CN103958949A - Sealing structure and rotating machine equipped with same - Google Patents

Abstract

The sealing structure (7) is provided with fins (40) that protrude from the outer circumferential surface of a rotor (5) along the circumferential direction (R), and stationary blades (30) on which an abradable film (60) is formed on the inner circumferential surface (50a) of the inner shroud (50) so as to face the fins (40), and depressions and protrusions are formed on the inner circumferential surface (50a) of the inner shroud (50) and the abradable film (60) is formed conforming to the depressions and protrusions.

Description

Sealing structure and rotating machine equipped with the sealing structure

technical field

The present invention relates to a sealing structure and a rotary machine provided with the sealing structure.

this application claims priority based on Japanese Patent Application No. 2012-023071 for which it applied to Japan on February 6, 2012, and uses the content here.

Background technique

Generally, around a rotor in a rotating machine such as a steam turbine or a gas turbine, by minimizing the gap between the rotor and stationary parts such as stator blades, the amount of fluid leakage is minimized, from the viewpoint of improving the performance of the rotating machine. Getting started is crucial.

Therefore, a sealing structure is adopted, which includes: fins protruding in the circumferential direction from the outer peripheral surface of the rotor; (Refer to the following Patent Document 1). With such a sealing structure, even when the rotor comes into contact with the stationary side member during rotation of the rotor, cutting off the abradable material can reduce heat generation at the contact portion and maintain the performance of the rotary machine.

Here, the sealing member is an annular member extending in the circumferential direction, and an abradable film formed by spraying an abradable material is formed on the inner peripheral surface thereof.

【Prior technical literature】

【Patent Literature】

[Patent Document 1] Japanese Patent Laid-Open No. 2009-174655

Contents of the invention

【Summary of Invention】

【Problems to be solved by the invention】

However, in the sealing structure described in the above-mentioned Patent Document 1, since it is necessary to provide a sealing member, there is a problem that the manufacturing is relatively laborious, and the processing cost is increased to increase the cost.

On the other hand, a technique in which the sealing member is omitted and the abradable material is directly sprayed on the stationary side member is conceivable.

Here, when the rotor rotates, a shearing force is generated in the axial direction between the inner shrouds of the adjacent stator blades, and thus the abradable material must bear the shearing force. However, since the abradable material has high machinability, the abradable material directly sprayed on the stator blade may be damaged by the shearing force and may fall off from the stator blade. Therefore, it cannot be applied simply by thermal spraying. .

The present invention is made in consideration of such a situation, and provides a sealing structure capable of preventing the abradable material from coming off even if the abradable material is damaged.

【solution】

According to a first aspect of the present invention, the sealing structure is characterized by comprising: fins protruding in the circumferential direction from the outer peripheral surface of the rotor; and stator blades facing the fins on the inner peripheral surface of the inner shroud. An abradable film is formed, and a concavo-convex shape is formed on the inner peripheral surface of the inner shield, and the abradable film is formed along the concavo-convex shape.

In such a sealing structure, the abradable film is formed along the concave-convex shape, and the abradable material enters the concave-convex shape, hardens and welds, so that the bonding area is increased, and firm bonding is possible. Accordingly, even when the abradable film is damaged, since the abradable film is firmly bonded, it is possible to prevent the abradable film from coming off.

In the sealing structure according to the first aspect of the present invention, the concave-convex shape may be formed by a concave portion formed from one of the inner peripheral surface of the inner shroud and the outer peripheral surface of the abradable film toward the inside thereof. constitute.

In such a sealing structure, the concavo-convex shape is formed, for example, by a concave portion formed from the inner peripheral surface of the inner shroud toward the inside thereof. Accordingly, since the abradable film enters the inside of the concave portion, the bonding force can be reliably improved. Thereby, even when the abradable film is damaged, it is possible to prevent the abradable film from coming off.

In the sealing structure according to the first aspect of the present invention, the recess may be formed to extend in the circumferential direction.

In such a sealing structure, the bonding force of the abradable film can be improved in the circumferential direction. Thereby, even when the abradable film is damaged, it is possible to prevent the abradable film from coming off.

In the sealing structure according to the first aspect of the present invention, the recess may be formed to extend in the axial direction of the rotor.

In such a sealing structure, the bonding force of the abradable film can be increased in the axial direction. Thereby, even when the abradable film is damaged, it is possible to prevent the abradable film from coming off.

In the sealing structure according to the first aspect of the present invention, the recess may be formed on a boundary between the inner shrouds adjacent in the circumferential direction.

In such a sealing structure, a recess is formed on the boundary line between adjacent inner shrouds, and the abradable film can enter the recess. Accordingly, when a shearing force is generated between adjacent inner shrouds along the boundary line, the shearing force can be reduced by the amount of entry of the abradable film, and thus deformation due to twisting of the stator blades can be prevented.

In the sealing structure according to the first aspect of the present invention, one of the inner peripheral surface of the inner shroud and the outer peripheral surface of the abradable film may be connected to the inner peripheral surface of the inner shroud. A second recess is formed facing the recess formed on the other side of the outer peripheral surface of the abradable film, and the sealing structure includes a pin member inserted between the recess and the second recess.

In such a sealing structure, for example, when a recess is formed on the side of the inner shroud, axial displacement of the inner shroud can be reduced by fitting and engaging the recess and the pin member. Furthermore, the joining force of the abradable film can be improved by joining the second concave portion and the pin member.

In the sealing structure according to the first aspect of the present invention, the recess may be formed in a cross-section perpendicular to the extending direction of the recess so as to follow from the inner peripheral surface of the inner shroud or the abradable film. The outer peripheral surface of the concave portion is formed in such a way that the width gradually becomes wider toward the bottom of the concave portion.

In such a sealing structure, the bonding area of the abradable film can be increased. Furthermore, when a force acts on the abradable film in the direction of falling off, resistance acts on the inclined surface of the abradable film corresponding to the surface formed toward the bottom of the concave portion, so that more firm joining can be achieved. Accordingly, even when the abradable film is damaged, since the abradable film is firmly bonded, it is possible to prevent the abradable film from coming off.

In the sealing structure according to the first aspect of the present invention, the recess may be formed from the inner peripheral surface of the inner shroud or from the abradable film in a cross section perpendicular to the extending direction of the recess. Arc shape with bulging outer peripheral surface.

In such a sealing structure, the bonding area of the abradable film can be increased, and thus the bonding force can be improved.

According to a second aspect of the present invention, a rotary machine is provided with any one of the sealing structures described above.

According to this configuration, since any of the sealing structures described above is provided, a desired sealing function can be exhibited, and even when the abradable film is damaged, the abradable film can be prevented from falling off.

【Invention effect】

According to the sealing structure described above and the rotary machine provided with the sealing structure, the abradable coating enters the concave-convex portion, hardens and welds, thereby enabling firm bonding. Therefore, even when the abradable film is damaged, it is possible to prevent the abradable film from coming off.

Description of drawings

FIG. 1 is a schematic diagram of a gas turbine (rotary machine) according to an embodiment of the present invention.

Fig. 2 is a perspective view of a sealing structure according to the embodiment of the present invention.

3 is a cross-sectional view taken along line X-X of FIG. 1 showing a stator vane that is a component of the sealing structure according to the first embodiment of the present invention.

4 is a cross-sectional view taken along line X-X in FIG. 1 , showing a stator vane that is a constituent member of a sealing structure according to a second embodiment of the present invention.

5 is a cross-sectional view taken along line X-X in FIG. 1 , showing a stator vane that is a constituent member of a sealing structure according to a third embodiment of the present invention.

6 is a cross-sectional view taken along line X-X of FIG. 1 showing a stator vane that is a component of a sealing structure according to a fourth embodiment of the present invention.

7 is a cross-sectional view taken along line X-X in FIG. 1 , showing stator blades that are components of the sealing structure according to a fifth embodiment of the present invention.

8 is a Y-Y cross-sectional view of FIG. 1 showing a stator vane, which is a constituent member of a sealing structure according to a sixth embodiment of the present invention.

9 is a Y-Y cross-sectional view of FIG. 1 showing a stator vane that is a constituent member of a sealing structure according to a seventh embodiment of the present invention.

10 is a Y-Y cross-sectional view of FIG. 1 showing a stator vane, which is a constituent member of a sealing structure according to an eighth embodiment of the present invention.

11 is a cross-sectional view showing a stator vane that is a constituent member of a sealing structure according to an eighth embodiment of the present invention.

Detailed ways

(first embodiment)

Hereinafter, a rotary machine according to a first embodiment of the present invention will be described with reference to the drawings.

A first embodiment of the present invention will be described with reference to FIG. 1 . A gas turbine (rotary machine) 1 includes: a compressor 2 that generates compressed air; a combustor 3 that mixes fuel with compressed air generated by the compressor 2 and combusts it to generate combustion gas M; The turbine 4 is rotationally driven as a working fluid.

The rotor 5 is inserted into the compressor 2 and the turbine 4 . The compressor 2 has: a compressor housing 2a through which the rotor 5 is inserted; a compressor rotor blade 2b capable of rotating together with the rotor 5; and a compressor stator blade 2c fixed to the compressor housing 2a. A plurality of compressor rotor blades 2b and compressor stator blades 2c are arranged radially along the circumferential direction R, respectively. Compressor moving blades 2b and compressor stationary blades 2c are alternately arranged in the axial direction (axial direction) P, and each of a plurality of blades arranged in the circumferential direction R constitutes one stage, and each stage is provided in multiple stages. Then, the sucked air circulates between the compressor vanes 2c, is compressed by the rotation of the compressor rotor vane 2b on the downstream side, and is compressed by repeating the above operation to generate compressed air.

Also, the turbine 4 has: a turbine casing 10 through which the rotor 5 is inserted; a turbine rotor blade 20 rotatable together with the rotor 5 ; and a turbine stator blade (stationary blade) 30 fixed to the turbine casing 10 . The turbine rotor blades 20 and the turbine stator blades 30 extend in the radial direction Q, and are arranged radially in plurality in the circumferential direction R, respectively. Furthermore, the turbine moving blades 20 and the turbine stator blades 30 are alternately arranged in the axial direction P, and each of a plurality of blades arranged in the circumferential direction R constitutes one stage, and each of multiple stages is provided. Then, the combustion gas M as the working fluid flowing in from the combustor 3 flows between the turbine rotor blades 30, rotates the turbine rotor blade 20 on the downstream side, and repeats the above-mentioned operation to flow to the rotor 5 to which the turbine rotor blade 20 is fixed. Apply torque to cause it to rotate.

In addition, in order to prevent the combustion gas M from leaking from the high-pressure side to the low-pressure side, a plurality of sealing structures 7 are provided along the axial direction P, and the sealing structures 7 will be described in detail below.

As shown in FIG. 2 , the sealing structure 7 includes: a plurality of fins 40 protruding from the outer peripheral surface of the rotor 5 ; and a turbine vane 30 .

The plurality of fins 40 protrude in the circumferential direction R from the outer peripheral surface of the rotor 5 and are arranged at intervals in the axial direction P. As shown in FIG. Furthermore, the fin 40 has the outer peripheral surface of the rotor 5 as a base end portion 40a, and forms a front end portion 40b so as to narrow in width from the base end portion 40a toward the turbine stator blade 30 side. In this manner, the plurality of fins 40 , 40 .

The turbine vane 30 has: an inner shroud 50 provided on the rotor 5 side; an abradable film 60 formed on the inner shroud 50; a blade main body 70 radially extending from the inner shroud 50; The outer shroud 80 is provided at the end.

The inner shroud 50 is called a Z-shape shroud, and has a Z-shape when viewed from the inner side in the radial direction Q. As shown in FIG. Furthermore, the inner shroud 50 is Z-shaped in order to suppress leakage of high-temperature gas from between the adjacent inner shroud 50 and to suppress twisting of the blade main body 70 .

In addition, the inner shroud 50 is arranged in the axial direction P, and is arranged in contact with the inner shroud 50 adjacent in the circumferential direction R. As shown in FIG.

In addition, as shown in FIG. 3 , a concavo-convex shape is formed on the inner peripheral surface 50 a of the inner shroud 50 . In the present embodiment, the concave portion 51 is formed to extend in the circumferential direction R from the inner peripheral surface 50 a of the inner shroud 50 toward the inside of the inner peripheral surface 50 a , in other words, toward the radially Q outer side.

The concave portion 51 has: a shield side base portion 51a; a pair of shield side wall portions 51b provided substantially perpendicularly from the inner peripheral surface 50a; the pair of shield side wall portions 51b are connected so as to be substantially perpendicular to the shield side wall portions 51b The shroud-side bottom 51c is provided ground.

In addition, in the present embodiment, the abradable film 60 is formed by spraying an abradable material on the inner peripheral surface 50 a of the inner shroud 50 so as to face the fins 40 (see FIG. 2 ). Furthermore, the abradable film 60 is formed along the concave-convex shape. In the present embodiment, the abradable film 60 is sprayed from the shroud-side base 51a of the concave portion 51 to the shroud-side bottom 51c to form the convex portion 61 .

The convex part 61 protrudes from the outer peripheral surface 60a of the abradable film 60 toward the inside of the inner shield 50, and has an abradable side base part 61a, a pair of abradable side wall parts 61b provided substantially perpendicularly from the outer peripheral surface 60a, and a pair of abradable side wall parts 61b. The abradable side top portion 61c is connected to the abradable side wall portion 61b.

In addition, the shroud-side base portion 51a of the concave portion 51 is joined to the abradable-side base portion 61a of the convex portion 61, the shroud side wall portion 51b of the concave portion 51 is joined to the abradable side wall portion 61b of the convex portion 61, and the shroud side wall portion 61b of the concave portion 51 is joined. The bottoms 51c are respectively engaged with the abradable-side tops 61c of the protrusions 61 .

It should be noted that, as the abradable material, for example, a nickel-based alloy can be used.

As shown in FIG. 2 , the blade main body 70 is formed of a ventral side 71 constituting the ventral side and a back side 72 constituting the dorsal side.

The ventral surface 71 is curved so as to bulge toward the dorsal surface 72 side, and the dorsal surface 72 is curved so as to bulge toward the same side as the ventral surface 71 .

The outer shroud 80 is arranged in contact with the outer shroud 80 adjacent in the axial direction P and the circumferential direction R. As shown in FIG.

In the gas turbine 1 provided with the sealing structure 7 configured in this way, the abradable material enters as the convex portion 61 into the concave portion 51 formed in the inner shroud 50 to be hardened and welded, so the bonding between the inner shroud 50 and the abradable film 60 The area increases. Accordingly, the inner shroud 50 and the abradable film 60 are firmly joined together with the increase in the joint area. In addition, since the concave portion 51 is formed to extend in the circumferential direction R, the bonding force between the inner shroud 50 and the abradable film 60 can be increased in the circumferential direction R. Therefore, even when the abradable film 60 is damaged when the gas turbine 1 is operated, it is possible to prevent the abradable film 60 from being peeled off from the inner shroud 50 and falling off.

In addition, in this embodiment, the abradable material can be directly provided on the inner shield 50 . Accordingly, compared with the conventional structure in which an abradable material is sprayed on the sealing member provided on the inner shroud 50 , the sealing member is not required, and the distance between the rotor 5 and the turbine vane 30 can be shortened accordingly. As a result, the turbine 4 and the entire gas turbine 1 can be reduced in size.

(second embodiment)

Hereinafter, a gas turbine 201 according to a second embodiment of the present invention will be described using FIG. 4 .

In this embodiment, the same reference numerals are assigned to the same components as those used in the above-mentioned embodiments, and description thereof will be omitted.

In the sealing structure 7 of the first embodiment, the pair of shield side wall portions 51b of the concave portion 51 formed in the inner shield 50 are formed substantially perpendicular to the shield side base portion 51a. On the other hand, in the sealing structure 207 of the present embodiment, the shroud side wall portion 251b is formed approximately perpendicular to the shroud side base portion 251a, but the shroud side wall portion 251d is formed at an acute angle with respect to the shroud side base portion 251a. .

That is, the concave portion 251 of the inner shroud 250 is formed so as to move from the inner peripheral surface 250 a of the inner shroud 250 toward the shroud-side bottom portion 251 c of the concave portion 251 in a cross section perpendicular to the direction in which the concave portion 251 extends (circumferential direction R). Formed in such a way that the width becomes wider. In the present embodiment, the shield side wall portion 251b is formed approximately perpendicular to the shield side base portion 251a, but the shield side wall portion 251d is formed from the opposite shield side wall portion 251b toward the shield side bottom portion 251c. Separated form. In this way, the width 261f of the shield-side bottom portion 251c is wider than the width 261e of the shield-side base portion 251a of the recess 251 in a cross section perpendicular to the extending direction (circumferential direction R) of the recess 251 .

In addition, the convex portion 261 of the abradable film 260 has a shape corresponding to the concave portion 251, and the abradable side wall portion 261d is formed so as to be separated from the abradable side wall portion 261b toward the abradable side top portion 261c.

In the gas turbine 201 including the sealing structure 207 configured in this way, the shroud side wall portion 251d and the abradable side wall portion 261d are inclined, so that the bonding area between the inner shroud 250 and the abradable film 260 can be further increased. Furthermore, when a force acts on the abradable film 260 inward in the radial direction Q in the direction of falling off, resistance acts outward in the radial direction Q on the abradable side wall portion 261d to prevent falling off. Thereby, the inner shroud 250 and the abradable film 260 can be bonded more firmly, so even if the abradable film 260 is damaged, the abradable film 260 can be prevented from peeling off from the inner shroud 250 to fall off.

(third embodiment)

Hereinafter, a gas turbine 301 according to a third embodiment of the present invention will be described using FIG. 5 .

In this embodiment, the same reference numerals are assigned to the same components as those used in the above-mentioned embodiments, and description thereof will be omitted.

In the sealing structure 207 of the second embodiment, the shroud side wall portion 251b is formed approximately perpendicular to the shroud side base portion 251a, and the shroud side wall portion 251d is formed at an acute angle to the shroud side base portion 251a. On the other hand, in the sealing structure 307 of the present embodiment, both the shield side wall portions 351b and 351d are formed at an acute angle with respect to the shield side base portion 351a.

That is, the concave portion 351 of the inner shroud 350 is formed so as to move from the inner peripheral surface 350 a of the inner shroud 350 toward the shroud-side bottom portion 351 c of the concave portion 351 in a cross section perpendicular to the extending direction (circumferential direction R) of the concave portion 351 . Formed in such a way that the width becomes wider. In the present embodiment, the shield side wall portions 351b and 351d are formed so as to be separated from each other toward the shield side bottom portion 351c. In this way, the width 361f of the shield-side bottom portion 351c is wider than the width 361e of the shield-side base portion 351a of the recess 351 in a cross section perpendicular to the extending direction (circumferential direction R) of the recess 351 .

In addition, the convex part 361 of the abradable film 360 has a shape corresponding to the concave part 351, and the abradable side wall parts 361b and 361d are formed so as to be separated from each other toward the abradable side top part 361c.

In the gas turbine 301 provided with the sealing structure 307 configured in this way, the shroud side wall portions 351b, 351d and the abradable side wall portions 361b, 361d are inclined, so that the bonding area between the inner shroud 350 and the abradable film 360 can be further increased. . Furthermore, when a force acts on the abradable film 360 inward in the radial direction Q in the direction of falling off, resistance acts outward in the radial direction Q on both the abradable side wall portions 361b and 361d to prevent falling off. Thereby, the inner shield 350 and the abradable film 360 can be bonded more firmly, so even if the abradable film 360 is damaged, the abradable film 360 can be prevented from peeling off from the inner shield 350 and falling off.

(fourth embodiment)

Hereinafter, a gas turbine 401 according to a fourth embodiment of the present invention will be described using FIG. 6 .

In this embodiment, the same reference numerals are assigned to the same components as those used in the above-mentioned embodiments, and description thereof will be omitted.

In the recess 51 of the inner shroud 50 of the sealing structure 7 of the first embodiment, the shroud side base 51a is substantially perpendicular to the shroud side wall 51b, and the shroud side wall 51b is also substantially perpendicular to the shroud side bottom 51c. On the other hand, the concave portion 451 of the sealing structure 407 according to the present embodiment has an arcuate shape so as to protrude from the inner peripheral surface 450 a of the inner shroud 450 in a cross section perpendicular to the extending direction (circumferential direction R) of the concave portion 451 . formed.

That is, the concave portion 451 of the inner shroud 450 has a semicircular shape swollen from the inner peripheral surface 450 a toward the inside of the inner shroud 450 .

In addition, the convex portion 461 of the abradable film 460 has a shape corresponding to the concave portion 451, and has a semicircular shape bulging outward from the outer peripheral surface 460a.

Also in the gas turbine 401 including the sealing structure 407 configured in this way, the joint area between the inner shroud 450 and the abradable film 460 can be increased, so that the inner shroud 450 and the abradable film 460 can be firmly joined.

(fifth embodiment)

Hereinafter, a gas turbine 501 according to a fifth embodiment of the present invention will be described using FIG. 7 .

In this embodiment, the same reference numerals are assigned to the same components as those used in the above-mentioned embodiments, and description thereof will be omitted.

In the sealing structure 7 of the first embodiment, the concave portion 51 is formed from the side of the inner peripheral surface 50 a of the inner shroud 50 toward the inside thereof. On the other hand, in the sealing structure 507 of the present embodiment, the concave portion 561 is formed from the outer peripheral surface 560 a of the abradable film 560 toward the inside thereof.

That is, the concave part 561 has: an abradable side base part 561a; a pair of abradable side wall parts 561b provided substantially perpendicularly from the outer peripheral surface 560a; Vertically disposed abradable side bottom 561c.

In addition, the convex portion 551 has a shape corresponding to the concave portion 561, protrudes from the inner peripheral surface 550a of the inner shroud 550 toward the inside of the abradable film 560, has an inner shroud base portion 551a, and is provided approximately perpendicularly from the inner peripheral surface 550a. The pair of shield side wall parts 551b and the shield side top part 551c which connects this pair of shield side wall parts 551b.

Also in the gas turbine 501 including the sealing structure 507 configured in this way, the bonding area between the inner shroud 550 and the abradable film 560 can be increased, so that the inner shroud 550 and the abradable film 560 can be firmly bonded.

In addition, since it is only necessary to selectively provide a concave portion on one of the inner shroud 550 and the abradable film 560 and provide a convex portion on the other, the degree of freedom in design increases.

(sixth embodiment)

Hereinafter, a gas turbine 601 according to a sixth embodiment of the present invention will be described using FIG. 8 .

In this embodiment, the same reference numerals are assigned to the same components as those used in the above-mentioned embodiments, and description thereof will be omitted.

In the sealing structure 7 of the first embodiment, the concave portion 51 is formed to extend in the circumferential direction R. As shown in FIG. On the other hand, in the seal structure 607 of the present embodiment, the concave portion 651 is formed to extend in the axial direction P. As shown in FIG.

That is, a plurality of recesses 651 are formed along the axial direction P and at intervals in the circumferential direction R on the inner side in the radial direction Q of the boundary line 654 between the adjacent inner shrouds 650 , 650 . . .

In addition, the abradable film 660 is formed as a convex portion 661 entering inside the concave portion 651 .

In the gas turbine 601 including the seal structure 607 configured in this way, the concave portion 651 is formed to extend along the axial direction P, so that the bonding force between the inner shroud 650 and the abradable film 660 can be increased in the axial direction P.

In addition, on the boundary line 654 between the adjacent inner shrouds 650, 650..., when a shearing force between the inner shrouds 650, 650... is generated, it is possible to reduce the abradable film 660 from entering the concave part as the convex part 661. The amount of shear force within 651. Accordingly, deformation due to twisting of the turbine vane 630 can be prevented, and the stability of the gas turbine 601 itself can be improved.

(seventh embodiment)

Hereinafter, a gas turbine 701 according to a seventh embodiment of the present invention will be described using FIG. 9 .

In this embodiment, the same reference numerals are assigned to the same components as those used in the above-mentioned embodiments, and description thereof will be omitted.

In the seal structure 607 of the sixth embodiment, the concave portion 651 is formed on the inner side in the radial direction Q of the boundary line 654 between the adjacent inner shrouds 650 , 650 . . . On the other hand, in the sealing structure 707 of the present embodiment, the concave portion 751 is formed within the dimension of the axial direction P of each inner shroud 750 .

That is, a plurality of recesses 751 are formed at substantially the center of the inner shroud 750 in the axial direction P dimension along the axial direction P and at intervals in the circumferential direction R. As shown in FIG.

In the gas turbine 701 including the seal structure 707 configured in this way, the concave portion 751 is formed to extend along the axial direction P, so that the bonding force between the inner shroud 750 and the abradable film 760 can be increased in the axial direction P.

(eighth embodiment)

Hereinafter, a gas turbine 801 according to an eighth embodiment of the present invention will be described with reference to FIGS. 10 and 11 .

Here, FIG. 10 is a Y-Y cross-sectional view of FIG. 1 of the sealing structure 807 according to this embodiment, and FIG. 11 is a cross-sectional view obtained by partially cutting the inner shroud 850 of the sealing structure 807 .

In this embodiment, the same reference numerals are assigned to the same components as those used in the above-mentioned embodiments, and description thereof will be omitted.

In the sealing structure 607 of the sixth embodiment, the concave portion 651 is only a structure formed from the inner peripheral surface 650 a of the inner shroud 650 toward the inside thereof. On the other hand, in the seal structure 807 of the present embodiment, the concave portion has a concave portion 851 formed from the inner peripheral surface 850a of the inner shroud 850 toward the inside thereof, and a concave portion 851 facing from the outer peripheral surface 860a of the abradable film 860 toward the inside. The second recess 862 is formed inside it. Furthermore, a pin member 890 is inserted between the concave portion 851 and the second concave portion 862 .

That is, as shown in FIG. 10 , the concave portion 851 is located on the inner side in the radial direction Q of the boundary line 854 between the adjacent inner shrouds 850 , 850 . . . The peripheral surface 850a is formed in plural toward the inside. Furthermore, as shown in FIG. 11 , the concave portion 851 is formed in two places at intervals in the axial direction P for one inner shield 850 .

In addition, the above-mentioned numerical value is an example, and it may be three parts, and it is not limited to this numerical value.

In addition, as shown in FIG. 10 , the second concave portion 862 is located on the inner side in the radial direction Q of the boundary line 854 between the adjacent inner shrouds 850 , 850 . . . A plurality of outer peripheral surfaces 860a are formed toward the inside thereof. Furthermore, as shown in FIG. 11 , the second concave portion 862 is formed in two places at intervals in the axial direction P for one inner shroud 850 .

In addition, the pin member 890 is a rod-shaped member, and one end 890 a is disposed on the shield-side bottom 851 c of the recess 851 , and the other end 890 b is disposed on the abradable-side bottom 861 c of the second recess 862 .

In addition, as a method of manufacturing the sealing structure 807 , the pin member 890 is inserted into the recess 851 of the inner shield 850 , an abradable material is sprayed to fix the pin member 890 to the recess 851 , and the abradable film 860 is formed.

In the gas turbine 801 provided with the sealing structure 807 in this way, the pin member 890 firmly couples the adjacent inner shrouds 850 , 850 .

In addition, since the other end 890b side of the pin member 890 protrudes when the abradable material is thermally sprayed, the abradable material is deposited well, and the abradable film 860 can be formed. Accordingly, the inner shield 850 and the abradable film 860 can be firmly joined via the pin member 890 .

In addition, each shape and combination of each component shown in the above-mentioned embodiment is an example, and various changes can be made based on design requirements etc. within the range which does not deviate from the summary of this invention.

In addition, in the above-mentioned embodiment, a gas turbine has been described as an example of a rotary machine, but it can also be applied to other rotary machines such as a steam turbine.

【Industrial Applicability】

According to the sealing structure described above and the rotary machine provided with the sealing structure, the abradable coating enters the concave-convex portion, hardens and welds, thereby enabling firm bonding. Therefore, even when the abradable film is damaged, it is possible to prevent the abradable film from coming off.

【Description of labels】

1, 201, 301, 401, 501, 601, 701, 801 gas turbine (rotating machinery)

5 rotors

7, 207, 307, 407, 507, 607, 707, 807 Sealing structure

30 Turbine stator blades (stator blades)

40 fins

50, 250, 350, 450, 550, 650, 750, 850 Inner shroud

50a, 250a, 350a, 550a, 650a, 850a inner peripheral surface

51, 251, 351, 451, 561, 651, 751, 851 Concave

60, 260, 360, 460, 560, 660, 760, 860 Abradable film

60a, 260a, 360a, 560a, 860a outer peripheral surface

654, 854 dividing line

R Circumferential

Claims (9)

1. a sealing configuration, possesses:

Fin, from the outer circumferential face of rotor along circumferentially outstanding;

And stator blade, at the inner peripheral surface of inner side guard shield, in the mode relative with described fin, be formed with and can wear away epithelium,

Inner peripheral surface at described inner side guard shield is formed with concaveconvex shape, and the described epithelium that wears away forms along described concaveconvex shape.

2. sealing configuration according to claim 1, wherein,

Described concaveconvex shape consists of towards its inner recess forming the side the inner peripheral surface from described inner side guard shield and the described outer circumferential face that wears away epithelium.

3. sealing configuration according to claim 2, wherein,

Described recess forms in the mode along described circumferential extension.

4. sealing configuration according to claim 2, wherein,

The mode that described recess extends with the axial direction along described rotor forms.

5. sealing configuration according to claim 3, wherein,

Described recess is formed on along on described circumferential adjacent described inner side guard shield separatrix each other.

6. sealing configuration according to claim 4, wherein,

A side in the inner peripheral surface of described inner side guard shield and the described outer circumferential face that wears away epithelium, the described recess that forms with opposite side in inner peripheral surface at described inner side guard shield and the described outer circumferential face that wears away epithelium is relative and be formed with the second recess,

Described sealing configuration possesses to the pin parts that insert between described recess and described the second recess.

7. according to the sealing configuration described in any one in claim 3～5, wherein,

Described recess on the cross section of the bearing of trend quadrature with this recess, with the inner peripheral surface along with from described inner side guard shield or the described outer circumferential face that wears away epithelium towards the bottom of this recess and the mode that width broadens gradually form.

8. according to the sealing configuration described in any one in claim 2～5, wherein,

Described recess, on the cross section of the bearing of trend quadrature with this recess, forms bloat from the inner peripheral surface of described inner side guard shield or the described outer circumferential face that wears away epithelium circular-arc.

9. a rotating machinery, it possesses the sealing configuration described in any one in claim 1～7.