Sealing device for a gas turbine and gas turbine

Abstract

This invention relates to the field of sealing technology and discloses a sealing device for a gas turbine and a gas turbine. The sealing device for a gas turbine includes a base, a cover plate, a sealing element, and an elastic element. The base is fixedly connected to a combustion chamber and has a through hole for communicating between the interior and exterior of the combustion chamber. A cavity is formed between the cover plate and the base. The sealing element is located in the cavity and has a mounting hole for installing an insertion device. The wall of the mounting hole forms a first sealing surface for achieving a seal between the sealing element and the insertion device. The sealing element also includes a second sealing surface for achieving a seal between the sealing element and the base. The elastic element is located between the sealing element and the cover plate. In the sealing device for a gas turbine of this invention, the elastic element makes the contact between the sealing element and the base tighter, resulting in a better sealing effect. Simultaneously, the elastic element provides a supporting force from the compressed air zone to the combustion zone, pressing the sealing element and preventing the gas from flowing back along the second sealing surface when combustion pulsations occur.

Description

Technical Field

[0001] This invention relates to the field of sealing technology, specifically to a sealing device for a gas turbine and a gas turbine. Background Technology

[0002] The start-up process of a gas turbine requires ignition and flame detection, and combustion status needs to be monitored using observation equipment during testing. These ignition and observation devices must be inserted into the combustion chamber from the outside through structures such as flame tubes. Due to thermal expansion during gas turbine operation, these devices are inserted into the combustion chamber with a certain gap at the edge of the insertion opening to prevent damage from contact with the edge. Under the influence of the internal and external pressure difference, compressed air can enter the combustion chamber through the gaps in the insertion area of ​​the igniter, flame detector, or observation equipment, posing a risk of affecting fuel combustion. Summary of the Invention

[0003] The present invention aims to at least partially solve one of the technical problems in the related art.

[0004] Therefore, embodiments of the present invention provide a sealing device for a gas turbine, which can achieve a seal between the insertion equipment and combustion.

[0005] This invention also proposes a gas turbine.

[0006] The sealing device for a gas turbine according to an embodiment of the present invention includes a base, a cover plate, a sealing element, and an elastic element. The base is fixedly connected to a combustion chamber and has a through hole for communicating between the interior and exterior of the combustion chamber. The cover plate is located on the side of the base away from the combustion chamber and is fixedly connected to the base, forming a cavity between the cover plate and the base. The sealing element is located in the cavity and includes a mounting hole communicating with the through hole for installing an insertion device. The wall of the mounting hole forms a first sealing surface for sealing between the sealing element and the insertion device. The sealing element includes a second sealing surface that contacts the base and seals between the sealing element and the base. The elastic element is disposed between the sealing element and the cover plate and provides elasticity to maintain a seal between the second sealing surface and the base.

[0007] In the sealing device for gas turbines of this invention, the base is positioned at the combustion chamber for easy installation of the insertion device. The sealing element includes a first sealing surface and a second sealing surface. The first and second sealing surfaces achieve a seal between the insertion device and the combustion chamber, preventing compressed air from easily entering the combustion chamber. An elastic element is positioned between the sealing element and the cover plate, enabling a tighter contact between the sealing element and the base, resulting in a better sealing effect. Furthermore, the elastic element provides a supporting force from the compressed air zone towards the combustion zone, pressing the sealing element and preventing gas from flowing back to the compressed air zone along the second sealing surface during combustion pulsation.

[0008] In some embodiments, the seal includes a flange, the base includes a groove, the end face of the flange forms a second sealing surface, the flange is located within the groove and the second sealing surface is in sealing engagement with the bottom of the groove.

[0009] In some embodiments, the second sealing surface is provided with a plurality of sealing teeth arranged at intervals.

[0010] In some embodiments, the gas turbine sealing device includes a support member located within the chamber and disposed on the outer periphery of the seal member, the support member being used to support the periphery of the seal member.

[0011] In some embodiments, the support member is a support ring, the inner ring of the support ring is sleeved on the outer periphery of the seal member, and the outer ring of the support ring is fixedly connected to the cover plate.

[0012] In some embodiments, the support ring is located on the upper side of the flange, and a third sealing surface is provided on the side of the flange near the support ring, the third sealing surface being used to achieve a seal between the support ring and the flange.

[0013] In some embodiments, the third sealing surface is provided with a plurality of sealing teeth, and the plurality of sealing teeth are arranged at intervals.

[0014] In some embodiments, the elastic member is provided with a plurality of slots, which can communicate the chamber with the external space of the combustion chamber.

[0015] In some embodiments, the elastic element and the sealing element are an integral structure, and / or the base, the cover plate, the sealing element and the elastic element are all made of metal.

[0016] The gas turbine of this invention includes a gas turbine body and a sealing device, wherein the sealing device is a gas turbine sealing device of any of the above embodiments. Attached Figure Description

[0017] Figure 1This is a front view of a sealing device for a gas turbine according to an embodiment of the present invention.

[0018] Figure 2 This is a cross-sectional view of a sealing device for a gas turbine according to an embodiment of the present invention.

[0019] Figure 3 This is a schematic diagram of the structure of the elastic element of the sealing device for a gas turbine according to an embodiment of the present invention.

[0020] Figure 4 This is a cross-sectional view of the sealing element of the gas turbine sealing device according to an embodiment of the present invention.

[0021] Figure 5 yes Figure 4 A magnified view of section B.

[0022] Figure 6 yes Figure 4 A magnified view of section C.

[0023] Figure 7 This is a schematic diagram of the structure of the support member of the sealing device for a gas turbine according to an embodiment of the present invention.

[0024] Figure 8 This is a schematic diagram of the base of the sealing device for a gas turbine according to an embodiment of the present invention.

[0025] Figure 9 This is a schematic diagram of the structure of the cover plate of the sealing device for a gas turbine according to an embodiment of the present invention.

[0026] Figure 10 This is an assembly diagram of the sealing device and insertion device for a gas turbine according to an embodiment of the present invention.

[0027] Figure 11 This is an assembly cross-sectional view of the sealing device and insertion device for a gas turbine according to an embodiment of the present invention.

[0028] Figure label:

[0029] 1. Base; 11. Through hole; 12. Groove; 2. Cover plate; 3. Seal; 31. Mounting hole; 311. First sealing surface; 32. Flange; 321. Second sealing surface; 322. Third sealing surface; 4. Elastic element; 41. Groove; 5. Support element; 6. Insertion device. Detailed Implementation

[0030] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0031] like Figure 1-11As shown, the sealing device for gas turbines in this embodiment of the invention includes a base 1, a cover plate 2, a sealing element 3, and an elastic element 4.

[0032] like Figure 1 , 2 As shown in Figures 8 and 9, the base 1 is fixedly connected to the combustion chamber. The base 1 is provided with a through hole 11, which connects the interior and exterior of the combustion chamber. The cover plate 2 is located on the side of the base 1 away from the combustion chamber and is fixedly connected to the base 1, forming a cavity between the cover plate 2 and the base 1. Specifically, the lower part of the base 1 is fixedly connected to the combustion chamber, and the upper part of the base 1 is connected to the cover plate 2. The through hole 11 communicates with the interior of the combustion chamber and allows the insertion device 6 to enter the interior of the combustion chamber for ignition or detection of the flame's combustion status.

[0033] The sealing element 3 is located in the chamber and includes a mounting hole 31 that communicates with the through hole 11 and is used to install the insertion device 6. The wall of the mounting hole 31 forms a first sealing surface 311, which is used to achieve a seal between the sealing element 3 and the insertion device 6. The sealing element 3 also includes a second sealing surface 321 that contacts the base 1 and is used to achieve a seal between the sealing element 3 and the base 1. An elastic element 4 is disposed between the sealing element 3 and the cover plate 2 and provides elastic force to maintain a seal between the second sealing surface 321 and the base 1. Specifically, multiple sealing teeth may be provided on the first sealing surface 311. The elastic element 4 is capable of elastic deformation, and by setting the elastic element 4 to allow relative displacement between the insertion device 6 and the combustion chamber, the leakage rate is reduced.

[0034] In the sealing device for gas turbines of this invention, the base is positioned at the combustion chamber for easy installation of the insertion device. The sealing element includes a first sealing surface and a second sealing surface. The first and second sealing surfaces achieve a seal between the insertion device and the combustion chamber, preventing compressed air from easily entering the combustion chamber. An elastic element is positioned between the sealing element and the cover plate, enabling a tighter contact between the sealing element and the base, resulting in a better sealing effect. Furthermore, the elastic element provides a supporting force from the compressed air zone to the combustion zone, pressing the sealing element and preventing gas from flowing back to the compressed air zone along the second sealing surface 321 when combustion pulsations occur.

[0035] In some embodiments, such as Figure 2 , 4 As shown in Figure 8, the sealing element 3 includes a flange 32, and the base 1 includes a groove 12. The end face of the flange 32 forms a second sealing surface 321. The flange 32 is located within the groove 12, and the second sealing surface 321 is in sealing engagement with the bottom of the groove 12. The engagement of the flange 32 and the groove 12 increases the contact area between the sealing element 3 and the base 1, resulting in a better sealing effect between the sealing element 3 and the base 1.

[0036] In some embodiments, such as Figure 4 , 5 As shown in Figure 6, the second sealing surface 321 is provided with multiple sealing teeth arranged at intervals. The multiple intervals of the sealing teeth can effectively increase the flow resistance, reduce the leakage, and make the sealing effect between the insertion device 6 and the sealing element 3 better.

[0037] In other embodiments, the first sealing surface 311 is also provided with multiple sealing teeth.

[0038] In some embodiments, such as Figure 1 , 2 As shown in Figure 7, the sealing device for a gas turbine includes a support member 5. The support member 5 is located inside the chamber and disposed on the outer periphery of the seal member 3. The support member 5 is used to support the periphery of the seal member 3. The support member 5 supports the periphery of the seal member 3, which can prevent the seal member 3 from moving circumferentially under the action of gas pressure, thereby avoiding air leakage from the second sealing surface 321.

[0039] In some embodiments, such as Figure 1 , 2 As shown in Figure 7, the support member 5 is a support ring. The inner ring of the support ring is fitted around the outer circumference of the sealing member 3, and the outer ring of the support ring is fixedly connected to the cover plate 2. Specifically, the inner ring of the support ring is fitted around the middle of the sealing member 3, and the outer ring of the support ring is located between the cover plate 2 and the base 1 and is fixedly connected to both the cover plate 2 and the base 1. The support ring provides circumferential support to the sealing member 3, preventing air leakage caused by circumferential movement of the sealing member 3.

[0040] In some embodiments, such as Figure 2 , 4 As shown in Figure 5, the support ring is located on the upper side of the flange 32. A third sealing surface 322 is provided on the side of the flange 32 near the support ring. The third sealing surface 322 is used to achieve a seal between the support ring and the flange 32. Both the third sealing surface 322 and the second sealing surface 321 are used to achieve a seal between the base 1 and the sealing element 3. The third sealing surface 322 enhances the sealing effect between the base 1 and the sealing element 3.

[0041] In some embodiments, such as Figure 2 , 4 As shown in Figure 5, multiple sealing teeth are provided on the third sealing surface 322, and the multiple sealing teeth are arranged at intervals. The sealing teeth can effectively increase the flow resistance, reduce the leakage, and enhance the sealing effect at the third sealing surface 322.

[0042] In some embodiments, such as Figure 2 , 3 As shown, the elastic element 4 is provided with multiple slots 41, which can connect the chamber to the external space of the combustion chamber. Figure 10, 11 As shown, the gas in the compressed air zone can enter the chamber through the slot 41 and act on the support member 5. At this time, the elastic member 4 and the compressed gas work together to press the seal member 3 against the base 1, ensuring the sealing effect between the base 1 and the seal member 3. At the same time, the slot 41 can absorb the deformation of the elastic member 4. The elastic member 4 can provide a supporting force from the compressed air zone to the combustion zone, press the seal member 3, and prevent the gas from flowing back to the compressed air zone along the second sealing surface 321 when combustion pulsates.

[0043] In some embodiments, the elastic element 4 and the sealing element 3 are an integral structure, and / or the base 1, cover plate 2, sealing element 3, and elastic element 4 are all made of metal. The combustion chamber temperature is high, and using conventional graphite or perfluororubber rings would risk burnout. Metal materials, however, have better high-temperature resistance, ensuring sealing performance.

[0044] The gas turbine of an embodiment of the present invention is described below.

[0045] The gas turbine of this invention includes a gas turbine body and a sealing device. The sealing device has the same structure as the sealing device for gas turbines in the above embodiments, and will not be described again here.

[0046] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0047] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0048] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0049] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0050] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0051] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A sealing device for a gas turbine, characterized in that, include: A base for fixed connection with a combustion chamber, the base being provided with a through hole for communicating between the interior and exterior of the combustion chamber; A cover plate, the cover plate being located on the side of the base away from the combustion chamber and the cover plate being fixedly connected to the base, forming a cavity between the cover plate and the base; A sealing element is located in the chamber. The sealing element includes a mounting hole that communicates with the through hole and is used to mount an insertion device. The wall of the mounting hole forms a first sealing surface, which is used to achieve a seal between the sealing element and the insertion device. The sealing element includes a second sealing surface, which contacts the base and is used to achieve a seal between the sealing element and the base. An elastic element is disposed between the seal and the cover plate, the elastic element being used to provide elastic force to maintain a seal between the second sealing surface and the base; The sealing element includes a flange, the base includes a groove, the end face of the flange forms a second sealing surface, the flange is located within the groove and the second sealing surface is in sealing engagement with the bottom of the groove; The second sealing surface is provided with multiple sealing teeth arranged at intervals; The system includes a support member located within the cavity and disposed on the outer periphery of the seal, the support member being used to support the circumference of the seal. The support member is a support ring, the inner ring of which is sleeved on the outer circumference of the sealing member, and the outer ring of which is fixedly connected to the cover plate; The elastic element is provided with multiple slots, which can connect the cavity with the external space of the combustion chamber.

2. The sealing device for a gas turbine according to claim 1, characterized in that, The support ring is located on the upper side of the flange, and a third sealing surface is provided on the side of the flange near the support ring. The third sealing surface is used to achieve a seal between the support ring and the flange.

3. The sealing device for a gas turbine according to claim 2, characterized in that, The third sealing surface is provided with multiple sealing teeth, which are arranged at intervals.

4. The sealing device for a gas turbine according to any one of claims 1-3, characterized in that, The elastic element and the sealing element are an integral structure, and / or the base, the cover plate, the sealing element and the elastic element are all made of metal.

5. A gas turbine, comprising a gas turbine body and a sealing device, characterized in that, The sealing device is the gas turbine sealing device according to any one of claims 1-4.

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