A seal assembly between a vane and a support ring

Abstract

The application provides a sealing assembly between a stationary vane and a support ring, the stationary vane (1) and the support ring (2) define an airflow channel, the airflow channel has an assembly gap formed by cooperation of the stationary vane (1) and the support ring (2), and the sealing assembly is used for sealing the assembly gap, and the sealing assembly comprises: a first nest (3) fixed on a blade root of the stationary vane (1); a second nest (5) fixed on the support ring (2); and a sealing body (4) installed between the first nest (3) and the second nest (5), and the sealing body (4) is radially compressively deformed to seal the assembly gap of the stationary vane (1) and the support ring (2) by itself. The sealing assembly adopts a radial press-fitting installation mode, does not need to use additional auxiliary installation materials, and reduces installation difficulty.

Description

Technical Field

[0001] This invention relates to a gas turbine, and more specifically, to a radial sliding self-sealing assembly between a stator blade and a support ring. Background Technology

[0002] The high-temperature components of heavy-duty gas turbines can operate at temperatures exceeding 1,000 degrees Celsius because they are cooled by air. To ensure sufficient air is delivered to the cooled components, highly effective sealing components are required for the cooling channels.

[0003] In existing technologies, as heavy-duty gas turbines operate, the sealing components experience wear due to sliding, leading to increasing leakage. The sealing components can even be damaged, creating foreign objects in the hot passages, damaging the blades, and affecting the unit's safety and reliability. Current technologies employ axial installation of the sealing components, while radial installation requires extremely high precision and necessitates the use of auxiliary fixing agents. Without these agents, the sealing components can be damaged during insertion, reducing their sealing performance.

[0004] In the prior art, patent CN107131009B provides a self-locking sealing structure to improve the axial clearance between rotating and stationary components inside a turbomachinery. A sealing ring is installed between a rotating disk and a support ring, and a honeycomb ring is installed outside the sealing ring. The sealing ring has a rotating cavity with an opening facing the rotating disk. One path of cooling sealing air from the air system enters the rotating cavity of the sealing ring through the meshing tooth gap between the blades and the rotating disk. Another path of sealing air enters the rotating cavity tangentially under the guidance of the concave arc structure of the rotating disk. After the two paths of cooling sealing air merge in the rotating cavity, they enter the main flow channel through the axial clearance between the honeycomb ring and the rotating disk. The rotating disk has a concave arc structure at the low radius of the assembly meshing tooth groove, and the tangential extension of the top end of the arc structure intersects the rotating cavity of the sealing ring. This patent improves the sealing effect of the axial clearance to a certain extent, but the sealing structure provided by this patent cannot automatically adjust according to thermal expansion or vibration during the thermal expansion of the support ring and the rotating disk, thus the sealing effect is not effective.

[0005] To address the above problems, this invention provides a solution. Summary of the Invention

[0006] The main objective of this invention is to provide a radial sliding self-sealing structure, the compression ratio of which can be adaptively adjusted to solve the problems in the prior art.

[0007] To achieve the above objectives, according to one aspect of the present invention, a sealing assembly between a stationary blade and a support ring is provided. The stationary blade and the support ring define an airflow channel, and the airflow channel has an assembly gap formed by the mating of the stationary blade and the support ring. The sealing assembly is used to seal the assembly gap. The sealing assembly includes: a first nest fixed to the root of the stationary blade; a second nest fixed to the support ring; and a sealing body installed between the first and second nests. The sealing body is radially compressible to self-seal the assembly gap between the stationary blade and the support ring. This sealing assembly adopts a radial press-fit installation method, which differs from the traditional axial sealing method. This radial sealing groove sealing assembly structure does not require additional auxiliary installation materials, reducing the installation difficulty.

[0008] Furthermore, the radial compression of the sealing body can be adaptively adjusted according to the expansion and / or position changes of the stator and support ring. This adaptive adjustment capability of the sealing body ensures good sealing performance of the sealing assembly during operation.

[0009] Furthermore, the second nest and the first nest are arranged radially opposite each other, and the sealing body generates radial compression under the action of the second nest and the first nest to achieve self-sealing.

[0010] Furthermore, the second nest and the first nest generate a relative radial displacement between each other, with the value of the relative displacement being Δx, and the compression amount is adaptively adjusted according to the displacement value.

[0011] Furthermore, the relative displacement between the second nest and the first nest is generated by the thermal expansion force of the stationary blade and the support ring.

[0012] Furthermore, the relative displacement between the second nest and the first nest is generated by the vibration force of the stationary blade and the support ring.

[0013] Furthermore, the sealing body has a pre-compression amount during initial installation, which can increase the sealing contact stress.

[0014] Furthermore, the sealing body is positioned between the second nest and the first nest. Under the action of the second nest and the first nest, the sealing body slides relative to the second nest and the first nest and generates radial compression.

[0015] Furthermore, the first nest includes a first mounting groove, and the second nest includes a second mounting groove, with the first and second mounting grooves accommodating the sealing body.

[0016] Furthermore, the first mounting groove has a first inclined surface and a second inclined surface, the first and second inclined surfaces forming a first included angle α; and / or the second mounting groove has a third inclined surface and a fourth inclined surface, the third and fourth inclined surfaces forming a second included angle β. The self-sealing assembly of the present invention comprises fewer parts, and the sealing body achieves sealing of the assembly gap between the stator blade and the support ring by cooperating with the double inclined surfaces of the first and second nested parts. Moreover, under the thermal expansion of a heavy fuel turbine, the sealing body and the double inclined surfaces adaptively deform to achieve a good seal, with lower requirements for the installation process.

[0017] Furthermore, the values ​​of the first included angle α and the second included angle β are related to the compression ratio ε, where the compression amount of the sealing body is the ratio of the initial volume of the sealing body to the compression ratio ε.

[0018] Furthermore, the sealing body is a sphere with a diameter of D.

[0019] Furthermore, the first included angle α = sin -1 ((2×D×ε) / Δx), and / or the second included angle β=sin -1 ((2×D×ε) / Δx).

[0020] Furthermore, the first included angle α is equal to the second included angle β.

[0021] Furthermore, the compression ratio ε is 5%-25%.

[0022] Furthermore, the sealing body is a spherical metal braid.

[0023] Furthermore, the metal braided component includes metal braided rope.

[0024] Furthermore, the first nest has a T-shaped cross-section and is installed into the blade root along the circumferential direction of the blade root; and / or the second nest has a T-shaped cross-section and is installed into the support ring along the circumferential direction of the support ring.

[0025] Furthermore, the first nest includes a long side end and a short side end, a first mounting groove is disposed at the short side end, and the opening direction of the first included angle α formed by the first inclined surface and the second inclined surface of the first mounting groove is toward the joint surface of the first nest and the second nest; and / or the second nest includes a long side end and a short side end, a second mounting groove is disposed at the short side end, and the opening direction of the second included angle β formed by the third inclined surface and the fourth inclined surface of the second mounting groove is toward the joint surface of the first nest and the second nest.

[0026] Applying the technical solution of this invention, the radial sliding self-sealing structure between the gas turbine turbine turbine blades and the annular support ring of this invention, through the design of a radial sealing groove and the addition of a double-inclined nested structure, forms a self-sealing inclined surface, achieving zero leakage at this point. The structural features of the sealing assembly of this invention allow for serialized design; the first and second nests can be used with sealing assemblies of various diameters. Furthermore, the sealing groove of this invention is a radial seal, unlike axial seals, eliminating the need for a fixing compressive agent and reducing damage to the sealing ropes during installation. Attached Figure Description

[0027] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0028] Figure 1 A schematic diagram of a radially sliding self-sealing structure of an annular transparent vane and a support ring according to the present invention is shown in operation; and

[0029] Figure 2 It shows Figure 1 CC section view;

[0030] Figure 3 It shows Figure 2 A magnified view of a portion of the image.

[0031] The above figures include the following reference numerals:

[0032] 1. Stationary blade; 2. Support ring; 3. First nest; 4. Sealing body; 5. Second nest; 6. First mounting groove; 7. Second mounting groove; α, First included angle; β, Second included angle. Detailed Implementation

[0033] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0034] The present invention will be further described in detail below with reference to specific embodiments. These embodiments should not be construed as limiting the scope of protection claimed by the present invention. The term "comprising" indicates the presence of a feature, but does not exclude the presence or addition of one or more other features. The terms "lateral," "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for ease of description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention. In addition, the terms "first," "second," etc., are used to distinguish different objects, not to describe a specific order.

[0035] In this description, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances. Furthermore, in the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0036] The high-temperature components of heavy-duty gas turbines can operate at temperatures exceeding 1,000 degrees Celsius because they employ air cooling measures. The design of the cooling configuration is crucial to ensuring sufficient air is delivered to the cooled components. The sealing structure of the cooling channels is key to guaranteeing effective cooling.

[0037] like Figures 1-3 As shown, the cooling airflow channel formed by the stationary blade 1 and the support ring 2 is part of the cooling channel between the stationary blade 1 and the moving blade, with the cooling airflow flowing from A to B. This airflow channel passes through the stationary blade 1 and the support ring 2. If the assembly gap between the stationary blade 1 and the support ring 2 cannot be sealed well, airflow leakage will occur, and the cooling airflow will flow from A to C. To ensure good cooling effect, it is necessary to prevent the cooling airflow from A to C. Therefore, a sealing component with good sealing effect needs to be designed to seal the assembly gap.

[0038] The sealing assembly provided by this invention is a radially sliding self-sealing structure between a transparent stator blade 1 and an annular support ring 2, capable of sealing the assembly gap between the stator blade 1 and the support ring 2. This sealing assembly adopts a radial press-fit insertion method, comprising: a first nest 3 fixed to the blade root; a second nest 5 fixed to the support ring 2; and a sealing body 4 installed between the first nest 3 and the second nest 5. The sealing body 4 is used to seal the designed gap formed by the first nest 3 and the second nest 5, thereby sealing the assembly gap between the stator blade 1 and the support ring 2. The sealing body 4 is radially compressible to increase the sealing contact stress required for sealing, thereby reducing the leakage of cooling air and sealing the cooling airflow channel formed by the stator blade 1 and the support ring 2, achieving a good cooling effect for high-temperature components. In this sealing assembly, the first nest 3 is installed on the blade root of the stator blade 1, and the second nest 5 is installed on the support ring 2. The first nest 3, the second nest 5, and the sealing body 4 form a radial press-fit installation method. Unlike traditional axial sealing methods, this radial sealing groove sealing assembly structure does not require additional auxiliary installation materials, reducing installation difficulty. When the self-sealing assembly seals the airflow channel, the sealing body 4 installed between the first nest 3 and the second nest 5 has a pre-compression amount during initial installation. This pre-compression amount can provide sealing contact stress and improve the reliability of the seal.

[0039] The compression of the sealing body 4 can be adaptively adjusted under external force, which can be the thermal expansion force or vibration force of the stationary vane 1 and the support ring 2. That is, the radial compression of the sealing body 4 can be adaptively adjusted according to the change in expansion difference caused by the temperature difference between the stationary vane 1 and the support ring 2, or it can be adaptively adjusted according to the positional improvement caused by the vibration of the stationary vane 1 and the support ring 2. Under the action of external force, the displacement value of the second nest 5 relative to the first nest 3 is Δx. Under the action of the relative displacement between the second nest 5 and the first nest 3, the compression is adaptively adjusted according to the displacement value Δx. For different heavy-duty gas turbines, the displacement value Δx is different, ranging from 1 to 3 mm. The adaptive adjustment performance of the sealing body ensures good sealing performance of the sealing assembly in the working state.

[0040] The sealing body 4 is disposed between the second nest 5 and the first nest 3. Under the action of the second nest 5 and the first nest 3, the sealing body 4 slides relative to the second nest 5 and the first nest 3 and generates radial compression.

[0041] The sealing body 4 is a sphere with a diameter of D, and can be made of metal braided components, such as metal braided rope. The ratio of the compression amount of the sealing body 4 to its initial volume is called the compression ratio ε. The compression ratio ε is a range value, from min% to max%. The minimum value min is 5-8, and the maximum value max is 15-25. Its value is related to the diameter D of the sealing body 4; the larger the diameter D, the larger the value of the compression ratio ε.

[0042] like Figure 3 As shown, the first nest 3 and the second nest 5 are arranged opposite to each other. The sealing body 4 generates radial compression under the action of the second nest 5 and the first nest 3 to achieve self-sealing. The second nest 5 and the first nest 3 generate relative radial displacement between each other, the value of which is Δx. The compression is adaptively adjusted according to the displacement value. The relative displacement between the second nest 5 and the first nest 3 is generated by the thermal expansion force of the stationary blade 1 and the support ring 2, or it can be generated by the vibration force of the stationary blade 1 and the support ring 2.

[0043] The first nest 3 and the second nest 5 each include a first mounting groove 6 and a second mounting groove 7. The first mounting groove 6 and the second mounting groove 7 are used to accommodate the sealing body 4. The first mounting groove 6 has a first inclined surface and a second inclined surface, forming a first included angle α; and / or the second mounting groove 7 has a third inclined surface and a fourth inclined surface, forming a second included angle β. By providing the first nest 3 and the second nest 5 on the stationary blade 1 and the support ring 2, and through the double-inclined nesting structure of the first mounting groove 6 and the second mounting groove 7, the sealing body 4 can be pre-compressed during the installation of the sealing assembly, providing sealing contact stress. When the heavy-duty gas turbine operates at high temperatures, a relative expansion difference occurs between the gas turbine stationary blade 1 and the support ring 2, resulting in a relative displacement between the first nest 3 and the second nest 5, further compressing the sealing body 4 to achieve adaptive adjustment of the compression ratio ε of the compression body. It can be seen that the self-sealing assembly of the present invention includes only a few parts, and the sealing body 4 achieves sealing of the assembly gap between the stationary blade 1 and the support ring 2 through the double-inclined surface cooperation with the first nest 3 and the second nest 5. Furthermore, under the thermal expansion of heavy fuel turbines, the sealing body with four double-sloped surfaces adaptively deforms to achieve a good seal, with low requirements for installation process.

[0044] The first nest 3 has a cross-section including a long side and a short side, which can be T-shaped or trapezoidal. It is installed into the mounting groove of the blade root along the circumferential direction of the blade root. The mounting groove in the circumferential direction of the blade root is also T-shaped or trapezoidal. The second nest 5 has a T-shaped cross-section, which can be T-shaped or trapezoidal, including a long side and a short side. It is installed into the support ring 2 along the circumferential direction of the support ring 2. The mounting groove in the circumferential direction is also T-shaped or trapezoidal.

[0045] The first mounting groove 6 is disposed at the short side end, and the opening direction of the first included angle α formed by the first inclined surface and the second inclined surface of the first mounting groove 6 is toward the joint surface of the first nest 3 and the second nest 5; and / or the second nest 5 includes a long side end and a short side end, and the second mounting groove 7 is disposed at the short side end, and the opening direction of the second included angle β formed by the third inclined surface and the fourth inclined surface of the second mounting groove 7 is toward the joint surface of the first nest 3 and the second nest 5.

[0046] To adapt to the high-temperature conditions of heavy-duty gas turbines, the first nest 3 and the second nest 5 are made of high-temperature alloy materials, and their double-sloped nested structure can also be processed by 3D printing.

[0047] Besides being related to the diameter D of the sealing body 4 spheres, the compressibility ε is also related to the values ​​of the first included angle α and the second included angle β. When the diameter D of the sealing body 4 spheres is constant, the larger the values ​​of the first included angle α and the second included angle β, the greater the compressibility.

[0048] Conversely, the values ​​of the first included angle α of the first mounting groove 6 and the second included angle β of the second mounting groove 7, i.e., the included angle of the double inclined surfaces of the first mounting groove 6 and the second mounting groove 7, are determined by factors such as the compression ratio of the compression body. Influencing factors also include the spherical diameter D of the sealing body 4 and the displacement Δx of the second nest 5 relative to the first nest 3. Through summarization, the formula for calculating the first included angle α is: α = sin -1 ((2×D×ε) / Δx). The design basis of the second included angle β is consistent with that of the first included angle α, and the second included angle β can be designed to have the same value as the first included angle α. Not only can the values ​​of the first included angle α and the second included angle β be designed to be consistent, but the structures of the first mounting groove 6 and the second mounting groove 7, and the structures of the first nest 3 and the second nest 5 can also be designed to be consistent. According to the above formula, the double-inclined nest structure of the radial sliding self-sealing structure of the present invention can be serialized. Different first included angle α and second included angle β can be selected according to the sphere diameter D of the sealing body 4 and the required compression ratio. This serialized design facilitates engineering installation and application, and further utilizes product standardization and maintenance convenience.

[0049] Based on the relationship between the included angle of the double inclined planes and the compression ratio of the sealing body 4, a series of double inclined plane inner and first nested 3 structures can be designed according to the above formula. Appropriate double inclined plane angles can be selected for different heavy-duty gas turbines to ensure optimal sealing performance for each unit. In practical engineering applications, the first nested 3 and the second nested 5 can be replaced, and a more effective double inclined plane inner and first nested 3 structure can be selected based on sealing performance and other test results.

[0050] As can be seen from the above description, the above embodiments of the present invention achieve the following technical effects: The radial sliding self-sealing structure between the gas turbine turbine turbine blade 1 and the annular support ring 2 of the present invention forms a self-sealing inclined surface by designing a radial sealing groove and adding a double-inclined nested structure, thus achieving zero leakage at this point; the structural features of the sealing component of the present invention allow for serialized design, and the first nest 3 and the second nest 5 can be used with sealing components of various diameter specifications; and the sealing groove of the present invention is a radial seal, unlike an axial seal, which does not require the installation of a fixing compressive agent, reducing damage to the sealing rope during installation.

[0051] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A sealing assembly between a stationary vane and a support ring, wherein the stationary vane (1) and the support ring (2) define an airflow channel, the airflow channel having an assembly gap formed by the cooperation of the stationary vane (1) and the support ring (2), the sealing assembly being used to seal the assembly gap, characterized in that, The sealing assembly includes: a first nest (3) fixed to the root of the stationary blade (1); a second nest (5) fixed to the support ring (2); and a sealing body (4) installed between the first nest (3) and the second nest (5), the sealing body (4) being radially compressible to self-seal the assembly gap between the stationary blade (1) and the support ring (2).

2. The sealing assembly according to claim 1, characterized in that, The radial compression of the sealing body (4) can be adaptively adjusted with the expansion and / or position change of the stationary blade (1) and the support ring (2).

3. The sealing assembly according to claim 2, characterized in that, The second nest (5) and the first nest (3) are arranged opposite each other in the radial direction. The sealing body generates radial compression under the action of the second nest (5) and the first nest (3) to achieve self-sealing.

4. The sealing assembly according to claim 3, characterized in that, The second nest (5) and the first nest (3) generate a relative radial displacement between each other, the value of which is Δx, and the compression amount is adaptively adjusted according to the value of which is relative radial displacement.

5. The sealing assembly according to claim 4, characterized in that, The relative radial displacement of the second nest (5) and the first nest (3) is generated by the thermal expansion force of the stationary blade (1) and the support ring (2).

6. The sealing assembly according to claim 5, characterized in that, The relative radial displacement of the second nest (5) and the first nest (3) is generated by the vibration force of the stationary blade (1) and the support ring (2).

7. The sealing assembly according to claim 6, characterized in that, The sealing body has a pre-compression amount during initial installation, which can increase the sealing contact stress.

8. The sealing assembly according to claim 7, characterized in that, The sealing body is disposed between the second nest (5) and the first nest (3). Under the action of the second nest (5) and the first nest (3), the sealing body slides relative to the second nest (5) and the first nest (3) and generates radial compression.

9. The sealing assembly according to any one of claims 4-8, characterized in that, The first nest (3) includes a first mounting groove (6), and the second nest (5) includes a second mounting groove (7), the first mounting groove (6) and the second mounting groove (7) accommodating the sealing body (4).

10. The sealing assembly according to claim 9, characterized in that, The first mounting groove (6) has a first inclined surface and a second inclined surface, the first inclined surface and the second inclined surface forming a first included angle α; and / or the second mounting groove (7) has a third inclined surface and a fourth inclined surface, the third inclined surface and the fourth inclined surface forming a second included angle β.

11. The sealing assembly according to claim 10, characterized in that, The values ​​of the first included angle α and the second included angle β are related to the compression ratio ε, wherein the compression amount of the sealing body (4) is the ratio of the initial volume of the sealing body (4) to the compression ratio ε.

12. The sealing assembly according to claim 11, characterized in that, The sealing body (4) is a sphere with a diameter of D.

13. The sealing assembly according to claim 12, characterized in that, The first included angle α = sin -1 ((2×D×ε) / Δx), and / or the second included angle β=sin -1 ((2×D×ε) / Δx).

14. The sealing assembly according to claim 13, characterized in that, The first included angle α is equal to the second included angle β.

15. The sealing assembly according to claim 14, characterized in that, The compression ratio ε is 5%-25%.

16. The sealing assembly according to claim 15, characterized in that, The sealing body (4) is a spherical metal braid.

17. The sealing assembly according to claim 16, characterized in that, The metal braided component includes a metal braided rope.

18. The sealing assembly according to claim 17, characterized in that, The first nest (3) has a T-shaped cross section and is installed into the leaf root along the circumferential direction of the leaf root; and / or the second nest (5) has a T-shaped cross section and is installed into the support ring (2) along the circumferential direction of the support ring (2).

19. The sealing assembly according to claim 18, characterized in that, The first nest (3) includes a long side end and a short side end, the first mounting groove (6) is disposed on the short side end, and the opening direction of the first included angle α formed by the first inclined surface and the second inclined surface of the first mounting groove (6) is toward the joint surface of the first nest (3) and the second nest (5); and / or the second nest (5) includes a long side end and a short side end, the second mounting groove (7) is disposed on the short side end, and the opening direction of the second included angle β formed by the third inclined surface and the fourth inclined surface of the second mounting groove (7) is toward the joint surface of the first nest (3) and the second nest (5).

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