JP5713937B2 - SEALING DEVICE, GAS TURBINE HAVING SEALING DEVICE - Google Patents

Description

  The present invention relates to a sealing device between adjacent segments.

  In general, a gas turbine in a thermal power plant is a compressor that sucks air and raises the pressure to a predetermined pressure, a combustor that generates combustion gas by mixing air pressurized by the compressor with fuel, and high-temperature and high-pressure combustion gas. Is composed of a turbine that generates power by expanding, and a generator that converts the power generated by the turbine into electrical energy.

In the configuration of the turbine section, when the high-temperature combustion gas flows through the combustion gas flow path in which the moving and stationary blades of the turbine are arranged, the turbine rotor rotates at high speed to generate power (shaft rotational force).
Therefore, in order to obtain a high output with the gas turbine, it is important to increase the temperature of the combustion gas at the inlet of the turbine section and to improve the efficiency of the gas turbine.

  As the temperature of such a gas turbine increases, the moving blades and stationary blades of the turbine have a structure in which a cooling medium can be supplied into the blades in order to protect the blade members from the heat of the high-temperature combustion gas. Generally, air extracted at a predetermined pressure from a compressor is introduced into a casing or turbine rotor as a cooling medium, and after cooling the inside of the blade, the cooling medium is burned from pores or slits provided in the blade. There is a method of discharging directly to the flow path. A part of the cooling medium introduced for cooling the stationary blades is used as a seal for the turbine wheel space and is discharged to the combustion gas flow path.

  Constituent members such as a stationary blade and a diaphragm are annularly arranged in the circumferential direction as a segment structure, but a gap is provided between segments adjacent in the circumferential direction in consideration of the amount of thermal elongation. This gap is designed so as not to become zero even at the time of gas turbine rated operation. The cooling medium flow path formed inside the casing and turbine rotor communicates with the combustion gas flow path through the gap between the segments, and a part of the cooling medium introduced for cooling the blades and sealing the wheel space is used. Leaks into the combustion gas flow path through the gap between the segments. Such leakage of the cooling medium itself is a loss, and the gas temperature in the combustion gas flow path and the mixing loss between the cooling medium and the combustion gas are generated, resulting in a decrease in turbine performance. Reducing the efficiency and output.

  Therefore, a seal groove is provided on the facing surface between adjacent segments via a gap in the circumferential direction, a plate-like member is inserted into the groove, and bent portions that elastically press into the groove at both ends of the plate-like member. There is a method of suppressing the leakage of the cooling medium from the gap between the segments by making a pressure contact between the sealing device and the inner wall surface of the seal groove by using a sealing device having linear protrusions (see Patent Document 1). .

JP-A-10-2203

  The prior art described in Patent Document 1 is a plate-like member in which a seal groove is provided on opposite axial surfaces of the stationary blade shrouds adjacent to each other in the circumferential direction, and a bent portion and a linear protrusion are provided in both seal grooves. Even if the seal plate is inserted and the seal groove is deformed due to thermal deformation of the shroud, the gap between the seal plate and the seal groove is reduced by the pressure contact of the linear protrusions of the seal plate, thereby improving the sealing performance. Is. However, in addition to the deformation of the seal groove due to thermal deformation, a deviation occurs in the amount of thermal expansion in the radial direction between adjacent segments, and thus there may be a positional deviation in the radial direction between both of the opposed seal grooves. Therefore, in the seal plate, when the seal groove is misaligned, the gap between the seal plate and the seal groove is widened, which may reduce the sealing performance.

  In addition, a plurality of intersecting seal grooves are usually provided on the opposed axial surfaces of the stationary blade shrouds adjacent to each other in the circumferential direction. At the end surfaces where the two seal plates inserted into the two seal grooves intersecting in the axial direction come into contact with each other, it is difficult to bring the seal plates into surface contact due to the structure. If there is a deviation in the amount of thermal expansion in the radial direction between adjacent segments, the seal plate is twisted three-dimensionally, so that a large amount of cooling medium leaks from the end of the seal plate, and the sealing performance may drop sharply. is there.

  An object of the present invention is to provide a highly reliable sealing device that can flexibly cope with a deviation in the amount of thermal elongation between segments.

In a sealing device that is attached to a pair of grooves provided on opposing surfaces and seals the flow of fluid between the opposing surfaces, a recess extending in the extending direction of the pair of grooves and an extending direction of the pair of grooves a first member and a convex portion are arranged alternately extending, characterized in that it comprises a second member mounted on the lower surface of the upper surface and the convex portion of the concave portion.

  It is possible to provide a highly reliable sealing device that can flexibly cope with a deviation in the amount of thermal expansion between segments.

The system diagram of a gas turbine. FIG. 3 is a cross-sectional view of the vicinity of the compressor rear stage of the gas turbine, the vicinity of the combustor, and the turbine high pressure section. The enlarged view of the 2nd stage stationary blade body of a gas turbine. The perspective view of the general seal structure of the outer peripheral side of the 2nd stage stationary blade body segment of a gas turbine. The turbine axial direction sectional view showing the structure of the sealing device between the stationary blade body segments which a gas turbine adjoins. The turbine circumferential direction sectional drawing showing the structure of the sealing device of the stationary blade body segment of a gas turbine. 1 is a circumferential cross-sectional view of a sealing device according to a first embodiment of the present invention. The turbine circumferential direction sectional drawing showing the structure of the sealing device which is 1st embodiment of this invention. The turbine axial direction sectional drawing showing the structure of the sealing device between the stationary blade body segments which is 2nd embodiment of this invention. The circumferential direction sectional drawing of the sealing device which is 3rd embodiment of this invention. The circumferential direction sectional drawing of the sealing device which is 4th embodiment of this invention.

Hereinafter, the present invention will be described in detail based on illustrated embodiments.
First, the configuration of the gas turbine will be described with reference to the gas turbine system diagram of FIG. A gas turbine 00 used in a thermal power plant or the like generates a combustion gas 104 by mixing and combusting a compressor 1 that sucks air 101 and raises the pressure to a predetermined pressure, and air 102 that has been pressurized by the compressor 1 and fuel 103. Combustor 2, turbine 3 that generates power by expansion of high-temperature and high-pressure combustion gas 104, and generator 4 that converts the power generated in turbine 3 into electrical energy, compressor 1, turbine 3, power generation The machine 4 rotates around the rotation shaft 5.

  Further, the moving and stationary blades of the turbine 3 have a structure in which a cooling medium can be supplied into the blades in order to protect the blade members from the heat of the high-temperature combustion gas 104. The air (cooling medium) extracted from the compressor 1 at a predetermined pressure passes through the cooling air flow path 201 of the stationary blade and the cooling air flow path 202 of the moving blade, cools the inside of the moving blade and stationary blade by heat exchange, and then enters the blade. It is directly discharged from the provided pores and slits to the combustion gas flow path. In this embodiment, a single-shaft gas turbine for a thermal power plant is used, but a two-shaft type that can drive a pump or a process compressor as a load device instead of the generator 4. You may use what was comprised with the turbine.

  FIG. 2 shows a cross-sectional view of the vicinity of the latter stage of the compressor, the vicinity of the combustor, and the turbine high pressure section. FIG. 2 shows an upper half structure with respect to the rotating shaft 5. The turbine 3 includes stationary blades 11a and 12a and moving blades 11b and 12b, rotor disks 13a and 13b, a spacer disk 14 and a stacking bolt 15 which are alternately arranged in the flow path of the combustion gas 104. Flows through the combustion gas flow path in which the moving and stationary blades are arranged, so that the rotor rotates at high speed to generate power.

  Next, the flow of the cooling medium when cooling the blades will be described with reference to FIG. 2 using the turbine second stage stationary blade 12a as an example. Air 201 (hereinafter, the cooling medium is described as air), which is a cooling medium extracted from the compressor 1 to the turbine blades at a predetermined pressure corresponding to the gas path pressure, has an introduction hole (not shown) provided in the casing 25. It passes through and is introduced into the cooling air supply cavity 31 of the second stage stationary blade 12a. The cooling air supplied to the cooling air supply cavity 31 is supplied to the second stage stationary blade body 21 that is annularly arranged in the circumferential direction on the inner peripheral side of the casing. A part of the cooling air supplied to the second stage stationary blade body 21 rises in temperature while cooling the second stage stationary blade 12a by exchanging heat when passing through the cooling path inside the second stage stationary blade body 21, and the second stage stationary blade 12a is discharged to the gas path 6 through a film hole or blade trailing edge ejection hole formed on the surface, and is mixed with the combustion gas 104 which has been thermally expanded through the first stage stationary blades 11a and 11b, and is subjected to the second stage motion. It becomes the working gas of the blade 12b.

  On the other hand, the other part of the cooling air supplied to the second stage stationary blade body 21 is supplied to the cavity 32 of the diaphragm 22 that is annularly arranged on the inner peripheral side of the second stage stationary blade body 21 in the circumferential direction. The cooling air introduced into the cavity 32 is supplied to the first stage rotor blade rear wheel space 35 formed by the first stage rotor disk 13 a, the spacer disk 14, and the diaphragm 22. After that, via a seal fin 23 provided between the diaphragm 22 and the spacer disk 14, it is branched into a second stage rotor blade front wheel space 36 formed by the second stage rotor disk 13b, the spacer disk 14 and the diaphragm 22. , Used as sealing air for suppressing the working combustion gas 104 from entering the wheel spaces 35 and 36.

  FIG. 3 shows an enlarged view of the second stage stationary blade body 21. The second stage stationary blade body 21 has a segment structure arranged annularly in the circumferential direction on the inner peripheral side of the turbine casing. At the segment end face of the second stage stationary blade body 21 adjacent in the circumferential direction, seal grooves 62, 63, 64 extending in the turbine axial direction and the radial direction are formed in the shroud of the outer peripheral side wall 42 of the second stage stationary blade 12a. It is provided to intersect in the vicinity. In the segment end faces adjacent to each other in the circumferential direction, a gap is provided between the segments in consideration of the amount of thermal elongation, and this gap value is designed not to become zero even during turbine rated operation. Therefore, the cooling air 201 supplied to the second stage stationary blade body 21 is discharged as leaked air into the gas path through the circumferential gap between the segments and the gaps at both ends in the axial direction. In order to suppress this leakage, a seal device is installed in the seal groove between the segments.

  FIG. 4 is a perspective view of a general seal structure on the outer peripheral side of adjacent second stage stationary blade body segments 21a and 21b. Between the end face 63a of the second stage stationary blade body segment 21a and the opposing end face 63b of the adjacent stationary blade body segment 21b, in order to suppress the leakage of cooling air into the gas path via the circumferential gap between the segments, A plurality of seal grooves 61 a, 61 b, 63 a, 63 b, 64 a, 64 b extending in the turbine axial direction and the radial direction and having a depth in the circumferential direction can be provided and mounted in the respective seal grooves between the segments. Sealing devices 51, 52 and 53 are provided. As a result, the gap between the stationary blade body segments is blocked, and the segment gap can be sealed.

  FIG. 5 is a turbine axial direction sectional view showing the structure of the sealing device between the stationary blade body segments 21a and 21b. FIG. 5A shows a sectional view of the sealing device when the sealing device is assembled, and FIG. 5B shows a sectional view of the sealing device when the gas turbine is operated.

  As shown in FIG. 5 (a), at the time of assembly, the two stationary blade body segments 21a and 21b have a gap δc in the circumferential direction at the opposed end surfaces 63a and 63b, and the stationary blade body segment 21a has a seal groove 61a. The stationary blade body segment 21b is provided with a seal groove 61b, and a seal device 52 is installed so as to bridge the circumferential gap between the seal grooves. If the state at the time of assembly is ideally maintained even during the operation of the gas turbine, the sealing device 52 is connected to the cooling air flow path 201 by the pressure difference between the flow path of the cavity 31 to which the cooling air is supplied and the flow path of the combustion gas 104. It is pushed in the direction of the arrow. As a result, the contact surfaces of the seal groove in each segment with the seal device 52 are brought into a surface contact state on the surfaces 71a and 71b, and the flow of cooling air around the seal groove and leaking into the combustion gas flow path is blocked. Leakage air in the gap between the wing body segments 21a and 21b is almost sealed.

  However, during operation of the gas turbine, the temperature of each member rises due to inflow heat from the working gas and cooling air. As a result, thermal expansion occurs in the stationary blade body segments 21a and 21b, and the circumferential gap δc between the segments during assembly is δh () as shown in FIG. <Δc). Since the stationary blade body segment 21a and the stationary blade body segment 21b are designed not to contact each other even during gas turbine rated operation, the gap value δh does not become zero. Further, thermal elongation occurs not only in the circumferential direction but also in the turbine radial direction. A radial displacement δr occurs in the seal grooves 61a and 61b due to a deviation in the amount of heat due to heat flow in the stationary blade body segments 21a and 21b. Thereby, when the sealing device 52 such as a metal flat plate is attached to the sealing groove, the contact surface of the sealing device 52 and the sealing groove in each segment changes from the surface contact state to the line contact state in the axial lines 72a and 72b. To do.

  By changing from the surface contact to the line contact state, the sealing performance is lowered, the cooling air goes around the inside of the seal groove, and the leakage 301 to the flow path of the combustion gas 104 occurs. This leakage of the cooling medium itself is a loss, and the gas temperature in the combustion gas flow path and the mixing loss between the cooling medium and the combustion gas cause a decrease in the performance of the turbine. Reduce efficiency and output.

  FIG. 6 is a sectional view in the turbine circumferential direction in the vicinity of the end of the sealing device 52 extending in the axial direction of the stationary blade body segment 21a. The stationary blade body segment 21a is provided with seal grooves 61a and 64a extending in the axial direction and the radial direction so as to intersect with each other, and sealing devices 52 and 53 are provided so as to close the axial gap where the respective seal grooves intersect. It is installed. Ideally, it is desirable that both sealing devices 52 and 53 are in surface contact at the position where the seal grooves intersect when the gas turbine is operated. During operation of the gas turbine, the temperature of each member rises due to inflow heat from the working gas or cooling air, and thermal expansion occurs in the stationary blade body segment 21a. Therefore, in consideration of the thermal elongation, an axial gap is provided between the two seal devices 52 and 53 at the position where the seal grooves 61a and 64a intersect during assembly, and the gap is set to be zero during rated operation. To do. However, depending on the amount of deviation of the thermal expansion of the stationary blade body segment, the sealing device does not always come into surface contact, but the surface contact state changes to the line contact state, and the sealing performance is reduced, so that the cooling air flows radially from the axial gap. The possibility of leakage 302 into the combustion gas 104 flow path increases. Further, when a radial positional deviation δr (FIG. 5) occurs due to a thermal elongation deviation generated between the stationary blade body segments, the mounted sealing devices 52 and 53 are twisted in a three-dimensionally complicated manner. The contact state changes from line contact to point contact, and cooling air leakage may increase.

  FIG. 7 is a cross-sectional view of the sealing device according to the first embodiment of the present invention in the turbine circumferential direction. The structure of the sealing device 70 shown in FIG. 7 is that a member of the heat-resistant metal thin plate 71 is provided with irregularities in the radial direction along the axial direction, and a metallic cloth material, brush material, or porous material is provided in the concave and convex portions. Is the one that is attached. By adopting a thin plate shape, it is possible to improve the followability to the thermal elongation deviation between the stationary blade body segments as compared with the flat plate sealing device.

  FIG. 8 is a turbine circumferential cross-sectional view showing the structure of the sealing device when the sealing device 70 according to the first embodiment of the present invention shown in FIG. 7 is attached to the outer shroud between the stationary blade body segments 21a. is there. In FIG. 8, one seal device 70 is mounted in the shroud so as to extend in the turbine axial direction and the radial direction and straddle two intersecting seal grooves 61 a and 64 a. The sealing device is pressed to the combustion gas flow path side by the differential pressure between the cavity 31 side to which cooling air is supplied and the combustion gas 104 flow path side. As shown in FIG. 8, at the intersecting portion of two intersecting seal grooves 61a and 64a, the seal device 70 is assembled so that the thin plate recess 71b is disposed on the cavity side (high pressure side) of the cooling air. It is desirable that the thin plate 71 is positioned on the lower pressure side than the cloth material 72. On the other hand, when assembled so that the convex portion of the thin plate is arranged on the cavity side, that is, when the thin plate 71 is located on the high pressure side of the cloth material 72, the bending from the convex portion of the thin plate to the concave portion is caused by the pressure difference of the cooling air. When the stress acts, there is a possibility that the cloth member 72 attached to the concave portion of the thin plate is detached.

  Further, it is desirable that the circumferential cross section of the sealing device of FIG. If there is a step between the circumferential cross section of the thin plate and the circumferential cross section of the cloth member attached to the uneven portion of the thin plate, the cooling is performed when the sealing device 70 is installed in the seal grooves 61a and 64a between the stationary blade body segments. There is a possibility that the air may enter the seal groove in the circumferential direction, and the cooling air may leak from the cavity 31 side to the combustion gas 104 flow path side through the step portion of the seal device. By making the circumferential cross section of the sealing device flat, it is possible to reduce the leakage of cooling air that goes around the seal groove. The circumferential cross section of the sealing device of the present invention needs to form a plane, but if the plane has irregularities, it is also possible to insert a shim at the circumferential end.

  Next, the effect of the sealing device according to the present embodiment during gas turbine operation will be described with reference to FIGS. The two sealing devices 52 and 53 mounted in the axially extending seal groove 61a and the radially extending seal groove 64a are assembled so that the gap at the intersection is zero during operation of the gas turbine. However, with the operation of the gas turbine, the temperature of each member rises due to the inflow heat from the working combustion gas and the cooling air. As a result, deviations in the amount of thermal elongation occur in the stationary blade body segments 21a and 21b, and the two sealing devices 52 and 53 generate gaps at the intersections of the sealing devices due to complicated three-dimensional twisting. Here, as shown in FIG. 8, a thin seal device 70 is mounted across the two seal grooves 61a and 64a, thereby eliminating a gap generated at the portion where the seal grooves intersect. As a result, the sealing performance can be significantly improved. Further, even when a radial deviation occurs between the opposing segments due to the deviation of the thermal elongation amount of the stationary blade body segment, the sealing device 70 is deformed flexibly, and the inner wall surfaces of the seal grooves 61a and 64a and the seals are sealed. The contact area with the apparatus can be increased, and the leakage of cooling air can be effectively suppressed and good sealing performance can be maintained. Thereby, the reliability and efficiency of a gas turbine can be improved.

The thin plate shape of the sealing device 70 according to the first embodiment of the present invention has a simple structure in which rectangular irregularities are alternately formed in the radial direction along the axial direction. Therefore, it is possible to shape the shape of a flat thin plate by a single press process, and the processing cost can be reduced. For example, as shown in FIG. 4, it is possible to insert the sealing device 70 of this embodiment into the sealing grooves 61a and 64a into which the flat plate plates which are the conventional sealing devices 52 and 53 are inserted. .
Sealing devices disposed between stationary blade body segments of a gas turbine are generally replaced in accordance with regular maintenance of the gas turbine. Therefore, since the seal device 70 of this embodiment can share the seal groove into which the conventional seal device is inserted, the seal of the present invention can be used from the conventional seal device without remodeling the seal groove at the time of maintenance and inspection of the gas turbine. Maintenance costs can be acquired by changing to a device.

  FIG. 9 is a sectional view in the turbine axis direction of the sealing device 70 according to the second embodiment of the present invention. FIG. 9 is different from FIG. 8 in that radial concavo-convex portions are formed along the circumferential direction of the thin plate in the cross section in the turbine axial direction. The sealing device according to the present embodiment spans between the seal grooves 61a and 61b formed on the opposing end faces of the stationary blade body segments 21a and 21b facing each other so as to have the same radial direction position. The flow path connecting the cavity 31 to which the cooling air formed by the gap is supplied and the flow path of the combustion gas 104 is blocked. With the operation of the gas turbine, the temperature of each member rises due to the inflow heat from the working combustion gas and the cooling air, and a deviation in the amount of thermal expansion occurs in the stationary blade body segment. As a result, a radial shift occurs in the seal groove.

  By using the seal device according to the present embodiment, the seal device 70 installed in the seal grooves 61a and 61b is pressed against the inner wall surfaces of the seal grooves 61a and 61b by high-pressure cooling air. It can be deformed flexibly with respect to deformation. Thereby, the contact surface of the inner wall surface of the seal groove and the seal device can be always maintained in a surface contact state. In addition, when the positional deviation in the radial direction of the seal groove is large, even if the edge portion of the seal groove end surface interferes with the seal device, there is a possibility of damaging the seal device itself by having the cloth material. As a result, the reliability of the sealing device can be increased.

FIG. 10 shows a cross-sectional shape of a sealing device 80 according to the third embodiment of the present invention. The difference from the cross-sectional shape shown in FIG. 7 is that the concavo-convex portion formed in the radial direction of the thin plate 81 is not a rectangle but a trapezoid that is inclined with respect to the axial direction. Thereby, it is possible to sandwich the cloth material by, for example, inclining the cloth material attached to the concave portion of the thin plate 81 in the axial direction of the thin plate.
Therefore, it is possible to prevent the cloth material from coming off the thin plate, and to improve the reliability of the sealing device.

  FIG. 11 shows a cross-sectional shape of a sealing device 90 according to the fourth embodiment of the present invention. The difference from the cross-sectional shape shown in FIG. 7 is that the uneven portions formed in the radial direction of the thin plate 91 are not rectangular but elliptical. Thereby, like the sealing device shown in FIG. 10, for example, a cloth member attached to the concave portion of the thin plate 91 can be sandwiched. Furthermore, when a deviation in the amount of thermal elongation occurs in the stationary blade body segment and a large deviation occurs in the radial direction in the seal groove, damage to the seal device due to interference between the edge portion of the seal groove and the seal device can be suppressed. Can improve the reliability. However, there is a possibility that the manufacturing cost and the processing cost of the oval sealing device are higher than those of the rectangular sealing device.

  In each of the embodiments, the example in which the present invention is applied to the second stage stationary blade body segment has been described. However, the gap is not limited to the portion, for example, a stationary blade segment of another paragraph, a moving blade shroud, a stationary blade diaphragm, or the like. The present invention can be applied to other places where a plurality of constituent members are adjacent to each other and cooling air may leak from the gaps between the constituent members, and the effect can be obtained.

  The present invention can be applied to any structure in which a plurality of members including a high-temperature portion of a gas turbine are connected to block a high-temperature fluid and a low-temperature fluid and the connecting portion requires cooling.

  The sealing device of each of the embodiments described above is mounted in seal grooves 61a, 61b, 63, and 64, which are a pair of grooves provided on the end surface 63a and the opposite end surface 63b, which are opposed to each other. In the sealing devices 51, 52, and 53 for sealing the flow of fluid, the first members are formed by alternately arranging the concave portions 71b, 81b, and 91b extending in the longitudinal direction and the convex portions 71a, 81a, and 91a extending in the longitudinal direction. Cross members 72, 82, 92, etc., which are second members, are mounted on the thin plate 71 and the upper surfaces of the recesses 71b, 81b, 91b and the lower surface of the projections. According to such a sealing material, since the shape of the thin plates 71, 81, 91 as the first member is easily deformed compared to the flat plate, the thermal elongation deviation between the opposed end surfaces 63a, 63b as compared with the flat plate sealing device. Can be improved, and a highly reliable sealing device can be provided.

  In the present specification, the longitudinal direction is the length direction of the sealing device that is parallel to the end surface 63a and the opposed end surface 63b and corresponds to the length direction of the seal grooves 61a, 61b, 63, 64. Is a direction perpendicular to the paper surface (screen) of this specification. A concave part and a convex part mean the seal device in a state where it is mounted in a pair of seal grooves dug in the horizontal direction as shown in FIG. That is, in the state shown in FIGS. 7, 9, 10, and 11, the first member has a downward convex portion as a concave portion, and the upward convex portion as a convex portion.

  The sealing devices 70 and 80 shown in FIG. 7 and FIG. 10 have one cross member 72, 82, etc., which is a second member mounted on the upper surface of the concave portions 71b, 81b, and one upper surface of the convex portions 71a, 81a. A flat surface is formed, and a single flat surface is formed by the cross members 72, 82 and the like, which are the second members mounted on the lower surfaces of the convex portions 71a, 81a, and the lower surfaces of the concave portions 71b, 81b. Thus, by making the circumferential cross section of the sealing device flat, it is possible to suppress a decrease in sealing performance due to the cooling air entering the sealing groove.

  The sealing devices 80 and 90 shown in FIGS. 10 and 11 have a reduced portion whose width decreases from the bottom to the top with respect to the shape of the recesses 81b and 91b in a cross section cut by a plane perpendicular to the longitudinal direction. . The reduced portion can hold and hold the cloth members 82, 92, etc., can prevent the cloth members 82, 92, etc. from coming off from the thin plates 81, 91, and improve the durability and reliability of the sealing devices 80, 90. Can be made. The sealing devices 80 and 90 also have reduced portions for the convex portions 71a and 81a, and have the same effects as the concave portions 81b and 91b.

  In particular, the sealing device 80 shown in FIG. 10 includes a figure surrounded by a concave portion 81b of the thin plate 81 and a flat portion such as a cloth member 82 and a convex portion of the thin plate 81 in a cross section cut by a plane perpendicular to the longitudinal direction. A figure surrounded by 81a and a plane part such as the cross member 82 is a trapezoid, and the plane part such as the cross member 82 constitutes a short side of the trapezoid. According to this configuration, the above-described reduced portion can inevitably be provided, and a highly reliable sealing device can be obtained.

  Further, in the sealing device 90 shown in FIG. 11, in the cross section cut by the plane perpendicular to the longitudinal direction, the cross section of the thin plate 91a is composed only of a smooth line having a continuous curvature. That is, the reliability can be improved as compared with the shape having a corner like the sealing devices 70 and 80 shown in FIGS. This is because damage due to interference between the edge portion of the seal groove and the seal device can be suppressed.

  The seal device 70 shown in FIG. 7 includes a figure surrounded by a concave portion 71b of the first member and a flat portion of the second member, and a convex portion of the first member, in a cross section cut by a plane perpendicular to the longitudinal direction. The figure surrounded by 71a and the plane part of the second member is a rectangle. That is, the thin plate 71 of the sealing device 70 has a simple structure in which rectangular irregularities are alternately formed. Therefore, it is possible to shape the shape of a flat thin plate by a single press process, and the processing cost can be reduced.

  The above-described sealing devices 70, 80, and 90 are, for example, gas turbine 00 having a compressor 1, a combustor 2, and a turbine 3, and the turbine 3 is a member assembled in a segment shape in the circumferential direction with respect to the rotation axis of the rotor 5. The stationary blade body segments 21a and 21b, which are assembled in a segment shape, are seal grooves 61a that are a pair of grooves facing the adjacent surfaces of the stationary blade body segments 21a and 21b. 61b, and is fitted in this groove. As described above, by using the sealing devices 70, 80, and 90 of the embodiments in the gas turbine, it is possible to suppress the leakage of the cooling air on the sealing surface and provide a highly efficient gas turbine.

  Further, in the embodiment shown in FIG. 8, the stationary blade body segments 21 a and 21 b assembled in a segment form include a pair of seal grooves 61 a and 61 b that are a pair of first grooves opposed to adjacent surfaces. The seal grooves 61a and 61b are provided with seal grooves 64a and 64b, which are a pair of second grooves, and a seal device 70 is mounted so as to straddle the first groove and the second groove. As a result, the sealing performance can be drastically improved as much as there is no gap between the portions where the seal grooves intersect with each other, as compared with the case where the seal grooves 61 and 64 are provided with separate seal plates. Furthermore, it is preferable that the thin plate 71 as the first member is located on the flow path side of the combustion gas 104 on the low pressure side at the intersection of the first seal groove 61 and the second seal groove 64. This is because the bending stress directed from the thin plate 71 toward the cross member 72 due to the pressure difference of the cooling air acts to suppress the possibility of the cross member 72 attached to the thin plate 71 coming off, and the reliability of the sealing device can be improved. In addition, the crossing part said here means the area | region which serves as both the seal groove 61 and the seal groove 64, when each of the seal grooves 61 and 64 is assumed to be a rectangle. Ideally, the first member faces the low pressure side in all regions of this intersection. However, when it is difficult in terms of structure, if at least the first member faces the low pressure side in more regions than the second member, the reliability improvement effect can be obtained.

00 Gas turbine 1 Compressor 2 Combustor 3 Turbine 4 Generator 11a, 12a Stator blade 11b, 12b Rotor blade 13 Rotor disk 14 Spacer disk 21a, 21b Stator blade segment 22 Diaphragm 25 Casing 31, 32 Cavity 35, 36 Wheel space 41, 42 Endwall 51, 52, 53, 70, 80, 90 Sealing device 61a, 61b, 62, 63, 64 Seal groove 71, 81, 91 Thin plate 72, 82, 92 Cross member 73 Thin plate recess 104 Combustion gas 202 Cooling air flow path 301, 302 leakage

Claims (12)

In a sealing device that is mounted in a pair of grooves provided on opposing surfaces and seals the flow of fluid between the opposing surfaces,
A first member in which concave portions extending in the extending direction of the pair of grooves and convex portions extending in the extending direction of the pair of grooves are alternately arranged;
Sealing device, characterized in that it comprises a second member mounted on the lower surface of the upper surface and the convex portion of the concave portion. In a sealing device that is mounted in a pair of grooves provided on opposing surfaces and seals the flow of fluid between the opposing surfaces,
A first member in which concave portions extending in the depth direction of the pair of grooves and convex portions extending in the depth direction of the pair of grooves are alternately arranged;
Sealing device, characterized in that it comprises a second member mounted on the lower surface of the upper surface and the convex portion of the concave portion. The sealing device according to claim 1 or 2 ,
A flat surface is formed by the second member mounted on the upper surface of the concave portion and the upper surface of the convex portion,
One sealing device is characterized in that a flat surface is formed by the second member mounted on the lower surface of the convex portion and the lower surface of the concave portion. The sealing device according to any one of claims 1 to 3 ,
The sealing device according to claim 1, wherein the first member is a thin metal plate. The sealing device according to any one of claims 1 to 4 ,
The sealing device, wherein the second member is one of a cloth material, a brush material, and a porous material. The sealing device according to any one of claims 3 to 5 ,
In a cross section taken along a plane perpendicular to the depth direction in the stretching direction or the pair of grooves of said pair of grooves, said first member recess and the second graphic surrounded by the flat portion of the member, and , sealing device, characterized in that said first graphic surrounded by the convex portion and the flat portion of the second member of the member is rectangular. The sealing device according to any one of claims 1 to 5 ,
In a cross section cut by a plane perpendicular to the extending direction of the pair of grooves or the depth direction of the pair of grooves , the concave portion has a reduced portion whose width decreases from the bottom to the top. Sealing device. The sealing device according to any one of claims 3 , 4 , 5 , and 7 ,
In a cross section taken along a plane perpendicular to the depth direction in the stretching direction or the pair of grooves of said pair of grooves, said first member recess and the second graphic surrounded by the flat portion of the member, and the figure surrounded by the flat portion of the first member and the second member and the protrusion of a trapezoidal, and wherein the planar portion of the second member constituting the short side of the trapezoid Sealing device. The sealing device according to claim 1 or 2 ,
In a cross section taken along a plane perpendicular to the depth direction in the stretching direction or the pair of grooves of said pair of grooves, the cross section of the first member is composed of only continuous smooth line has curvature A sealing device characterized. In a gas turbine having a compressor, a combustor and a turbine,
The turbine has members assembled into segments in the circumferential direction,
The member assembled in the segment shape includes a pair of grooves facing the adjacent surfaces of the member,
A gas turbine, wherein the seal device according to any one of claims 1 to 9 is mounted in the groove. In a gas turbine having a compressor, a combustor and a turbine,
The turbine has members assembled into segments in the circumferential direction,
The members assembled in the segment shape are a pair of first grooves facing the adjacent surfaces of the members,
A pair of second grooves intersecting the first groove;
A gas turbine, wherein the seal device according to any one of claims 1 to 9 is mounted so as to straddle the first groove and the second groove. The gas turbine of claim 11 .
The gas turbine according to claim 1, wherein the first member is located on a low pressure side at an intersection of the first groove and the second groove.