JP2015063997A - Turbine blade - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a turbine blade for impingement cooling, capable of reducing crossflow, actively controlling a flow of a cooling medium, and efficiently recovering the cooling medium.SOLUTION: A stator blade 10 includes: a blade wall 11; and an insert 15. The insert 15 is provided opposed to an internal surface of the blade wall 11, and includes an outer insert plate 22 including holes 23 at position opposed to the blade wall 11, an inner insert plate 21 provided opposed to the outer insert plate 22 on an opposite side to the blade wall 11, and hollow bridges 25 coupling the inner insert plate 21 to the outer insert plate 22. Openings 24 communicating a space between the blade wall 11 and the outer insert plate 22 with a space in contact with a surface of the inner insert plate 21 on an opposite side to the outer insert plate 22 are provided to pass through the respective hollow bridges 25. Each opening 24 is located between the two rows of holes 23. A cooling medium supplied to the space between the inner insert plate 21 and the outer insert plate 22 is injected from the holes 23 to the internal surface of the blade wall 11.

Description

  The present invention relates to a turbine blade, and more particularly, to a cooling structure that cools a turbine blade of a gas turbine by impingement cooling.

  Since turbine blades (stator blades and moving blades) of a gas turbine are exposed to combustion gas, it is necessary to cool them by some cooling mechanism. One method for cooling the turbine blades is impingement cooling. For example, a hole for ejecting a cooling medium (typically cooling air) is provided in an impingement plate inserted in a blade wall having a hollow structure, and the cooling medium is injected from the hole into the inner surface of the blade wall, thereby The wing is cooled. In general, an insert inserted into a turbine blade is used as an impingement plate. As for the technology for cooling a high-temperature member (especially a turbine stationary blade) of a gas turbine by impingement cooling, for example, Japanese Patent Application Laid-Open No. 2002-161705, Japanese Patent Application Publication No. 2003-532821, Japanese Patent No. 3110227, Japanese Patent Application Laid-Open No. Nos. 093801, 9-91991, and 9-53406.

  One problem in impingement cooling of turbine blades is a phenomenon in which a cooling medium flows in a direction along the blade inner surface in a gap between the insert and the blade inner surface, that is, a so-called cross flow. The cooling medium that has collided with the inner surface of the blade wall changes its direction in the direction along the inner surface of the blade and flows. When this flow interferes with the cooling medium ejected toward the inner surface of the blade wall, the cooling efficiency is lowered.

  Japanese Patent Laying-Open No. 2010-38141 discloses a technique for reducing cross flow. FIG. 1 is a perspective view showing a cooling structure by impingement cooling disclosed in this publication. In the cooling structure of FIG. 1, a plurality of nozzle tubes 109 are provided along the cooling surface 105a of the high temperature member 105 (for example, a blade wall of a turbine blade). The nozzle pipe 109 is provided with an air outlet 109a at a position facing the cooling surface 105a, and further, a rib 115 is provided at a position between the nozzle pipe 109 on the cooling surface 105a. In this structure, after the jet flow ejected from the nozzle tube 109 toward the cooling surface 105a of the high temperature member 105 collides with the cooling surface 105a, the gap between the nozzle tubes 109 is opposite to the cooling surface 105a of the high temperature member 105. Flowing. In FIG. 1, the flow of the cooling medium to the opposite side of the cooling surface 105a of the high temperature member 105 is indicated by the symbol f. According to the structure as shown in FIG. 1, the cross flow can be reduced and the cooling efficiency can be improved.

  However, according to the inventors' investigation, there is room for further improvement in this technique. That is, in the cooling structure of FIG. 1, the flow of the cooling medium after cooling the high temperature member 105 is not sufficiently controlled. There is a technical advantage in actively controlling the flow of the cooling medium after cooling the hot member. For example, it is preferable to reuse the cooling medium if the flow of the cooling medium is positively controlled to efficiently collect the cooling medium.

JP 2002-161705 A Japanese translation of PCT publication No. 2003-532821 Japanese Patent No. 3110227 JP-A-6-093401 Japanese Patent Laid-Open No. 9-41991 Japanese Patent Laid-Open No. 9-53406 JP 2010-38141 A

  Therefore, an object of the present invention is to provide a technique that enables cross-flow reduction and positive control of the flow of the cooling medium in a turbine blade that performs impingement cooling, thereby enabling efficient recovery of the cooling medium. There is.

  In one aspect of the present invention, a turbine blade includes a blade wall and an insert inserted in a space formed inside the blade wall. The insert is provided so as to face the inner surface of the blade wall, and faces the outer insert plate having the first hole and the second hole at a position facing the blade wall and the surface of the outer insert plate on the opposite side of the blade wall. An inner insert plate, and a bridge connecting the outer insert plate and the inner insert plate. An opening that communicates the first space between the blade wall and the outer insert plate and the second space in contact with the surface of the inner insert plate on the opposite side of the outer insert plate is provided through the bridge. The opening is located between the first hole and the second hole. The cooling medium supplied to the third space between the outer insert plate and the inner insert plate is jetted from the first hole and the second hole to the inner surface of the blade wall. In such a structure, for example, the cooling medium injected from the first hole to the inner surface of the blade wall is recovered from the opening without interfering with the cooling medium injected from the second hole. In addition, the flow of the cooling medium is controlled so that the cooling medium sprayed on the inner surface of the blade wall is recovered in the second space, and the cooling medium can be recovered efficiently.

  The outer insert plate includes a first protrusion and a second protrusion that protrude toward the wing wall, the first hole is provided in the first protrusion, and the second hole is provided in the second protrusion. An opening may be provided between the first protrusion and the second protrusion. In such a configuration, the crossflow can be suppressed while reducing the distance between the first hole, the second hole, and the inner surface of the blade wall to improve the cooling efficiency.

  Instead, the first hole and the second hole, and the end of the opening provided therebetween on the blade wall side may be on substantially the same plane.

  The cooling medium recovered in the second space may be supplied to other parts of the turbine blade and used for cooling, or may be recovered outside the turbine blade.

  In another aspect of the present invention, the blade includes a blade wall and an insert inserted into a space formed inside the blade wall. The insert is provided so as to face the inner surface of the wing wall, and the outer insert plate provided with a hole at a position facing the wing wall and the inner side provided to face the outer insert plate on the opposite side of the wing wall. An insert plate and first and second bridges connecting the outer insert plate and the inner insert plate are provided. A first opening and a second opening communicating the first space between the blade wall and the outer insert plate and the second space in contact with the surface of the inner insert plate on the opposite side of the outer insert plate are the first and second openings, respectively. Two bridges are provided. The hole provided in the outer insert plate is located between the first and second openings. The cooling medium supplied to the second space is jetted from the first and second openings to the inner surface of the blade wall. In such a structure, for example, the cooling medium injected from the first opening to the inner surface of the blade wall is recovered from the hole provided in the outer insert plate without interfering with the cooling medium injected from the second opening. In addition, the flow of the cooling medium is controlled so that the cooling medium sprayed on the inner surface of the blade wall is recovered in the third space between the outer insert plate and the inner insert plate, and the cooling medium can be recovered efficiently.

  The cooling medium recovered in the third space may be supplied to the other part of the turbine blade and used for cooling, or may be recovered outside the turbine blade.

  In still another aspect of the present invention, the impingement cooling structure is provided so as to face the object to be cooled, the outer impingement plate having the first hole and the second hole at the position facing the object to be cooled, and the object to be cooled An inner impingement plate provided opposite to the surface of the outer impingement plate on the opposite side, and a bridge connecting the outer impingement plate and the inner impingement plate. An opening that communicates the first space between the object to be cooled and the outer impingement plate and the second space in contact with the surface of the inner impingement plate on the opposite side of the outer impingement plate is provided through the bridge. . The opening is located between the first hole and the second hole. The cooling medium supplied to the third space between the outer impingement plate and the inner impingement plate is jetted from the first hole and the second hole to the object to be cooled.

  In still another aspect of the present invention, the impingement cooling structure is provided so as to face the inner surface of the object to be cooled, and includes an outer impingement plate having a hole at a position facing the object to be cooled, and an opposite side of the object to be cooled. An inner impingement plate provided facing the surface of the outer impingement plate; and first and second bridges connecting the outer impingement plate and the inner impingement plate. The first opening and the second opening communicating the first space between the object to be cooled and the outer impingement plate and the second space in contact with the surface of the inner impingement plate on the opposite side of the outer impingement plate, respectively, It passes through the first and second bridges. A hole provided in the outer impingement plate is located between the first and second openings. The cooling medium supplied to the second space is jetted from the first and second openings to the cooling target.

  ADVANTAGE OF THE INVENTION According to this invention, in the turbine blade which performs impingement cooling, while reducing a cross flow and controlling the flow of a cooling medium positively, a cooling medium can be collect | recovered efficiently.

It is a perspective view which shows the cooling structure by the conventional impingement cooling. It is a figure which shows the structure of the gas turbine in which the gas turbine stationary blade of embodiment of this invention is used. It is sectional drawing which shows the structure of the gas turbine stationary blade of the 1st Embodiment of this invention. It is sectional drawing which shows the structure of the insert of the double structure inserted in the internal space of the front edge vicinity of the gas turbine stationary blade of 1st Embodiment. It is sectional drawing which shows the structure of the insert of the double structure inserted in internal space in the rear edge vicinity of the gas turbine stationary blade of 1st Embodiment. It is a perspective view which shows the structure of the double structure insert of 1st Embodiment. It is a front view which shows the structure of the double structure insert of 1st Embodiment. It is sectional drawing which shows the structure in the II cross section of the double structure insert of 1st Embodiment. It is sectional drawing which shows the structure in the II-II cross section of the double structure insert of 1st Embodiment. It is sectional drawing which shows the structure of the gas turbine stationary blade of 2nd Embodiment. It is a perspective view which shows the structure of the double structure insert of 2nd Embodiment. It is sectional drawing which shows the structure of the insert of the double structure of 2nd Embodiment. It is sectional drawing which shows the other structure of the gas turbine stationary blade in 2nd Embodiment. It is sectional drawing which shows other structure of the gas turbine stationary blade in 2nd Embodiment. It is sectional drawing which shows the structure of the gas turbine stationary blade of 3rd Embodiment. It is a front view which shows the structure of the insert of the double structure in 3rd Embodiment. It is sectional drawing which shows the structure in the III-III cross section of the insert of the double structure of 3rd Embodiment. It is sectional drawing which shows the structure in the IV-IV cross section of the insert of the double structure of 3rd Embodiment. It is sectional drawing which shows the modification of the structure of the gas turbine stationary blade of 2nd Embodiment.

(First embodiment)
FIG. 2 is a diagram showing a structure of a gas turbine in which the gas turbine stationary blade according to the first embodiment of the present invention is used, particularly a portion where combustion gas flows from the combustor 1 to the first row stationary blade 10. It is. An attachment flange 2 and an outer shroud 4 provided at the end of the transition piece of the combustor 1 are fixed via a transition piece outlet seal 3. The stationary blade 10 is fixed between the outer shroud 4 and the inner shroud 5. When the combustion gas 8 flows from the combustor 1 toward the row of the stationary blades 10, the combustion gas 8 is directed in a desired direction by the stationary blades 10 to move the moving blades (not shown) positioned downstream of the stationary blades 10. It is rotated, and thereby a rotational driving force is obtained. Although only the first row of stationary blades 10 is shown in FIG. 1, in general, a plurality of rows of stationary blades and a plurality of rows of moving blades are provided.

  Cooling air 6 is supplied to the stationary blade 10 from the outer shroud 4. The cooling air 6 is a cooling medium that is introduced into the stationary blade 10 and used for cooling the stationary blade 10. As will be described later, in the present embodiment, the stationary blade 10 is configured such that a part of the cooling air 6 is recovered. The recovered air is shown as recovered air 7 in FIG.

  FIG. 3 is a cross-sectional view showing the structure of the stationary blade 10. The stationary blade 10 includes a blade wall 11, partition walls 12, 13, and 14, and inserts 15, 16, 17, and 18. The insert 15 is inserted into a space A formed by the blade wall 11 and the partition wall 12 near the leading edge of the stationary blade 10. The insert 16 is inserted into a space B formed by the blade wall 11 and the partition walls 12, 13, and 14 on the central portion and the ventral side of the stationary blade 10. The insert 17 is inserted into a space C formed by the blade wall 11 and the partition walls 12, 13, and 14 on the center and back side of the stationary blade 10. The insert 18 is inserted in a space D formed by the blade wall 11 and the partition wall 13 near the rear edge of the stationary blade 10.

  Here, among the four inserts, the insert 15 inserted into the space A and the insert 18 inserted into the space D have a double structure. As shown in FIG. 4, the insert 15 includes an inner insert plate 21 and an outer insert plate 22, and is supported by support portions 12 a and 12 b provided on the partition wall 12. The space between the inner insert plate 21 and the outer insert plate 22 is used as a flow path for supplying the cooling air 6, and the cooling air 6 passes through the hole provided in the outer insert plate 22 to the inner wall of the blade wall 11. And is used for impingement cooling. The cooling air that has collided with the inner wall of the blade wall 11 passes through the inner insert plate 21 and the outer insert plate 22 through a passage (that is, the space inside the inner insert plate 21 (that is, the inner insert plate 21). It is introduced into the space (in contact with the surface opposite to the outer insert plate 22) and collected. The recovered cooling air is illustrated at 7. Similarly in the insert 18 shown in FIG. 5, the insert 18 has a double structure including an inner insert plate 21 and an outer insert plate 22. However, in the insert 18, the cooling air collected in the space surrounded by the inner insert plate 21 is introduced into the tail portion of the stationary blade 10 provided with the cooling pins 20 and used for cooling the tail portion of the stationary blade 10. Thereafter, the air is discharged from the opening provided at the rear edge of the stationary blade 10 to the outside of the stationary blade 10. As will be described later, such a double structure guides the flow of cooling air that has collided with the inner wall of the blade wall 11 to the inside of the inner insert plate 21 while reducing the cross flow, and collects it as the recovered air 7. Make it possible. The double structure used in the inserts 15 and 18 will be described in detail later.

  On the other hand, in the structure shown in FIG. 3, the inserts 16 and 17 have a general single structure. The cooling air introduced into the internal space of the inserts 16 and 17 is blown onto the inner wall of the blade wall 11 through the holes provided in them. The cooling air blown to the blade wall 11 is ejected to the outside of the stationary blade 10 through the cooling hole 19 provided in the blade wall 11 and used for film cooling of the outer surface of the blade wall 11. However, it should be noted that the above-described double structure can be applied to the inserts 16 and 17 as well.

  Hereinafter, the double structure used in the inserts 15 and 18 of the present embodiment will be described in detail. Below, although the structure of the insert 15 is demonstrated in detail, the insert 18 also has the same structure.

  FIG. 6 is a perspective view showing the structure of the inner insert plate 21 and the outer insert plate 22, and FIG. 7 is a front view of the outer insert plate 22 as viewed from the blade wall 11. 8A is a cross-sectional view showing the structure of the inner insert plate 21 and the outer insert plate 22 in the II section of FIG. 7, and FIG. 8B is the inner insert plate 21 and the outer structure in the II-II section of FIG. 3 is a cross-sectional view showing a structure of an insert plate 22. FIG.

  As shown in FIGS. 8A and 8B, the outer insert plate 22 is provided so as to face the blade wall 11, and the inner insert plate 21 is provided so as to face the outer insert plate 22. The outer insert plate 22 is provided with a protrusion 22a that protrudes toward the blade wall 11, and a hole 23 is provided at the tip of the protrusion 22a. As shown in FIGS. 6 and 7, the protrusion 22 a is provided so as to extend in a direction parallel to the flow of the cooling air 6, and the hole 23 is a direction parallel to the flow of the cooling air 6. Are arranged side by side.

  As shown in FIG. 8B, the inner insert plate 21 and the outer insert plate 22 are connected by a hollow bridge 25. The hollow bridge 25 is hollow, and the internal space of the hollow bridge 25 is an inner insert opposite to the outer insert plate 22 and the space between the wing wall 11 and the outer insert plate 22, as shown in FIG. It is used as an opening 24 that communicates with a space adjacent to the surface of the plate 21. The opening 24 and the hollow bridge 25 are provided between the two protrusions 22a (that is, between the rows of the two holes 23).

  Hereinafter, impingement cooling using the insert 15 having such a structure will be described. As shown in FIG. 8A, the cooling air 6 supplied to the space between the inner insert plate 21 and the outer insert plate 22 is ejected from the hole 23 provided in the outer insert plate 22 toward the blade wall 11. Is done. As shown in FIG. 8B, the cooling air that has collided with the blade wall 11 is introduced into the space inside the inner insert plate 21 from the opening 24 provided between the rows of the two holes 23. The space inside the inner insert plate 21 is used as a flow path for collecting the collected air 7. The insert 15 having such a structure prevents the cooling air ejected from the holes 23 in one row from flowing into the vicinity of the holes 23 in the other row and causing a cross flow after colliding with the blade wall 11. And the cooling efficiency of impingement cooling can be improved. In addition, since the flow of the cooling air is guided to the space inside the inner insert plate 21 through the opening 24, the cooling air can be efficiently controlled to collect the cooling air.

  In addition, the structure in which the protruding portion 22 a protrudes toward the blade wall 11 reduces the distance between the blade wall 11 and the hole 23, while the portion between the protruding portion 22 a of the outer insert plate 22 and the blade wall 11. It is possible to increase the distance between. First, such a structure has an advantage of improving the cooling efficiency of impingement cooling by reducing the distance between the blade wall 11 and the hole 23. Second, the cooling air that has collided with the blade wall 11 has the advantage that the cross flow is less likely to occur due to the increased space between the protruding portion 22a of the outer insert plate 22 and the blade wall 11. is there.

(Second Embodiment)
9, FIG. 10 and FIG. 11 illustrate the structure of a gas turbine stationary blade according to a second embodiment of the present invention, and in particular, another structure of an insert having a double structure. 9 to 11, the double structure is applied to the insert 16 </ b> A that is inserted into the space B formed by the blade wall 11 and the partition walls 12, 13, 14 on the center and the ventral side of the stationary blade 10. ing. The insert 16 </ b> A is supported by a support portion 12 c provided on the partition wall 12 and a support portion 13 a provided on the partition wall 13.

  The insert 16A illustrated in FIGS. 9 to 11 has a structure similar to the insert 15 of FIGS. 6, 7, 8A, and 8B, except that the protrusion 22a is not provided. . Referring to FIG. 10, the insert 16 </ b> A includes an inner insert plate 31 and an outer insert plate 32. A hole 33 is provided in the outer insert plate 32. The holes 33 are arranged side by side in the direction in which the cooling air 6 flows. The inner insert plate 31 and the outer insert plate 32 are connected by a hollow bridge 35 and an end bridge 36. The end bridge 36 connects the ends of the inner insert plate 31 and the outer insert plate 32, and the end bridge 36 is connected to a support portion 12 c provided on the partition wall 12. In addition, as shown in FIG. 11, the interior of the hollow bridge 35 is in contact with the space between the outer insert plate 32 and the wing wall 11 and the surface of the inner insert plate 31 opposite to the outer insert plate 32. Are used as openings 34 communicating with each other. The opening 34 is located between two rows of holes 33. In this embodiment, since the outer insert plate 32 is not provided with a protrusion, the row of the specific two holes 33 and the end on the blade wall 11 side of the opening 34 provided therebetween are substantially on the same plane. is there.

  In the insert 16A having such a structure, impingement cooling is performed as follows. The cooling air 6 is supplied to the space between the inner insert plate 31 and the outer insert plate 32. The cooling air 6 supplied to the space between the inner insert plate 31 and the outer insert plate 32 is ejected from the hole 33 provided in the outer insert plate 32 toward the blade wall 11. As shown in FIG. 9, the cooling air that has collided with the blade wall 11 is recovered in the space between the inner insert plate 31 and the partition wall 14 from the opening 34 provided between the rows of the two holes 33. The

  Here, in the structure of FIG. 9, the cooling air collected in the space between the inner insert plate 31 of the insert 16 </ b> A and the partition wall 14 is further used for impingement cooling the portion on the back side of the blade wall 11. The Specifically, the partition wall 14 is provided with an opening 14 a that communicates the ventral space B and the dorsal space C in the center of the stationary blade 10. In the space C, an insert 17 </ b> A facing the inner wall of the wing wall 11 is provided. The insert 17 </ b> A is supported by a support portion 12 d provided on the partition wall 12 and a support portion 13 b provided on the partition wall 13. The insert 17A is provided with holes for impingement cooling. The cooling air recovered in the space between the inner insert plate 21 and the partition wall 14 is introduced into the space C through the opening 14a, and further injected onto the inner surface of the blade wall 11 through the hole provided in the insert 17A. The The cooling air injected to the inner surface of the blade wall 11 is jetted to the outside of the stationary blade 10 through the cooling hole 19 and used for film cooling of the outer surface of the blade wall 11.

  The insert 16A of the second embodiment is similar to the insert 15 of the first embodiment. After the cooling air ejected from the holes 33 in one row collides with the blade wall 11, It is possible to prevent the occurrence of a cross flow by flowing in the vicinity, and the cooling efficiency of impingement cooling can be improved. In addition, since the flow of the cooling air is guided to the space between the inner insert plate 31 and the partition wall 14 through the opening 34, the cooling air can be efficiently controlled to collect the cooling air.

  In addition, since the insert 16A of the second embodiment has no protrusion on the outer insert plate 32, the space required for installation is small compared to the insert 15 of the first embodiment, and the hole 33 Cooling unevenness at the position between the rows is reduced, and there is also an advantage that processing for forming the insert 16A is easy.

  As shown in FIG. 12, a configuration in which the partition wall 14 is not provided is also possible. Even in this case, the cooling air injected from the outer insert plate 32 to the inner surface of the abdominal blade wall 11 through the hole 33 passes through the opening 34 to the surface of the inner insert plate 31 on the opposite side of the outer insert plate 32. It is collected in the space that touches. The recovered cooling air is injected to the inner surface of the back blade wall 11 through a hole provided in the insert 17A. The cooling air injected to the inner surface of the blade wall 11 is jetted to the outside of the stationary blade 10 through the cooling hole 19 and used for film cooling of the outer surface of the blade wall 11.

  Further, as shown in FIG. 13, the cooling air recovered in the space between the inner insert plate 31 and the partition wall 14 is formed by the blade wall 11 and the partition wall 13 near the trailing edge of the stationary blade 10. It may be introduced into the space D and used for impingement cooling in the space D. In this case, an insert 18 </ b> A is provided in the space D along the inner surface of the blade wall 11. The insert 18 </ b> A is supported by support portions 13 c and 13 d provided on the partition wall 13 and a support portion 11 a provided on the inner surface of the blade wall 11. The insert 18A is provided with a number of holes used for impingement cooling. The cooling air collected in the space between the inner insert plate 31 and the partition wall 14 is introduced into the space D through the opening 13e provided in the partition wall 13, and further, the blade wall through the hole provided in the insert 18A. 11 is sprayed on the inner surface. The cooling air sprayed to the inner surface of the ventral blade wall 11 is ejected to the outside of the stationary blade 10 through the cooling hole 19 and used for film cooling of the outer surface of the blade wall 11. On the other hand, the cooling air jetted onto the inner surface of the back blade wall 11 is introduced into the tail of the stationary blade 10 provided with the cooling pin 20 and used for cooling the tail of the stationary blade 10, and then the stationary blade 10. It is discharged to the outside of the stationary blade 10 through an opening provided at the rear edge.

(Third embodiment)
FIGS. 14, 15, 16A, and 16B illustrate the structure of the gas turbine stationary blade according to the third embodiment of the present invention, and in particular, show another aspect of the insert having a double structure. In the third embodiment, the double structure is applied to the insert 18 </ b> B inserted into the space D formed by the blade wall 11 and the partition wall 13 near the trailing edge of the stationary blade 10.

  The insert 18B has a structure similar to that of the insert 16A of the second embodiment described above as a spatial topology, but is configured such that the flow of cooling air is in the opposite direction. That is, as shown in FIG. 14, in the insert 18B, the cooling air 6 supplied to the inside of the inner insert plate 41 is used for impingement cooling, and the cooling air used for impingement cooling is used for the inner insert plate. It is comprised so that it may collect | recover in the space between 41 and the outer side insert board 42. FIG. Hereinafter, the structure of the insert 18B will be described in detail.

  As shown in FIGS. 16A and 16B, the inner insert plate 41 and the outer insert plate 42 are connected by a hollow bridge 45. The inside of the hollow bridge 45 is used as an opening 44 that communicates the space between the outer insert plate 42 and the blade wall 11 and the space in contact with the surface of the inner insert plate 41 opposite to the outer insert plate 42. As shown in FIG. 15, the outer insert plate 42 is provided with a plurality of holes 43, from which the space between the outer insert plate 42 and the blade wall 11 and the inner insert plate 41 are provided. The space between the outer insert plate 42 and the outer insert plate 42 communicates with each other through a hole 43. In the present embodiment, each of the openings 44 has a smaller area than the hole 43.

  In the insert 18B having such a structure, impingement cooling is performed as follows. The cooling air 6 is supplied to a space inside the inner insert plate 41 (a space in contact with the surface of the inner insert plate 41 opposite to the outer insert plate 42). The cooling air 6 supplied to the space inside the inner insert plate 41 is injected toward the inner surface of the blade wall 11 through the opening 44. The cooling air that has collided with the blade wall 11 is collected in the space between the inner insert plate 41 and the outer insert plate 42 from the hole 43 provided between the rows of the two openings 44. As shown in FIG. 14, the cooling air collected in the space between the inner insert plate 41 and the outer insert plate 42 is introduced into the tail portion of the stationary blade 10 provided with the cooling pin 20, and the stationary blade 10. After being used for cooling the tail of the blade, it is discharged to the outside of the stationary blade 10 through an opening provided at the rear edge of the stationary blade 10.

  The insert 18B of the third embodiment is similar to the inserts 15 and 16A of the first and second embodiments. After the cooling air ejected from the openings 44 in one row collides with the blade wall 11, It is possible to prevent the occurrence of a cross flow by flowing in the vicinity of the opening 44 in the row, and the cooling efficiency of impingement cooling can be improved. In addition, since the flow of the cooling air is guided to the space between the inner insert plate 41 and the outer insert plate 42 through the holes 43, the flow of the cooling air can be efficiently controlled to collect the cooling air. .

  In any of the above-described embodiments, as shown in FIG. 17, the inner surface of the blade wall 11 may be provided with a protrusion 50 for controlling the flow of cooling air that has collided with the blade wall 11. The protrusion 50 is provided so as to protrude from the blade wall 11 toward the outer insert plates 22, 32, 42. FIG. 17 illustrates a configuration in which the protrusion 50 is provided on the inner surface of the blade wall 11 in the structure of the second embodiment. The protrusion 50 is provided at a position between a row of holes 23 and 33 or openings 44 for injecting cooling air to the blade wall 11. The protrusion 50 may be configured as a rib extending in a direction parallel to the direction of the row of the holes 23, 33 or the openings 44, and the pins arranged in a direction parallel to the direction of the row of the holes 23, 33 or the openings 44 May be configured as a sequence of

  Although various embodiments of the present invention have been specifically described above, the present invention should not be construed as being limited to the above-described embodiments. In particular, those skilled in the art will appreciate that the recovered cooling air is not limited to the applications mentioned in the above embodiments and can be used in a variety of applications. For example, the cooling air is recovered outside the stationary blade 10 as the recovered air 7, and other components (for example, a gas turbine stationary blade, a split ring that supports the gas turbine stationary blade (also referred to as a shroud, a ring segment, etc.), combustion It can also be used for cooling the liner (inner cylinder, tail cylinder, etc.) of the vessel. Moreover, it is also possible to use another cooling medium instead of the cooling air depending on the application. Furthermore, although cooling of the stationary blade 10 is described in the above-described embodiment, the present invention can be applied to impingement cooling of other members (for example, moving blades of a gas turbine) in principle. Will be readily understood by those skilled in the art.

1: Combustor 2: Mounting flange 3: Outlet seal 4: Outer shroud 5: Inner shroud 6: Cooling air 7: Recovered air 10: Stator blade 11: Blade wall 11a: Support parts 12, 13, 14: Partition wall 12a 12b, 12c, 13a, 13b, 13c, 13d: Support portions 14a, 13e: Openings 15, 16, 16A, 17, 17A, 18, 18A, 18B: Inserts 19: Cooling holes A, B, C, D: Spaces 20: Cooling pin 21: Inner insert plate 22: Outer insert plate 22a: Protruding portion 23: Hole 24: Opening 25: Hollow bridge 31: Inner insert plate 32: Outer insert plate 33: Hole 34: Opening 35: Hollow bridge 36: End bridge 41: Inner insert plate 42: Outer insert plate 43: Hole 44: Opening 45: Hollow bridge 50: Protrusion 105: High temperature member 105a:却面 109: nozzle pipe 109a: air injection port 115: rib

Claims (10)

The wing wall,
A first insert inserted into a space formed inside the wing wall,
The first insert is
An outer insert plate provided to face the first inner surface of the wing wall and having a first hole and a second hole at a position facing the first inner surface;
An inner insert plate provided facing the surface of the outer insert plate on the opposite side of the wing wall;
A bridge connecting the outer insert plate and the inner insert plate;
An opening that connects the first space between the wing wall and the outer insert plate and the second space in contact with the surface of the inner insert plate on the opposite side of the outer insert plate is provided through the bridge.
The opening is located between the first hole and the second hole;
The cooling medium supplied to the third space between the outer insert plate and the inner insert plate is sprayed from the first hole and the second hole to the first inner surface of the blade wall,
The cooling medium sprayed on the inner surface of the blade wall is introduced into the second space through the opening,
The turbine blade that is used for cooling the second inner surface by injecting the cooling medium supplied to the second space onto a second inner surface facing the first inner surface of the blade wall. The turbine blade according to claim 1,
Furthermore,
A second insert provided in a space formed inside the blade wall so as to face the second inner surface;
The second insert has a third hole at a position facing the second inner surface,
The turbine blade, wherein the cooling medium supplied to the second space is injected from the third hole to the second inner surface of the blade wall. The turbine blade according to claim 1 or 2,
The turbine blade, wherein the entire amount of the cooling medium supplied to the second space is used for cooling the second inner surface. The turbine blade according to any one of claims 1 to 3,
The blade wall is provided with a cooling hole that communicates the second inner surface and the outside of the turbine blade,
A turbine blade that is used for film cooling of the outer surface of the turbine blade, in which the cooling medium injected onto the second inner surface of the blade wall is ejected to the outside of the turbine blade through the cooling hole. The turbine blade according to any one of claims 1 to 4,
The first inner surface is an inner surface of a ventral side portion of the wing wall;
The second inner surface is an inner surface of a back portion of the blade wall. The turbine blade according to any one of claims 1 to 5,
An end of the first hole and the second hole and a blade wall side of the opening provided between the first hole and the second hole are substantially on the same plane. The wing wall,
An insert inserted into a space formed inside the wing wall,
The insert is
An outer insert plate provided to face the inner surface of the wing wall, and provided with a hole at a position facing the wing wall;
An inner insert plate provided facing the surface of the outer insert plate on the opposite side of the wing wall;
A first bridge and a second bridge connecting the outer insert plate and the inner insert plate;
A first opening and a second opening communicating the first space between the blade wall and the outer insert plate and the second space in contact with the surface of the inner insert plate on the opposite side of the outer insert plate, respectively; Provided through the first and second bridges;
The hole provided in the outer insert plate is located between the first and second openings;
A turbine blade in which the cooling medium supplied to the second space is injected from the first and second openings onto the inner surface of the blade wall. The turbine blade according to claim 7, wherein
The cooling medium sprayed on the inner surface of the blade wall is introduced into a third space between the outer insert plate and the inner insert plate through the hole provided in the outer insert plate.
The turbine blade used for cooling by supplying the cooling medium in the third space to the other part of the turbine blade. The turbine blade according to claim 7, wherein
The cooling medium sprayed on the inner surface of the blade wall is introduced into a third space between the outer insert plate and the inner insert plate through the hole provided in the outer insert plate.
The turbine blade in which the cooling medium in the third space is recovered outside the turbine blade. The turbine blade according to any one of claims 7 to 9,
A turbine blade provided with a protrusion protruding toward the outer insert plate at a position between the first opening and the second opening of the blade wall.

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