Turbine seal assembly, turbine and gas turbine

Abstract

The application discloses a turbine sealing assembly, a turbine and a gas turbine, and relates to the technical field of turbine sealing assemblies, turbines and gas turbines. The turbine sealing assembly comprises a first piece, a second piece and a sealing piece, a fluid channel is arranged between the first piece and the second piece, at least one of the first piece and the second piece is provided with a groove, the groove is communicated with the fluid channel, and the opening size of the groove gradually decreases along the direction away from the fluid channel; the sealing piece is matched between the first piece and the second piece, the sealing piece divides the fluid channel into a cold gas section and a gas section, the cold gas section is used for the inflow of cold gas, the gas section is used for the inflow of gas, part of the sealing piece is matched in the groove, and the sealing piece can be deformed when the pressure and / or temperature of the cold gas and / or the gas changes. The turbine sealing assembly, the turbine and the gas turbine can avoid the situation that the parts on the cold gas side of the turbine are easily burnt and damaged, and the overall operation performance of the gas turbine is improved.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and more specifically, to a turbine sealing assembly, a turbine using the aforementioned turbine sealing assembly, and a gas turbine using the aforementioned turbine. Background Technology

[0002] The turbine is one of the most important components of a gas turbine, used to convert the internal energy of the high-temperature combustion gases produced in the combustion chamber into mechanical energy. However, in related technologies, the components on the cold-gas side of the gas turbine are easily burned and damaged, which reduces the overall operating performance of the gas turbine, as well as its safety and economy. Summary of the Invention

[0003] This invention is based on the inventor's discoveries and understanding of the following facts and problems:

[0004] In related technologies, a turbine includes moving blades and stationary blades. Taking the moving blade as an example, multiple circumferentially spaced retaining rings are provided on the outer periphery of the moving blade. These retaining rings are arranged in a ring shape. The inside of the retaining rings is used for the flow of high-temperature combustion gas, while the outside of the retaining rings is used for the flow of cool air. In related technologies, high-pressure cool air needs to be introduced between two adjacent retaining rings to prevent high-temperature combustion gas from flowing to the outside of the retaining rings. However, introducing high-pressure cool air results in excessive consumption of cool air, and the cool air is also prone to mixing with other cool air, reducing the overall operating performance of the gas turbine.

[0005] In related technologies, researchers considered installing a sealing strip at the interval between the two retaining rings to prevent high-temperature gas from flowing to the outside of the retaining rings. In this case, a gap would form between the sealing strip and the retaining rings, allowing cool air from the outside of the retaining rings to flow into the high-temperature gas side, thus blocking the high-temperature gas. However, in actual operating conditions, the pressure or temperature of the high-temperature gas varies with the unit load. When the pressure or temperature of the high-temperature gas is high, it can still flow into the cool air side through the gap, easily causing burns to components on the cool air side and reducing the overall operating performance of the gas turbine.

[0006] The present invention aims to at least partially solve one of the technical problems in the related art.

[0007] To address this, this invention provides a turbine sealing assembly that can prevent components on the cold gas side of the turbine from being easily burned and damaged, thereby improving the overall operating performance of the gas turbine.

[0008] This invention also proposes a turbine that uses the above-described turbine sealing assembly.

[0009] This invention also proposes a gas turbine that utilizes the aforementioned turbine.

[0010] The turbine sealing assembly of this invention includes:

[0011] A first piece and a second piece, wherein a fluid channel is provided between the first piece and the second piece, and at least one of the first piece and the second piece is provided with a groove, the groove communicating with the fluid channel, and the opening size of the groove gradually decreasing along the direction away from the fluid channel;

[0012] A sealing element, fitted between the first and second elements, divides the fluid passage into a cold air section and a gas flow section, the cold air section allowing cold air to flow in and the gas flow section allowing gas to flow in. A portion of the sealing element fits within the groove. The sealing element is deformable in response to changes in the pressure and / or temperature of the cold air and / or the gas, and is adapted to adjust the gap between the sealing element and the groove wall by deformation to prevent leakage of cold air from the cold air section to the gas flow section.

[0013] The turbine sealing assembly of this invention can prevent the components on the cold gas side of the turbine from being easily burned and damaged, thereby improving the overall operating performance of the gas turbine.

[0014] In some embodiments, there are two grooves, namely a first groove and a second groove. The first groove is disposed on the first piece, and the second groove is disposed on the second piece. One side of the sealing member is fitted in the first groove, and the other side of the sealing member is fitted in the second groove.

[0015] In some embodiments, the seal includes a first segment, a second segment, and a third segment, the third segment being connected between the first segment and the second segment, the first segment fitting within the first groove, the second segment fitting within the second groove, and at least one of the first segment, the second segment, and the third segment being deformable.

[0016] In some embodiments, the third segment is bendable and retractable, and the third segment is adapted to bend and retract when the pressure and / or temperature of the gas increases to pull the first segment out of the first slot and the second segment out of the second slot.

[0017] In some embodiments, the third section bulges into the cold gas section when the pressure and / or temperature of the gas increases.

[0018] In some embodiments, the first groove has a first groove width in the extension direction of the fluid channel, the first groove width gradually decreasing along the direction away from the fluid channel;

[0019] And / or, the second groove has a second groove width in the extension direction of the fluid channel, the second groove width gradually decreasing in the direction away from the fluid channel.

[0020] In some embodiments, the extension direction of the fluid channel is defined as a first direction, and the direction perpendicular to the first direction is defined as a second direction;

[0021] The first groove has a first inner wall and a second inner wall arranged opposite to each other. The width of the gap between the first inner wall and the second inner wall in the first direction forms the width of the first groove. The first inner wall and the second direction are at an angle, and the second inner wall and the second direction are parallel.

[0022] And / or, the second groove has a third inner wall and a fourth inner wall arranged opposite to each other, the spacing width of the third inner wall and the fourth inner wall in the first direction forming the width of the second groove, the third inner wall and the second direction forming an angle, and the fourth inner wall and the second direction being parallel.

[0023] In some embodiments, the seal has a phase change temperature that is consistent with a lower limit of the temperature of the gas.

[0024] In some embodiments, the material of the seal is one or more of nickel-titanium alloy, nickel-cobalt alloy, copper-zinc alloy, and titanium-platinum alloy.

[0025] The turbine in this embodiment of the invention includes a turbine sealing assembly, which is the turbine sealing assembly described in any of the above embodiments.

[0026] In some embodiments, the turbine includes a stationary blade comprising a plurality of blades arranged circumferentially spaced apart, wherein one of two adjacent blades forms a first element and the other forms a second element, and the interval between two adjacent blades forms the fluid passage.

[0027] In some embodiments, the blade includes a blade body, an outer end plate, and an inner end plate. The blade body is connected between the outer end plate and the inner end plate. A sealing element is provided between the outer end plates of two adjacent blades, and a sealing element is provided between the inner end plates of two adjacent blades. The space between the outer end plate and the inner end plate is used for gas to pass through.

[0028] In some embodiments, the turbine includes a moving blade and a retaining ring, the retaining ring surrounding the outer periphery of the moving blade, the retaining ring including a plurality of sub-retaining rings arranged circumferentially spaced, one of two adjacent sub-retaining rings forming the first piece and the other forming the second piece, the interval between two adjacent sub-retaining rings forming the fluid passage.

[0029] The gas turbine in this embodiment of the invention includes a turbine, which is the turbine described in any of the above embodiments. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the extension of the sealing element of the turbine sealing assembly according to an embodiment of the present invention. Figure 1 .

[0031] Figure 2 This is a schematic diagram of the extension of the sealing element of the turbine sealing assembly according to an embodiment of the present invention. Figure 2 .

[0032] Figure 3 This is a schematic diagram of the shrinkage of the seal element in the turbine sealing assembly according to an embodiment of the present invention. Figure 1 .

[0033] Figure 4 This is a schematic diagram of the shrinkage of the seal element in the turbine sealing assembly according to an embodiment of the present invention. Figure 2 .

[0034] Figure 5 This is a three-dimensional schematic diagram of the turbine stator blade according to an embodiment of the present invention.

[0035] Figure 6 yes Figure 5 A schematic diagram of the central static leaf.

[0036] Figure 7 yes Figure 6 A cross-sectional view of the middle static blade.

[0037] Figure 8 This is a three-dimensional schematic diagram of the turbine's moving blade and retaining ring according to an embodiment of the present invention.

[0038] Figure 9 yes Figure 8 Front view schematic diagram of the moving blade and the retaining ring.

[0039] Figure 10 This is a schematic diagram of the assembly of a portion of the moving blade and retaining ring of a turbine according to an embodiment of the present invention.

[0040] Figure label:

[0041] First item 1;

[0042] The second item 2;

[0043] Fluid passage 3; Cooling section 31; Gas section 32;

[0044] Groove 4; First groove 41; First inner wall 411; Second inner wall 412; Second groove 42; Third inner wall 421; Fourth inner wall 422;

[0045] Seal 5; First section 51; Second section 52; Third section 53; First seal 501; Second seal 502;

[0046] Blade 6; outer end plate 61; blade 62; inner end plate 63;

[0047] 7. Moving leaves;

[0048] 8. Sub-ring. Detailed Implementation

[0049] 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.

[0050] like Figures 1 to 4 As shown, the turbine sealing assembly of this embodiment of the invention includes a first component 1, a second component 2, and a sealing component 5.

[0051] A fluid channel 3 is provided between the first piece 1 and the second piece 2, and at least one of the first piece 1 and the second piece 2 is provided with a groove 4, which communicates with the fluid channel 3, and the opening size of the groove 4 gradually decreases along the direction away from the fluid channel 3.

[0052] like Figure 1 As shown, the first piece 1 and the second piece 2 can be arranged at intervals in the left and right directions. The interval between the first piece 1 and the second piece 2 forms a fluid channel 3, which can be used for airflow or liquid flow.

[0053] Both the first component 1 and the second component 2 can have grooves 4, meaning there are two grooves 4: a first groove 41 and a second groove 42. The first groove 41 is located in the first component 1, and the second groove 42 is located in the second component 2. The left side of the sealing element 5 can fit into the first groove 41, and the right side of the sealing element 5 can fit into the second groove 42. Figure 1 As shown, the first groove 41 can be located on the right side of the first piece 1 with its opening facing the right, and the second groove 42 can be located on the left side of the second piece 2 with its opening facing the left. Both the first groove 41 and the second groove 42 are connected to the fluid channel 3.

[0054] It should be noted that the groove depth of the first groove 41 and the groove depth of the second groove 42 can both be arranged along the left and right direction. The opening size of the groove 4 can be the opening size of the groove 4 in a vertical plane perpendicular to the left and right direction. The opening size of the first groove 41 gradually increases from left to right, and the opening size of the second groove 42 gradually increases from right to left.

[0055] It is understood that in some other embodiments, the groove 4 may be provided only on the first piece 1 or the second piece 2. For example, the groove 4 may be provided on the first piece 1, one side of the seal 5 may fit into the groove 4 of the first piece 1, and the other side of the seal 5 may be connected to the second piece 2.

[0056] The seal 5 fits between the first piece 1 and the second piece 2. The seal 5 divides the fluid channel 3 into a cold air section 31 and a gas section 32. The cold air section 31 allows cold air to flow in, and the gas section 32 allows gas to flow in. Part of the seal 5 fits in the groove 4. The seal 5 can deform when the pressure and / or temperature of the cold air and / or gas changes. The seal 5 is adapted to adjust the gap between the seal 5 and the groove wall of the groove 4 by deformation to prevent the leakage of cold air from the cold air section 31 to the gas section 32.

[0057] Specifically, such as Figure 1 and Figure 2 As shown, the left side of the seal 5 can be inserted into the first groove 41, and the right side of the seal 5 can be inserted into the second groove 42. Along the vertical direction, the seal 5 divides the fluid channel 3 into two sections: a cold air section 31 and a gas section 32. The cold air section 31 can be located above the gas section 32. In use, the upper side of the seal 5 allows for the flow of cold air, with some cold air flowing into the cold air section 31. The lower side of the seal 5 allows for the flow of high-temperature gas, with some gas flowing into the gas section 32. The seal 5 provides a certain degree of sealing, effectively separating the cold air and gas.

[0058] The seal 5 can be made of a shape memory alloy; for example, the shape of the seal 5 can change with temperature. When the gas temperature is low, such as... Figure 1 and Figure 2 As shown, at this time, the seal 5 can be in a flat state. The left side of the seal 5 can extend into the first groove 41, and the right side of the seal 5 can extend into the second groove 42. At this time, the gap between the seal 5 and the groove wall of the first groove 41 is small, and the gap between the seal 5 and the groove wall of the second groove 42 is also small. The gap formed allows some cold air to pass through and flow into the gas section 32. The cold air flowing into the gas section 32 will form a barrier to the gas, thereby preventing the gas from intruding into the cold air section 31 or even the upper side of the seal 5.

[0059] When the gas temperature rises, such as Figure 3 and Figure 4 As shown, the seal 5 will shrink and deform with the change of temperature, that is, the seal 5 can shrink into the fluid channel 3. The gap between the groove wall of the first groove 41 and the left side of the seal 5, and the gap between the groove wall of the second groove 42 and the right side of the seal 5 will become larger. As a result, more cold air can flow into the gas section 32 from the gap and achieve the blocking of the gas.

[0060] As cold air enters the gas section 32, the seal 5 will be enclosed within the cold air, meaning the ambient temperature of the seal 5 will decrease. Under the influence of the cold air, the seal 5 will flatten again and return to its original position. Figure 1 and Figure 2 The seal 5 will deform cyclically as the temperature of the gas changes, thus automatically adjusting the amount of cold gas leakage.

[0061] In other embodiments, the seal 5 can also deform with changes in the temperature of the cold air. For example, when the temperature of the cold air decreases, the seal 5 can flatten, thereby reducing the gap between the seal 5 and the groove wall of the groove 4, achieving a blocking effect with a small amount of cold air at a lower temperature. When the temperature of the cold air increases, the seal 5 can contract, thereby increasing the gap between the seal 5 and the groove wall of the groove 4, achieving a blocking effect with a larger amount of cold air at a higher temperature.

[0062] In the turbine sealing assembly of this invention, when the sealing element 5 deforms, it can cooperate with the groove 4 to adjust the gap between the sealing element 5 and the groove wall of the groove 4. This allows the amount of cold gas leaking from the gap to automatically adapt to changes in gas temperature or pressure, thereby enabling the amount of leaked cold gas to automatically adapt to changes in the gas turbine load. This avoids the situation where gas intrusion on the cold gas side is easily caused when the gas temperature or pressure of the gas turbine changes, and thus avoids the situation where the components on the cold gas side of the turbine are easily burned and damaged, thereby protecting the turbine components and improving the overall operating performance of the gas turbine.

[0063] In some embodiments, the seal 5 includes a first segment 51, a second segment 52 and a third segment 53, the third segment 53 being connected between the first segment 51 and the second segment 52, the first segment 51 fitting within a first groove 41, the second segment 52 fitting within a second groove 42, and at least one of the first segment 51, the second segment 52 and the third segment 53 being deformable.

[0064] like Figure 3 As shown, in the left-right direction, the seal 5 includes a first segment 51, a second segment 52, and a third segment 53, wherein the third segment 53 is located in the middle, the first segment 51 is located to the left of the third segment 53, and the second segment 52 is located to the right of the third segment 53. Figure 3 As shown, the first segment 51, the second segment 52, and the third segment 53 can all be formed by shape memory alloy. When in use, the first segment 51, the second segment 52, and the third segment 53 can all deform with the temperature change of the gas. This can enhance the deformation sensitivity of the seal 5, that is, under the same temperature difference, the seal 5 has a larger deformation range, which improves the flexibility of adjustment.

[0065] It is understood that in some other embodiments, only the first segment 51, the second segment 52, or the third segment 53 may be formed by shape memory alloy; or the first segment 51 and the second segment 52 may be formed by shape memory alloy, while the third alloy may not be deformable.

[0066] In some embodiments, the third segment 53 is bendable and retractable, and the third segment 53 is adapted to bend and retract when the pressure of the gas increases and / or the temperature rises to pull the first segment 51 out of the first groove 41 and the second segment 52 out of the second groove 42.

[0067] like Figure 3 As shown, only the third segment 53 of the seal 5 can be bent and deformed. For example, when the temperature of the gas rises, the seal 5 can bend towards the center, and the first segment 51 and the second segment 52 will have relative displacement. That is, the first segment 51 can be pulled out from the first groove 41, and the second segment 52 can be pulled out from the second groove 42. Since the opening size of the first groove 41 and the opening size of the second groove 42 are both different, the gap between the first segment 51 and the groove wall of the first groove 41, and the gap between the second segment 52 and the groove wall of the second groove 42 will also change. This allows more cold air to flow into the gas section 32 of the fluid channel 3 from the gaps, thus blocking the gas.

[0068] Because the first segment 51 and the second segment 52 are not deformable, the guiding nature of the assembly of the first segment 51 and the first groove 41 can be guaranteed, as can the guiding nature of the assembly of the second segment 52 and the second groove 42. This avoids the situation where the first segment 51 is easily contacted and interfered with by the groove wall of the first groove 41 when it is deformed, and also avoids the situation where the second segment 52 is easily contacted and interfered with by the groove wall of the second groove 42 when it is deformed.

[0069] In some embodiments, when the pressure and / or temperature of the gas increases, the third section 53 bulges into the cold gas section 31. For example... Figure 3 and Figure 4 As shown, when the third section 53 rises into the cold air section 31, the resulting rise can guide the direction of the cold air flow, and the cold air can be divided into two parts at the rise. One part can be guided into the first groove 41 by the action of the left slope of the rise, and the other part can be guided into the second groove 42 by the action of the right slope of the rise, which facilitates the balanced distribution of cold air into the first groove 41 or the second groove 42.

[0070] In addition, it also avoids the situation where when the third section 53 bulges into the gas section 32, a pit will form on the side of the third section 53 facing the cold air section 31, and the pit will reflect the cold air upwards. This avoids the problem that the cold air in the upper part of the third section 53 can easily cause airflow interference and affect the leakage of cold air into the gas section 32.

[0071] In some embodiments, the first groove 41 has a first groove width in the extending direction (vertical direction) of the fluid channel 3, and the first groove width gradually decreases along the direction away from the fluid channel 3. For example... Figure 4 As shown, the width of the first slot can be considered as L1, and the width of the first slot gradually increases from left to right. This simplifies the arrangement of the first slot 41, ensuring that the gap between the first segment 51 and the wall of the first slot 41 remains consistent along the front-to-back direction (perpendicular to the page direction), thus facilitating the consistency and balance of cold air flow in the front-to-back direction.

[0072] In other embodiments, the second groove 42 has a second groove width in the extending direction of the fluid channel 3, and the second groove width gradually decreases along the direction away from the fluid channel 3. For example... Figure 4 As shown, the width of the second slot can be considered as L2, and the width of the second slot gradually increases from right to left. This simplifies the arrangement of the second slot 42, ensuring that the gap between the walls of the second segment 52 and the second slot 42 remains consistent along the front-to-back direction (perpendicular to the page direction), thus facilitating the consistency and balance of cold air flow in the front-to-back direction.

[0073] In some embodiments, the extending direction of the fluid channel 3 is defined as a first direction, and the direction perpendicular to the first direction is defined as a second direction. For example... Figure 2 As shown, the first direction can be up and down, and the second direction can be left and right.

[0074] The first groove 41 has a first inner wall 411 and a second inner wall 412 arranged opposite to each other. The width of the gap between the first inner wall 411 and the second inner wall 412 in a first direction forms the width of the first groove. The first inner wall 411 is at an angle to the second direction, that is, the first inner wall 411 is generally inclined from the lower left to the upper right, and the second inner wall 412 is parallel to the second direction, that is, the second inner wall 412 is generally located in the horizontal plane. Therefore, when the seal 5 deforms, the gap between the first segment 51 and the second inner wall 412 can remain largely unchanged, while the gap between the second segment 52 and the first inner wall 411 can increase. This allows more cold air to flow into the first groove 41, while the inflow of high-temperature gas can remain basically unchanged, thus regulating the amount of cold air leakage and further ensuring the blocking effect on high-temperature gas.

[0075] In other embodiments, the second groove 42 has a third inner wall 421 and a fourth inner wall 422 arranged opposite to each other. The width of the gap between the third inner wall 421 and the fourth inner wall 422 in the first direction forms the width of the second groove. The third inner wall 421 forms an angle with the second direction, that is, the third inner wall 421 is generally inclined from the upper left to the lower right, and the fourth inner wall 422 is parallel to the second direction, that is, the fourth inner wall 422 is generally located in the horizontal plane. Thus, when the seal 5 deforms, the gap between the second segment 52 and the fourth inner wall 422 can remain largely unchanged, while the gap between the second segment 52 and the third inner wall 421 can increase. This allows more cold air to flow into the second groove 42, while the inflow of high-temperature gas can remain basically unchanged, thus regulating the amount of cold air leakage and further ensuring the blocking effect on high-temperature gas.

[0076] In some embodiments, the seal 5 has a phase change temperature, which coincides with the lower limit of the gas temperature. Specifically, the seal 5 can be made of a shape memory alloy, and the phase change temperature of the seal 5 is the temperature at which the seal 5 begins to deform from its initial state. This phase change temperature can be consistent with the lowest temperature of the gas. Thus, when the gas temperature is at its lowest, the seal 5 is in a fully flattened state. When the gas temperature increases, the seal 5 will deform accordingly, ensuring that the deformation adjustment of the seal 5 is largely synchronized with the gas temperature change. This avoids the situation where the seal 5 cannot adjust the gap through deformation when the gas temperature changes.

[0077] In some embodiments, the seal 5 is made of one or more of nickel-titanium alloy, nickel-cobalt alloy, copper-zinc alloy, and titanium-platinum alloy. In other embodiments, the first segment 51, the second segment 52, and the third segment 53 of the seal 5 can be made of different shape memory alloys. For example, the first segment 51 and the second segment 52 can be made of nickel-titanium alloy, and the third segment 53 can be made of titanium-platinum alloy. This allows for the achievement of different deformation performance requirements at different locations of the seal 5.

[0078] The turbine according to an embodiment of the present invention is described below.

[0079] The turbine in this embodiment of the invention includes a turbine sealing assembly, which can be the turbine sealing assembly described in the above embodiments. The turbine sealing assembly of this embodiment can prevent the components on the cold air side of the turbine from being easily burned and damaged, thus improving the overall operating performance of the turbine.

[0080] In some embodiments, such as Figures 5 to 7As shown, the turbine includes a stationary blade, which is circular in shape and comprises multiple blades 6. The multiple blades 6 are arranged circumferentially at intervals, meaning that the stationary blade can be assembled by arranging the multiple blades 6 at circumferential intervals. One of two adjacent blades 6 forms a first component 1, and the other forms a second component 2. The interval between two adjacent blades 6 forms a fluid channel 3.

[0081] In some embodiments, such as Figures 5 to 7 As shown, the blade 6 includes a blade body 62, an outer end plate 61, and an inner end plate 63. The blade body 62 is connected between the outer end plate 61 and the inner end plate 63. A sealing element 5 is provided between the outer end plates 61 of two adjacent blades 6, and a sealing element 5 is provided between the inner end plates 63 of two adjacent blades 6. The space between the outer end plate 61 and the inner end plate 63 is used for gas to pass through.

[0082] like Figure 7 As shown, for ease of description, the seal 5 between two adjacent outer end plates 61 is referred to as the first seal 501, and the seal 5 between two adjacent inner end plates 63 is referred to as the second seal 502. During turbine operation, as... Figure 5 As shown, the gas can flow through the space enclosed by the first seal 501, the second seal 502, and the two adjacent blades 62, while the inner and outer sides of the stationary blade can be circulated by cold air. The first seal 501 can prevent the gas from flowing into the outer side of the stationary blade, and the second seal 502 can prevent the gas from flowing into the inner side of the stationary blade.

[0083] Optionally, during use, the third section 53 of the first seal 501 can protrude outwards, and the third section 53 of the second seal 502 can protrude inwards. This facilitates the leakage of cold air from the inside and outside of the stationary vane to the combustion chamber.

[0084] In some embodiments, such as Figures 8 to 10 As shown, the turbine includes a moving blade 7 and a retaining ring. The retaining ring surrounds the outer periphery of the moving blade 7 and includes a plurality of sub-retaining rings 8. The plurality of sub-retaining rings 8 are arranged circumferentially at intervals. One of two adjacent sub-retaining rings 8 forms a first piece 1 and the other forms a second piece 2. The interval between two adjacent sub-retaining rings 8 forms a fluid channel 3.

[0085] like Figure 10 As shown, the retaining ring can be suspended inside the holding ring, the moving blade 7 can rotate inside the retaining ring, and the gas can flow in the annular space between the moving blade 7 and the retaining ring. The sealing element 5 between two adjacent sub-retaining rings 8 can prevent the gas from entering the outer side of the retaining ring, thus protecting the components on the outer periphery of the retaining ring.

[0086] The gas turbine of an embodiment of the present invention is described below.

[0087] The gas turbine in this embodiment of the invention includes a turbine, which can be the turbine described in the above embodiments. The turbine in this embodiment of the invention can prevent the components on the cold gas side from being burned and damaged by the high-temperature gas, thus ensuring the overall operating performance of the gas turbine.

[0088] 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.

[0089] 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 technical features indicated. 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.

[0090] 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.

[0091] 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.

[0092] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the 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.

[0093] Although the above embodiments have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Any changes, modifications, substitutions and variations made to the above embodiments by those skilled in the art are within the protection scope of the present invention.

Claims

1. A turbine seal assembly comprising: The application relates to a sealing device for a fluid channel, comprising: a first piece and a second piece, a fluid channel being arranged between the first piece and the second piece, and at least one of the first piece and the second piece being provided with a groove, the groove being in communication with the fluid channel, and the opening size of the groove gradually decreasing in a direction away from the fluid channel; a sealing piece being arranged between the first piece and the second piece, the sealing piece separating the fluid channel into a cold gas section and a fuel gas section, the cold gas section being capable of allowing cold gas to flow in, and the fuel gas section being capable of allowing fuel gas to flow in, part of the sealing piece being arranged in the groove, the sealing piece being capable of deforming when the pressure and / or temperature of the cold gas and / or the fuel gas changes, and the sealing piece being adapted to adjust the gap size between the sealing piece and the groove wall of the groove by deforming to prevent the cold gas in the cold gas section from leaking into the fuel gas section; the groove has two grooves, i.e. a first groove and a second groove, the first groove being arranged in the first piece, and the second groove being arranged in the second piece, one side of the sealing piece being arranged in the first groove, and the other side of the sealing piece being arranged in the second groove.

2. The turbine seal assembly of claim 1, wherein, the sealing piece comprises a first section, a second section and a third section, the third section being connected between the first section and the second section, the first section being arranged in the first groove, and the second section being arranged in the second groove, at least one of the first section, the second section and the third section being capable of deforming.

3. The turbine seal assembly of claim 2, wherein, the third section is capable of bending and shrinking, and the third section is adapted to bend and shrink to pull the first section out of the first groove and the second section out of the second groove when the pressure of the fuel gas increases and / or the temperature of the fuel gas increases.

4. The turbine seal assembly of claim 3, wherein, the third section bulges into the cold gas section when the pressure of the fuel gas increases and / or the temperature of the fuel gas increases.

5. The turbine seal assembly of claim 1, wherein, the first groove has a first groove width in the extension direction of the fluid channel, and the first groove width gradually decreases in a direction away from the fluid channel; and / or, the second groove has a second groove width in the extension direction of the fluid channel, and the second groove width gradually decreases in a direction away from the fluid channel.

6. The turbine seal assembly of claim 5, wherein, the extension direction of the fluid channel is defined as a first direction, and a direction perpendicular to the first direction is defined as a second direction; the first groove has oppositely arranged first and second inner walls, the interval width of the first and second inner walls in the first direction forming the first groove width, the first inner wall and the second direction forming an angle, and the second inner wall being parallel to the second direction; and / or, the second groove has oppositely arranged third and fourth inner walls, the interval width of the third and fourth inner walls in the first direction forming the second groove width, the third inner wall and the second direction forming an angle, and the fourth inner wall being parallel to the second direction.

7. The turbine seal assembly of claim 1, wherein, the sealing piece has a phase transition temperature, and the phase transition temperature is consistent with the lower limit value of the temperature of the fuel gas.

8. The turbine seal assembly of any one of claims 1-7, wherein, the material of the sealing piece is one or more of nickel-titanium alloy, nickel-cobalt alloy, copper-zinc alloy and titanium-platinum alloy.

9. A turbine characterized by A turbine seal assembly comprising the turbine seal assembly according to any one of claims 1-8.

10. The turbine of claim 9 wherein, A stationary vane comprising a plurality of vanes, the plurality of vanes being circumferentially spaced apart, one of two adjacent vanes forming the first piece and the other forming the second piece, the spacing between the two adjacent vanes forming the fluid passage.

11. The turbine of claim 10 wherein, The vanes comprise a blade body, an outer end plate and an inner end plate, the blade body being connected between the outer end plate and the inner end plate, a seal being provided between the outer end plates of two adjacent vanes and a seal being provided between the inner end plates of two adjacent vanes, the outer end plate and the inner end plate being for the passage of combustion gas therebetween.

12. The turbine of claim 9 wherein, A rotor blade and a shroud, the shroud being annularly arranged on an outer circumferential side of the rotor blade, the shroud comprising a plurality of sub-shrouds, the plurality of sub-shrouds being circumferentially spaced apart, one of two adjacent sub-shrouds forming the first piece and the other forming the second piece, the spacing between the two adjacent sub-shrouds forming the fluid passage.

13. A gas turbine engine characterized by, A turbine comprising the turbine according to any one of claims 9-12.

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