JP6615710B2 - Turbine vane - Google Patents

Description

  The present invention relates to a turbine vane.

  A gas turbine is a machine that takes out its thermal energy as rotational force by blowing high-temperature and high-pressure gas onto turbine blades, and many of the main components are exposed to high-temperature gas. For this reason, it is necessary to forcibly cool a component having a high heat load.

  Cooling air used for cooling is pressurized in a compressor connected to the same shaft as the turbine and distributed to each part to be cooled. For example, cooling air is supplied to some stationary blades, which are parts having a high heat load, through an extraction pipe attached to the outer peripheral side of the turbine. In the stationary blades supplied with cooling air in this way, only a part of the supplied cooling air is used for cooling the blades, and the remaining cooling air is used for endwalls and turbines arranged on the inner peripheral side of the blades. It is used as purge air for cooling the wheels or the like, or for discharging hot gas that tends to enter the wheel space between the turbine wheels.

  In a gas turbine, a structure for effectively using cooling air that has passed through a cooling air passage formed in a stationary blade and entered a diaphragm cavity as purge air is disclosed (for example, Patent Document 1, paragraph). 0022, see FIG.

  Also, in the turbine vanes of gas turbines, there are individual turbine nozzle segments for individual impingement cooling, as opposed to the need to cool with minimal cooling air leakage between components (e.g., Patent Document 2). The turbine nozzle divided body is an arc-shaped outer band divided body and an airfoil-shaped turbine stationary blade protruding radially inward from the outer band divided body, the turbine stationary blade having a hollow interior, A turbine stationary blade; an impingement cooling plate assembly fixed to the outer band and integrally formed with an impingement cavity with the outer band split body, wherein the impingement cooling plate assembly includes the impingement The impingement cold plate assembly having at least one impingement hole formed in the cold plate assembly, the impingement hole being arranged to flow cooling air through the outer band segment; and at least one impingement A cooling insert, and the at least one The impingement cooling insert has at least one impingement hole formed in the at least one impingement cooling insert and disposed inside the turbine vane, wherein the at least one impingement cooling insert comprises: Engaging with an opening in the impingement cold plate assembly, the at least one impingement cooling insert is blocked from direct fluid communication with the impingement cavity.

JP 2003-343207 A Special table 2015-514921 gazette

  In the case of a turbine vane having an internal cooling structure as in Patent Document 2, a part of the cooling air flowing in from the outer peripheral side passes through an impingement hole formed on a side surface of the impingement cooling insert and enters the impingement cavity at high speed. And then collides with the inner peripheral surface of the turbine vane. As a result, the heat transfer coefficient is improved and heat is removed from the inner peripheral surface of the turbine stationary blade. On the other hand, the rest of the cooling air passes through the hole provided in the bottom of the impingement cooling insert, flows into the diaphragm cavity through the bottom hole formed in the bottom of the turbine stationary blade, and cools the end wall and the turbine wheel. Used for

  Here, the members that form the impingement cooling plate assembly including the impingement cooling inserts are different from the members that form the turbine stator blades, so that the amount of thermal extension is different. In order to prevent mutual interference, a gap is provided between the bottom of the impingement cooling insert and the bottom of the turbine vane. For this reason, the cooling air can pass as leaked air between the impingement cavity and the diaphragm cavity through this gap.

  In this way, the gap between the bottom of the impingement cooling insert and the bottom of the turbine vane changes depending on the hot extension situation. This may cause problems such as insufficient cooling of the blades and insufficient purge air of the wheel space.

  The present invention has been made on the basis of the above-mentioned matters, and the object thereof is to provide a turbine stationary blade that can reduce the amount of leakage between the impingement cavity and the diaphragm cavity at a low cost regardless of the state of hot elongation. To do.

In order to solve the above problems, for example, the configuration described in the claims is adopted. The present application includes a plurality of means for solving the above-described problems. To give an example, an airfoil portion that is disposed substantially radially around the rotating shaft of the turbine and has a hollow portion therein, and the blade A turbine vane including an end wall portion connected to an inner diameter side end portion of a mold portion and an insert installed in the hollow portion, wherein the insert is a large diameter portion disposed in the hollow portion When the has a bottom plate forming a gap between the provided at the bottom of the large diameter portion said end wall portion, and the bottom refrigerant passage extends beyond the end wall portion from the plate portion, the refrigerant flow A plate-like member connected to the outer periphery of the refrigerant flow path portion as the seal structure, and a seal structure that suppresses a refrigerant from flowing through a gap between the outer periphery of the path portion and the end wall portion, The end member is the end member Sandwiched therebetween, characterized in that it is arranged on the diaphragm cavity side opposite the base plate.

  According to the present invention, since the seal structure that can reduce the leak amount between the impingement cavity and the diaphragm cavity is provided, it is possible to inexpensively provide a turbine vane that can reduce the leak amount regardless of the state of hot extension.

It is a fragmentary sectional view showing composition of a turbine part of a gas turbine provided with a 1st embodiment of a turbine stationary blade of the present invention. It is sectional drawing which shows 1st Embodiment of the turbine stationary blade of this invention. It is sectional drawing which shows the form of the conventional turbine stationary blade. It is sectional drawing which expands and shows the leak part in 1st Embodiment of the turbine stationary blade of this invention. It is sectional drawing which shows 2nd Embodiment of the turbine stationary blade of this invention. It is sectional drawing which expands and shows the leak part in 2nd Embodiment of the turbine stationary blade of this invention. It is sectional drawing which shows 3rd Embodiment of the turbine stationary blade of this invention. It is sectional drawing which shows 4th Embodiment of the turbine stationary blade of this invention. It is sectional drawing which shows 5th Embodiment of the turbine stationary blade of this invention. It is sectional drawing which shows 6th Embodiment of the turbine stationary blade of this invention.

  Hereinafter, embodiments of a turbine stationary blade of the present invention will be described with reference to the drawings.

FIG. 1 is a partial cross-sectional view showing a configuration of a turbine section of a gas turbine provided with a first embodiment of a turbine stationary blade of the present invention. As shown in FIG. 1, the turbine section of the gas turbine includes a casing 80, and a first stage stationary blade 1a, a first stage moving blade 3a, and a second stage stationary blade, which are arranged in order from the upstream side on the inner periphery of the casing 80. 1b, 2nd stage moving blade 3b, 3rd stage stationary blade 1c, 3rd stage moving blade 3c, 4th stage stationary blade 1d, 4th stage moving blade 3d, and turbine rotor 100 rotatably disposed on the inner peripheral side of casing 80 And.

The casing 80 includes shrouds 71 to 74 disposed at predetermined intervals in the turbine rotor longitudinal direction on the inner peripheral portion thereof. The shrouds 71 and 72 support an outer diameter side end wall 4b formed on the outer diameter side of the second stage stationary blade 1b and an outer diameter side end wall 4c formed on the outer diameter side of the third stage stationary blade 1c. The shrouds 73 and 74 support the outer diameter side end wall 4c of the third stage stationary blade 1c and the outer diameter side end wall 4d formed on the outer diameter side of the fourth stage stationary blade 1d. An outer diameter side end wall 4 a formed on the outer diameter side of the first stage stationary blade 1 a is supported by a casing 80 .

A cavity 5b is defined on the outer peripheral side of the second stage stationary blade 1b by the shrouds 71, 72 and the outer diameter side end wall 4b of the second stage stationary blade 1b, and the outer diameter side end wall 4c of the shrouds 72, 73 and the third stage stationary blade 1c. A cavity 5c is defined on the outer peripheral side of the third stage stationary blade 1c. Similarly, a cavity 5d is defined on the outer peripheral side of the fourth stage stationary blade 1d by the shrouds 73 and 74 and the outer diameter side end wall 4d of the fourth stage stationary blade 1d. A cavity 5a is defined on the outer peripheral side of the first stage stationary blade 1a by a casing 80 and an outer diameter side end wall 4a of the first stage stationary blade 1a.

The casing 80 is provided with a plurality of air introduction holes connected to the cavities 5a to 5d. These air introduction holes are connected to piping for extracting cooling air from a compressor (not shown).

  Inner diameter side end walls 2a to 2d are formed on the inner diameter sides of the first stage stationary blade 1a, the second stage stationary blade 1b, the third stage stationary blade 1c, and the fourth stage stationary blade 1d. Each of the second stage rotor blade 3b, the third stage rotor blade 3c, and the fourth stage rotor blade 3d is arranged in a circumferential direction with a predetermined gap to constitute a single stage stator blade cascade, There are provided stationary vane diaphragms 31b to 31d supported via inner diameter side end walls 2b to 2d connecting the peripheral sides. Therefore, when the stationary blade cascades of the first stage stationary blade 1a, the second stage stationary blade 1b, the third stage stationary blade 1c, and the fourth stage stationary blade 1d are viewed from the axial direction, the airfoil portion of the stationary blade is radially centered about the rotation axis of the turbine. Looks arranged.

  The first stage rotor blade 3a, the second stage rotor blade 3b, the third stage rotor blade 3c, and the fourth stage rotor blade 3d are each arranged annularly on the outer periphery of the turbine rotor 100, and constitute a rotor blade cascade. The stationary blade cascade of the same paragraph is arranged on the front side of each stage blade cascade.

  Next, a first embodiment of the turbine vane of the present invention will be described with reference to FIG. FIG. 2 is a cross-sectional view showing a first embodiment of a turbine vane of the present invention. In FIG. 2, the same reference numerals as those shown in FIG. In the present embodiment, a third stage stationary blade 1c will be described as an example of the turbine stationary blade 1.

  As shown in FIG. 2, the turbine stationary blade 1 includes an airfoil portion 10 having a hollow portion therein, an outer diameter side end wall 4 formed on the outer diameter side of the airfoil portion 10, and the airfoil portion 10. Are provided with an inner diameter side end wall 2 formed on the inner diameter side, and a core plug 21 as an insert fitted in a hollow portion inside the airfoil portion 10.

  An opening 11 is provided in the outer diameter side end wall 4, and cooling air from the cavity shown in FIG. 1 is introduced into the airfoil portion 10.

  A blade bottom hole 12 is provided in the inner diameter side end wall 2, and cooling air from the inside of the airfoil portion 10 is introduced into the diaphragm cavity 31.

  The core plug 21 is provided on a large-diameter portion 21A disposed in a hollow portion inside the airfoil portion 10 and a core plug bottom plate 24 provided on the bottom portion of the large-diameter portion 21, and passes through the blade bottom hole 12 to form a diaphragm. A small-diameter portion 21B that enters the cavity 31 and constitutes the inner-circumferential cooling air flow path 23 as a refrigerant flow path portion is provided.

  In the present embodiment, a seal structure is provided on the outer peripheral side of the inner peripheral side cooling air flow path 23 of the core plug 21 and on the diaphragm cavity 31 side opposite to the core plug bottom plate 24 with the inner diameter side end wall 2 therebetween. The plate-like member 40 is arranged.

  Here, for comparison with the present embodiment, a conventional turbine stationary blade will be described with reference to FIG. FIG. 3 is a cross-sectional view showing a conventional turbine stationary blade. In FIG. 3, the same reference numerals as those shown in FIGS. 1 and 2 are the same parts, and detailed description thereof is omitted.

  FIG. 3 shows a conventional turbine vane having a typical internal cooling structure. The only difference from the embodiment of the present invention is the presence or absence of the plate-like member 40. In the case of the conventional example, as shown in FIG. 3, a plate-like shape is formed on the outer peripheral side of the inner peripheral side cooling air flow path 23 on the diaphragm cavity 31 side opposite to the core plug bottom plate 24 with the inner diameter side end wall 2 therebetween. The member 40 is not provided.

  In FIG. 3, a part of the cooling air flowing in from the opening 11 on the outer peripheral side passes through a hole (not shown) formed in the side surface of the core plug 21 from the space 13 inside the core plug at a high speed to the impingement cavity 14. It blows out and collides with the inner peripheral surface 15 of the airfoil portion 10. As a result, the heat transfer coefficient is improved and heat is removed from the inner peripheral surface 15. Further, the cooling air jetted into the impingement cavity 14 flows out through a hole (not shown) provided in the airfoil portion 10 and contributes to cooling from the outside by covering the blade surface.

On the other hand, the remainder of the cooling air flowing in from the opening 11 on the outer peripheral side flows into the diaphragm cavity 31 through the inner peripheral cooling air flow path 23.

  Here, in order to prevent mutual interference due to the difference in the amount of thermal extension, the inner peripheral side cooling air flow path 23 and the blade bottom hole 12 between the core plug bottom plate 24 and the inner diameter side end wall 2 or as a refrigerant flow path portion. A gap is provided between the inner wall and the inner wall. Therefore, the cooling air can pass as leaked air between the impingement cavity 14 and the diaphragm cavity 31 through this gap. For this reason, if there is a difference in internal pressure between the impingement cavity 14 and the diaphragm cavity 31, there is a possibility that the cooling air leaks through the blade bottom hole 12.

  Next, the details of the configuration and operation in this embodiment will be described with reference to FIG. FIG. 4 is an enlarged sectional view showing a leak portion in the first embodiment of the turbine vane of the present invention.

  As shown in FIG. 4, in the present embodiment, a gap 50 is formed between the core plug bottom plate 24 and the inner diameter side end wall 2, and the outer peripheral portion of the inner peripheral side cooling air passage 23 serving as the refrigerant passage portion and the blades. A gap 52 is defined between the bottom hole 12 and a gap 51 is defined between the inner end wall 2 and the plate-like member 40 serving as a seal structure. In the present embodiment, three narrow portions of gaps 50, 51, 52 are provided between the impingement cavity 14 and the diaphragm cavity 31. This increases the overall length of the narrow portion and increases the resistance given to the fluid as compared with the conventional example without the gap 51, so that the sealing effect is increased. As a result, the amount of leakage can be reduced as compared with the conventional example.

  In the conventional example, when thermal deformation occurs in the direction in which the gap 50 between the core plug bottom plate 24 and the inner diameter side end wall 2 widens, the sealing effect in the gap 50 between the core plug bottom plate 24 and the inner diameter side end wall 2 is achieved. Since the gap 52 between the inner peripheral cooling air flow path 23 and the blade bottom hole 12 hardly changes, there is a problem that the sealing effect as a whole is lowered.

  On the other hand, according to the present embodiment, when thermal deformation occurs in the direction in which the gap 50 between the core plug bottom plate 24 and the inner diameter side end wall 2 widens, the inner diameter side end wall 2 and the plate shape as a seal structure are formed. Since the gap 51 between the member 40 is deformed in a narrowing direction, the reduction in the sealing effect in the gap 50 between the core plug bottom plate 24 and the inner diameter side end wall 2 is reduced to a plate shape as the inner diameter side end wall 2 and the sealing structure. A gap 51 between the member 40 and the member 40 is supplemented, and a decrease in the sealing effect due to thermal deformation can be suppressed.

  On the other hand, when the gap 51 between the inner diameter side end wall 2 and the plate-like member 40 serving as the sealing structure is deformed in a widening direction, the gap 50 between the core plug bottom plate 24 and the inner diameter side end wall 2 is narrowed. It will be deformed in the direction, and a decrease in the sealing effect due to thermal deformation can also be suppressed.

  As described above, it is possible to obtain the turbine stationary blade 1 that has a higher sealing effect than the conventional technology and is less likely to change the sealing effect due to thermal deformation. In addition, after inserting the core plug 21 in the inside of the turbine stationary blade 1, the plate-like member 40 as the seal structure can be incorporated from the diaphragm cavity 31 side and fixed by a method such as welding or adhesion. Therefore, complicated processing is not necessary and it can be carried out relatively inexpensively.

  According to the above-described first embodiment of the turbine vane of the present invention, the seal structure 40 that can reduce the amount of leakage between the impingement cavity 14 and the diaphragm cavity 31 is provided, so that regardless of the state of hot extension. The turbine stationary blade 1 that can reduce the amount of leakage can be provided at low cost.

  Further, according to the first embodiment of the turbine stationary blade of the present invention described above, the narrow portion between the core plug bottom plate 24 and the inner diameter side end wall 2, the inner peripheral side cooling air flow path 23, and the blade bottom hole 12. Since another narrow part is added in addition to the narrow part between the inner wall and the inner wall, the amount of leakage can be reduced as compared with the prior art. Further, when the narrow portion between the core plug bottom plate 24 and the inner diameter side end wall 2 expands and heat extension occurs in a direction in which the sealing effect is weakened, the additional narrow portion is reduced and the sealing effect is strengthened. The amount of leakage is not affected by hot elongation.

  Furthermore, according to the first embodiment of the turbine stator blade of the present invention described above, the plate-like member 40 as the seal structure is inserted from the diaphragm cavity 31 side after the core plug 21 is inserted into the turbine stator blade 1. Since it can be fixed by a method such as incorporation, welding or adhesion, it is easy to process and can be implemented at low cost.

  Hereinafter, a second embodiment of the turbine vane of the present invention will be described with reference to the drawings. FIG. 5 is a sectional view showing a second embodiment of the turbine vane of the present invention, and FIG. 6 is an enlarged sectional view showing a leak portion in the second embodiment of the turbine vane of the present invention. 5 and 6, the same reference numerals as those shown in FIG. 1 to FIG. 4 are the same parts, and detailed description thereof is omitted.

  Although the second embodiment of the turbine vane of the present invention shown in FIG. 5 is configured by the same equipment as the first embodiment, the following configuration is different. The present embodiment is different in that a convex portion 41A to the inner diameter side end wall 2 is provided at an end portion of a plate-like member 41 serving as a seal structure.

  Specifically, for example, when the plate-like member is circular when viewed from the front, one convex portion is provided in a wall shape in the direction standing upright on the outer peripheral portion of the plate surface, and is formed in a cylindrical shape without a ceiling portion. Has been.

  As shown in FIG. 6, in the present embodiment, a gap 51 </ b> A is defined between the inner diameter side end wall 2 and the convex portion 41 </ b> A of the plate-like member 41 as the seal structure. In the present embodiment, for example, when the cooling air leaks from the impingement cavity 14 to the diaphragm cavity 31, the cooling air that flows is indicated by an arrow. The cooling air from the impingement cavity 14 first passes through the gap 50 and then passes through the gap 52 and reaches the plate-like member 41 as the seal structure.

  Thereafter, the cooling air passes through the gap 51 between the inner diameter side end wall 2 and the plate-like member 41 serving as the seal structure, but at the end, the cooling air passes through the gap 51A between the convex portion 41A and the diaphragm cavity. It flows into 31. The flow passage area of the cooling air rapidly changes from the gap 51 to the gap 51A in the convex portion 41A. This sudden change in flow path area induces flow disturbance. As a result, the pressure loss in the convex portion 41A is increased and the resistance given to the fluid is increased, so that the sealing effect is increased. As a result, a more remarkable sealing effect can be obtained as compared with a structure with little change in the channel area.

  According to the second embodiment of the turbine vane of the present invention described above, the same effects as those of the first embodiment can be obtained.

  Hereinafter, a third embodiment of the turbine vane of the present invention will be described with reference to the drawings. FIG. 7 is a cross-sectional view showing a third embodiment of the turbine vane of the present invention. In FIG. 7, the same reference numerals as those shown in FIG. 1 to FIG.

  Although the third embodiment of the turbine vane of the present invention shown in FIG. 7 is configured with almost the same equipment as the first embodiment, the following configuration is different. The present embodiment is different in that a plurality of convex portions 42A to the inner diameter side end wall 2 are provided on a plate-like member 42 as a seal structure.

  Specifically, for example, when the plate-like member is circular in a front view, a plurality of convex portions 42A are provided in a wall shape in a direction standing upright on the plate surface. Since the plate-like member 42 as the seal structure is provided with a plurality of convex portions 42A, a plurality of narrow portions and enlarged portions are provided between the inner diameter side end wall 2 and the seal structure 42 having the plurality of convex portions 42A. Will be continuously connected. Since the flow of the cooling air is vigorously disturbed by the continuous narrow portion and the enlarged portion, the pressure loss increases and the sealing effect also increases.

  According to the third embodiment of the turbine vane of the present invention described above, the same effects as those of the first embodiment can be obtained.

  Hereinafter, a fourth embodiment of the turbine stationary blade of the present invention will be described with reference to the drawings. FIG. 8 is a cross-sectional view showing a fourth embodiment of a turbine vane of the present invention. In FIG. 8, the same reference numerals as those shown in FIG. 1 to FIG.

  The fourth embodiment of the turbine vane of the present invention shown in FIG. 8 is configured with almost the same equipment as that of the first embodiment, but the following configuration is different. The present embodiment is different in that a convex portion 43A to the inner diameter side end wall 2 is formed by bending the plate-like member 43 at the end of the plate-like member 43 as a seal structure. According to the present embodiment, since the seal structure having the convex portion 43A is provided by bending, there is an advantage that molding is easy.

  According to the fourth embodiment of the turbine vane of the present invention described above, the same effects as those of the first embodiment can be obtained.

  Hereinafter, a fifth embodiment of the turbine vane of the present invention will be described with reference to the drawings. FIG. 9 is a cross-sectional view showing a fifth embodiment of the turbine vane of the present invention. In FIG. 9, the same reference numerals as those shown in FIGS. 1 to 8 are the same parts, and detailed description thereof is omitted.

  Although the fifth embodiment of the turbine vane of the present invention shown in FIG. 9 is composed of almost the same equipment as the first embodiment, the following configurations are different. Specifically, the difference is that the plate-like member 41 as the seal structure in the second embodiment shown in FIG. 5 is made of an elastic material.

  According to the present embodiment, as shown in FIG. 9, when the turbine stationary blade 1 is in a cold state, the convex portion 41 </ b> A of the plate-like member 41 as the seal structure is in contact with the inner diameter side end wall 2. Can be arranged.

  In the present embodiment, when the transition from the cold temperature state to the heat input state causes thermal deformation in the direction in which the gap 50 between the core plug bottom plate 24 and the inner diameter side end wall 2 widens due to the movement 60 of the core plug 21, Since 41 is formed of an elastic material, the deformation 61 is avoided so that the portion other than the convex portion 41A is close to the inner diameter side end wall 2 side, so that damage to the seal structure is avoided. As a result of such deformation, the plate-like member 41 serving as the seal structure having the convex portion 41A can always be in contact with the inner diameter side end wall 2. In this case, a gap between the inner diameter side end wall 2 and the sealing structure having the convex portion 41A is not formed, so that a very high sealing effect can be obtained.

  According to the fifth embodiment of the turbine vane of the present invention described above, the same effects as those of the first embodiment can be obtained.

  Hereinafter, a sixth embodiment of the turbine vane of the present invention will be described with reference to the drawings. FIG. 10 is a cross-sectional view showing a sixth embodiment of the turbine vane of the present invention. In FIG. 10, the same reference numerals as those shown in FIG. 1 to FIG. 9 are the same parts, and detailed description thereof will be omitted.

  The sixth embodiment of the turbine vane of the present invention shown in FIG. 10 is configured with almost the same equipment as the first embodiment, but the following configuration is different. Specifically, the difference is that the plate member 43 as the seal structure in the fourth embodiment shown in FIG. 8 is made of an elastic material.

  Also in the present embodiment, as shown in FIG. 10, when the turbine stationary blade 1 is in a cold state, a part of the plate-like member 43 as a seal structure is arranged in contact with the inner diameter side end wall 2. can do.

  The movement 60 of the core plug 21 due to thermal deformation can be absorbed by the deformation 61 of the plate-like member 43 serving as a seal structure. As a result of such deformation, the plate-like member 43 serving as the seal structure can always be in contact with the inner diameter side end wall 2, so that a very high sealing effect can be obtained.

  According to the sixth embodiment of the turbine vane of the present invention described above, the same effect as in the first embodiment can be obtained.

1: turbine stationary blade, 2: inner diameter side end wall, 4: outer diameter side end wall, 10: airfoil portion, 11: opening on outer peripheral side, 12: blade bottom hole, 13: space inside core plug, 14: in pin-di cavity, 15: inner circumferential surface, 21: core plug (insert), 23: inner circumferential side cooling air passage (refrigerant channel portion), 24: core plug bottom plate, 31: diaphragm cavity, 40: plate-like member (seal Structure), 41: plate-like member (sealing structure having convex portions), 42: plate-like member (sealing structure having plural convex portions), 43: plate-like member (curved sealing structure), 50: core plug bottom plate 24 Between the inner diameter side end wall 2 and the inner peripheral side end wall 2 and the sealing structure, 52: between the outer peripheral portion of the inner peripheral side cooling air flow path 23 and the blade bottom hole 12. Gap, 60: Core plug Moving, 61: deformation of the seal structure, 71, 72, 73, 74: shroud

Claims (6)

An airfoil portion disposed substantially radially around the rotation axis of the turbine and having a hollow portion therein;
An end wall connected to the inner diameter side end of the airfoil, and
A turbine vane including an insert installed in the hollow portion,
The insert includes a large-diameter portion disposed in the hollow portion, a bottom plate provided at a bottom portion of the large-diameter portion and forming a gap between the end-wall portion and the bottom plate beyond the end-wall portion. and a refrigerant flow path portion extending Te,
A seal structure that suppresses the flow of refrigerant through the gap between the outer periphery of the refrigerant flow path portion and the end wall portion ;
A plate-like member connected to the outer periphery of the refrigerant flow path portion as the seal structure;
The turbine stator blade according to claim 1, wherein the plate-like member is disposed on a diaphragm cavity side opposite to the bottom plate with the end wall portion interposed therebetween . The turbine stationary blade according to claim 1 ,
A turbine vane characterized in that the plate-like member is provided with at least one convex portion that is convex toward the end wall portion. The turbine stationary blade according to claim 1 ,
An end of the plate-like member is curved in a direction approaching the end wall. The turbine stationary blade according to claim 1 ,
The plate-shaped member is made of an elastic material, and is in contact with the end wall portion at at least one location. The turbine stationary blade according to claim 2 , wherein
The said plate-shaped member is formed with the elastic raw material, The said convex part is contacting the said end wall part at at least one place. The turbine stationary blade characterized by the above-mentioned. The turbine stationary blade according to claim 3 ,
The plate-shaped member is formed of an elastic material, and an end portion of the plate-shaped member is in contact with the end wall portion at at least one location.

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