain distance upstream of the outlet and then develop downstream to form a four-claw anti-vibration ring device that completely eliminates the corner vortex. In a feasible embodiment of the present invention, the distance from the starting point of the anti-vibration ring 62 to the outlet of the swirl annular cavity channel 5 is P, and 0≤P / L1≤0.5. By adjusting the relative position of the head of the swirl shell 1 and the end wall structure of the anti-vibration ring 62, the flame stabilization ability is further enhanced and the combustion oscillation is weakened.

[0039] In a feasible embodiment of the present invention, the anti-vibration ring 62 has a tip structure, and the tip structure is located at the corner of the flame tube 4, which further weakens the heat release pulsation in the combustion chamber and changes the swirl flow in the swirl flow annular channel 5, thereby achieving the purpose of regulating the combustion oscillation in the combustion chamber.

[0040] In a feasible embodiment of the present invention, the anti-vibration ring 62 is a symmetrical structure to adapt to a rectangular combustion chamber.

[0041] The second aspect of the present invention provides a combustion chamber, including a swirl shell 1, a center body 2, a swirler 3, a flame tube 4 and the above-mentioned four-claw anti-vibration ring device 6, the center body 2 and the swirler 3 are arranged in the swirl shell 1, under the action of the swirler 3, a swirl flow annular channel 5 is formed on the inner side of the swirl shell 1, and the swirl flow annular channel 5 is connected to the flame tube 4, and the four-claw anti-vibration ring device 6 is arranged on the end wall of the flame tube 4 close to the center body.

[0042] A third aspect of the present invention provides a gas turbine, comprising the four-claw anti-vibration ring device 6 as described above or the combustion chamber as described above.

[0043] According to the gas turbine provided by the present invention, the gas turbine includes an aircraft engine or a gas turbine. Since it includes the four-claw anti-vibration ring device as described above, it can also completely eliminate the corner vortex in the combustion chamber, thereby weakening the heat release pulsation in the combustion chamber and realizing the regulation of combustion oscillations.

[0044] In summary, the present invention provides a four-claw anti-vibration ring device, a combustion chamber and a gas turbine. By arranging an anti-vibration ring 62 with a tip structure in different curved surface forms upstream of the combustion chamber, the angular vortex structure in the rectangular combustion chamber can be completely eliminated, and the heat release pulsation in the combustion chamber can be weakened, thereby achieving the purpose of weakening the combustion oscillation. Moreover, the structure does not increase the structure and weight of the combustion chamber, and can even reduce the local weight of the combustion chamber, while weakening the combustion oscillation in the combustion chamber.

[0045] In the description of the embodiments of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" 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 an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.

[0046] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "mode", "specific mode", or "some modes" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or mode are included in at least one embodiment or mode of the embodiment of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or mode. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or modes in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or modes described in this specification and the features of the different embodiments or modes, without contradiction.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A four-claw anti-vibration ring device, characterized in that: Used in a rectangular combustion chamber, the rectangular combustion chamber comprising a swirl shell (1), a center body (2), a swirler (3) and a flame tube (4), the center body (2) and the swirler (3) being arranged in the swirl shell (1), and under the action of the swirler (3), a swirl flow annular cavity channel (5) is formed on the inner side of the swirl shell (1); The four-claw anti-vibration ring device (6) is used to connect the swirl flow annular cavity channel (5) and the flame tube (4), and the four-claw anti-vibration ring device (6) comprises: A connecting ring (61) connected to the cyclone housing (1); An anti-vibration ring (62) has one end connected to the connection ring (61) and the other end in contact with the inner wall of the flame tube (4) to eliminate the corner vortex area of ​​the rectangular combustion chamber.

2. The four-claw anti-vibration ring device according to claim 1, characterized in that: The center section of the anti-vibration ring (62) adopts a linear expansion form, wherein the expansion angle is α; the axial length of the center section of the anti-vibration ring is L1, and the height of the center section of the anti-vibration ring is h, then , , H and W are the height and width of the flame tube respectively; r is the inner diameter length of the connecting ring; the total length of the expansion section of the anti-vibration ring is L2, ; Among them, 0≤α≤90°, 1≤H / r≤3; 1≤W / r≤3.

3. The four-claw anti-vibration ring device according to claim 1, characterized in that: The central cross section of the anti-vibration ring (62) adopts a curve expansion form, and the central curve is constructed by adopting a reverse Witosinski curve. ,in, is the outlet radius of the curved surface, is the entrance radius of the curved surface, and , L is , where L2 is related to the flame tube height H and the flame tube width W, and satisfies the corresponding relationship: 。 4. The four-claw anti-vibration ring device according to claim 1, characterized in that: The central cross section of the anti-vibration ring (62) adopts a curve expansion form, and the central curve is constructed using a bicubic curve.

5. The four-claw anti-vibration ring device according to claim 1, characterized in that: The distance from the starting point of the anti-vibration ring (62) to the outlet of the swirl annular cavity channel (5) is P, and 0≤P / L1≤0.

5.

6. The four-claw anti-vibration ring device according to any one of claims 1 to 5, characterized in that: The anti-vibration ring (62) has a tip structure, and the tip structure is located at a corner of the flame tube (4).

7. The four-claw anti-vibration ring device according to claim 6, characterized in that: The anti-vibration ring (62) has a symmetrical structure.

8. A combustion chamber, characterized in that: The invention comprises a swirl shell (1), a center body (2), a swirler (3), a flame tube (4) and a four-claw anti-vibration ring device (6) as claimed in any one of claims 1 to 7, wherein the center body (2) and the swirler (3) are arranged in the swirl shell (1), and under the action of the swirler (3), a swirl flow annular cavity channel (5) is formed on the inner side of the swirl shell (1), and the swirl flow annular cavity channel (5) is connected with the flame tube (4), and the four-claw anti-vibration ring device (6) is used to connect the swirl flow annular cavity channel (5) and the flame tube (4).

9. A gas turbine, characterized in that: It comprises a four-claw anti-vibration ring device (6) as claimed in any one of claims 1 to 7 or a combustion chamber as claimed in claim 8.

10. The gas turbine according to claim 9, characterized in that The gas turbine includes an aircraft engine or a gas turbine.

Images