Gas turbine nozzle sealing structure

Abstract

The present invention discloses a gas turbine nozzle sealing structure. The present invention relates to the field of gas turbines, and in particular to a gas turbine nozzle sealing structure, comprising a turbine nozzle, an intermediate gas seal body, a sealing ring, a nozzle gas seal body and an axial elastic unit component, wherein the nozzle gas seal body is sleeved on the intermediate gas seal body; the turbine nozzle ring is provided on the outer shell of the nozzle gas seal body; an L-shaped groove is provided on the axial cross section of the intermediate gas seal body; the sealing ring is an annular structure and is provided in the L-shaped groove; an annular groove A is provided on one side of the L-shaped groove close to the air outlet side, an axial elastic element is installed in the annular groove A, and under the elastic force of the axial elastic element, the air inlet side end face of the L-shaped groove is always in contact with the air inlet side end face of the sealing sector.

Description

Technical Field

[0001] The present invention relates to the field of gas turbines, and in particular to a gas turbine nozzle sealing structure. Background Art

[0002] When a gas turbine is operating, high-temperature, high-pressure compressed air discharged from the compressor outlet enters the annular chamber formed by the intermediate gas seal body and the outer cylinder, where the burner is located. A portion of this compressed air enters the burner to cool it and mix with it for combustion, while a portion enters the internal cavity of each turbine nozzle ring to cool the metal temperature of the turbine nozzle. To prevent this high-temperature, high-pressure compressed air from leaking into the chamber between the turbine nozzle and the turbine blades, and to improve gas turbine operating efficiency, a sealing structure is required between the intermediate gas seal body and the turbine nozzle ring. This structure not only forms an effective seal between the turbine nozzle ring and the intermediate gas seal body, but also accommodates the expansion mismatch between the turbine nozzle and the intermediate gas seal body caused by temperature differences.

[0003] Existing sealing structures either use a hard connection structure between the intermediate gas seal body and the turbine nozzle ring to ensure sealing performance, but have poor ability to adapt to thermal expansion imbalance, which reduces the safety and reliability of the gas turbine; or use a gap design or flexible connection structure to adapt to the thermal expansion imbalance between the intermediate gas seal body and the turbine nozzle ring, but have no sealing effect or have poor sealing performance, which reduces the operating efficiency of the gas turbine. Therefore, there is a need for a device that can adapt to the thermal expansion imbalance between the turbine nozzle and the intermediate gas seal body and effectively seal the gap between the turbine nozzle and the intermediate gas seal body, so that high-temperature and high-pressure compressed air will no longer leak into the chamber between the turbine nozzle and the turbine blades, thereby improving the operating efficiency of the gas turbine. Summary of the Invention

[0004] The object of the present invention is to provide a gas turbine nozzle sealing structure to solve the above-mentioned problems.

[0005] The technical solution adopted in the present invention is as follows:

[0006] A gas turbine nozzle sealing structure includes a turbine nozzle, an intermediate gas seal body, a sealing ring, a nozzle gas seal body, and an axial elastic unit. The turbine nozzles can be connected end to end to form a turbine nozzle ring. The intermediate gas seal body and the nozzle gas seal body are annular structures. The nozzle gas seal body is sleeved outside the intermediate gas seal body. The turbine nozzle ring is sleeved outside the nozzle gas seal body.

[0007] An L-shaped groove is provided on the axial section of the intermediate gas seal body; the opening of the L-shaped groove is provided on the side of the intermediate gas seal body away from the rotating axis of the gas turbine;

[0008] The sealing ring is an annular structure, the axial cross section of the sealing ring matches the L-shaped groove, and is arranged in the L-shaped groove;

[0009] An annular groove A is provided on one side of the L-shaped groove close to the air outlet side. An axial elastic element that is always in a compressed state is installed in the annular groove A. Under the elastic force of the axial elastic element, the air inlet side end face of the L-shaped groove is always in contact with the air inlet side end face of the sealing ring.

[0010] Furthermore, a radial elastic element that is always in a compressed state is provided between the surface of the L-shaped groove close to the rotating axis of the gas turbine and the inner circumferential surface of the sealing ring. Under the elastic force of the radial elastic element, the outer circumferential surface of the sealing ring is always in contact with the inner circumferential surface of the nozzle gas seal body.

[0011] Furthermore, the sealing ring is composed of a plurality of sealing segments, and the sealing segments can be connected end to end to form the sealing ring.

[0012] Furthermore, the sealing sector is provided with a plurality of grooves C along the axial direction of the gas turbine, and the openings of the grooves C face the rotation axis of the gas turbine;

[0013] The intermediate gas seal body is provided with a plurality of blind holes matching the groove C. The blind holes pass through the L-shaped groove along the axial direction of the gas turbine, and the openings of the blind holes are provided on the gas outlet side of the intermediate gas seal body.

[0014] Furthermore, a limiting member is included. When the sealing ring is assembled into the intermediate gas sealing body, the blind hole of the intermediate gas sealing body corresponds to the groove C of the sealing sector, and the limiting member is assembled in the blind hole and the groove C.

[0015] Furthermore, each turbine nozzle is provided with a support leg on one side close to the rotation axis of the gas turbine;

[0016] The nozzle gas seal body is provided with an annular groove B with an opening facing away from the rotation axis of the gas turbine. When the turbine nozzle ring is arranged on the nozzle gas seal body, the support legs are assembled in the annular groove B.

[0017] Furthermore, a plurality of circular holes are provided on the outlet side support plate of the annular groove B; a groove D is provided on the support leg along the axial direction of the gas turbine, and the opening of the groove D faces the rotation axis of the gas turbine.

[0018] Furthermore, it includes a centering piece. When the turbine nozzle ring is assembled into the nozzle gas seal body, the circular hole of the nozzle gas seal body corresponds to the groove D of the turbine nozzle, and the centering piece is assembled in the circular hole and the groove D.

[0019] Furthermore, a method for assembling a gas turbine nozzle sealing structure includes the following steps:

[0020] S1: Insert the legs of the turbine nozzle into the annular groove D. Connect multiple turbine nozzles end to end to form a turbine nozzle ring.

[0021] S2: After installing the turbine nozzle, adjust its relative position to the nozzle gas seal body so that the circular hole corresponds to the groove D;

[0022] S3: Insert the centering piece into the circular hole and groove D to keep the turbine nozzle ring and the nozzle gas seal body relatively stationary;

[0023] S4: Install the axial elastic element in the annular groove A of the middle gas seal body, and install the radial elastic element on the bottom surface of the L-shaped groove;

[0024] S5: Place several sealing segments into the L-shaped groove and connect them end to end to form a sealing ring, compress the axial elastic element and the radial elastic element, and align the grooves C one by one with the blind holes;

[0025] S6: Insert the limiter into the blind hole and the groove C to keep the sealing ring and the intermediate gas sealing body relatively still;

[0026] S7: Sleeve the assembly of the turbine nozzle ring and the nozzle gas seal body onto the assembly of the intermediate gas seal body and the sealing ring, so that the outer circumferential surface of the sealing ring fits with the inner circumferential surface of the nozzle gas seal body.

[0027] Furthermore, in step S5: first connect the sealing segments end to end, leaving the last segment open, then install the axial elastic element and the radial elastic element into the L-shaped groove to compress them, and align the grooves C with the blind holes one by one, and then connect the last opening.

[0028] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0029] The present invention adopts a simple technical solution, which is easy to operate and highly feasible. It improves the existing technology that does not adopt sealing or adopts a sealing method with poor sealing effect. This solution can adapt to the thermal expansion imbalance between the turbine nozzle and the intermediate gas seal body, and can effectively seal the gap between the turbine nozzle and the intermediate gas seal body, so that high-temperature and high-pressure compressed air will no longer leak into the chamber between the turbine nozzle and the turbine blades, thereby improving the operating efficiency of the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is an axonometric three-dimensional view of the turbine nozzle ring of the present invention.

[0031] Figure 2 This is an axonometric three-dimensional view of the turbine nozzle of the present invention.

[0032] Figure 3 This is a side view of the gas outlet of the nozzle gas seal body of the present invention.

[0033] Figure 4 yes Figure 3 AA section view in.

[0034] Figure 5 This is the side view of the gas outlet of the intermediate gas seal body of the present invention

[0035] Figure 6 This invention Figure 5 BB section view in

[0036] Figure 7 This is the axonometric three-dimensional view of the sealing ring of the present invention

[0037] Figure 8 This is the side view of the gas outlet of the sealing sector of the present invention

[0038] Figure 9 This invention Figure 8 CC section view in

[0039] Figure 10 This is the overall assembly diagram of the present invention

[0040] Figure 11 This invention Figure 10 Middle DD cross-sectional view

[0041] Figure 12 This invention Figure 10 Middle EE cross-sectional view

[0042] Markings in the figure: 1-turbine nozzle ring, 11-turbine nozzle, 111-support leg, 112-groove D, 2-nozzle gas seal body, 21-inner circumferential surface of nozzle gas seal body, 22-annular groove B, 23-outlet side support plate, 24-circular hole, 3-intermediate gas seal body, 31-L-shaped groove, 32-inlet side end face, 33-annular groove A, 34-blind hole, 35-bottom surface, 36-outlet side end face, 4-sealing ring, 41-sealing sector, 411-outer circumferential surface, 412-inlet side end face, 413-groove C, 414-inner circumferential surface of sealing ring, 5-axial elastic element, 6-radial elastic element, 7-centering piece, 8-limiting piece. DETAILED DESCRIPTION

[0043] The present invention will be described in detail below with reference to the accompanying drawings.

[0044] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0045] In this embodiment, if Figure 10As shown, it includes a turbine nozzle, an intermediate gas seal body, a sealing ring, a nozzle gas seal body and an axial elastic unit. The turbine nozzle can be connected end to end to form a turbine nozzle ring. The intermediate gas seal body and the nozzle gas seal body are annular structures. The nozzle gas seal body is sleeved outside the intermediate gas seal body. The turbine nozzle ring is provided on the outer surface of the nozzle gas seal body. The turbine nozzle ring is composed of multiple turbine nozzles connected end to end and sleeved outside the nozzle gas seal body. The advantage of such a setting is that since the turbine nozzle ring and the nozzle gas seal body are hard-linked by some structures, the adoption of such a segmented design can make the later assembly and sleeve more convenient and simple. The nozzle gas seal body is sleeved outside the intermediate gas seal body, and the intermediate gas seal body, the nozzle gas seal body and the turbine nozzle ring are tightly coaxially sleeved.

[0046] The intermediate gas seal body has an L-shaped groove on its axial cross section; the L-shaped groove opening is located on the side of the intermediate gas seal body away from the axis; the sealing ring has an annular structure, the axial cross section of the sealing ring matches the L-shaped groove, and is disposed within the L-shaped groove; the L-shaped groove is provided to accommodate the sealing ring, and the L-shaped shape can achieve radial position limiting, so that when the sealing ring is subjected to radial force from the radial elastic element, it will not fall out of the intermediate gas seal body during installation due to the lack of radial restraint.

[0047] The L-shaped groove is provided with an annular groove A on one side close to the air outlet side, and an axial elastic element which is always in a compressed state is installed in the annular groove A. Under the elastic force of the axial elastic element, the air inlet side end face of the L-shaped groove is always in fit with the air inlet side end face of the sealing ring. In this embodiment, the axial elastic unit is an annular structure composed of elastic flexible material, which is installed in the annular groove A. The L corner of the L-shaped groove is set at one end of the air outlet side, so that the air outlet side face of the annular groove A is flat. The advantage of such a setting is that when the sealing ring is placed in the L-shaped groove, under the action of the axial elastic unit, it can fit tightly with the inner corner of the L-shaped groove facing the air inlet side, thereby achieving the best sealing effect; an annular groove A is provided on the one side of the L-shaped groove close to the air outlet side, and an axial elastic element which is always in a compressed state is installed. The sealing ring is subjected to force and fits tightly with the L-shaped groove, thereby sealing the high-temperature and high-pressure compressed air.

[0048] In this embodiment, if Figure 6As shown, a radial elastic element that is always in a compressed state is provided between the surface of the L-shaped groove close to the rotating axis of the gas turbine and the inner circumferential surface of the sealing ring. The radial elastic unit is an annular structure composed of elastic and flexible material and is installed in the surface of the L-shaped groove close to the rotating axis of the gas turbine. Under the elastic force of the radial elastic element, the outer circumferential surface of the sealing ring is always in contact with the inner circumferential surface of the nozzle gas seal body. Under the combined action of the axial elastic element, the sealing ring is tightly attached to the inner wall of the L-shaped groove on the air inlet side and the nozzle gas seal body, isolating the high-temperature and high-pressure compressed air generated during the operation of the gas turbine. After being exposed to high temperature, the intermediate gas seal body and the nozzle gas seal body will produce a certain degree of uneven thermal expansion. At the same time, under the action of the two elastic units, the sealing ring and the intermediate gas seal body are always pressed tightly, and this difference will be eliminated, thereby improving the operating efficiency of the gas turbine.

[0049] Furthermore, in this embodiment, Figure 7 As shown, the sealing ring is composed of several sealing segments, and the sealing segments can be connected end to end to form a sealing ring. A connecting structure is set at the end of the sealing segment, and the connection does not affect the overall sealing of the sealing ring. The advantage of such a setting is that since the sealing ring is set in the L-shaped groove of the middle gas seal body, if an integrated design is adopted, it will bring inconvenience to the installation and subsequent maintenance and replacement. Therefore, a segmented design is adopted. During the installation and replacement process, the segments can be taken out in segments. The segmented installation greatly saves manpower and material resources, while also ensuring the sealing performance and optimizing the efficiency of the gas turbine.

[0050] Further, such as Figure 8 As shown, the sealing sector is provided with a groove C along the axial direction of the gas turbine, with the opening of the groove C facing the rotation axis of the gas turbine. The intermediate gas seal body is provided with a blind hole matching the groove C. The blind hole passes through the L-shaped groove along the axial direction of the gas turbine, and the opening of the blind hole is provided on the gas outlet side of the intermediate gas seal body. In this embodiment, a spacing n is provided between the side of the blind hole away from the gas turbine rotation axis and the side of the groove C away from the gas turbine rotation axis. This spacing, after the stopper is inserted, ensures that the sealing sector is not subject to radial movement caused by the expansion of the nozzle gas seal body toward the gas turbine rotation axis. This ensures that the stopper, sealing ring, and radial elastic unit will not rupture due to excessive pressure, thereby failing to achieve optimal sealing and reducing gas turbine efficiency. Furthermore, the blind hole extends to the gas inlet side of the intermediate gas seal body but does not penetrate through the intermediate gas seal body. This arrangement ensures that after the stopper is inserted, the stopper will not be radially deflected by external pressure, but will be fixed within the blind hole, thereby securing the sealing ring and limiting the relative position between the sealing ring and the intermediate gas seal body.

[0051] Further, it includes a limiter, such as Figure 12As shown, when the sealing ring is assembled into the intermediate air seal body, the blind hole of the intermediate air seal body corresponds to the groove C of the sealing sector, and the limiter is assembled in the blind hole and the groove C. After the groove C of the sealing sector is installed into the intermediate air seal body corresponding to the blind hole, the limiter is inserted therein and fixed. Preferably, the limiter is a cylindrical structure. This mechanism can make insertion simple and does not require alignment of the direction. It can be inserted between them. At the same time, the insertion end is set to a frustum structure, which is conducive to locating the blind hole and inserting it accurately. At the same time, the diameter of the limiter matches the diameter of the blind hole and the two sides of the groove C, and the gap left is small, which can ensure that the sealing sector will not slide in the circumferential direction.

[0052] Furthermore, each turbine nozzle is provided with a support leg on the side close to the rotation axis of the gas turbine, and the nozzle gas seal body is provided with an annular groove B with an opening facing away from the rotation axis of the gas turbine. When the turbine nozzle ring is arranged on the nozzle gas seal body, the support leg is assembled in the annular groove B. The support leg adopts a long strip structure with a shape matching the groove. This structure can increase the contact length between the support leg and the groove, greatly improving the connection firmness between the turbine nozzle and the nozzle gas seal body, making the overall structure stable and improving the efficiency of the gas turbine.

[0053] Furthermore, a plurality of circular holes are provided on the outlet side support plate of the annular groove B; a groove D is provided on the support leg along the axial direction of the gas turbine, and the opening of the groove D faces the rotation axis of the gas turbine. The number of the groove D corresponds to the number of the circular holes, and one groove D is provided for each support leg. When installing the turbine nozzle, the groove D is aligned with the circular hole of the nozzle gas seal body, and the turbine nozzles are installed one by one. A spacing m is provided between the circular hole away from the rotation axis of the gas turbine and the groove D away from the rotation axis of the gas turbine. After the centering piece is inserted, the spacing m can absorb the thermal expansion difference between the turbine nozzle and the nozzle gas seal body in the radial direction to ensure the efficiency of the gas turbine.

[0054] Furthermore, in this embodiment, Figure 12 As shown, it includes a centering piece. When the turbine nozzle ring is assembled into the nozzle gas seal body, the circular hole of the nozzle gas seal body corresponds to the groove D of the turbine nozzle, and the centering piece is assembled in the circular hole and the groove D. When the centering piece is installed into the circular hole and the groove D, it can effectively limit the turbine nozzle ring and the nozzle gas seal body to prevent relative sliding between the two, affecting the sealing efficiency and reducing the efficiency of the gas turbine. The centering piece is a cylindrical structure, which can make insertion simple. There is no need to align the direction. It can be inserted between them. At the same time, the insertion end is set to a frustum structure, which is conducive to finding the circular hole and inserting it accurately. At the same time, the diameter of the centering piece matches the diameter of the circular hole and the two sides of the groove D. The gap left is small, which can ensure that the turbine nozzle ring will not slide in the circumferential direction.

[0055] A method for assembling a gas turbine nozzle sealing structure comprises the following steps:

[0056] S1: Insert the legs of the turbine nozzle into the groove D. Connect multiple turbine nozzles end to end to form a turbine nozzle ring. This method can place the turbine nozzle ring outside the nozzle gas seal body without changing the structure of the turbine nozzle and the nozzle gas seal body, and ensure that the structure is stable and firm.

[0057] S2: After installing the turbine nozzle, adjust its relative position to the nozzle gas seal body so that the circular hole corresponds to the groove D. Adjusting this corresponding position will facilitate the subsequent insertion of the centering piece.

[0058] S3: Insert the centering piece into the circular hole and groove D, so that the turbine nozzle ring and the nozzle gas seal body remain relatively still. When inserting, pay attention to whether it is inserted into the right position to avoid the risk of falling off later. At the same time, check whether the centering piece is inserted into each circular hole;

[0059] S4: Install the axial elastic element in the annular groove A of the middle gas seal body. After installation, check along the circumference to see if it is firmly fixed in the groove A to prevent it from falling off. Install the radial elastic element on the bottom of the L-shaped groove. Since the radial elastic element has elasticity, it can be directly installed on the bottom of the L-shaped groove.

[0060] S5: Place several sealing segments into the L-shaped groove and connect them end to end to form a sealing ring. Press the axial elastic element and the radial elastic element, and align the grooves C with the blind holes one by one. When installing the sealing segments, apply a certain amount of force to ensure that the two elastic elements are squeezed into place before they are installed in place.

[0061] S6: Insert the stopper into the blind hole and groove C, so that the sealing ring and the intermediate gas seal body remain relatively still. When inserting, pay attention to whether it is inserted into the right position to avoid the risk of falling off later. At the same time, check whether the stopper is inserted into each blind hole;

[0062] S7: Slide the combination of the turbine nozzle ring and the nozzle gas seal body onto the combination of the intermediate gas seal body and the sealing ring, so that the outer circumference of the sealing ring fits with the inner circumference of the nozzle gas seal body. During installation, be sure to slowly rotate the combination of the intermediate gas seal body and the sealing ring left and right to fit the nozzle gas seal body, otherwise the sealing effect of the sealing ring will be affected.

[0063] Furthermore, in step S5, the sealing segments are first connected end to end, leaving the last segment open, and then the axial elastic element and the radial elastic element are compressed in the L-shaped groove, and the grooves C are aligned with the blind holes one by one, and then the last opening is connected. This can reduce the connection operations in a narrow operating area and save manpower and material resources.

[0064] The above description is only a preferred embodiment of the invention and is not intended to limit the invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the invention should be included in the scope of protection of the invention.

Claims

1. A gas turbine nozzle sealing structure, characterized in that: It includes a turbine nozzle, an intermediate gas seal body, a sealing ring, a nozzle gas seal body and an axial elastic unit. The turbine nozzle can be connected end to end to form a turbine nozzle ring. The intermediate gas seal body and the nozzle gas seal body are annular structures. The nozzle gas seal body is sleeved on the intermediate gas seal body. The nozzle gas seal body is outer-mounted with a turbine nozzle ring. The intermediate gas seal body is provided with an L-shaped groove on the axial cross section; the opening of the L-shaped groove is provided on the side of the intermediate gas seal body away from the rotation axis of the gas turbine; The sealing ring is an annular structure, the axial cross section of the sealing ring matches the L-shaped groove, and is arranged in the L-shaped groove; An annular groove A is provided on one side of the L-shaped groove close to the air outlet side, and an axial elastic element which is always in a compressed state is installed in the annular groove A. Under the elastic force of the axial elastic element, the air inlet side end face of the L-shaped groove is always in contact with the air inlet side end face of the sealing ring.

2. The gas turbine nozzle sealing structure according to claim 1, characterized in that: A radial elastic element that is always in a compressed state is provided between the surface of the L-shaped groove close to the rotating axis of the gas turbine and the inner circumferential surface of the sealing ring. Under the elastic force of the radial elastic element, the outer circumferential surface of the sealing ring is always in contact with the inner circumferential surface of the nozzle gas seal body.

3. The gas turbine nozzle sealing structure according to claim 1, characterized in that: The sealing ring is composed of a plurality of sealing sectors, and the sealing sectors can be connected end to end to form a sealing ring.

4. A gas turbine nozzle sealing structure according to claim 3, characterized in that: The sealing sector is provided with a plurality of grooves C along the axial direction of the gas turbine, and the openings of the grooves C face the rotation axis of the gas turbine; The intermediate gas seal body is provided with a plurality of blind holes matching the groove C. The blind holes pass through the L-shaped groove along the axial direction of the gas turbine. The openings of the blind holes are provided on the gas outlet side of the intermediate gas seal body.

5. The gas turbine nozzle sealing structure according to claim 4, characterized in that: It includes a limiting piece. When the sealing ring is assembled into the intermediate gas sealing body, the blind hole of the intermediate gas sealing body corresponds to the groove C of the sealing sector, and the limiting piece is assembled in the blind hole and the groove C.

6. The gas turbine nozzle sealing structure according to claim 1, wherein: The turbine nozzle is provided with a support leg on one side close to the rotation axis of the gas turbine; The nozzle gas seal body is provided with an annular groove B with an opening facing away from the rotation axis of the gas turbine. When the turbine nozzle ring is arranged on the nozzle gas seal body, the support leg is assembled in the annular groove B.

7. A gas turbine nozzle sealing structure according to claim 6, characterized in that: The outlet side support plate of the annular groove B is provided with a plurality of circular holes; the support leg is provided with a groove D along the axial direction of the gas turbine, and the opening of the groove D faces the rotation axis of the gas turbine.

8. The gas turbine nozzle sealing structure according to claim 7, characterized in that: It includes a centering piece. When the turbine nozzle ring is assembled into the nozzle gas seal body, the circular hole of the nozzle gas seal body corresponds to the groove D of the turbine nozzle, and the centering piece is assembled in the circular hole and the groove D.

9. A method for assembling a gas turbine nozzle sealing structure, applied to a gas turbine nozzle sealing structure according to any one of claims 1 to 8, characterized in that: The following steps are involved: S1: Insert the legs of the turbine nozzle into the groove D. Connect multiple turbine nozzles end to end to form a turbine nozzle ring. S2: After installing the turbine nozzle, adjust its relative position to the nozzle gas seal body so that the circular hole corresponds to the groove D; S3: Insert the centering piece into the circular hole and groove D to keep the turbine nozzle ring and the nozzle gas seal body relatively stationary; S4: Install the axial elastic element in the annular groove A of the intermediate gas seal body, and install the radial elastic element on the surface of the L-shaped groove close to the rotating axis of the gas turbine; S5: Place several sealing segments into the L-shaped groove and connect them end to end to form a sealing ring, compress the axial elastic element and the radial elastic element, and align the grooves C one by one with the blind holes; S6: Insert the limiter into the blind hole and the groove C to keep the sealing ring and the intermediate gas sealing body relatively still; S7: Sleeve the assembly of the turbine nozzle ring and the nozzle gas seal body onto the assembly of the intermediate gas seal body and the sealing ring, so that the outer circumferential surface of the sealing ring fits with the inner circumferential surface of the nozzle gas seal body.

10. The method for assembling a gas turbine nozzle sealing structure according to claim 9, characterized in that: In step S5: first connect the sealing segments end to end, leaving the last segment open, then install them into the L-shaped groove to compress the axial elastic element and the radial elastic element, and align the grooves C with the blind holes one by one, and then connect the last opening.

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