JP2010276010A - Turbine vane, method for manufacturing turbine vane, and gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a turbine vane, which is configured so that a cooling flow passage can be easily and accurately formed in the inner part, and thermal stress in operation can be suppressed, a method for manufacturing the turbine vane, and a gas turbine. <P>SOLUTION: The turbine stator vane 10 includes an outer frame 20 formed in a cylindrical shape along the vane height direction to form an outer sheath, a support part 21 provided within the outer frame 20 and supported by the outer frame 20, and an insert member 22 inserted into the outer frame 20 while securing a gap that forms a cooling flow passage 11b with the inner circumferential surface of the outer frame 20, and fixed to the support part 21 at only one of both ends in the vane height direction thereof. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a turbine blade, a manufacturing method thereof, and a gas turbine including the turbine blade.

  A turbine blade used for a stationary blade or a moving blade of a gas turbine is exposed to a high-temperature working fluid, and thus has a cooling structure. That is, a cooling flow path is formed in the turbine blade along the blade height direction. Then, through this cooling flow path, compressed air generated by the compressor or water vapor generated by the steam turbine is circulated as a cooling fluid, and depending on the temperature conditions of the working fluid, cooling holes formed on the turbine blade surface Cooling is performed by discharging the cooling fluid from the outside to the outside.

In such turbine blades, the cooling flow path can be formed by, for example, a method of integrally forming with the blade body by casting or a method of drilling in the blade body. There is a problem in that it is necessary to provide a cooling flow path formed with high accuracy.
The blade body has a cavity, and a plurality of fitting grooves are formed on the wall surface of the cavity along the blade height direction over the entire circumference, and the wall surface and the gap are disposed in the cavity of the blade body. And the turbine blade provided with the insert which has the jetty fitted by the fitting groove | channel of the blade main body on the outer wall surface is proposed. In such a turbine blade, since the jetty formed in the insert is fitted in the fitting groove formed in the blade body, a gap due to a dimensional difference is formed between the blade body and the insert. Thus, this gap can be used as a cooling channel (for example, see Patent Document 1).

JP-A-6-330705

  However, in the turbine blade of Patent Document 1, the plurality of fitting grooves formed over the entire circumference of the wall surface of the cavity and the jetty are fitted, so that the blade body and the insert are excluded except for a range of cooling channels. They are fixed to each other over the entire height direction and over the entire circumference of the wing. During operation, the blade body is heated directly by the working fluid and becomes high temperature, while the insert becomes relatively low temperature inside the cooling channel, resulting in a difference in thermal elongation and thermal stress. There was a problem that would occur.

  The present invention has been made in view of the above-described circumstances, and it is possible to easily and accurately form a cooling flow path inside and to suppress generation of thermal stress during operation. A turbine blade, a method for manufacturing the turbine blade, and a gas turbine are provided.

In order to solve the above problems, the present invention proposes the following means.
The turbine blade of the present invention includes an outer frame that is formed in a cylindrical shape along the blade height direction and forms an outer shell, a support portion that is provided inside the outer frame and supported by the outer frame, and the outer frame An insertion member that is inserted inside with a gap serving as a cooling flow path between the inner peripheral surface and the support member that is fixed to the support portion only at either one of both ends in the blade height direction. It is a feature.

  The turbine blade according to the present invention has an outer frame that is formed in a cylindrical shape along the blade height direction and forms an outer shell, and is spanned between mutually facing surfaces of the outer frame, and defines an interior that penetrates in the blade height direction. A plurality of support portions supported by the outer frame and inserted into the interior with gaps serving as cooling flow paths between the inner peripheral surface of the outer frame and the blade height direction. And an insertion member fixed to the support portion only at either one of both ends.

  Further, the turbine blade manufacturing method of the present invention includes an inner peripheral surface of the outer frame inside the outer frame formed in a cylindrical shape along the blade height direction and having a support portion attached therein. The insertion member is inserted with a gap serving as a cooling flow path between them, and only one of both end portions in the direction of the blade height of the insertion member is fixed to the support portion. .

  According to this configuration and method, the outer frame and the insertion member are integrated by the insertion member being fixed to the support portion supported by the outer frame, and the inner peripheral surface of the outer frame and the insertion member are inserted. A cooling channel is formed by a gap formed between the members. Here, the cooling flow path can be easily formed by simply inserting the insertion member into the outer frame, and can be formed with high accuracy due to the dimensional difference between them. Further, the insertion member is fixed to the support portion at only one of the both ends in the blade height direction, and is thus supported in a cantilever manner via the support portion with respect to the outer frame. ing. Therefore, even if there is a difference in thermal expansion between the outer frame exposed to the working fluid and the insertion member inside the cooling flow path, the end portion where the insertion member is fixed to the support portion is the base end. Therefore, the generation of thermal stress can be effectively suppressed.

  In the turbine blade, it is more preferable that the insertion member is configured in a frame shape having a hollow inside.

  According to this configuration, since the insertion member is configured in a frame shape having a hollow inside, the weight can be reduced as a whole, and the insertion member itself can be reduced in comparison with a solid member. Generation of thermal stress can also be suppressed. Moreover, since it can comprise by assembling a board | plate material in frame shape, manufacture is easy and cost reduction can be achieved.

  Further, in the above turbine blade, the insertion member has an opening at least a part of a range facing the support portion and the other end portion opposite to one end portion fixed to the support portion. More preferably.

  According to this configuration, in the insertion member, at least a part of the range facing the support part, excluding the range where the cooling flow path needs to be formed and one end part which needs to be fixed to the support part, And by setting it as the structure which opened the other edge part, weight reduction, reduction of a thermal stress, and manufacture and cost reduction can further be aimed at.

  In the turbine blade described above, it is more preferable that the insertion member is fixed to the support portion at an end portion on the downstream side of the cooling channel among both end portions in the blade height direction.

  According to this configuration, even if a part of the cooling fluid flowing into the cooling flow channel flows between the insertion member and the support portion on the upstream side, the insertion member and the support portion are fixed on the downstream side. It is regulated that it will flow out as it is. Thereby, the pressure acting by the cooling fluid between the insertion member and the support portion can be increased, and as a result, the flow rate of the cooling fluid flowing between the insertion member and the support portion can be reduced, Cooling can be effectively performed by the cooling fluid flowing through the cooling channel. In addition, the cooling fluid that has flowed in between the insertion member and the support portion joins the cooling flow path on the downstream side, which causes the cooling fluid to be relatively hot and the cooling effect to be reduced. Cooling can be performed more effectively on the side.

  In the turbine blade described above, the insertion member may be fixed to the support portion at an end portion on the upstream side of the cooling flow path, out of both ends in the blade height direction.

  According to this configuration, since the insertion member and the support portion are fixed on the upstream side, the cooling fluid is prevented from flowing between the insertion member and the support portion, and the cooling flow path is formed. Cooling can be effectively performed by the cooling fluid so as to flow in. Further, even if the cooling fluid flows in between the insertion member and the support portion from the cooling channel, the insertion member and the support portion are not fixed on the downstream side, and can be discharged as they are.

  Further, in the above turbine blade, the insertion members are provided in pairs in the blade height direction, and one of the insertion members on the upstream side of the cooling flow path, on both sides of the blade height direction, The other end of the insertion member, which is the downstream side of the cooling flow path, is fixed to the support portion at the downstream end, and is fixed to the support portion at the upstream end. It is also good.

  According to this configuration, one of the insertion members is fixed to the support portion upstream of the cooling flow path, thereby restricting the cooling fluid from flowing between the insertion member and the support portion. The cooling can be effectively performed by flowing into the cooling flow path. Further, even if the cooling fluid flows from the cooling flow path between one of the insertion members and the support portion, it may flow out as it is because the other insertion member and the support portion are fixed on the downstream side. It is regulated. As a result, the pressure acting on the cooling fluid between each insertion member and the support portion can be increased, and as a result, the flow rate of the cooling fluid flowing between the insertion member and the support portion can be reduced. Cooling can be effectively performed by the cooling fluid flowing through the cooling channel. In addition, the cooling fluid that flows between the other of the insertion members and the support portion joins the cooling flow path on the downstream side, so that the cooling fluid becomes relatively high temperature and the cooling effect is reduced. Thus, cooling can be performed more effectively on the downstream side.

  In the turbine blade described above, it is more preferable that the insertion member is inserted into the outer frame such that the gap serving as the cooling flow path changes in the blade height direction.

  According to this configuration, it is possible to effectively cool by increasing the flow velocity in a range where the cooling channel is narrow, and for example, the cooling channel is set at a position where the temperature can be relatively high in the blade height direction. By setting it to be narrow, it is possible to optimize the cooling.

  In the turbine blade described above, it is more preferable that a restricting means for restricting the flow of fluid from the cooling flow path is provided between the insertion member and the support portion.

  According to this configuration, it is possible to restrict the cooling fluid flowing through the cooling flow path from flowing between the insertion member and the support portion by the restriction means, and to allow the cooling fluid to flow through the cooling flow path. Effective cooling.

  Further, in the above turbine blade, the blade body includes, as the cooling passage, a supply side passage through which cooling gas is supplied and flows from one side to the other in the blade height direction, and the supply side passage. There are a plurality of discharge-side passages into which the circulated cooling gas flows in, flows from the other in the blade height direction to the other and is discharged, and the supply-side passages and the discharge-side passages are alternately arranged. More preferably.

  According to this configuration, the supply-side flow path and the discharge-side flow path are alternately arranged, so that the separation distance between the supply-side flow path and the discharge-side flow path is shortened to minimize the overall length of the flow path. As a limit, pressure loss can be suppressed. In addition, it is possible to prevent a so-called cross flow in which the cooling gas flowing from the supply side flow channel into the discharge side flow channel is mixed with the cooling gas from the other supply side flow channel. Generation of pressure loss and reduction in impingement cooling efficiency can be prevented. For this reason, cooling gas can be circulated through the cooling channel at a larger flow rate to effectively perform cooling.

  The gas turbine of the present invention is characterized in that the turbine blade is provided as a stationary blade or a moving blade.

  According to this configuration, the turbine blades can be effectively cooled, the generation of thermal stress can be suppressed, and the turbine blades can be suitably operated in a high temperature environment.

According to the turbine blade of the present invention, it is possible to easily and accurately form a cooling flow path inside, and to effectively suppress generation of thermal stress during operation.
In addition, according to the turbine blade manufacturing method of the present invention, the cooling flow path can be easily and accurately formed in the turbine blade, and the generation of thermal stress when the turbine blade is operated is effective. Can be suppressed.
Moreover, according to the gas turbine of this invention, by providing the said turbine blade, it can be made to operate | move favorably in a high temperature environment, and high output can be achieved.

In the turbine blade of the first embodiment according to the present invention, it is a cross-sectional view (at a cutting line AA shown in FIG. 2) broken along a plane orthogonal to the blade height direction. It is the perspective view which fractured | ruptured a part which shows the detail of the turbine stationary blade of 1st Embodiment which concerns on this invention. FIG. 2 is a perspective view of the turbine stationary blade shown in FIG. 1, broken at a cutting line BB. It is a typical half section view showing a gas turbine provided with a turbine blade of a 1st embodiment of the present invention. It is sectional drawing which shows the detail of the flow path for cooling in the turbine blade of 1st Embodiment which concerns on this invention. It is sectional drawing which looked at the side which showed typically the turbine blade of 1st Embodiment which concerns on this invention. It is sectional drawing which looked at the side which showed typically the turbine blade of 2nd Embodiment which concerns on this invention. It is sectional drawing which looked at the side which showed typically the turbine blade of 3rd Embodiment which concerns on this invention. It is sectional drawing which looked at the side which showed typically the turbine blade of 4th Embodiment which concerns on this invention. In the turbine blade of the fifth embodiment according to the present invention, it is a perspective view broken at the same position as the cutting line BB in FIG. It is sectional drawing which shows the detail of the flow path for cooling, and the control means in the turbine blade of 5th Embodiment which concerns on this invention. It is the perspective view which fractured | ruptured a part which shows the detail of the turbine stationary blade of 6th Embodiment which concerns on this invention. It is sectional drawing which looked at the side which showed typically the turbine blade of 6th Embodiment which concerns on this invention. It is sectional drawing in the cutting line CC of FIG. It is sectional drawing in the cutting line DD of FIG. It is sectional drawing in the cutting line EE of FIG. In the turbine blade of the embodiment according to the present invention, it is a cross-sectional view seen from the side showing a modification of the cooling flow path. FIG. 6 is a cross-sectional side view of another modification of the cooling channel in the turbine blade according to the embodiment of the present invention.

(First embodiment)
A first embodiment according to the present invention will be described below with reference to the drawings.
FIG. 1 is a cross-sectional view of the turbine blade of the present embodiment, taken along a plane perpendicular to the blade height direction. FIG. 2 is a partially broken perspective view showing details of the turbine vane of the present embodiment, and FIG. 1 shows a cross section taken along a cutting line AA in FIG. FIG. 3 shows a perspective view taken along the cutting line BB in FIG.
FIG. 4 is a schematic half sectional view showing a gas turbine provided with the turbine blade of the present embodiment.
As shown in FIG. 4, the gas turbine 1 includes a compressor 2 that generates compressed air, and a combustion gas G1 (see FIG. 2) that is a working fluid by supplying fuel to the compressed air supplied from the compressor 2. A plurality of combustors 3 to be generated and a turbine 4 having at least one stage of turbine stationary blades 10 and turbine rotor blades 6 and generating rotational power by combustion gas G1 supplied from the combustor 3 are provided. .

  Further, a rotor 7 extending in the axial direction D is integrally attached to the gas turbine 1 from the compressor 2 to the turbine 4, and the rotor 7 has a bearing portion 7 a having one end provided in the compressor 2. Is supported rotatably in the circumferential direction R of the turbine 4 around the axis O, and the other end is supported rotatably in the circumferential direction R of the turbine 4 by a bearing portion 7 b provided in the turbine 4. Hereinafter, the compressor 2 side is defined as the front side and the turbine 4 side is defined as the rear side along the axial direction D of the rotor 7.

  The compressor 2 includes a compressor casing 2b disposed with the air intake port 2a for taking in air facing forward, a plurality of compressor vanes 2c disposed in the compressor casing 2b, and a plurality of compressor movements. And a wing 2d. The compressor stationary blades 2 c are fixed to the inner peripheral surface of the compressor casing 2 b and extended toward the rotor 7, and are arranged at equal intervals in the circumferential direction R of the turbine 4. The compressor blades 2d are fixed to the outer peripheral surface of the rotor 7 and extended toward the inner peripheral surface of the compressor casing 2b, and are arranged at equal intervals in the circumferential direction R of the turbine 4. . The compressor stationary blades 2c and the compressor rotor blades 2d are arranged in multiple stages so as to alternate along the axial direction D.

  The combustor 3 includes an inner cylinder 3a having a burner (not shown), an outer cylinder 3b for guiding compressed air supplied from the compressor 2 to the inner cylinder 3a, and a fuel injector (not shown) for supplying fuel to the inner cylinder 3a. And a tail cylinder 3c that guides the combustion gas G1 from the inner cylinder 3a to the turbine 4. According to the combustor 3 configured as described above, in the inner cylinder 3a, the compressed air guided from the outer cylinder 3b and the fuel supplied from the combustion injector are mixed, and the mixed fluid is burned by the burner. Thus, the combustion gas G1 can be generated, and the combustion gas G1 can be guided to the turbine 4 through the tail cylinder 3c. The plurality of combustors 3 are disposed in the circumferential direction R of the turbine 4 and are disposed in a combustor casing 3d having a front end portion connected to a rear end portion of the compressor casing 2b.

  The turbine 4 includes a turbine casing 5 having a front end portion connected to a rear end portion of the combustor casing 3d, the turbine stationary blades 10 and the turbine motions arranged in multiple stages in the turbine casing 5 in the axial direction. Wings 6 are provided. The turbine stationary blades 10 at each stage are arranged in the circumferential direction R at an equal interval, are fixed to the turbine casing 5 side, and extend radially toward the rotor 7 side. Similarly, the turbine rotor blades 6 at each stage are also arranged in the circumferential direction R at equal intervals, are fixed to the rotor 7 side, and extend radially toward the turbine casing 5 side.

  Further, the turbine 4 is provided with a bypass passage (not shown) through which air inside the compressor 2 is supplied from the compressor 2 by bypassing the combustor 3. The air supplied to the turbine 4 through this bypass flow path is circulated inside each of the turbine stationary blade 10 and the turbine rotor blade 6 as a cooling gas which is a cooling fluid. Details will be described later. An exhaust chamber 8 that opens toward the rear side is connected to the rear end of the turbine casing 5. The exhaust chamber 8 is provided with an exhaust diffuser 8a that converts the dynamic pressure of the combustion gas G1 that has passed through the turbine stationary blade 5 and the turbine rotor blade 6 into a static pressure.

  In the gas turbine 1 configured as described above, first, air taken in from the air intake port 2a of the compressor 2 passes through the compressor stationary blades 2c and the compressor rotor blades 2d arranged in multiple stages and is compressed. Compressed air is generated. Next, in the combustor 3, the combustion gas G <b> 1 is generated from the compressed air as described above, and this combustion gas G <b> 1 is guided to the turbine 4. The combustion gas G1 passes through the range where the turbine stationary blades 5 and the turbine rotor blades 6 are arranged as the combustion gas flow path 4a, so that the rotor 7 is rotationally driven, and the gas turbine 1 can output rotational power. it can. The exhaust gas after rotationally driving the rotor 7 is converted into a static pressure by the exhaust diffuser 8a in the exhaust chamber 8, and then released to the atmosphere.

  Next, details of each turbine stationary blade 10 will be described. As shown in FIG. 2, the turbine stationary blade 10 includes a blade body 11 that extends in the blade height direction H corresponding to the turbine radial direction, and an outer side that is provided at both ends of the blade body 11 and supports the blade body 11. A shroud 12 and an inner shroud 13 are provided. The outer shroud 12 and the inner shroud 13 are respectively provided with main body portions 12a and 13a in which cooling blades 14 and 15 are formed on the side opposite to the surface on which the blade main body 11 is attached, and the main body portion 12a, And lids 12b and 13b which are attached to 13a and seal the cooling chambers 14 and 15. The main body portions 12a and 13a of the outer shroud 12 and the inner shroud 13 are formed with a plurality of openings that communicate with the inside of the blade body 11 and supply and discharge the cooling gas G2 into the blade body 11. .

  Further, the lids 12b and 13b of the outer shroud 12 are connected to a bypass passage (not shown) connected to the compressor 2 and supplied with a cooling gas G2, and a first supply port 16 and a second supply port 17 A discharge port 18 for collecting the cooling gas G2 that has cooled the inside of the blade body 11 is provided. The first supply port 16 communicates with the cooling chamber 14 of the outer shroud 12. The second supply port 17 communicates with an impingement cooling channel 11b (see FIG. 1) for impingement cooling inside the blade body 11.

  As shown in FIG. 2, impingement plates 12 c and 13 c for performing impingement cooling are provided in the cooling chambers 14 and 15 of the outer shroud 12 and the inner shroud 13. The impingement plates 12c and 13c are provided so as to partition the cooling chambers 14 and 15 in the blade height direction H, respectively, and a large number of impingement cooling holes 12d and 13d are formed.

  On the other hand, a cooling channel 11b, which will be described later, is formed inside the blade body 11, and a front edge cooling hole 11c, a rear edge cooling hole 11d, a film, and the like communicating with the cooling channel 11b are formed on the surface. Various cooling holes such as the cooling hole 11e are formed. For this reason, the cooling gas G2 supplied from the compressor 2 via a bypass passage (not shown) flows into the blade body 11 from the second supply port 17 and performs impingement cooling, for example, as in the present embodiment. Later, it is discharged from the trailing edge cooling hole 11d to the combustion gas flow path 4a. On the other hand, it flows into the cooling chambers 14 and 15 from the first supply port 16 and is first injected from the impingement cooling holes 12d and 13d to impinge cool the main body portions 12a and 13a of the outer shroud 12. Next, the cooling gas G2 flows into the cooling channel 11b inside the blade body 11 from each opening to cool the blade body 11 from the inside, and further, the leading edge cooling hole 11c, the trailing edge cooling hole 11d, and the film It is discharged from the cooling hole 11e to the combustion gas flow path 4a, and the blade body 11 is further cooled and discharged together with the combustion gas G1. On the other hand, the cooling gas G2 that has not been released from the cooling holes flows into the cooling chambers 14 and 15 of the inner shroud 13 from the cooling channel 11b, and after impingement cooling the inner shroud 13, It is discharged from the outlet 18 of the outer shroud 12 through another cooling channel 11b.

  Next, details of the wing body 11 will be described. As shown in FIGS. 1 and 3, the blade main body 11 of the turbine stationary blade 10 includes an outer frame 20 which is formed in a cylindrical shape along the blade height direction H and forms an outer shell, and is provided inside the outer frame 20. And a support portion 21 supported by the outer frame 20 and an insertion member 22 inserted into the interior with a gap serving as a cooling flow path 11b between the inner peripheral surface of the outer frame 20. The outer frame 20 is formed with the above-described various cooling holes, and a rib 20a extending along the blade height direction H on the inner peripheral surface protrudes toward the insertion member 22 as a protrusion. Yes. A plurality of ribs 20a are formed at intervals along the inner periphery of the outer frame 20, and the amount of protrusion corresponds to the width required for the cooling channel 11b.

  Moreover, the support part 21 is substantially plate-shaped, and is being fixed to the internal peripheral surface so that the inside of the outer frame 20 may be divided into the insertion space 20b in which the insertion member 22 is inserted, respectively. In the present embodiment, as the support portion 21, the first support portion 21 </ b> A spanned between the outer frames 20 at two locations, the front edge side and the rear edge side, from the ventral side to the back side of the wing body 11, and the wing body. 11 between the outer frame 20 and the first support portion 21A from the front edge to the rear edge, and the second support portion 21B spanned between the first support portions 21A. These support portions 21 form six insertion spaces 20b. And the insertion member 22 is inserted in each insertion space 20b. Each insertion member 22 is fixed to the support portion 21 only in one of the blade height direction H both ends 22a and 22b. Which of the two end portions 22a and 22 is fixed to each insertion member 22 corresponds to the direction in which the cooling gas G2 flows through the corresponding cooling flow path 11b. It is fixed at one end 22a on the downstream side of the cooling channel 11b.

  The insertion member 22 is configured in a frame shape having a hollow inside. More specifically, each insertion member 22 is formed by bending and bending a substantially plate-like member along its outer edge according to the shape of the insertion space 20b to be inserted. Particularly in the present embodiment, the insertion member 22 includes a flow path forming portion 23 that faces the outer frame 20, and a side plate portion 24 that is disposed along the first support portion 21A from the side edge of the flow path forming portion 23. And the end plate portion 25 fixed so as to seal the hollow portion surrounded by the flow path forming portion 23 and the side plate portion 24 at the one end portion 22a fixed to the support portion 21. For this reason, each insertion member 22 is a frame-like member that forms an opening in the range facing the second support portion 21B and the other end portion 22b opposite to the one end portion 22a where the end plate portion 25 is provided. It is configured as. And the insertion member 22 forms the welding part 26 between each support part 21 in the edge part of the end plate part 25, and is being fixed to the support part 21. As shown in FIG.

  Here, as shown in FIG. 5, the insertion member 22 has gaps D <b> 20 and D <b> 21 between the support portion 21 and the rib 20 a provided on the outer frame 20 at normal temperature when the gas turbine 1 is not operating. In addition, when the gas turbine 1 is in operation and the combustion gas flow path 4a is in a high-temperature environment, the dimensions are such that it contacts the support portion 21 and the rib 20a provided on the outer frame 20 due to thermal expansion. Is formed. In FIG. 3, the end plate portion 25 of the insertion member 22 is integrated so that the side plate portion 24 and the edge portion coincide with each other, but the edge portion of the end plate portion 25 is formed to form the gap D21. It may be configured to project from the side plate portion 24.

  The blade body 11 of the turbine stationary blade 10 configured as described above can be manufactured as follows. That is, first, the outer frame 20 and the support portion 21 are formed. Specifically, for example, a method of integrally forming by casting is conceivable. Moreover, after forming only the outer frame 20, it is good also as what fixes each support part 21 to an internal peripheral surface by welding, brazing, etc. FIG. On the other hand, the insertion member 22 is formed by, for example, bending and bending a single plate-like member to form the flow path forming portion 23 and the side plate portion 24, and then forming the member that becomes the end plate portion 25 as the flow path forming portion 23. And it can form by fixing to the edge of the side-plate part 24 by welding, brazing, etc. Further, the insertion member 22 may be integrally formed by casting. Then, the insertion members 22 are respectively inserted into the insertion spaces 20b formed by the integrated outer frame 20 and the support portion 21, and welded to the support portion 21 at the edge of the end plate portion 25 of each insertion member 22. By forming the welded portion 26, the blade body 11 having the cooling channel 11b as shown in FIGS. 1 and 3 can be manufactured. Thus, the cooling flow path 11b in the blade body 11 of the turbine stationary blade 10 of the present embodiment can be easily formed simply by inserting the insertion member 22 into the outer frame 20, It can be formed with high accuracy due to the dimensional difference with the insertion member 22.

Next, the effect | action of the turbine stationary blade 10 of this embodiment is demonstrated based on FIG. FIG. 6 is a cross-sectional view of the turbine vane 10 viewed from the side, but is schematically shown for easy understanding of the operation of the turbine vane 10.
As shown in FIG. 6, the cooling gas G <b> 2 supplied from the first supply port 16 to the cooling chamber 14 of the outer shroud 12 is partitioned by the support portion 21 in the blade main body 11 from one side in the blade height direction H. It flows into a part of the inserted insertion space 20b. The inflowing cooling gas G2 flows through the cooling flow passage 11b from one side in the blade height direction to the other side in the blade height direction H, and supports the insertion member 22 between the insertion member 22 and the support portion 21. It circulates also to an internal cavity from the opening of the other end part 22b which is not fixed to the part 21. Here, the insertion member 22 is fixed to the support portion 21 at the one end portion 22a on the downstream side, so that the cooling gas G2 flowing into the internal cavity of the insertion member 22 is restricted from flowing out as it is. Thereby, it is possible to increase the pressure acting between the insertion member 22 and the support portion 21 and the cooling gas G2 in the internal cavity of the insertion member 22, and as a result, between the insertion member 22 and the support portion 21, and The flow rate of the cooling gas G2 flowing into the internal cavity of the insertion member 22 can be reduced, and the cooling gas G2 flowing through the cooling flow path 11b is exposed to the combustion gas G1 flowing through the external combustion gas flow path 4a. Thus, the outer frame 20 that becomes high temperature can be effectively cooled.

  On the other hand, the one end portion 22a of the insertion member 22 is closed by a welded portion 26 in which the end plate portion 25 and the support portion 21 are welded, and therefore between the insertion member 22 and the support portion 21 and the insertion member 22. The cooling gas G2 flowing through the internal cavity joins the cooling flow path 11b through the gap between the support portion 21 and the side plate portion 24. For this reason, the flow rate of the cooling gas G2 becomes larger on the downstream side of the cooling channel 11b than on the upstream side, and the flow rate can be increased to perform cooling more effectively. Then, the cooling gas G <b> 2 flows through the cooling chamber 15 of the inner shroud 13 into another insertion space 20 b partitioned by the support portion 21 inside the blade body 11. The inflowing cooling gas G2 flows through the cooling flow passage 11b and the internal cavity of the insertion member 22, and on one side in the blade height direction H on the downstream side, the cooling gas G2 flows through the internal cavity of the insertion member 22. However, it can join with the cooling gas G2 which distribute | circulates the flow path 11b for cooling, and can cool similarly.

  As described above, in the blade body 11 of the turbine stationary blade 10 of the present embodiment, the cooling gas G2 is circulated through the cooling flow path 11b formed by the outer frame 20, the support portion 21, and the insertion member 22, and the combustion gas The outer frame 20 exposed to G1 can be effectively cooled. Here, the outer frame 20 is a member located in an environment where the outer frame 20 is cooled by the cooling gas G2 but is directly exposed to the combustion gas G1, whereas the insertion member 22 is located at a position inside the cooling channel 11b. It is a member to do. For this reason, the blade body 11 has a high temperature as a whole when the combustion gas G1 flows into the combustion gas flow path 4a and is at a high temperature when the blade body 11 is not operating. 20 and the insertion member 22 have a difference in thermal elongation that occurs during operation with respect to normal temperature. However, as described above, the insertion member 22 is fixed to the support portion 21 only at one end portion 22a in the blade height direction H, thereby supporting the outer frame 20 in a cantilever manner via the support portion 21. It has become a state. Therefore, even if there is a difference in thermal expansion between the outer frame 20 exposed to the combustion gas G1 and the insertion member 22 inside the cooling flow path 11b, the insertion member 22 has the one end portion 22a at the base end. Therefore, the generation of thermal stress can be effectively suppressed. Therefore, in the gas turbine 1 provided with such a turbine vane 10, the turbine vane 10 can be effectively cooled and the generation of thermal stress can be suppressed. It can be operated and higher output can be achieved.

  Further, as described above, in the turbine stationary blade 10 of the present embodiment, the insertion member 22 is a frame-like member, so that the weight of the turbine stationary blade 10 as a whole can be measured and a solid member can be measured. Compared to the above, the generation of thermal stress in the insertion member 22 itself can be suppressed. Moreover, since it can comprise by assembling a board | plate material in frame shape, manufacture is easy and cost reduction can be achieved. In particular, in the present embodiment, in the insertion member 22, the end provided on the flow path forming portion 23 that is a range where the cooling flow path 11 b needs to be formed and the one end portion 22 a that needs to be fixed to the support portion 21. Except for the plate part 25, the range facing the second support part 21B and the other end part 22b are configured to open, thereby reducing weight, reducing thermal stress, and facilitating manufacturing and reducing costs. Can be further planned.

(Second Embodiment)
Next, a second embodiment of the present invention will be described. FIG. 7 shows a second embodiment of the present invention. FIG. 7 is a schematic view similar to FIG. 6 in the first embodiment. Moreover, in this embodiment, the same code | symbol is attached | subjected to the member common to the member used in embodiment mentioned above, and the description is abbreviate | omitted.

  As shown in FIG. 7, in the turbine vane 30 of this embodiment, the basic configuration is the same as that of the first embodiment, but the fixing position of the insertion member 31 inserted into the outer frame 20 and the support portion 21 is the same. Unlike the first embodiment, which is fixed at one end 31a on the downstream side of the cooling channel 11b, the other end 31b on the upstream side is fixed. More specifically, the insertion member 31 includes the flow path forming portion 23, the side plate portion 24, and the end plate portion 32 as in the first embodiment, but the end plate portion 32 is connected to the other end portion 31b. The welded portion 33 is provided and fixed between the edge portion of the end plate portion 32 and the support portion 21.

  In such a turbine stationary blade 30, when the cooling gas G2 flows into the blade body 11 from the cooling chamber 14 of the outer shroud 12, the insertion member 31 and the support portion 21 are fixed upstream of the cooling channel 11b. Thus, the cooling gas G2 is restricted from flowing between the insertion member 31 and the support portion 21 and into the internal cavity of the insertion member 31, and the cooling gas G2 flows into the cooling flow path 11b. Cooling can be effectively performed by G2. Further, even if the cooling gas G2 flows from the cooling channel 11b between the insertion member 31 and the support portion 21 and further into the internal cavity of the insertion member 31, the insertion member 31 and the support portion 21 are downstream. Since it is not fixed, it can be discharged as it is.

(Third embodiment)
Next, a third embodiment of the present invention will be described. FIG. 8 shows a third embodiment of the present invention. FIG. 8 is a schematic view similar to FIG. 6 in the first embodiment. Moreover, in this embodiment, the same code | symbol is attached | subjected to the member common to the member used in embodiment mentioned above, and the description is abbreviate | omitted.

  As shown in FIG. 8, the basic configuration of the turbine stationary blade 40 of this embodiment is the same as that of the first embodiment, but insertion members 41 and 42 are paired in each insertion space 20 b of each blade body 11. And are inserted in order in the blade height direction H. The one insertion member 41 located on the one side in the blade height direction H, that is, on the upstream side of the cooling flow path 11b, is not fixed to the support portion 21 at the one end 41a on the downstream side, and thus on the upstream side. Only the other end 41b is fixed. Further, the other insertion member 42 located on the other side in the blade height direction, that is, on the downstream side of the cooling flow path 11b is fixed to the support portion 21 at one end portion 42a on the downstream side. The other end 42b is not fixed. Each of the insertion members 41 and 42 is formed by the flow path forming portion 23, the side plate portion 24, and the end plate portion 43, and the end plate portion 43 is fixed to the support portion 21 respectively. It is provided at the end and fixed to the support portion 21 by a welded portion 44 provided at the edge of the end plate portion 43. In addition, the insertion members 41 and 42 are fixed to the support portion 21, respectively, and a gap D 40 is formed in the blade height direction H.

  In such a turbine stationary blade 40, one insertion member 41 located upstream of the cooling flow path 11b is fixed to the support portion 21 at the other end 41b on the upstream side, so that the cooling gas G2 is generated. It is possible to effectively cool between the one insertion member 41 and the support portion 21 and between the insertion member 41 and the internal cavity of the insertion member 41 and to effectively flow into the cooling channel 11b. it can. Further, the cooling gas G2 flows from the cooling flow path 11b between the one insertion member 41 and the support portion 21 or into the internal cavity of the one insertion member 41, and further, the other one located downstream from the one end portion 41a. Even if it flows into the insertion member 42 side, the other insertion member 42 and the support portion 21 are fixed on the downstream side, so that they flow out as they are. Thereby, the pressure which acts with the cooling gas G2 between each insertion member 41 and 42 and the support part 21 and the internal cavity of the insertion members 41 and 42 can be raised. Therefore, as a result, the flow rate of the cooling gas G2 flowing between the insertion members 41 and 42 and the support portion 21 and into the internal cavities of the insertion members 41 and 42 can be reduced, and the cooling channel 11b is circulated. The outer frame 20 can be effectively cooled by the cooling gas G2. In addition, the cooling gas G2 flowing between the other insertion member 42 and the support portion 21 and into the internal cavity of the other insertion member 42 joins the cooling flow path 11b on the downstream side, whereby the cooling gas Cooling can be performed more effectively on the downstream side where G2 becomes relatively high temperature and the cooling effect becomes small.

  Moreover, in this embodiment, the insertion members 41 and 42 that make a pair are fixed to the support portion 21 in a cantilevered manner, and a gap D40 is formed between them, so that thermal expansion occurs. However, it is possible to prevent thermal stress from being generated due to contact with each other. In addition, even if this clearance gap D40 becomes small when thermal expansion generate | occur | produces at the time of an operation | movement from a viewpoint which distribute | circulates the cooling gas G2 to the flow path 11b for cooling, it is the one end part 41a of the insertion member 41, and the insertion part 42. It is preferable that the clearance is set so as to ensure a slight gap that does not contact the other end 42b.

(Fourth embodiment)
Next, a fourth embodiment of the present invention will be described. FIG. 9 shows a fourth embodiment of the present invention. FIG. 9 is a schematic view similar to FIG. 6 in the first embodiment. Moreover, in this embodiment, the same code | symbol is attached | subjected to the member common to the member used in embodiment mentioned above, and the description is abbreviate | omitted.

  As shown in FIG. 9, in the turbine vane 50 of this embodiment, the basic configuration is the same as that of the first embodiment, but the insertion member 51 is inserted into each insertion space 20 b formed in the outer frame 20. Accordingly, the width of the cooling flow path 50a formed between the insertion member 51 and the outer frame 20 is different in that it changes in the blade height direction H. More specifically, since the cross-sectional shape of the insertion member 51 is changed in the blade height direction H, the cooling flow path 50a is smaller in the downstream width B2 than in the upstream width B1. Thus, the width gradually changes in the blade height direction H.

  In such a turbine stationary blade 50, it is possible to effectively cool by increasing the flow velocity on the downstream side where the width of the cooling channel 50a is relatively narrow. In general, on the downstream side of the cooling flow path 50a, cooling is performed by the cooling gas G2 that has been cooled on the upstream side and the temperature has increased, and therefore, the cooling efficiency may be reduced. However, it is possible to effectively cool the entire cooling flow path 50a by increasing the flow rate of the cooling gas G2 on the downstream side to increase the cooling efficiency as in the present embodiment.

  In the above description, the insertion member 51 is formed so as to reduce the width of the cooling flow path 50a on the downstream side with respect to the upstream side. However, the present invention is not limited to this. Depending on the usage conditions of the turbine blade, the width may be narrowed at the intermediate portion. The cooling can be optimized by setting the cooling flow path to be narrow at a position where the temperature can be relatively high.

(Fifth embodiment)
Next, a fifth embodiment of the present invention will be described. 10 and 11 show a fifth embodiment of the present invention. In this embodiment, the same members as those used in the above-described embodiment are denoted by the same reference numerals, and the description thereof is omitted.

  As shown in FIGS. 10 and 11, in the turbine vane 60 of this embodiment, the cooling gas G2 flows between the insertion member 22 and the first support portion 21A from the cooling channel 11b. A restricting means 61 for restricting is provided. Specifically, in the present embodiment, the restricting means 61 includes a concave groove 61a formed along the blade height direction H on the surface of the first support portion 21A facing the side plate portion 24 of the insertion member 22. And a labyrinth structure that is formed on the side plate portion 24 of the insertion member 22 along the blade height direction H, and that protrudes toward the first support portion 21A and is inserted into the groove 61a. Yes.

  In such a turbine stationary blade 60, the cooling gas G <b> 2 flowing through the cooling flow path 11 b is generated by inserting the protruding portion 61 b into the groove 61 a along the height direction H in the regulating means 61. It is possible to restrict the inflow between the insertion member 22 and the first support portion 21A. For this reason, the flow volume of the cooling gas G2 which distribute | circulates to the flow path 11b for cooling can be made larger, and it can cool effectively by this.

(Sixth embodiment)
Next, a sixth embodiment of the present invention will be described. 12 to 16 show a sixth embodiment of the present invention. In this embodiment, the same members as those used in the above-described embodiment are denoted by the same reference numerals, and the description thereof is omitted.

  As shown in FIG. 12, the turbine stationary blade 70 of the present embodiment also has a blade main body 71 extending in the blade height direction H corresponding to the turbine radial direction, and the blade main body 71, as in the first embodiment. An outer shroud 12 and an inner shroud 13 that are provided at both ends and support the wing body 71 are provided. In addition, since the structure of the outer shroud 12 and the inner shroud 13 is the same as that of the first embodiment, the description thereof is omitted.

  As shown in FIGS. 13 and 14, the blade main body 71 of the turbine stationary blade 70 is formed in a cylindrical shape along the blade height direction H and is provided inside the outer frame 72. In addition, a support portion 73 supported by the outer frame 72 and an insertion member 74 inserted into the interior with a gap serving as a cooling flow path 71b between the inner peripheral surface of the outer frame 72 are provided. As in the first embodiment, the outer frame 72 has various cooling holes and ribs 72a projecting toward the insertion member 74 as projecting portions.

  The support part 73 is substantially plate-shaped, is spanned between the back side and the abdomen side of the outer frame 72 facing each other, and a plurality of support parts 73 are arranged at intervals from the front edge side to the rear edge side. The outer frame 72 is fixed to the inner peripheral surface so as to divide the inside of the outer frame 72 into a plurality of insertion spaces 72b into which the insertion members 74 are inserted. In the present embodiment, these support portions 73 form four insertion spaces 72b (72b-1 to 72b-1). An insertion member 74 is inserted into each insertion space 72b.

  As shown in FIGS. 12 and 13, in the present embodiment, two first supply ports 16 to which the cooling gas G2 is supplied and two discharge ports 18 for collecting the cooling gas G2 are provided. Of the four insertion spaces 72b, the insertion space 72b-1 on the most leading edge side communicates with one of the first supply ports 16 and can supply the cooling gas G2 from the first supply port 16 to the inside. ing. Further, the insertion space 72b-2 adjacent to the rear edge side of the insertion space 72b-1 communicates with one of the discharge ports 18, and the internal cooling gas G2 can be discharged from the discharge port 18. Further, the insertion space 72b-3 adjacent to the rear edge side of the insertion space 72b-2 communicates with the other of the first supply ports 16, and can supply the cooling gas G2 from the first supply port 16 to the inside. Yes. Further, the insertion space 72b-4 adjacent to the rear edge side of the insertion space 72b-3 communicates with the other of the discharge ports 18, and the internal cooling gas G2 can be discharged from the discharge port 18. That is, as shown in FIGS. 13 to 16, the cooling flow path 71 b formed in each insertion space 72 b is supplied with the cooling gas G <b> 2 from the first supply port 16, and the blade height direction H is changed from one to the other. And a discharge side flow path through which the cooling gas G2 flows from the other side to the other side and is discharged from the discharge port 18 are alternately set in order from the front edge side. .

  In the turbine blade 70 of the present embodiment, the direction in which the outer frame 72 is restrained by the support portion 73 is only one direction between the back surface and the abdominal surface, thereby increasing the degree of freedom of thermal deformation of the outer frame 72, Reduction of thermal stress can be achieved. Further, as in the other embodiments described above, the insertion member 74 is fixed to the support portion 73 on only one side in the blade height direction H and is supported in a cantilevered manner, so that thermal stress is generated in the insertion member 74. Can be effectively suppressed. And also in the turbine blade 70 of the present embodiment, the outer frame 72 can be effectively cooled by causing the cooling gas G2 to flow through the cooling flow path 71b as in the other embodiments. In the present embodiment, the plurality of cooling flow paths 71b are alternately set as a supply-side flow path to which the cooling gas G2 is supplied and a discharge-side flow path from which the cooling gas G2 is discharged. By doing so, the separation distance between the supply-side flow path that is the cooling flow path 71b of the one insertion space 72b and the discharge-side flow path that is the cooling flow path 71b of the other insertion space 72b is shortened. can do. Thereby, the length of the whole flow path of the cooling gas G2 flowing into the discharge side flow path from the supply side flow path via the cooling chamber 15 of the inner shroud 13 and discharged can be minimized. The pressure loss caused by circulating the cooling gas G2 inside the blade 70 can be suppressed. Further, it is possible to regulate the flow in which the cooling gas G2 between the supply side flow paths flows into the discharge side flow path after joining in the cooling chamber 15 of the inner shroud 13, and the cooling chamber can be controlled from one supply side flow path. The so-called cross flow in which the cooling gas G2 flowing into the cooling chamber 15 and flowing into the cooling chamber 15 from the other supply-side flow channel is mixed with the cooling gas G2 flowing into the cooling chamber 15 can be prevented. And the fall of impingement cooling efficiency can be prevented. As described above, by reducing the flow path length and preventing the occurrence of crossflow, it is possible to prevent the impingement cooling efficiency from being lowered while minimizing the pressure loss. For this reason, it is possible to cool the outer frame 72 effectively by circulating the cooling gas G2 through the cooling flow path 71b at a large flow rate, and to perform the impingement cooling effectively in the outer shroud 12 and the inner shroud 13. Can do. Further, in the present embodiment, by alternately supplying the supply-side channels and the discharge-side channels of the plurality of cooling channels 71b, the most leading edge side is a supply-side channel through which the low-temperature cooling gas G2 flows. The leading edge portion that becomes the highest temperature can be effectively cooled.

  As mentioned above, although embodiment of this invention was explained in full detail with reference to drawings, the concrete structure is not restricted to this embodiment, The design change etc. of the range which does not deviate from the summary of this invention are included.

  In the turbine stationary blade of each of the embodiments described above, a plurality of cooling flow paths are provided in the blade body 11 (71), and the cooling gas G2 flows from the outer shroud 12 through any of the cooling flow paths. 13, and the cooling gas G <b> 2 flows from the inner shroud 13 and flows out to the outer shroud 12 through another cooling channel, but is not limited thereto. For example, as shown in FIG. 17, the cooling gas G <b> 2 may be supplied from the outer shroud 12, flow into all the cooling channels 11 b, flow out to the inner shroud 13, and be recovered. Further, as shown in FIG. 18, the cooling gas G2 may be supplied from the inner shroud 13, flow into all the cooling channels 11b, flow out to the outer shroud 12, and be recovered.

  Moreover, although all the insertion members are frame-shaped and have an opening in a part thereof, the present invention is not limited to this. For example, it may be formed in a box shape having no opening, or may be formed of a solid member. Moreover, although the insertion member shall be fixed to a support part in the edge part which becomes the upstream or downstream of a cooling flow path, it is not restricted to this. For example, even if it is fixed to the support portion at the intermediate position in the blade height direction, the same effect can be obtained by adopting a structure that projects from the fixed portion to both sides in the blade height direction. In addition, the insertion member is fixed to the support portion by welding. However, the insertion member is not limited to this, and may be brazed or mechanically coupled with a bolt or the like. Further, although the support portion is provided so as to partition the inside of the outer frame, it is not limited thereto. It suffices to be disposed at least at a position where the insertion member is fixed by being supported by the outer frame.

  Further, although the turbine stationary blade of the above embodiment has been described, the present invention is not limited to this, and is applicable to a turbine blade that is used in a high temperature environment and requires a cooling structure, that is, applicable to a moving blade. is there. Furthermore, the present invention is not limited to the stationary blade and the moving blade of the gas turbine, but can be applied to the stationary blade and the moving blade of the steam turbine.

1 Gas turbine 6 Turbine blade (turbine blade)
10, 30, 40, 50, 60, 70 Turbine stationary blade (turbine blade)
11b, 50a, 71b Cooling flow path 20, 72 Outer frame 21, 73 Support part 22, 31, 41, 42, 51, 74 Insertion member 61 Restricting means H Blade height direction

Claims (13)

An outer frame that is formed in a cylindrical shape along the blade height direction and forms an outer shell;
A support portion provided inside the outer frame and supported by the outer frame;
An insertion member that is inserted inside with a gap serving as a cooling channel between the inner peripheral surface of the outer frame and fixed to the support portion only at either one of both ends in the blade height direction. A turbine blade characterized by comprising: An outer frame that is formed in a cylindrical shape along the blade height direction and forms an outer shell;
A plurality of support portions that are spanned across mutually facing surfaces of the outer frame and are provided so as to define an interior penetrating in the blade height direction and supported by the outer frame;
An insertion member that is inserted inside with a gap serving as a cooling channel between the inner peripheral surface of the outer frame and fixed to the support portion only at either one of both ends in the blade height direction. A turbine blade characterized by comprising: In the turbine blade according to claim 1 or 2,
The turbine blade according to claim 1, wherein the insertion member is configured in a frame shape having a hollow inside. The turbine blade according to claim 3, wherein
The turbine is characterized in that the insertion member has an opening at least a part of a range facing the support part and the other end opposite to one end part fixed to the support part. Wings. In the turbine blade according to any one of claims 1 to 4,
The turbine blade according to claim 1, wherein the insertion member is fixed to the support portion at an end portion on the downstream side of the cooling channel among both end portions in the blade height direction. In the turbine blade according to any one of claims 1 to 4,
The turbine blade according to claim 1, wherein the insertion member is fixed to the support portion at an end portion on the upstream side of the cooling flow path among both ends in the blade height direction. In the turbine blade according to any one of claims 1 to 4,
The insertion members are provided in pairs in the blade height direction, and one of the insertion members on the upstream side of the cooling flow path at both ends of the blade height direction is the end portion on the upstream side. A turbine blade, wherein the turbine blade is fixed to a support portion, and the other of the insertion members on the downstream side of the cooling flow path is fixed to the support portion at an end portion on the downstream side. In the turbine blade according to any one of claims 1 to 7,
The turbine blade according to claim 1, wherein the insertion member is inserted into the outer frame such that the gap serving as the cooling channel changes in the blade height direction. In the turbine blade according to any one of claims 1 to 8,
At least one of the outer frame or the insertion member is provided with a protruding portion that protrudes toward the other,
The insertion member is inserted into the outer frame so that the protrusion and the outer frame or the other of the insertion member have a gap at room temperature and are in contact with each other during operation. Turbine wing. In the turbine blade according to any one of claims 1 to 9,
A turbine blade characterized in that a restricting means for restricting the flow of fluid from the cooling flow path is provided between the insertion member and the support portion. In the turbine blade according to any one of claims 1 to 10,
The blade main body is supplied with cooling gas as the cooling flow path and flows from one side to the other in the blade height direction, and the cooling gas flowing through the supply side flow path flows in. Each having a plurality of discharge-side flow passages that are circulated and discharged from the blade height direction to the other,
The turbine blade according to claim 1, wherein the supply side flow path and the discharge side flow path are alternately arranged.   A gas turbine comprising the turbine blade according to any one of claims 1 to 11 as a stationary blade or a moving blade.   Inside the outer frame, which is formed in a cylindrical shape along the blade height direction and has a support portion attached inside, there is a gap as a cooling channel between the inner frame and the inner peripheral surface of the outer frame. Then, the insertion member is inserted, and only one of both end portions in the direction of the blade height of the insertion member is fixed to the support portion.

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