Gas turbine and sealing ring and sealing structure thereof

Abstract

The utility model discloses a gas turbine and a sealing ring and a sealing structure thereof, and relates to the technical field of gas turbines. The sealing ring comprises a first sealing edge and a second sealing edge which are connected in sequence; strip-shaped grooves in one-to-one correspondence with the bolts are formed in the second sealing edge; the first sealing edge is matched with the inserting groove; and the strip-shaped grooves are matched with the corresponding bolts. After the sealing ring is heated and expanded, the stress generated on the bolt is small, and the bolt is difficult to crack due to the small stress. In other words, the probability of unreliable sealing between the flame tube and the turbine guider due to thermal expansion can be reduced. The sealing ring and the flame tube are connected in an inserted mode to form sealed connection, that is, even if the flame tube vibrates, the sealing performance between the sealing ring and the flame tube is not prone to being affected, and the sealing reliability between the turbine guider and the flame tube can be improved.

Description

Technical Field

[0001] This application relates to the technical field of gas turbines, and particularly to a gas turbine, its sealing ring, and sealing structure. Background Art

[0002] In a gas turbine, the sealing at the tail of the combustion chamber is crucial for the gas turbine, and the quality of the sealing will directly affect the overall working efficiency of the gas turbine. In the prior art, as Figure 4 shown, the key point of the sealing at the tail of the combustion chamber of a certain type of gas turbine is to set a sealing ring between the combustion chamber and the turbine guide vane, and the sealing ring is fixed to the combustion chamber and the turbine guide vane respectively by bolts. However, the above sealing structure is not reliable, and there are at least two reasons: First, since the sealing ring is a hot-end component, if the sealing ring expands due to heat, and the thermal deformations of the sealing ring and the turbine guide vane or the combustion chamber are not coordinated, it will inevitably cause stress on the corresponding bolts. Second, since the combustion chamber is a cantilever structure, the connection between the combustion chamber and the sealing ring is easily affected by vibration. If the corresponding combustion chamber of the gas turbine is a low-emission combustion chamber, because the low-emission combustion chamber is more likely to have oscillating combustion phenomenon, the vibration between the combustion chamber and the sealing ring will be aggravated. That is to say, the above problems of uncoordinated thermal deformation and vibration may cause cracks in the bolts. When the cracks expand to a certain extent, the sealing ring will lose its sealing function. Utility Model Content

[0003] The purpose of this application is to provide a gas turbine, its sealing ring, and sealing structure to solve the technical problem of unreliable sealing between the combustion chamber and the turbine guide vane of the gas turbine in the prior art.

[0004] To achieve the above purpose, this application provides the following technical solutions:

[0005] In a first aspect, this application proposes a technical solution for a sealing ring of a gas turbine. The gas turbine includes a combustion chamber and a turbine guide vane; the sealing ring is arranged between the combustion chamber and the turbine guide vane; the sealing ring is connected to the turbine guide vane by a plurality of bolts, and the combustion chamber is provided with a plugging groove; the sealing ring includes a first sealing edge and a second sealing edge connected in sequence; strip-shaped grooves corresponding to the bolts one by one are opened on the second sealing edge; the first sealing edge is adapted to the plugging groove; and the strip-shaped grooves are adapted to the corresponding bolts.

[0006] As a specific solution in the technical solution of this application, the inner diameter of the first sealing edge decreases in a first direction; the first direction is parallel to the axial direction of the sealing ring and points from the first sealing edge to the second sealing edge.

[0007] As a specific solution in the technical solution of the present application, after the first sealing edge is inserted into the insertion slot, the insertion slot still has an insertion allowance along the extension direction of the first sealing edge.

[0008] As a specific solution in the technical solution of the present application, the length direction of the strip-shaped groove is parallel to the radial direction of the second sealing edge, and the length of the strip-shaped groove is 2 to 4 times the diameter of the corresponding bolt.

[0009] In a second aspect, the present application provides a technical solution for a sealing structure of a gas turbine, and the sealing structure includes:

[0010] A combustion chamber liner; the combustion chamber liner is provided with an insertion slot;

[0011] A turbine guide vane;

[0012] A sealing ring of the gas turbine as described in any one of the first aspects.

[0013] As a specific solution in the technical solution of the present application, the combustion chamber liner further includes a diversion pipe, a first end of the diversion pipe is located inside the combustion chamber liner, and a second end of the diversion pipe extends into the turbine guide vane.

[0014] As a specific solution in the technical solution of the present application, the inner diameter of the diversion pipe decreases along a first direction.

[0015] As a specific solution in the technical solution of the present application, the combustion chamber liner is further provided with a guiding portion, and a cross-section of the guiding portion is in a flared shape.

[0016] As a specific solution in the technical solution of the present application, the spacing of the insertion slots increases along a first direction, and the maximum spacing is less than or equal to the thickness of the first sealing edge.

[0017] In a third aspect, the present application provides a technical solution for a gas turbine, and the gas turbine includes a sealing ring of the gas turbine as described in any one of the first aspects, and / or includes a sealing structure of the gas turbine as described in any one of the second aspects.

[0018] Compared with the prior art, the beneficial effects of the present application are:

[0019] The sealing ring in the present application generates less stress on the bolts after thermal expansion, and the small stress is difficult to cause cracks in the bolts. That is to say, the present application can reduce the probability of unreliable sealing between the combustion chamber liner and the turbine guide vane due to thermal expansion. And the sealing ring in the present application is inserted into the combustion chamber liner to form a sealed connection. That is to say, in the present application, even if the combustion chamber liner vibrates, it is difficult to affect the sealing performance between the sealing ring and the combustion chamber liner, that is, the sealing reliability between the turbine guide vane and the combustion chamber liner can be improved. Brief Description of the Drawings

[0020] Figure 1 FIG. 5 is a three-dimensional schematic diagram of a seal ring proposed in an embodiment of the present application;

[0021] Figure 2 is Figure 1 the front view of the seal ring in FIG. 5;

[0022] Figure 3 FIG. 15 is a side sectional view of another seal ring proposed in an embodiment of the present application;

[0023] Figure 4 is a sectional view of a sealing structure in the prior art;

[0024] Figure 5 FIG. 23 is a sectional view of a sealing structure proposed in an embodiment of the present application;

[0025] Figure 6 FIG. 27 is a sectional view of another sealing structure proposed in an embodiment of the present application;

[0026] Figure 7 is Figure 6 an enlarged view of part C in FIG. 32;

[0027] Figure 8 is Figure 6 an enlarged view of part D in FIG. 38.

[0028] In the figures: 1, combustion chamber; 11, insertion slot; 12, diversion pipe; 13, guiding part; 2, turbine guide vane; 3, seal ring; 31, first sealing edge; 32, second sealing edge; 33, strip-shaped groove. Detailed Embodiments

[0029] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the protection scope of the present application.

[0030] It should be noted that in the description of the present application, the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present application.

[0031] In addition, it should be understood that for ease of description, the dimensions of the various components shown in the drawings are not drawn in actual proportional relationships. For example, the thickness or width of some layers may be exaggerated relative to other layers.

[0032] It should be noted that similar reference numerals and letters represent similar items in the following drawings. Therefore, once an item is defined or described in one drawing, it will not be necessary to further specifically discuss and describe it in the descriptions of subsequent drawings.

[0033] To solve the technical problem of unreliable sealing of the existing sealing ring in the background art, the present application proposes a sealing ring 3 for a gas turbine. Specifically, in this embodiment, the gas turbine includes a combustion chamber 1 and a turbine guide vane 2. The sealing ring 3 is disposed between the combustion chamber 1 and the turbine guide vane 2, and the sealing ring 3 is connected to the turbine guide vane 2 by a plurality of bolts. The combustion chamber 1 is further provided with a socket groove 11. The sealing ring 3 includes a first sealing edge 31 and a second sealing edge 32 connected in sequence. A strip-shaped groove 33 corresponding to each bolt is formed on the second sealing edge 32. The first sealing edge 31 is adapted to the socket groove 11, and the strip-shaped groove 33 is adapted to the corresponding bolt.

[0034] It should be clear that when this embodiment is in use, as Figure 5 and Figure 6 shown, the first sealing edge 31 is inserted into the socket groove 11. The first sealing edge 31 being adapted to the socket groove 11 means that, as Figure 7 shown, after the first sealing edge 31 is inserted into the socket groove 11, the socket groove 11 still has a certain insertion margin along the extension direction of the first sealing edge 31 (i.e., the direction B as Figure 7 shown). That is to say, if the first sealing edge 31 expands due to heat, the first sealing edge 31 can freely expand along its extension direction. If the first sealing edge 31 can freely expand along its extension direction, then the first sealing edge 31 (i.e., the sealing ring 3) will not form a large stress with the combustion chamber 1, that is, the sealed connection between the sealing ring 3 and the combustion chamber 1 will not be damaged. It is easy to understand that since the sealing ring 3 and the combustion chamber 1 are not connected by bolts but by an insertion connection method, even if the combustion chamber 1 vibrates, it will not affect the sealed connection between the sealing ring 3 and the combustion chamber 1.

[0035] It should be clear that when this embodiment is in use, as Figure 5 and Figure 6 shown, the bolts are passed through the corresponding strip-shaped grooves 33, and the bolts are tightened to connect the second sealing edge 32 to the turbine guide vane 2, that is, to connect the sealing ring 3 to the turbine guide vane 2. The strip-shaped groove 33 being adapted to the corresponding bolt means that, as Figure 8 shown, after the bolts are tightened, the second sealing edge 32 along its extension direction (i.e., asFigure 8 In the direction E) shown in the figure, there is still a certain amount of movement space. That is to say, if the second sealing edge 32 expands due to heat, the second sealing edge 32 can expand freely along its extension direction. If the second sealing edge 32 can expand freely along its extension direction, the second sealing edge 32 (that is, the sealing ring 3) will not form a large stress between the bolts, that is, the sealing connection between the sealing ring 3 and the turbine guide vane 2 will not be damaged.

[0036] In summary, the sealing ring of the gas turbine proposed in the embodiment of the present application generates less stress on the bolts after thermal expansion, and the smaller stress makes it difficult for the bolts to crack. In other words, the sealing ring proposed in the present application can reduce the probability of unreliable sealing due to thermal expansion. And the sealing ring and the flame tube in the present application are plug-in-connected to form a sealed connection, that is, in the present application, even if the flame tube vibrates, it is difficult to affect the sealing performance between the sealing ring and the flame tube, that is, it can improve the sealing reliability between the turbine guide and the flame tube.

[0037] It should be understood that in the embodiments of the present application, there is no limitation on the shape and structure of the first sealing edge 31. For example, the first sealing edge 31 may be a square tubular structure, or Figure 3 In order to improve the sealing performance between the sealing ring 3 and the flame tube 1, as shown in the circular tubular structure. Figure 3 As shown, the first sealing edge 31 is along the first direction (i.e. Figure 3 The inner diameter decreases in the direction B) shown in the figure. The first direction is parallel to the axial direction of the sealing ring 3 and points from the first sealing edge 31 to the second sealing edge 32. It should be noted that if the first sealing edge 31 is Figure 5 As shown, during the process of the flame tube 1 and the sealing ring 3 being plugged in, the closer the flame tube 1 is to the sealing ring 3, the tighter the connection between the first sealing edge 31 and the plug-in groove 11 is, that is, the better the sealing performance is.

[0038] It should be noted that in the embodiment of the present application, the length of the strip groove 33 (ie, Figure 2 or Figure 8 The length L shown in the figure is greater than the diameter of the bolt (i.e. Figure 8 If the length of the strip groove 33 is greater than the diameter of the bolt, the second sealing edge 32 has a certain expansion margin. It is easy to understand that in the embodiment of the present application, if the length of the strip groove 33 is short, the effect of eliminating the stress on the bolt is limited. If the length of the strip groove 33 is long, it will affect the overall strength performance of the sealing ring 3. In order to eliminate the thermal expansion stress on the bolt as much as possible and meet the use strength requirements of the sealing ring 3 itself, the inventor has verified through multiple experiments that it can be as follows Figure 2As shown, the length direction of the strip-shaped groove 33 is set to be parallel to the radial direction of the second sealing edge 32, and the length of each strip-shaped groove 33 is 2 to 4 times the diameter of the corresponding bolt.

[0039] It should be clear that the sealing ring of the gas turbine proposed in the embodiment of the present application generates less stress on the bolts after thermal expansion, and it is difficult for the small stress to cause cracks in the bolts. That is to say, the sealing ring proposed in the present application can reduce the probability of sealing unreliability caused by thermal expansion. And the sealing ring in the present application is connected to the flame tube by insertion to form a sealed connection. That is to say, even if the flame tube vibrates in the present application, it is difficult to affect the sealing performance between the sealing ring and the flame tube, that is, it can improve the sealing reliability between the turbine guide vane and the flame tube.

[0040] After introducing the embodiment of the sealing ring of the gas turbine proposed in the present application, the following introduces an embodiment of a sealing structure of a gas turbine proposed in the present application, as Figure 5 and Figure 6 As shown, the sealing structure includes a flame tube 1, a turbine guide vane 2, and the sealing ring of the gas turbine proposed in any one of the above embodiments. In this embodiment, the flame tube 1 is provided with an insertion slot 11 adapted to the first sealing edge 31.

[0041] It should be clear that the sealing structure of the gas turbine proposed in the embodiment of the present application generates less stress on the bolts after thermal expansion, and it is difficult for the small stress to cause cracks in the bolts. That is to say, the sealing structure proposed in the present application can reduce the probability of sealing unreliability caused by thermal expansion. And the sealing ring in this sealing structure is connected to the flame tube by insertion to form a sealed connection. That is to say, even if the flame tube vibrates in the present application, it is difficult to affect the sealing performance between the sealing ring and the flame tube, that is, it can improve the sealing reliability between the turbine guide vane and the flame tube.

[0042] In order to further improve the sealing reliability, in an embodiment of the present application, the flame tube 1 further includes a diversion tube 12. As Figure 6 shown, the first end of the diversion tube 12 is located inside the flame tube 1, and the second end of the diversion tube 12 extends into the turbine guide vane 2. That is to say, in the embodiment of the present application, the diversion tube 12 directly guides the high-temperature gas inside the flame tube 1 to the turbine guide vane 2. That is to avoid the phenomenon that the high-temperature gas leaks through the gap between the flame tube 1 and the turbine guide vane 2 and affects the working efficiency of the gas turbine.

[0043] In order to further improve the sealing reliability, in an embodiment of the present application, the inner diameter of the draft tube 12 decreases along the first direction (i.e., the axial direction of the combustion chamber 1). During the flow of the fluid, if the flow path decreases, the flow velocity of the fluid increases and the pressure decreases. It is easy to understand that if the pressure of the high-temperature gas between the combustion chamber 1 and the turbine guide vane 2 decreases, it is difficult for the high-temperature gas to leak through the gap between the combustion chamber 1 and the turbine guide vane 2, that is, the sealing reliability can be further improved.

[0044] In order to further improve the sealing reliability, in an embodiment of the present application, as Figure 7 shown, the spacing of the insertion slots 11 increases along the first direction (i.e., the direction B as Figure 7 shown), and the maximum spacing of the insertion slots 11 is less than or equal to the thickness of the first sealing edge 31. It should be clear that since the maximum spacing of the insertion slots 11 is less than or equal to the thickness of the first sealing edge 31, during the thermal deformation and expansion of the first sealing edge 31, if the expansion of the first sealing edge 31 is greater, the connection formed with the insertion slots 11 is tighter, that is, the sealing reliability can be improved.

[0045] In order to reduce the splicing difficulty between the insertion slots 11 and the first sealing edge 31 during installation, in an embodiment of the present application, the combustion chamber 1 is further provided with a guiding portion 13, and the cross-section of the guiding portion 13 is in the shape of a flared opening. As Figure 7 shown, since the cross-section of the guiding portion 13 is in the shape of a flared opening, during the splicing process of the insertion slots 11 and the first sealing edge 31, the guiding portion 13 can smoothly guide the first sealing edge 31 into the insertion slots 11, that is, the splicing difficulty between the insertion slots 11 and the first sealing edge 31 during installation is reduced.

[0046] It should be clear that the sealing structure of the gas turbine proposed in the embodiment of the present application generates less stress on the bolts after thermal expansion, and the small stress is difficult to cause cracks in the bolts. That is to say, the sealing structure proposed in the present application can reduce the probability of the occurrence of unreliable sealing due to thermal expansion. And the sealing ring in this sealing structure is inserted into the combustion chamber to form a sealed connection. That is to say, in the present application, even if the combustion chamber vibrates, it is difficult to affect the sealing performance between the sealing ring and the combustion chamber, that is, the sealing reliability between the turbine guide vane and the combustion chamber can be improved.

[0047] After introducing the sealing structure of the gas turbine proposed in the embodiment of the present application, the following introduces an embodiment of a gas turbine proposed in the present application. Specifically, this gas turbine includes the sealing ring of the gas turbine proposed in any one of the above embodiments, or includes the sealing structure of the gas turbine proposed in any one of the above embodiments.

[0048] It should be clear that for the gas turbine proposed in the embodiments of the present application, the sealing ring generates less stress on the bolts after thermal expansion, and the small stress is difficult to cause cracks in the bolts. That is to say, the gas turbine proposed in the present application can reduce the probability of unreliable sealing caused by thermal expansion. Moreover, the sealing ring and the combustion chamber liner in this gas turbine are connected in a plug-in manner to form a sealed connection. That is to say, in the present application, even if the combustion chamber liner vibrates, it is difficult to affect the sealing performance between the sealing ring and the combustion chamber liner, that is, the sealing reliability between the turbine guide vane and the combustion chamber liner can be improved.

[0049] Although the embodiments of the present application have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present application. The scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A sealing ring of a gas turbine, the gas turbine comprising a combustion chamber (1) and a turbine guide vane (2); the sealing ring (3) is arranged between the combustion chamber (1) and the turbine guide vane (2); the sealing ring (3) is connected to the turbine guide vane (2) by a plurality of bolts, characterized in that, The combustion chamber (1) is provided with a socket groove (11); the sealing ring (3) includes a first sealing edge (31) and a second sealing edge (32) connected in sequence; a strip-shaped groove (33) corresponding to each bolt is formed in the second sealing edge (32); the first sealing edge (31) is adapted to the socket groove (11); the strip-shaped groove (33) is adapted to the corresponding bolt.

2. The seal ring of the gas turbine according to claim 1, characterized in that, The inner diameter of the first sealing edge (31) decreases in the first direction; the first direction is parallel to the axial direction of the sealing ring (3) and points from the first sealing edge (31) to the second sealing edge (32).

3. The seal ring of the gas turbine according to claim 1, characterized in that, After the first sealing edge (31) is inserted into the socket groove (11), there is still a socket allowance along the extending direction of the first sealing edge (31) in the socket groove (11).

4. The sealing ring of the gas turbine according to any one of claims 1 to 3, characterized in that, The length direction of the strip-shaped groove (33) is parallel to the radial direction of the second sealing edge (32), and the length of the strip-shaped groove (33) is 2 to 4 times the diameter of the corresponding bolt.

5. A sealing structure of a gas turbine, characterized in that Comprising: A combustion chamber (1); the combustion chamber (1) is provided with a socket groove (11); A turbine guide vane (2); A sealing ring of a gas turbine according to any one of claims 1 to 4.

6. The sealing structure of the gas turbine according to claim 5, characterized in that The combustion chamber (1) further includes a guide pipe (12), the first end of the guide pipe (12) is located inside the combustion chamber (1), and the second end of the guide pipe (12) extends into the turbine guide vane (2).

7. The sealing structure of a gas turbine according to claim 6, wherein, The inner diameter of the guide pipe (12) decreases in the first direction.

8. The sealing structure of the gas turbine according to claim 5, characterized in that The combustion chamber (1) is further provided with a guiding portion (13), and the cross section of the guiding portion (13) is in a flared shape.

9. The seal structure of a gas turbine according to claim 5, characterized in that, The spacing of the socket grooves (11) increases in the first direction, and the maximum spacing of the socket grooves (11) is less than or equal to the thickness of the first sealing edge (31).

10. A gas turbine, characterized in that, Comprising a sealing ring of a gas turbine according to any one of claims 1 to 4, and / or comprising a sealing structure of a gas turbine according to any one of claims 5 to 9.

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