Gas turbine, double seal, and gas turbine engine

Abstract

The present invention discloses a gas turbine, a double-layer seal and a gas turbine engine. The gas turbine includes a housing, a stator vane assembly and a seal. The stator vane assembly includes a plurality of stator vanes arranged at intervals in the circumferential direction of the housing. The lower edge plate is connected to the end of the stator vane body, and the side of the lower edge plate facing away from the body is a cold air cavity. The cold air cavity includes a high-pressure cavity and a low-pressure cavity arranged at intervals in the axial direction of the housing. The side surface of the lower edge plate has a mounting groove extending in the axial direction of the housing. The seal is clamped between adjacent stator vanes and fitted in the mounting groove, and there is a ventilation gap between the seal and the mounting groove. The ventilation gap includes a first gap opposite to the high-pressure cavity and a second gap opposite to the low-pressure cavity. The seal has a cavity communicating with the high-pressure cavity, and the side wall of the cavity in the circumferential direction of the housing has an exhaust port, and the exhaust port is opposite to the first gap and the second gap. The gas turbine of the present invention can prevent gas from invading the cold air cavity, has a small cold air leakage amount, and has a high cooling efficiency of the gas turbine.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and particularly relates to a gas turbine, a double-layer seal, and a gas turbine. Background Art

[0002] A gas turbine is an internal combustion power machine that uses continuously flowing gas as the working medium to drive an impeller to rotate at a high speed, thereby converting the energy of fuel into mechanical energy. Among them, the turbine is one of the core components of the gas turbine. The turbine blades operate in a high-temperature environment. When the turbine is operating, it is necessary to prevent high-temperature gas from invading the non-flow path surface through the gap between the lower edge plates of the stationary blades of the turbine. In the related art, cold air leaks from the cold air cavity inside the lower edge plate of the stationary blade into the gas passage to prevent the intrusion of high-temperature gas. However, in the related art, the cold air leakage of the gas turbine is large, the cooling efficiency of the gas turbine is low, and when the gas side pressure is large, gas intrusion will occur. Summary of the Invention

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

[0004] To this end, an embodiment of the present invention provides a gas turbine that can prevent gas from invading the cold air cavity, has a small cold air leakage, and has a high cooling efficiency of the gas turbine.

[0005] An embodiment of the present invention also provides a double-layer seal.

[0006] An embodiment of the present invention further provides a gas turbine.

[0007] The gas turbine according to the embodiment of the present invention includes: a housing having a gas passage and a cold air cavity, the cold air cavity including a high-pressure cavity and a low-pressure cavity, and the high-pressure cavity and the low-pressure cavity are spaced apart in the axial direction of the housing;

[0008] A stator vane assembly is provided inside the housing. The stator vane assembly includes a plurality of stator vanes. The plurality of stator vanes are arranged in multiple groups at intervals in the axial direction of the housing. Each group of stator vanes includes a plurality of stator vanes arranged at intervals in the circumferential direction of the housing. Each stator vane includes a body and a lower edge plate. The lower edge plate is connected to the end of the body, and the side of the lower edge plate facing away from the body is a cold air cavity, and the side of the lower edge plate facing the body is a gas passage. The lower edge plate has a cold air inlet, and the cold air inlet communicates with the high-pressure cavity to inject cold air into the high-pressure cavity. Both side surfaces of the lower edge plate opposite to each other in the circumferential direction of the housing have mounting grooves extending in the axial direction of the housing; A seal is provided. The seal is clamped between adjacent stator vanes in the circumferential direction of the housing and fits in the mounting groove. There is a ventilation gap between the outer side surface of the seal and the inner wall surface of the mounting groove. The ventilation gap includes a first gap opposite to the high-pressure cavity and a second gap opposite to the low-pressure cavity in the axial direction of the housing. The seal has a cavity. At least one side wall of the cavity in the circumferential direction of the housing has an exhaust port extending in the axial direction of the housing. The exhaust port is at least partially opposite to the second gap in the axial direction of the housing, and the exhaust port is at least partially opposite to the first gap in the axial direction of the housing. The side surface of the seal facing the high-pressure cavity has an air inlet communicating with the cavity.

[0009] In the gas turbine according to the embodiment of the present invention, the seal is clamped between the lower end plates of adjacent stator vanes, and a ventilation gap communicating the cold air cavity and the gas passage is formed between the seal and the lower end plate. The ventilation gap includes a first gap opposite to the high-pressure cavity and a second gap opposite to the low-pressure cavity. The seal has a cavity. The cavity has an air inlet communicating with the high-pressure cavity, and an exhaust port is provided on the side surface of the cavity opposite to the lower end plate. The exhaust port is at least partially opposite to the second gap, and the exhaust port is at least partially opposite to the first gap. Thus, the cold air in the high-pressure cavity can enter the cavity of the seal through the air inlet and flow to the second gap through the exhaust port, so that the pressure of the cold air at the second gap is greater than the gas side pressure, thereby preventing the gas from invading the cold air cavity. Moreover, the airflow discharged from the exhaust port can form an airflow impact at the ventilation gap, and the direction of the airflow impact is perpendicular to the leakage direction of the cold air. Therefore, an air barrier can be formed by using the airflow impact to prevent the gas from invading, and the cold air leakage rate can be slowed down. The cold air leakage amount is small, and the cooling efficiency of the gas turbine is high.

[0010] In some embodiments, the seal is made of a shape memory alloy material. When the temperature difference between the cavity and the cold air cavity is less than a set value, the size of the air inlet remains unchanged. When the temperature difference between the cavity and the cold air cavity is greater than the set value, the seal automatically deforms to increase the size of the air inlet.

[0011] In some embodiments, the seal includes an upper sealing plate, a lower sealing plate, and a connecting side plate. The upper sealing plate and the lower sealing plate are stacked and spaced apart. The connecting side plate is connected between the upper sealing plate and the lower sealing plate, and the upper sealing plate, the lower sealing plate, and the connecting side plate can enclose the cavity. At least one of the upper sealing plate and the lower sealing plate has an air inlet communicating with the cavity.

[0012] In some embodiments, the upper sealing plate and the lower sealing plate are integrally formed.

[0013] In some embodiments, the inner side surface of the upper sealing plate includes an inclined surface that extends obliquely toward the lower sealing plate in a direction close to the exhaust port, and / or the inner side surface of the lower sealing plate includes an inclined surface that extends obliquely toward the upper sealing plate in a direction close to the exhaust port.

[0014] In some embodiments, a partition is provided on the side surface of the lower edge plate facing away from the body. The partition is axially located between the high-pressure chamber and the low-pressure chamber in the housing to separate the high-pressure chamber and the low-pressure chamber.

[0015] In some embodiments, the seal further includes a sealing support plate. The sealing support plate is connected to the side surface of the lower sealing plate facing away from the upper sealing plate, and the sealing support plate is circumferentially located between adjacent stationary blades in the housing and fits within the partition.

[0016] In some embodiments, the body has a cold air passage that communicates the cold air inlet and the cold air source.

[0017] The double-layer seal of the embodiment of the present invention includes an upper sealing plate, a lower sealing plate, and a connecting side plate. The upper sealing plate and the lower sealing plate are stacked and spaced apart. The connecting side plate is connected between the upper sealing plate and the lower sealing plate, and the upper sealing plate, the lower sealing plate, and the connecting side plate can enclose a cavity. At least one side of the peripheral wall of the cavity has an exhaust port, and at least one of the upper sealing plate and the lower sealing plate has an air inlet communicating with the cavity.

[0018] The double-layer seal of the embodiment of the present invention, when applied to seal a gas chamber, for example, can utilize the internal channels of the double-layer seal to achieve the air flow transfer between different gas chambers according to requirements, so as to achieve the purpose of reducing the pressure in the high-pressure chamber or increasing the pressure in the low-pressure chamber. Moreover, the air flow discharged from the exhaust port can form a wind barrier in the plane, and by using the blocking effect of the wind barrier, purposes such as dust prevention and flow resistance can be achieved.

[0019] The gas turbine of the embodiment of the present invention includes the gas turbine or the double-layer seal described in the above embodiment.

[0020] The gas turbine of the embodiment of the present invention has good performance and a long service life by adopting the above gas turbine or double-layer seal. Description of the Drawings

[0021] Figure 1 It is a schematic structural diagram of the gas turbine of the embodiment of the present invention.

[0022] Figure 2 It is an enlarged partial structural view of the gas turbine of the embodiment of the present invention.

[0023] Figure 3 It is a sectional view of the gas turbine of the embodiment of the present invention.

[0024] Figure 4 is Figure 3 an enlarged view of part A in

[0025] Figure 5 It is a schematic structural diagram of the double-layer seal of the embodiment of the present invention.

[0026] Reference Signs:

[0027] Stator vane 1, body 11, lower edge plate 12, partition plate 121, high-pressure chamber 122, low-pressure chamber 123, installation groove 124, ventilation gap 125, seal 2, upper sealing plate 21, lower sealing plate 22, sealing support plate 23, air inlet 24, exhaust port 25, gas passage 3. Detailed Embodiment

[0028] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0029] As Figures 1 - 5 shown, the gas turbine of the embodiment of the present invention includes a housing, a stator vane assembly, and a seal 2.

[0030] Specifically, the housing has a gas passage 3 and a cold air chamber. The cold air chamber includes a high-pressure chamber 122 and a low-pressure chamber 123. The high-pressure chamber 122 and the low-pressure chamber 123 are spaced apart axially in the housing. The stationary vane assembly is provided in the housing. The stationary vane assembly includes a plurality of stationary vanes 1. The plurality of stationary vanes 1 are spaced apart axially in the housing to form multiple groups. Each group of stationary vanes 1 includes a plurality of stationary vanes 1 spaced apart circumferentially in the housing. The stationary vane 1 includes a body 11 and a lower edge plate 12. The lower edge plate 12 is connected to the end of the body 11, and the side of the lower edge plate 12 facing away from the body 11 is the cold air chamber, and the side of the lower edge plate 12 facing the body 11 is the gas passage 3. The lower edge plate 12 has a cold air inlet, and the cold air inlet communicates with the high-pressure chamber 122 to inject cold air into the high-pressure chamber 122. The opposite side surfaces of the lower edge plate 12 in the circumferential direction of the housing both have mounting grooves 124 extending axially in the housing.

[0031] It can be understood that in the circumferential direction of the housing, the adjacent stationary vanes 1 are spaced apart. Then, the gap between the adjacent lower edge plates 12 can serve as a communication passage between the cold air chamber and the gas passage 3. The cold air in the cold air chamber can leak cold air into the gas passage 3 through the communication passage to prevent the intrusion of gas.

[0032] Further, the seal 2 is clamped between the adjacent stationary vanes 1 in the circumferential direction of the housing and is fitted in the mounting groove 124. There is a ventilation gap 125 between the outer side surface of the seal 2 and the inner wall surface of the mounting groove 124. The ventilation gap 125 includes a first gap opposite to the high-pressure chamber 122 and a second gap opposite to the low-pressure chamber 123 axially in the housing. The seal 2 has a cavity. At least one side wall of the cavity in the circumferential direction of the housing has an exhaust port 25 extending axially in the housing. The exhaust port 25 is at least partially opposite to the second gap axially in the housing, and the exhaust port 25 is at least partially opposite to the first gap axially in the housing. The side surface of the seal 2 facing the high-pressure chamber 122 has an air inlet 24 communicating with the cavity.

[0033] It can be understood that when the cold air leaks directly from the gap between the lower edge plates 12, the leakage amount is too large, which is not conducive to the efficient operation of the gas turbine. By providing the seal 2 between the adjacent lower edge plates 12, the problem of large cold air leakage can be solved.

[0034] Specifically, a ventilation gap 125 is formed between the seal 2 and the inner wall surface of the mounting groove 124. Then, when the cold air leaks, it can flow along the surface of the seal 2 along the ventilation gap 125 to the gas passage 3. Since the size of the ventilation gap 125 is small, the leakage amount of the cold air can be reduced, and the cold air usage can be decreased.

[0035] In addition, it should be noted that there is also a situation where the pressure in the low-pressure chamber 123 of the gas turbine is less than the pressure in the gas passage 3. Under the action of the pressure difference, gas intrusion into the low-pressure chamber 123 may occur. However, the seal 2 of the present application can introduce the cold air in the high-pressure chamber 122 into the second gap where the low-pressure chamber 123 communicates with the gas passage 3, thereby increasing the pressure at the second gap and solving the problem of gas intrusion into the low-pressure chamber 123 through the second gap.

[0036] For easy understanding, the cold air flow process is as follows: A part of the cold air in the high-pressure chamber 122 flows along the surface of the seal 2 and through the first gap into the gas passage 3, and another part of the cold air flows into the cavity through the air inlet 24. The cold air in the cavity is then discharged through the air outlet 25. Since the air outlet 25 is at least partially opposite to the second gap, the cold air in the cavity can flow through the air outlet 25 into the second gap, increasing the cold air pressure at the second gap, thereby preventing gas from intruding into the low-pressure chamber 123. Moreover, the air flow discharged from the air outlet 25 can form an air flow impact at the second gap. At the same time, since the air outlet 25 is at least partially opposite to the first gap, the air flow discharged from the air outlet 25 can also form an air flow impact at the first gap. The air flow impact direction is perpendicular to the cold air leakage direction, so that an air barrier can be formed by using the air flow impact to prevent gas intrusion and the cold air leakage rate can be reduced.

[0037] In the gas turbine according to the embodiment of the present invention, the seal 2 is clamped between the lower end plates of the adjacent stationary blades 1, and an air-permeable gap 125 communicating the cold air chamber and the gas passage 3 is formed between the seal 2 and the lower end plates. The air-permeable gap 125 includes a first gap opposite to the high-pressure chamber 122 and a second gap opposite to the low-pressure chamber 123. The seal 2 has a cavity. The cavity has an air inlet 24 communicating with the high-pressure chamber 122, and an air outlet 25 is provided on the side surface of the cavity opposite to the lower end plate. The air outlet 25 is at least partially opposite to the second gap, and the air outlet 25 is at least partially opposite to the first gap. Thus, the cold air in the high-pressure chamber 122 can enter the cavity of the seal 2 through the air inlet 24 and flow through the air outlet 25 into the second gap, so that the cold air pressure at the second gap is greater than the gas side pressure, thereby preventing gas from intruding into the cold air chamber. Moreover, the air flow discharged from the air outlet 25 can form an air flow impact at the air-permeable gap 125, and the air flow impact direction is perpendicular to the cold air leakage direction, so that an air barrier can be formed by using the air flow impact to prevent gas intrusion and the cold air leakage rate can be reduced. The cold air leakage amount is small, and the cooling efficiency of the gas turbine is high.

[0038] Preferably, a part of the air outlet 25 in the axial direction of the housing is opposite to the first gap, and the other part is opposite to the second gap, that is, the extension length of the air outlet 25 exactly matches the extension length of the air-permeable gap 125. Then, the air barrier formed by the exhaust of the air outlet 25 can slow down the cold air leakage at any position of the air-permeable gap 125.

[0039] Preferably, the seal 2 is made of a shape memory alloy material. When the temperature difference between the cavity and the cold air cavity is less than the set value, the size of the air inlet 24 remains unchanged. When the temperature difference between the cavity and the cold air cavity is greater than the set value (which can be determined as gas intrusion at this time), the seal 2 automatically deforms to increase the size of the air inlet 24. In other words, when the pressure in the gas passage 3 is greater than the pressure in the cold air cavity, resulting in gas intrusion, the air inlet 24 of the seal 2 can automatically become larger to increase the cold air pressure in the cavity, thereby quickly increasing the cold air pressure at the second gap to prevent gas intrusion. At the same time, the impact flow rate of the impact air flow can be increased, improving the partition ability of the air barrier. It should be noted that the shape memory alloy material has the ability of automatic restoration, can be used for a long time, and does not require manual adjustment, which is simple and convenient.

[0040] Optionally, as Figure 5 shown, the seal 2 includes an upper sealing plate 21, a lower sealing plate 22 and a connecting side plate. The upper sealing plate 21 and the lower sealing plate 22 are stacked and arranged at intervals. The connecting side plate is connected between the upper sealing plate 21 and the lower sealing plate 22, and the upper sealing plate 21, the lower sealing plate 22 and the connecting side plate can enclose a cavity. At least one of the upper sealing plate 21 and the lower sealing plate 22 has an air inlet 24 communicating with the cavity. In other words, the seal 2 is a double-layer seal 2. The cold air in the high-pressure cavity 122 flows into the space between the upper sealing plate 21 and the lower sealing plate 22 through the air inlet 24, and then discharges to both sides along the gap between the two, so that air flow impacts can be formed at the air-permeable gaps 125 on both sides, avoiding gas bypassing the air-permeable gap 125 and intruding into the cold air cavity.

[0041] Preferably, the upper sealing plate 21 and the lower sealing plate 22 are integrally formed.

[0042] Preferably, the inner side surface of the upper sealing plate 21 includes an inclined surface, and the inclined surface extends obliquely downward toward the lower sealing plate 22 along the direction close to the exhaust port 25. Thus, when the cold air in the cavity flows toward the exhaust port 25, due to the inclined contraction of the inclined surface, the air flow velocity will gradually increase, and then it can be ejected from the exhaust port 25 at a high speed to form a reliable air barrier at the air-permeable gap 125, improving the reliability of anti-intrusion.

[0043] Preferably, the inner side surface of the lower sealing plate 22 includes an inclined surface, and the inclined surface extends obliquely upward toward the upper sealing plate 21 along the direction close to the exhaust port 25.

[0044] Furthermore, as Figure 1 and Figure 2As shown, a partition plate 121 is provided on the side of the lower edge plate 12 facing away from the main body 11. The partition plate 121 is axially located between the high-pressure chamber 122 and the low-pressure chamber 123 in the housing to separate the high-pressure chamber 122 and the low-pressure chamber 123. The seal 2 further includes a seal support plate 23. The seal support plate 23 is connected to the side of the lower sealing plate 22 facing away from the upper sealing plate 21, and the seal support plate 23 is circumferentially located between adjacent stationary blades 1 in the housing and is fitted inside the partition plate 121.

[0045] Thus, the seal support plate 23 can be assembled with the partition plate 121 to support the entire seal 2, and can also form an annular partition with the partition plate 121 to prevent the cold air in the high-pressure chamber 122 from directly flowing into the low-pressure chamber 123 through the gap between adjacent partition plates 121, so as to prevent a large amount of cold air leakage.

[0046] Optionally, an assembly groove can also be provided on the partition plate 121. A part of the seal support plate 23 is fitted in the assembly groove and a ventilation gap is formed at an interval from the groove wall.

[0047] Preferably, the main body 11 has a cold air passage, and the cold air passage communicates with the cold air inlet and the cold air source. That is to say, the cold air delivered from the cold air source enters the cold air chamber through the cold air passage, and the cold air can also exchange heat with the stationary blade 1, thereby cooling the stationary blade 1.

[0048] The double-layer seal of the embodiment of the present invention includes an upper sealing plate 21, a lower sealing plate 22 and a connecting side plate. The upper sealing plate 21 and the lower sealing plate 22 are stacked and arranged at intervals. The connecting side plate is connected between the upper sealing plate 21 and the lower sealing plate 22, and the upper sealing plate 21, the lower sealing plate 22 and the connecting side plate can enclose a cavity. At least one side of the peripheral wall of the cavity has an exhaust port 25, and at least one of the upper sealing plate 21 and the lower sealing plate 22 has an air inlet 24 communicating with the cavity.

[0049] That is to say, when the double-layer seal is applied to the sealing of the gas chamber, the air flow transfer between different gas chambers can be realized by using the internal channel of the double-layer seal according to the needs, so as to achieve the purpose of reducing the pressure in the high-pressure chamber 122 or increasing the pressure in the low-pressure chamber 123.

[0050] For example, as Figure 1 shown, the double-layer seal of the present application is applied to the stationary blade assembly of the gas turbine to reduce the cold air leakage. Specifically, the double-layer seal fitted between adjacent stationary blades 1 can introduce the cold air in the high-pressure chamber 122 into the cavity through the air inlet 24 on the lower sealing plate 22 and discharge it through the exhaust port 25. The exhaust port 25 exhausting towards the low-pressure chamber 123 can increase the cold air pressure in the low-pressure chamber 123, thereby preventing the gas in the gas passage 3 from having too high a pressure and causing gas intrusion into the low-pressure chamber 123.

[0051] The double-layer seal of the embodiment of the present invention, when applied to seal a gas chamber, etc., can realize the air flow transfer between different gas chambers through the internal channel of the double-layer seal according to requirements, so as to achieve the purpose of decompressing a high-pressure chamber or pressurizing a low-pressure chamber, and the air flow discharged from the exhaust port can form a wind barrier in a plane, and the partition function of the wind barrier is utilized to achieve purposes such as dust prevention and flow blocking.

[0052] The gas turbine of the embodiment of the present invention includes the gas turbine or the double-layer seal of the above embodiment.

[0053] For the gas turbine of the embodiment of the present invention, by adopting the above gas turbine or double-layer seal, the gas turbine has good performance and a long service life.

[0054] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying 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 to the present invention.

[0055] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0056] In the present invention, unless otherwise clearly specified and limited, the terms "mounted", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection, an electrical connection, or communicable with each other; it can be directly connected, or indirectly connected through an intermediate medium, and can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0057] In the present invention, unless otherwise clearly specified or limited, the first feature being "on" or "under" the second feature may mean that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may mean that the first feature is directly above or obliquely above the second feature, or merely indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "below" and "beneath" the second feature may mean that the first feature is directly below or obliquely below the second feature, or merely indicates that the horizontal height of the first feature is less than that of the second feature.

[0058] In the present invention, the terms "an embodiment", "some embodiments", "exemplifications", "specific exemplifications", or "some exemplifications", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or exemplification are included in at least one embodiment or exemplification of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or exemplification. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or exemplifications in a suitable manner. In addition, without conflict, those skilled in the art may combine and combine the different embodiments or exemplifications described in this specification and the features of the different embodiments or exemplifications.

[0059] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A gas turbine, characterized in that, comprising: a housing having a gas passage and a cold air chamber, the cold air chamber including a high-pressure chamber and a low-pressure chamber, the high-pressure chamber and the low-pressure chamber being spaced apart in the axial direction of the housing; a stator vane assembly provided in the housing, the stator vane assembly including a plurality of stator vanes, the plurality of stator vanes being spaced apart in the axial direction of the housing to form multiple groups, each group of stator vanes including a plurality of stator vanes spaced apart circumferentially of the housing, each stator vane including a body and a lower edge plate, the lower edge plate being connected to an end of the body and a side of the lower edge plate facing away from the body being the cold air chamber, a side of the lower edge plate facing the body being the gas passage, the lower edge plate having a cold air inlet, the cold air inlet communicating with the high-pressure chamber to inject cold air into the high-pressure chamber, and both side surfaces of the lower edge plate opposite to each other in the circumferential direction of the housing having mounting grooves extending in the axial direction of the housing; a seal member, the seal member being clamped between adjacent stator vanes in the circumferential direction of the housing and fitted in the mounting groove, and having a ventilation gap between an outer side surface of the seal member and an inner wall surface of the mounting groove, the ventilation gap including a first gap opposite to the high-pressure chamber and a second gap opposite to the low-pressure chamber in the axial direction of the housing, the seal member having a cavity, at least one side wall of the cavity in the circumferential direction of the housing having an exhaust port extending in the axial direction of the housing, the exhaust port being at least partially opposite to the second gap in the axial direction of the housing, and the exhaust port being at least partially opposite to the first gap in the axial direction of the housing, and a side surface of the seal member facing the high-pressure chamber having an air inlet communicating with the cavity; the seal member is made of a shape memory alloy material, when a temperature difference between the cavity and the cold air chamber is less than a set value, a size of the air inlet remains unchanged, and when the temperature difference between the cavity and the cold air chamber is greater than the set value, the seal member automatically deforms to increase a size of the air inlet.

2. The gas turbine according to claim 1, characterized in that, the seal member includes an upper sealing plate, a lower sealing plate and a connecting side plate, the upper sealing plate and the lower sealing plate being stacked and spaced apart, the connecting side plate being connected between the upper sealing plate and the lower sealing plate, and the upper sealing plate, the lower sealing plate and the connecting side plate enclosing the cavity, and at least one of the upper sealing plate and the lower sealing plate having an air inlet communicating with the cavity.

3. The gas turbine according to claim 2, characterized in that, the upper sealing plate and the lower sealing plate are integrally formed.

4. The gas turbine according to claim 2, characterized in that, an inner side surface of the upper sealing plate includes an inclined surface, the inclined surface extending obliquely towards the lower sealing plate in a direction close to the exhaust port, and / or an inner side surface of the lower sealing plate includes an inclined surface, the inclined surface extending obliquely towards the upper sealing plate in a direction close to the exhaust port.

5. The gas turbine according to claim 2, characterized in that, A partition is provided on the side surface of the lower edge plate facing away from the main body, and the partition is located between the high-pressure chamber and the low-pressure chamber in the axial direction of the housing to separate the high-pressure chamber and the low-pressure chamber.

6. The gas turbine according to claim 5, wherein, the seal further includes a seal support plate, the seal support plate is connected to the side surface of the lower layer seal plate facing away from the upper layer seal plate, and the seal support plate is located between adjacent stationary blades in the circumferential direction of the housing and is fitted within the partition.

7. The gas turbine according to claim 1, wherein, the main body has a cold air passage, and the cold air passage communicates with the cold air inlet and the cold air source.

8. A double-layer seal, wherein, applied to the gas turbine according to any one of claims 1-7, comprising an upper layer seal plate, a lower layer seal plate and a connecting side plate, the upper layer seal plate and the lower layer seal plate are stacked and spaced apart, the connecting side plate is connected between the upper layer seal plate and the lower layer seal plate, and the upper layer seal plate, the lower layer seal plate and the connecting side plate can enclose a cavity, at least one side of the peripheral wall of the cavity has an exhaust port, and at least one of the upper layer seal plate and the lower layer seal plate has an air inlet communicating with the cavity.

9. A gas turbine, wherein, comprising the gas turbine according to any one of claims 1-7 or the double-layer seal according to claim 8.

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