JP6813669B2 - Turbine vane row and turbine - Google Patents

Description

Embodiments of the present invention relate to turbine vane trains and turbines.

Due to demands for carbon dioxide reduction and resource saving, the efficiency of power plants is being improved. Therefore, in gas turbine power plants, the temperature of the working fluid is being actively promoted. With the increase in temperature of the working fluid, various attempts have been made for cooling methods for stationary blades and moving blades.

In recent years, power plants that use carbon dioxide as the working fluid of turbines have been studied. In this power plant, carbon dioxide generated in the combustor is circulated in the system as a working fluid. Specifically, the power plant is equipped with a combustor that burns fuels such as oxygen and hydrocarbons. Along with carbon dioxide and water vapor generated by combustion, carbon dioxide introduced into the combustor as a working fluid is introduced into the turbine, and the turbine is rotated to generate electricity.

Turbine exhaust (carbon dioxide and water vapor) discharged from the turbine is cooled by a heat exchanger to remove water and use it as working gas (carbon dioxide). The working gas is boosted by a compressor to become a supercritical fluid. Most of the boosted working gas is heated by the heat exchanger described above and circulated to the combustor. Of the boosted working gas, the portion corresponding to carbon dioxide generated by the combustion of fuel and oxygen supplied from the outside is recovered, for example, and used for other purposes.

When supercritical carbon dioxide is used as the working fluid, the inlet pressure of the turbine is about 20 times that of the conventional gas turbine, and the inlet density is 25 times or more. The temperature of the working fluid at the inlet of the turbine exceeds 1000 ° C., which is equivalent to the temperature of the working fluid at the inlet of the current gas turbine turbine. Therefore, as with the gas turbine, a cooling medium of about 350 to 550 ° C is supplied to the stationary blades and moving blades, and the cooling medium is passed through thin pipes and holes arranged inside to shroud the stationary blades and the rear of the stationary blades. It cools the segment and the blades.

Japanese Unexamined Patent Publication No. 2001-317302 JP-A-2015-509486

As described above, in the gas turbine, cooling is performed by passing a cooling medium through cooling pipes and holes arranged inside the vane. However, in a power plant using supercritical carbon dioxide as the working fluid, the density of the working fluid and the cooling medium is high, so when the diameter of the cooling pipes and holes is the same as that of the conventional gas turbine, the cooling medium The supply will increase, which is not appropriate from the viewpoint of improving the efficiency of the power generation system. Therefore, there is a demand for a technique capable of reducing the diameter of cooling pipes and holes, supplying an appropriate amount of cooling medium, and efficiently cooling.

An object of the present invention is to provide a turbine vane train and a turbine which can supply an appropriate amount of a cooling medium used for cooling a stationary blade and a shroud segment behind the stationary blade and can efficiently cool the blade. is there.

Turbine Shizutsubasaretsu embodiment is fixed to the casing, the working medium in order to drive a turbine a turbine stator blade row which leads to the turbine rotor blade row, and the tip of the turbine rotor blade row and before listen pacing In a turbine blade row having a shroud segment between the blades and a gap between the casing and the shroud segment, the blade effective portion and the engaging groove of the casing are engaged to supply a cooling medium. It has an engaging protrusion that faces the opening groove and the gap portion and forms the opening groove, and is provided on the outer ring side wall provided on the outer peripheral side of the blade effective portion and on the inner peripheral side of the blade effective portion. A stationary blade having an inner ring side wall, a cooling passage for passing the cooling medium to cool inside each of the blade effective portion, the outer ring side wall, and the inner ring side wall, and the stationary blade arranged along the circumferential direction. A plurality of seal plates arranged in the gap between the outer ring side wall and the outer ring side wall of the adjacent rotor blade and fitted in the grooves arranged on the outer ring side wall, and one of the plurality of seal plates. It is provided with more than one, and includes a refrigerant passage portion for passing the cooling medium from the opening groove toward the gap portion.

A system diagram of a gas turbine facility including the turbine of the embodiment. The figure which showed a part of the vertical cross section of the turbine of an embodiment. The figure which shows the vertical cross section of the stationary blade of an embodiment. The figure which shows the AA cross section of FIG. The figure which shows the structure when the stationary blade row of 1st Embodiment is seen from the rear in the axial direction. The figure which shows the structure of the seal plate of 1st Embodiment. The figure which shows the structure of the seal plate of 2nd Embodiment. The figure which shows the structure of the seal plate of 3rd Embodiment. The figure which shows the structure of the seal plate of 4th Embodiment. The figure which shows the structure of the seal plate of 5th Embodiment.

Hereinafter, embodiments of the present invention will be described with reference to the drawings.

FIG. 1 is a system diagram of a gas turbine facility 10 including a turbine provided with a turbine vane row of the embodiment. Although FIG. 1 shows a case where the present invention is applied to a gas turbine facility 10 using a CO ₂ turbine, the present invention is not limited to the CO ₂ turbine but is also applied to other gas turbines and steam turbines. can do.

As shown in FIG. 1, oxygen and fuel are supplied to the combustor 20 and burned. In addition, carbon dioxide that circulates as a working fluid is also introduced into the combustor 20. The flow rates of fuel and oxygen are adjusted to be, for example, a stoichiometric mixture ratio (theoretical mixture ratio) when they are completely mixed. As the fuel, for example, natural gas, hydrocarbons such as methane, coal gasification gas, and the like are used.

Combustion gas composed of carbon dioxide produced by combustion, water vapor, and carbon dioxide as a working fluid discharged from the combustor 20 is introduced into the turbine 21. The combustion gas that has expanded in the turbine 21 passes through the heat exchanger 22 and further through the heat exchanger 23. When passing through the heat exchanger 23, water vapor condenses into water. Water is discharged to the outside through the pipe 24. A generator 25 is connected to the turbine 21.

The dry working gas (carbon dioxide) separated from water vapor is pressurized by the compressor 26 to become a supercritical fluid. At the outlet of the compressor 26, the pressure of the dry working gas is, for example, about 30 MPa.

A part of the dry working gas boosted by the compressor 26 is heated in the heat exchanger 22 and supplied to the combustor 20 as a working fluid. The dry working gas introduced into the combustor 20 is, for example, ejected from the upstream side of the combustor 20 together with the fuel and the oxidizer into the combustion region, or after the combustor liner is cooled, the combustion region in the combustor liner is released from a dilution hole or the like. It is ejected to the downstream side of.

Further, a part of the dry working gas of the supercritical fluid is introduced into the turbine 21 as a cooling medium through a pipe branched from the middle of the flow path in the heat exchanger 22. The temperature of this cooling medium is preferably, for example, about 350 ° C. to 550 ° C. for the reason of the cooling effect and the thermal stress generated in the object to be cooled.

The rest of the dry working gas boosted by the compressor 26 is discharged to the outside of the system. The dry working gas discharged to the outside is recovered by, for example, a recovery device. Further, the dry working gas discharged to the outside can be used for, for example, EOR (Enhanced Oil Recovery) used at an oil mining site. In the above-mentioned system, for example, carbon dioxide corresponding to the amount of carbon dioxide produced by burning fuel and oxygen in the combustor 20 is discharged to the outside of the system.

Next, the configuration of the turbine 21 of the embodiment will be described.

FIG. 2 is a diagram showing a part of a vertical cross section of the turbine 21. As shown in FIG. 2, a stationary blade 31 is arranged inside the cylindrical casing 30. A plurality of stationary blades 31 (only one is shown in FIG. 2) are arranged along the circumferential direction of the casing 30, and these stationary blades 31 form a stationary blade row.

Further, on the immediate downstream side of the stationary blade row, a plurality of moving blades 34 (only one is shown in FIG. 2) are planted in the rotor disk 33 of the turbine rotor 32 in the circumferential direction. Is placed. The stationary blade rows and the moving blade rows are alternately arranged along the axial direction of the turbine rotor 32. The blade train and the blade train immediately downstream of this blade train form one turbine paragraph.

The outer circumference of the rotor blade 34 is surrounded by a shroud segment 35. The shroud segment 35 is for suppressing heat input from the combustion gas to the casing 30 and adjusting the gap with the tip of the moving blade 34 to maintain an appropriate gap. The shroud segment 35 is supported, for example, by a stationary blade 31 fixed to the casing 30. In this case, a gap 36 is formed in the circumferential direction between the shroud segment 35 and the casing 30.

As described above, an annular combustion gas passage 37 having a stationary blade row and a moving blade row is formed inside the casing 30.

Next, the configuration of the stationary blade 31 will be described with reference to FIGS. 3 and 4. FIG. 3 is a diagram showing a vertical cross section of the stationary blade 31, and FIG. 4 is a diagram showing an AA cross section of FIG. As shown in FIG. 3, the stationary blade 31 includes a blade effective portion 40, an outer ring side wall 50 provided on the outer peripheral side (radial direction outer side) of the blade effective portion 40, and an inner peripheral side (radial direction) of the blade effective portion 40. The inner ring side wall 60 provided on the inner side) is provided.

The blade effective portion 40 is a passage portion through which the combustion gas passes. The blade effective portion 40 is configured in an airfoil shape, for example, having a curved cross-sectional shape on the front edge side and a tapered cross-sectional shape on the trailing edge side. The front edge side of the blade effective portion 40 is composed of a hollow portion 41 having both ends open. The cross-sectional shape of the hollow portion 41 is not particularly limited, but can be, for example, a shape corresponding to the outer shape of the blade effective portion 40 on the front edge side, as shown in FIG.

Through holes 42 and 43 penetrating in the blade height direction (vertical direction in FIG. 3) are formed in the center and the trailing edge side of the blade effective portion 40. The cross-sectional shapes of the through holes 42 and 43 are not particularly limited. Here, for example, as shown in FIG. 4, the through hole 42 has a semi-elliptical shape, and the through hole 43 has a circular shape.

As the center of the blade effective portion 40, for example, the center of the camber line of the blade effective portion 40 is exemplified. Further, the front edge side means the front edge side from the center of the wing effective portion 40, and the trailing edge side means the trailing edge side from the center of the wing effective portion 40.

At least one through hole 43 is formed on the trailing edge side, and here, an example in which a plurality of through holes 43 are formed is shown. When a plurality of through holes 43 are formed, the through holes 43 are formed at equal intervals, for example, so that the hole diameter of the through holes 43 gradually decreases toward the trailing edge side as the blade thickness decreases. can do.

As shown in FIG. 3, an insert member 70 is arranged in the hollow portion 41 of the blade effective portion 40. The insert member 70 includes a plate-shaped portion 71 and a tubular portion 75.

The plate-shaped portion 71 is provided so as to cover the opening 51a of the outer ring side wall 50, which will be described later, which communicates with the hollow portion 41, and the opening 51b of the outer ring side wall 50, which will be described later, which communicates with the through hole 42 at the center. ing. The plate-shaped portion 71 is formed with an opening 72 communicating with the opening 51a and an opening 73 communicating with the opening 51b. For example, a part of the outer peripheral edge of the plate-shaped portion 71 is fixed at a predetermined position on the bottom portion of the opening groove 51 in the outer ring side wall 50 described later.

The tubular body portion 75 is a tubular body in which one end is fixed to the plate-shaped portion 71 and the other end is closed. The tubular body portion 75 is configured to be inserted into the hollow portion 41 with a predetermined gap between the inner wall 41a of the hollow portion 41 and the hollow portion 41. A plurality of ejection holes 76 are formed in a portion of the tubular body portion 75 facing the inner wall 41a of the hollow portion 41.

The distance between the outer surface 75a of the tubular body portion 75 and the inner wall 41a of the hollow portion 41 is preferably set to be substantially constant, for example. Thereby, for example, when the cooling medium ejected from the ejection hole 76 collides with the inner wall 41a to cool the blade effective portion 40, the entire blade effective portion 40 can be uniformly cooled. As the cooling medium, for example, a working gas (carbon dioxide) of a supercritical fluid is used.

As shown in FIG. 4, the outer ring side wall 50 has, for example, a polygonal flat plate shape. An opening groove 51 for introducing a cooling medium is formed in the outer ring side wall 50. At the bottom of the opening groove 51, an opening 51a communicating with the hollow portion 41 and an opening 51b communicating with the central through hole 42 are formed. The opening 51a is formed in the same opening shape as the hollow portion 41, and the opening 51b is formed in the same opening shape as the through hole 42.

Here, when the through hole 43 on the trailing edge side is formed, an opening communicating with the through hole 43 is formed, but a predetermined gap is formed on the outer side (outer peripheral side) in the radial direction from the through hole 43 on the trailing edge side. The opening is closed by the flat plate 52. As a result, a gap portion 53 communicating with the through hole 43 on the trailing edge side is formed. The outer ring side wall 50 is formed integrally with, for example, the blade effective portion 40.

A cooling hole 55 is formed on the inner peripheral side of the outer ring side wall 50 located on the front edge side to communicate the opening 51a with the outside of the outer ring side wall 50. The cooling hole 55 is a hole for discharging the cooling medium to the outside of the blade while cooling the outer ring side wall 50 by the cooling medium ejected from the ejection hole 76 of the tubular portion 75 toward the inner wall 41a of the hollow portion 41. A part of the cooling medium ejected from the ejection hole 76 flows between the inner wall 41a and the tubular body portion 75 toward the opening 51a. A plurality of cooling holes 55 are formed, for example, as shown in FIG. The cooling hole 55 functions as a front edge side cooling hole. With respect to the cooling hole 55, the space between the tubular body portion 75 and the hollow portion 41 acts as a cavity for allowing the cooling medium to flow into the cooling hole 55.

Further, a cooling hole 56 is formed on the inner peripheral side of the outer ring side wall 50 located on the trailing edge side to communicate the gap 53 with the outside of the outer ring side wall 50. The cooling hole 56 is a hole for discharging the cooling medium to the outside of the blade while cooling the outer ring side wall 50 by the cooling medium flowing into the gap 53. A plurality of the cooling holes 56 are formed, for example, as shown in FIG. Therefore, the cooling medium that has flowed into the gap 53 is dispersed and flows into each cooling hole 56. The cooling hole 56 functions as a trailing edge side outer ring cooling hole.

Further, in addition to the cooling hole 56, a cooling hole 100 is formed in which the gap portion 53 of the stationary blade 31 and the gap portion 36 between the shroud segment 35 and the casing 30 communicate with each other. The cooling hole 100 functions as a second trailing edge side outer ring cooling hole and also functions as a part of the side wall cooling passage. The shroud segment 35 includes a main body 110 and a plate-shaped member 120. A plurality of ejection holes 121 are formed in the plate-shaped member 120, the cooling medium is ejected from the void portion 36 through the ejection holes 121 to the gap portion 111, and the outlet is set to be located on the upstream side of the moving blade 34. It is discharged through the ejection hole 112.

At the other end of the outer ring side wall 50, an engaging protrusion 57 for engaging with the engaging groove of the casing 30 is formed. The engaging protrusion 57 projects, for example, along the turbine rotor axial direction. By providing the engaging protrusion 57, the stationary blade 31 can be arranged and supported (fixed) in the circumferential direction along the engaging portion groove 80 of the casing 30 formed in the circumferential direction.

Then, the opening groove 51 is covered from the outer peripheral side by, for example, the casing 30, and is in a closed state (see FIG. 2). Although not shown, the opening groove 51 communicates with the supply passage of the cooling medium provided in the casing 30. Then, the cooling medium is introduced into the opening groove 51 from this supply passage.

The shroud segment 35 is locked to, for example, a protrusion 59 on the inner peripheral side of the outer ring side wall 50 that protrudes along the turbine rotor axial direction. This eliminates the need for a conventional configuration such as a hook for attaching the shroud segment to the casing. Further, a gap 36 can be formed between the shroud segment 35 and the casing 30.

Like the outer ring side wall 50, the inner ring side wall 60 has, for example, a polygonal flat plate shape. As shown in FIG. 3, the inner ring side wall 60 includes a gap portion 61 communicating with the hollow portion 41, and a gap portion 62 communicating with the central through hole 42 and the trailing edge side through hole 43. The gap portion 61 functions as a front edge side gap portion, and the gap portion 62 functions as a trailing edge side gap portion.

Here, the gap portion 61 is formed of, for example, a recess formed on the inner surface of the inner ring side wall 60 and having the same cross-sectional shape as the opening cross-sectional shape of the hollow portion 41. The gap portion 62 is provided with, for example, a flat plate 63 that closes the opening portion communicating with the through hole 42 and the through hole 43 by providing a predetermined gap on the inside (inner peripheral side) in the radial direction from the through hole 42 and the through hole 43. Consists of. The inner ring side wall 60 is formed integrally with, for example, the blade effective portion 40.

On the outer peripheral side of the inner ring side wall 60 located on the front edge side, a cooling hole 65 that communicates the gap 61 with the outside of the inner ring side wall 60 is formed. The cooling hole 65 is a hole for discharging the cooling medium to the outside of the blade while cooling the inner ring side wall 60 by the cooling medium ejected from the ejection hole 76 of the tubular portion 75 toward the inner wall 41a of the hollow portion 41. A part of the cooling medium ejected from the ejection hole 76 flows between the inner wall 41a and the tubular body portion 75 toward the gap portion 61. A plurality of cooling holes 65 are formed, for example, as in the case of the cooling holes 55 of the outer ring side wall 50. The cooling hole 65 functions as a front edge side cooling hole.

Further, on the outer peripheral side of the inner ring side wall 60 located on the trailing edge side, a cooling hole 66 that communicates the gap portion 62 with the outside of the inner ring side wall 60 is formed. The cooling hole 66 is a hole for discharging the cooling medium to the outside of the blade while cooling the inner ring side wall 60 by a part of the cooling medium flowing into the gap portion 62. A plurality of cooling holes 66 are formed, for example, as in the case of the cooling holes 56 of the outer ring side wall 50. The cooling hole 66 functions as a trailing edge side inner ring cooling hole.

When the stationary blade 31 is arranged in the circumferential direction of the casing 30, since there is a gap between the inner ring side wall 60 and the inner ring side wall 60 of the adjacent stationary blade 31, a cooling medium is provided to the outside of the blade from the cooling holes 65 and 66. Can be discharged.

A plurality of the stationary blades 31 and the shroud segments 35 are arranged along the circumferential direction of the casing 30 to form a stationary blade row. In this stationary blade row, between the outer ring side wall 50, the inner ring side wall 60 and the shroud segment 35 of the stationary blade 31, and the outer ring side wall 50 and the inner ring side wall 60 and the shroud segment 35 of the stationary blade 31 adjacent to this in the circumferential direction. A gap is formed. A seal plate 38 for closing the gap is arranged in this gap.

The seal plate 38 is fitted into a groove arranged in the outer ring side wall 50, the inner ring side wall 60, and the shroud segment 35. The position where the seal plate 38 is arranged is indicated by a thick line and reference numeral 38 in the vertical sectional view of FIG. FIG. 2 shows a cross section of the outer ring side wall 50, the inner ring side wall 60, and the shroud segment 35, but the seal plate 38 is actually arranged on these side surfaces. The outer openings of the cooling holes 55, 56, 65, 66 shown in FIG. 3 are arranged so as to be located on the blade effective portion 40 side of the seal plate 38 provided at this portion.

FIG. 5 is a view of the stationary blade row of the first embodiment as viewed from the rear in the axial direction. As shown in FIG. 5, a seal plate 38 is installed between the outer ring side wall 50 and the inner ring side wall 60 of the stationary blade 31 and the outer ring side wall 50 and the inner ring side wall 60 of the adjacent stationary blade 31. In the example shown in FIG. 5, one circular hole 91 is formed in the central portion of the seal plate 38a arranged on the outer ring side wall 50 as a refrigerant passage portion through which the cooling medium passes. As shown in FIGS. 2 and 3, the position of the seal plate 38a on which the circular hole 91 is formed is the trailing edge side end portion of the stationary blade 31.

In the example shown in FIG. 5, in the stationary blade row in one paragraph, a seal plate 38a in which one circular hole 91 is formed is arranged at the same position in the gap between the stationary blade 31 and the adjacent stationary blade 31. ing. However, only one seal plate 38a may be arranged at one place in the stationary blade row of one paragraph. Further, for example, a total of two seal plates 38a may be arranged one by one only at positions separated by 180 ° along the circumferential direction of the casing 30 in the stationary blade row in one paragraph. Further, for example, a total of four seal plates 38a may be arranged one by one only at positions separated by 90 ° along the circumferential direction of the casing 30 in the stationary blade row in one paragraph. This point is the same for the seal plates 38b to 38d according to the second to fifth embodiments described later. Further, the number of circular holes 91 provided in one seal plate 38a is not limited to one, and may be plural.

FIG. 6 is a diagram showing the configuration of the seal plate 38a of the first embodiment. The seal plate 38a is arranged by fitting both end portions into a groove arranged on the outer ring side wall 50 of the stationary blade 31 and a groove arranged on the outer ring side wall 50 of the adjacent stationary blade 31. .. The shaded portion indicated by reference numeral 90 in FIG. 6 indicates the fitting portion between the groove and the seal plate 38a. The circular hole 91 through which the cooling medium passes is arranged in the gap formed between the outer ring side wall 50 of the stationary blade 31 and the outer ring side wall 50 of the adjacent stationary blade 31.

In the example of the seal plate 38a shown in FIGS. 5 and 6, the gap portion 36 (see FIGS. 2 and 3) is provided by the cooling hole 100 arranged in the stationary blade 31 and the circular hole 91 arranged in the seal plate 38a. Supply the cooling medium to. The cooling medium supplied to the gap 36 is used for cooling the shroud segment 35.

The cooling hole 100 is formed by electric discharge machining or the like when the blade effective portion 40 and the outer ring side wall 50 are integrally formed. Therefore, it is difficult to process the cooling hole 100 with high accuracy, and it is also difficult to maintain the cooling hole 100 after assembling the stationary blade row. On the other hand, since the seal plate 38a has a thin plate shape (for example, a thickness of about 1 mm to several mm), it is easy to process and can be processed with high accuracy. Therefore, the hole diameter of the circular hole 91 can be set with high accuracy, and an appropriate amount of the cooling medium can be supplied from the circular hole 91. Further, the seal plate 38a can be easily removed, and the supply amount of the cooling medium can be easily changed by replacing the seal plate 38a with another seal plate 38a having a different hole diameter of the circular hole 91. When the seal plate 38a having the circular holes 91 is used, the cooling holes 100 need not be arranged.

FIG. 7 is a diagram showing the configuration of the seal plate 38b of the second embodiment. In the seal plate 38b, one slit 92 is formed in the central portion thereof as a refrigerant passage portion through which the cooling medium is passed. The slit 92 has an aspect ratio of, for example, 2 or more. The slit 92 through which the cooling medium passes is arranged in the gap formed between the outer ring side wall 50 of the stationary blade 31 and the outer ring side wall 50 of the adjacent stationary blade 31.

FIG. 8 is a diagram showing the configuration of the seal plate 38c of the third embodiment. In the seal plate 38c, a refrigerant passage portion through which the cooling medium is passed is formed by a notch portion 93 formed in the central portion thereof. That is, the notch 93 forms an opening through which the cooling medium passes between the outer ring side wall 50 of the stationary blade 31 and the outer ring side wall 50 of the adjacent stationary blade 31. The position of the cutout portion 93 is not limited to the central portion in the longitudinal direction of the seal plate 38c. For example, a notch 93 may be provided at the upper end of the seal plate 38, and an opening may be arranged on the outer peripheral side of the outer ring side wall 50.

FIG. 9 is a diagram showing the configuration of the seal plate 38d of the fourth embodiment. The size of the seal plate 38d in the longitudinal direction is shorter than that of a normal one by, for example, 2 mm or more. As a result, an opening 94 is formed between the outer ring side wall 50 of the stationary blade 31 and the outer ring side wall 50 of the adjacent stationary blade 31 as a refrigerant passage portion through which the cooling medium passes. FIG. 9 shows an example in which the opening 94 is formed on the upper end side of the seal plate 38d.

FIG. 10 is a diagram showing the configuration of the seal plate 38e of the fifth embodiment. In this seal plate 38e, a plurality of seal plates 38e (FIG. 10 shows two examples) are arranged in a groove for fitting the seal plate 38e, and a gap is provided between the plurality of seal plates 38e. After opening, an opening 95 is formed in this gap as a refrigerant passage portion through which the cooling medium passes. The gap between the seal plates 38e is preferably 2 mm or more, for example. Further, FIG. 10 shows an example in which two seal plates 38e having the same length are used and an opening 95 is formed in the central portion between them. However, the lengths of the two seal plates 38e may be different, and the opening 95 may be formed at a position biased upward or downward from the central portion.

As described above, according to each of the above embodiments, an appropriate amount of the cooling medium used for cooling the stationary blade and the shroud segment behind the stationary blade can be supplied, and cooling can be performed efficiently. The location of the seal plates 38a to 38e on which the refrigerant passage portion through which the cooling medium passes is formed is not limited to the above, and may be another portion.

Although some embodiments of the present invention have been described above, these embodiments are presented as examples and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other embodiments, and various omissions, replacements, and changes can be made without departing from the gist of the invention. These embodiments and modifications thereof are included in the scope and gist of the invention, and are also included in the scope of the invention described in the claims and the equivalent scope thereof.

10 ... gas turbine equipment, 20 ... combustor, 21 ... turbine, 22, 23 ... heat exchanger, 24 ... piping, 25 ... generator, 26 ... compressor, 30 ... casing, 31 ... stationary blade, 32 ... turbine rotor , 33 ... rotor disk, 34 ... turbine, 35 ... shroud segment, 36 ... void, 37 ... combustion gas passage, 38, 38a, 38b, 38c, 38d, 38e ... seal plate, 40 ... blade effective part, 41 ... Hollow part, 41a ... Inner wall, 42,43 ... Through hole, 50 ... Outer ring side wall, 51 ... Opening groove, 51a, 51b ... Opening, 52 ... Flat plate, 53 ... Void part, 55 ... Cooling hole, 56 ... Cooling hole, 57 ... engaging protrusion, 59 ... protrusion, 60 ... inner ring side wall, 61, 62 ... gap, 63 ... flat plate, 65 ... cooling hole, 66 ... cooling hole, 70 ... insert member, 71 ... plate-shaped part, 72, 73 ... opening, 75 ... tubular part, 75a ... outer surface, 76 ... ejection hole, 80 ... engaging part groove, 90 ... fitting part, 91 ... circular hole, 92 ... slit, 93 ... notch, 94,95 ... opening, 100 ... cooling hole, 110 ... main body, 111 ... void, 111a ..., 112 ... ejection hole, 120 ... plate-shaped member, 121 ... ejection hole.

Claims (7)

Fixed to the casing, the working medium in order to drive a turbine a turbine stator blade row which leads to the turbine rotor blade row, with the shroud segment between the tip and the front Listen pacing of the turbine rotor blade row, wherein In a turbine blade row having a gap between the casing and the shroud segment.
The blade effective portion has an engaging protrusion that is engaged with the engaging groove of the casing and faces the opening groove to which the cooling medium is supplied and the gap portion to form the opening groove. The cooling medium is passed through the outer ring side wall provided on the outer peripheral side, the inner ring side wall provided on the inner peripheral side of the wing effective portion, and the inside of each of the wing effective portion, the outer ring side wall, and the inner ring side wall. A stationary wing with a cooling passage for cooling,
A plurality of seals arranged in the gap between the outer ring side wall of the stationary blade arranged along the circumferential direction and the outer ring side wall of the adjacent stationary blade and fitted in the groove arranged on the outer ring side wall. With the plate
A refrigerant flow portion which is arranged in one or more of the plurality of seal plates and allows the cooling medium to pass from the opening groove toward the gap portion.
A turbine vane train characterized by being equipped with. The first aspect of claim 1, wherein the refrigerant flow portion is provided on the seal plate disposed between the outer ring side wall of the stationary blade and the outer ring side wall of the adjacent stationary blade. Turbine stationary blade row. The turbine stationary blade row according to claim 1 or 2, wherein the refrigerant flow portion has a slit shape. The turbine stationary blade row according to claim 1 or 2, wherein the refrigerant flow portion is a notch portion formed in the seal plate. The invention according to any one of claims 1 to 4, wherein the seal plates on which the refrigerant flow portions are arranged are provided at positions separated by 180 ° along the circumferential direction of the casing. Turbine vane row. The invention according to any one of claims 1 to 4, wherein the seal plates on which the refrigerant passage portions are arranged are provided at positions separated by 90 ° along the circumferential direction of the casing. Turbine vane row. A turbine comprising the turbine vane row according to any one of claims 1 to 6.

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