WO2019102556A1

WO2019102556A1 - Turbine blade and turbine

Info

Publication number: WO2019102556A1
Application number: PCT/JP2017/042061
Authority: WO
Inventors: 慎次谷川; 富永　純一; 麻子猪亦; 奥野　研一; 秀幸前田; 悟関根
Original assignee: 東芝エネルギーシステムズ株式会社
Priority date: 2017-11-22
Filing date: 2017-11-22
Publication date: 2019-05-31

Abstract

Provided are a turbine blade (34) and a turbine, wherein the turbine blade (34) is effectively cooled to increase the efficiency of an electric power generation system. According to an embodiment, the turbine blade (34) has an inlet-side orifice plate (201) in which an inlet-side orifice (K201) is formed, and an outlet-side orifice plate (202) in which an outlet-side orifice (K202) is formed. A cooling medium flows into a cooling passage through the inlet-side orifice (K201) and flows out of the cooling passage through the outlet-side orifice (K202).

Description

Turbine blade and turbine

Embodiments of the present invention relate to turbine blades and turbines.

In order to meet the demand for carbon dioxide reduction, resource saving, etc., high efficiency is being promoted in power generation plants. Therefore, in the power plant, the temperature increase of the working fluid is actively promoted. In order to cope with the increase in temperature of the working fluid, various attempts have been made with respect to a method of cooling turbine blades (stationary blades, blades).

In recent years, a power plant using carbon dioxide as a working fluid of a turbine has been studied. In this power plant, carbon dioxide generated in the combustor is circulated as a working fluid. Specifically, this power plant includes a combustor that burns fuel such as hydrocarbon. Then, the turbine is driven to generate power by introducing carbon dioxide introduced into the combustor together with carbon dioxide and steam generated by combustion into the turbine as a working fluid. Then, the turbine exhaust (carbon dioxide and steam) discharged from the turbine is cooled by a heat exchanger to remove water and form pure carbon dioxide. The carbon dioxide is pressurized by the compressor to become a supercritical fluid. Most of the pressurized carbon dioxide is heated by the heat exchanger described above and circulated to the combustor. Of the pressurized carbon dioxide, an amount corresponding to the carbon dioxide generated in the combustion between the externally supplied fuel and oxygen is recovered and used for other applications.

When carbon dioxide, which is a supercritical fluid as described above, is used as the working fluid, the inlet pressure of the turbine is approximately 20 times that of the conventional gas turbine. Also, the inlet density of the turbine is more than 25 times higher than that of the conventional gas turbine. And, the temperature of the working fluid exceeds 1000 ° C. at the inlet of the turbine, which is equivalent to that of the current gas turbine. Therefore, as in the case of the conventional gas turbine, cooling is performed by supplying a cooling medium extracted from the power generation system at a temperature of about 350 to 550 ° C. to a turbine blade or the like provided as a stationary blade and a moving blade. ing. Cooling is performed by flowing a cooling medium through thin cooling channels (thin pipes, holes, etc.) provided inside the stationary blades and the moving blades.

JP, 2001-317302, A JP, 2015-059486, A International Publication No. 2016/135779

However, in the case where the cooling medium flows in the narrow cooling flow path formed inside the turbine blade and the cooling medium is extracted from the power generation system, the efficiency of the power generation system increases as the supply amount of the cooling medium increases. It can be difficult to improve. In particular, in a power plant using carbon dioxide in a supercritical state as a working fluid, the above problem is likely to occur because the density of the working fluid and the density of the cooling medium are large.

In addition, since it is not easy to adjust the amount of supply of the cooling medium to the cooling passage of the turbine blade and the amount of discharge of the cooling medium from the cooling passage of the turbine blade, the cooling of the turbine blade is made efficient It can be difficult to do.

Therefore, an object of the present invention is to provide a turbine blade and a turbine capable of effectively cooling the turbine blade and improving the efficiency of the power generation system.

The turbine blade of the embodiment has a cooling channel formed therein, and is cooled by flowing a cooling medium through the cooling channel. The turbine blade has an inlet-side orifice plate in which an inlet-side orifice is formed, and an outlet-side orifice plate in which an outlet-side orifice is formed. Here, the cooling medium flows into the cooling flow path through the inlet side orifice, and the cooling medium flows out of the cooling flow path through the outlet side orifice.

FIG. 1 is a system diagram showing a gas turbine installation according to the first embodiment. FIG. 2 is a cross-sectional view showing an essential part of a turbine in the gas turbine equipment according to the first embodiment. FIG. 3 is a perspective view showing a moving blade constituting a turbine stage in the turbine according to the first embodiment. FIG. 4 is a cross-sectional view schematically showing moving blades constituting a turbine stage in the turbine according to the first embodiment. FIG. 5 is a cross-sectional view schematically showing a snubber in the moving blade of the turbine according to the first embodiment. FIG. 6 is a cross-sectional view schematically showing an outlet-side orifice plate installed in a snubber in the blade of the turbine according to the first embodiment. FIG. 7 is a cross-sectional view schematically showing a platform and an implant in the moving blade of the turbine according to the first embodiment. FIG. 8 is a cross-sectional view schematically showing an inlet-side orifice plate installed in an implantation portion in the rotor blade of the turbine according to the first embodiment. FIG. 9 is a cross-sectional view schematically showing a stator blade constituting a turbine stage in the turbine according to the first embodiment. FIG. 10 is a cross-sectional view schematically showing a stator blade constituting a turbine stage in the turbine according to the first embodiment. FIG. 11 is a cross-sectional view schematically showing a stator blade constituting a turbine stage in the turbine according to the first embodiment. FIG. 12 is a cross-sectional view schematically showing an outlet-side orifice plate installed in a snubber in the blade of the turbine according to the second embodiment. FIG. 13 is a cross-sectional view schematically showing an inlet-side orifice plate installed in an implantation portion in a blade of a turbine according to a second embodiment. FIG. 14 is a cross-sectional view schematically showing an outlet-side orifice plate installed in a snubber in the blade of the turbine according to the third embodiment. FIG. 15 is a cross-sectional view schematically showing an inlet-side orifice plate installed in an implantation portion in a blade of a turbine according to a third embodiment. FIG. 16 is a cross-sectional view showing the main parts of a turbine in a gas turbine system according to a fourth embodiment. FIG. 17 is a cross-sectional view schematically showing an inlet-side orifice plate provided on a rotor disk in the turbine according to the second embodiment.

First Embodiment
A gas turbine installation according to a first embodiment will be described with reference to FIG. Here, the case where the turbine 21 is a so-called CO ₂ turbine is illustrated. The turbine 21 may be another gas turbine other than the CO ₂ turbine, or may be a steam turbine.

As shown in FIG. 1, in the gas turbine equipment 10, oxygen and fuel are supplied to the combustor 20, and carbon dioxide circulating in the gas turbine equipment 10 is supplied to the combustor 20 after being heated by the heat exchanger 22. Be done. In the combustor 20, fuel is added with heated carbon dioxide and oxygen and burned to generate carbon dioxide and steam as combustion gas. The flow rate of the fuel and the flow rate of oxygen are adjusted in the combustor 20 so that the stoichiometric mixing ratio (theoretical mixing ratio) can be obtained with the fuel and oxygen completely mixed. As fuel, natural gas, hydrocarbons such as methane, and coal gasification gas are used.

The combustion gas generated by the combustor 20 is introduced into the turbine 21. The combustion gas introduced into the turbine 21 as a working medium performs expansion work in the turbine 21. As a result, the generator 25 connected to the turbine 21 is driven to generate power. The combustion gas discharged from the turbine 21 flows through the heat exchanger 22 and then flows through the other heat exchanger 23. In the heat exchanger 23, the water vapor contained in the combustion gas discharged from the turbine 21 is condensed to become liquid water. The water is discharged to the outside through the pipe 24.

The dry working gas (carbon dioxide) obtained by separating the water vapor in the heat exchanger 23 is pressurized by the compressor 26 and becomes a supercritical fluid. At the outlet of the compressor 26, the pressure of the dry working gas is about 30 MPa.

A portion of the dry working gas boosted by the compressor 26 is heated by the combustion gas discharged from the turbine 21 in the heat exchanger 22 and supplied to the combustor 20. The dry working gas introduced into the combustor 20 is ejected from the upstream side of the combustor 20 to the combustion region (not shown) together with the fuel and oxygen, and after the combustor liner (not shown) is cooled, dilution holes are produced. And so forth to the downstream side of the combustion area.

Further, a part of the dry working gas, which is a supercritical fluid, is introduced into the turbine 21 as a cooling medium via a pipe branched from the middle of the flow passage in the heat exchanger 22. The temperature of the cooling medium is lower than the temperature of the combustion gas introduced to the turbine 21 as a working medium, and 350 ° C. in consideration of the cooling effect on the object to be cooled and the thermal stress generated on the object to be cooled. It is preferable that the temperature be about 550 ° C.

The remainder of the dry working gas boosted by the compressor 26 is discharged to the outside of the system. In the combustor 20, an amount of carbon dioxide corresponding to the carbon dioxide generated by the combustion is discharged. The dry working gas discharged to the outside is recovered by a recovery device. In addition, the dry working gas discharged to the outside is used in, for example, Enhanced Oil Recovery (EOR) used at oil mining sites.

The principal part of the turbine 21 which comprises said gas turbine installation 10 is demonstrated using FIG. In FIG. 2, a part of the turbine stages constituting the turbine 21 is enlarged and shown, the lateral direction corresponds to the axial direction along the rotation axis AX, and the longitudinal direction corresponds to a part in the radial direction.

As shown in FIG. 2, in the turbine 21, a stator vane 31 is provided in a cylindrical casing 30. Although not shown, a plurality of stator blades 31 are disposed along the rotational direction R (circumferential direction) of the turbine rotor 32 on the inner surface of the casing 30, and the plurality of stator blades 31 form a stator blade cascade. Configured.

Further, in the turbine 21, the turbine rotor 32 is accommodated inside the casing 30. A rotor disk 33 is formed on the outer peripheral surface of the turbine rotor 32 so as to protrude outward. A moving blade 34 is provided on the outer peripheral surface of the rotor disk 33. Although not shown, a plurality of moving blades 34 are arranged along the rotational direction R of the turbine rotor 32 on the outer peripheral surface of the rotor disk 33, and a plurality of moving blades 34 constitute a moving blade cascade. There is. The turbine stage is composed of a stationary blade cascade and a moving blade cascade provided on the downstream side (right side in FIG. 2) of the stationary blade cascade, and although not shown, the rotation axis AX of the turbine rotor 32 A plurality of turbine stages are arranged in the axial direction along.

Here, the moving blade 34 is surrounded by the shroud segment 35. The shroud segment 35 is installed to maintain the clearance between the tip portion of the moving blade 34 and the shroud segment 35 properly. The shroud segment 35 is supported by a stationary blade 31 fixed to the casing 30, and a gap 36 intervenes between the shroud segment 35 and the casing 30.

Further, an annular combustion gas passage 37 having a stator blade row and a blade row is formed inside the casing 30. The turbine 21 rotates the turbine rotor 32 in the rotational direction R by the combustion gas flowing through the combustion gas passage 37 as a working fluid to perform expansion work.

The essential parts of the moving blades 34 that constitute the turbine stage in the above-described turbine 21 will be described using FIGS. 3 and 4. FIG. 3 is a perspective view, and FIG. 4 is a cross-sectional view.

As shown in FIGS. 3 and 4, the moving blade 34 has a blade effective portion 40, a snubber 41 provided at one end located on the outer peripheral side (radial outer side) in the blade effective portion 40, and a blade effective portion 40. And a platform 42 provided at the other end located on the inner peripheral side (inside in the radial direction), and an implant 43 provided on the inner peripheral side of the platform 42.

Of the blades 34, the blade effective portion 40 is interposed between the snubber 41 and the platform 42 in the radial direction. Although not shown, a plurality of blade effective portions 40 are disposed in the rotational direction R of the turbine rotor 32, and a space between the plurality of blade effective portions 40 aligned in the rotational direction R functions as the combustion gas passage 37. Do.

The wing effective portion 40 is configured in a wing shape. Specifically, the cross-sectional shape located on the leading edge side (LE) in the wing effective portion 40 is curved. The cross-sectional shape located on the trailing edge side (TE) in the wing effective portion 40 is a tapered shape which becomes thinner toward the tip.

In the inside of the blade effective portion 40, a blade effective portion cooling hole 44 is formed. The blade effective portion cooling holes 44 extend in the radial direction (blade height direction) and function as a cooling flow path through which the cooling medium flows. The blade effective portion cooling holes 44 are formed to have a circular cross section.

Here, the blade effective portion cooling holes 44 include a leading edge side cooling hole 45, a central portion cooling hole 46, and a trailing edge side cooling hole 47. The central portion cooling hole 46 is provided in the central portion of the blade effective portion 40 including the center of the camber line. The front edge side cooling hole 45 is provided in the part located in the front edge side (LE) rather than the center part. The rear edge side cooling hole 47 is provided at a portion located on the rear edge side (TE) than the central portion. In FIG. 4, the front edge side cooling holes 45, the central portion cooling holes 46 and the rear edge side cooling holes 47 are illustrated on the same plane (xz plane) for convenience of illustration. It is provided along the curved surface corresponding to the camber line.

A plurality of each of the front edge side cooling hole 45, the central portion cooling hole 46, and the rear edge side cooling hole 47 is formed from the front edge side (LE) to the rear edge side (TE). Here, the front edge side cooling holes 45, the central portion cooling holes 46, and the rear edge side cooling holes 47 are formed at equal intervals from the front edge side (LE) to the rear edge side (TE). The front edge side cooling hole 45, the central portion cooling hole 46, and the wing portion effective portion 40 according to the thickness of the portion where the leading edge side cooling hole 45, the central portion cooling hole 46, and the trailing edge side cooling hole 47 are formed. The hole diameters of the trailing edge side cooling holes 47 are different. That is, when the cooling hole is formed in a portion where the blade thickness is large, the hole diameter of the cooling hole is large, and when the cooling hole is formed in a portion where the blade thickness is thin, the hole diameter of the cooling hole is small. It has become.

Specifically, three front edge side cooling holes 45 are formed, and three central portion cooling holes 46 are formed. The plurality of front edge side cooling holes 45 and the plurality of central portion cooling holes 46 are parallel to one another and have the same hole diameter. Five trailing edge cooling holes 47 are formed, and the plurality of trailing edge cooling holes 47 are formed so as to be parallel to one another. The hole diameter of the trailing edge side cooling hole 47 is smaller than the hole diameter of the leading edge side cooling hole 45 and the central portion cooling hole 46.

A leading edge side cavity 48 is formed on the leading edge side (LE) inside the wing effective portion 40. The front edge side cavity 48 is located on the outer peripheral side of the blade effective portion 40, and functions as a cooling flow passage through which a cooling medium flows. The front edge side cavity 48 intervenes between the plurality of front edge side cooling holes 45 and the plurality of central portion cooling holes 46. The front edge side cavity 48 receives the coolant from the plurality of front edge side cooling holes 45. Then, the cooling medium which has flowed into and collected at the front edge side cavity 48 flows out from the front edge side cavity 48 to each of the plurality of central portion cooling holes 46.

A trailing edge cavity 49 is formed on the trailing edge side (TE) inside the wing effective portion 40. The trailing edge side cavity 49 is located on the inner peripheral side of the blade effective portion 40, and functions as a cooling flow passage through which the cooling medium flows. The trailing edge side cavity 49 intervenes between the plurality of central portion cooling holes 46 and the plurality of trailing edge side cooling holes 47. The trailing edge side cavity 49 receives the cooling medium from the plurality of central portion cooling holes 46. Then, the cooling medium which has flowed into and collected at the trailing edge side cavity 49 flows out of the trailing edge side cavity 49 to each of the plurality of trailing edge side cooling holes 47.

The details of the snubber 41 that constitutes the moving blade 34 will be described using FIG. 5 together with FIG. 4. 5 shows a cross section of the Z1-Z2 portion shown in FIG. 4, the horizontal direction corresponding to the axial direction along the rotation axis AX, the vertical direction substantially corresponding to the rotation direction R, and perpendicular to the paper surface The direction substantially corresponds to the radial direction.

The snubber 41 is a polygonal flat plate as shown in FIGS. 4 and 5. The snubber 41 is installed to suppress the occurrence of vibration due to the rotation of the moving blade 34. The snubber 41 can suppress the occurrence of vibration due to the contact between the adjacent snubbers 41 in the rotational direction R. The snubber 41 is integrally formed with the wing effective portion 40.

Inside the snubber 41, a snubber cooling hole 50 and a snubber cavity 51 are formed. The snubber cooling hole 50 and the snubber cavity 51 function as a cooling flow path through which the cooling medium flows. The snubber cooling hole 50 is formed in a portion of the snubber 41 located on the central portion and the leading edge side (LE) of the wing effective portion 40. The snubber cooling holes 50 are circular, and a plurality of (five in this case) are arranged in the rotational direction R. The snubber cavity 51 is formed in a portion of the snubber 41 located on the trailing edge side (TE) of the wing effective portion 40.

The plurality of snubber cooling holes 50 are in communication with the snubber cavity 51, and the plurality of trailing edge cooling holes 47 are in communication with the snubber cavity 51. Therefore, in the snubber 41, after the cooling medium flows from the plurality of trailing edge side cooling holes 47 into the snubber cavity 51, the cooling medium flowing into the snubber cavity 51 flows to each of the plurality of snubber cooling holes 50.

At a portion of the snubber cooling hole 50 located on the front edge side (LE) of the blade effective portion 40, an outlet side orifice plate 202, which is an outlet from which the cooling medium flows out from the moving blades 34, is installed.

The details of the outlet orifice plate 202 will be described with further reference to FIGS. 4 and 5 as well as FIG. FIG. 6 schematically shows a cross section of a portion X1-X2 shown in FIG.

The outlet-side orifice plate 202 is a plate-like body as shown in FIG. 4 to FIG. 6, and a plurality of outlet-side orifices K202 are formed. The plurality of outlet orifices K 202 are circular and arranged in the rotational direction R, and are provided to communicate with the plurality of snubber cooling holes 50 respectively.

The diameter of each of the plurality of outlet orifices K202 is smaller than the diameter of each of the plurality of snubber cooling holes. The plurality of outlet orifices K202 are formed to have the same hole diameter.

The details of the platform 42 and the implanting part 43 that constitute the moving blade 34 will be described using FIG. 7 together with FIG. 4. In FIG. 7, a cross section is shown, the horizontal direction corresponds to the rotation direction R, the vertical direction corresponds to the radial direction, and the direction perpendicular to the paper surface corresponds to the axial direction along the rotation axis AX.

The platform 42 has an implantation cavity 53 formed therein, as shown in FIGS. 4 and 7. The implantation cavity 53 functions as a cooling flow path through which the cooling medium flows. Here, the platform 42 is integrally formed with the wing effective portion 40.

As shown in FIGS. 4 and 7, the implanting portion 43 is provided on the platform 42 inward in the radial direction (the lower side in each drawing). The implanting portion 43 is configured to be implanted and fixed to the rotor disk 33. Here, the implantation unit 43 is formed in a Christmas tree shape.

In the implantation section 43, an implantation cooling hole 52 is formed inside. The implantation cooling hole 52 functions as a cooling flow path through which the cooling medium flows. The implant cooling holes 52 extend in the radial direction, and the cross-sectional shape of the implant cooling holes 52 is rectangular. Here, a plurality of implantation cooling holes 52 are provided (see FIG. 4).

The implant cooling holes 52 communicate with the implant cavity 53 at the outer side in the radial direction (the upper side in each figure). The implantation cavity 53 communicates with the front edge side cooling hole 45 at the radially outer side. For this reason, in the platform 42 and the implanting portion 43, after the coolant has flowed into the implanting cavity 53 from each of the plurality of implanting cooling holes 52, the coolant having flowed into the implanting cavity 53 has a plurality of It flows to each of the front edge side cooling holes 45.

A radially inner side (lower side in each drawing) of the implantation cooling hole 52 is an inlet through which the cooling medium flows into the moving blade 34, and in the present embodiment, the inlet side orifice plate 201 is installed.

The details of the inlet-side orifice plate 201 will be described with further reference to FIGS. 4 and 7 as well as FIG. FIG. 8 schematically shows a cross section of the Z3-Z4 portion shown in FIG.

As shown in FIG. 4, FIG. 7 and FIG. 8, the inlet side orifice plate 201 is a plate-like body, and a plurality of inlet side orifices K201 are formed. The plurality of inlet-side orifices K 201 are circular and axially aligned, and are provided in communication with the implantation cooling holes 52.

The hole diameter of each of the plurality of inlet-side orifices K201 is smaller than the hole diameter of each of the plurality of implanted cooling holes 52. The plurality of inlet-side orifices K201 are formed to have the same hole diameter.

The flow of the cooling medium in the moving blade 34 described above will be described. As described above, carbon dioxide, which is a supercritical fluid, is used as the cooling medium.

In the present embodiment, the cooling medium passes through the inlet orifice K201 formed in the inlet orifice plate 201, and then passes to the implant cooling hole 52 whose opening is larger than the inlet orifice K201. It flows in from the flow path formed in the disc 33). That is, the cooling medium flows from the inlet-side orifice K201 whose opening area is sharply reduced to the implantation cooling hole 52 whose opening area is rapidly expanded. Since the opening area of the inlet side orifice K201 is rapidly reduced, pressure loss occurs, the flow rate of the cooling medium increases, and the flow rate of the cooling medium decreases.

Then, the cooling medium having flowed into the implantation cooling holes 52 flows from the inside to the outside in the radial direction. Thereby, the implantation unit 43 is cooled. Then, the cooling medium flows from the implantation cooling hole 52 to the implantation cavity 53. In the implantation cavity 53, the cooling medium flows from the inside to the outside in the radial direction. As a result, the platform 42 is cooled.

Next, the cooling medium flows from the implantation cavity 53 to the front edge cooling hole 45. In the front edge side cooling holes 45, the cooling medium flows from the inside to the outside in the radial direction. Thereby, the leading edge side (LE) of the wing effective portion 40 is cooled. Then, the cooling medium flows from the front edge side cooling hole 45 to the central portion cooling hole 46 via the front edge side cavity 48. In the central portion cooling holes 46, the cooling medium flows from the radially outer side to the inner side. As a result, the central portion of the wing effective portion 40 is cooled. Then, the cooling medium flows from the central portion cooling hole 46 to the trailing edge side cooling hole 47 via the trailing edge side cavity 49. In the trailing edge side cooling holes 47, the cooling medium flows from the inside to the outside in the radial direction. Thereby, the trailing edge side (TE) of the wing effective portion 40 is cooled. As a result, the entire wing effective portion 40 is cooled.

Next, the cooling medium flows from the trailing edge cooling hole 47 to the snubber cavity 51. In the snubber cavity 51, the cooling medium flows from the trailing edge side (TE) to the leading edge side (LE). Thereby, the trailing edge side (TE) of the snubber 41 is cooled. Then, the cooling medium flows from the snubber cavity 51 to the snubber cooling hole 50. In the snubber cooling holes 50, the cooling medium flows in the direction from the trailing edge side (TE) to the leading edge side (LE). As a result, the front edge side (LE) of the snubber 41 is cooled.

Then, the cooling medium is discharged from the snubber cooling hole 50 to the outside of the moving blade 34 through the outlet side orifice K 202 formed in the outlet side orifice plate 202. That is, the cooling medium flows from the snubber cooling hole 50 to the outlet side orifice K 202 whose opening area is sharply reduced, and then flows to the outside of the moving blade 34 whose opening area is rapidly expanded. Since the opening area of the outlet side orifice K 202 is rapidly reduced, pressure loss occurs, the flow rate of the cooling medium increases, and the flow rate of the cooling medium decreases. Therefore, the fluid (main stream combustion gas) flows from the outside of the moving blade 34 back to the outlet side orifice K 202 and is prevented from flowing into the moving blade 34.

As described above, as the cooling flow path through which the cooling medium flows, the implantation cooling hole 52, the implantation cavity 53, the front edge side cooling hole 45, the front edge side cavity 48, and the central portion cooling hole 46 A trailing edge side cavity 49, a trailing edge side cooling hole 47, a snubber cavity 51, and a snubber cooling hole 50 are provided, and each portion is cooled by the cooling medium.

The cooling medium discharged to the outside of the moving blades 34 is mixed with the combustion gas flowing in the combustion gas passage 37 (see FIG. 2), and then rotates the turbine blades together with the combustion gas to cause the turbine to work.

The stator vanes 31 constituting the turbine stage in the above-described turbine 21 will be described with reference to FIGS. 9 to 11. FIG. 9 shows a cross section mainly including the vane 31. FIG. 10 shows a cross section of a portion AA shown in FIG. FIG. 11 shows a cross section of a portion BB shown in FIG.

The vane 31 includes a blade effective portion 140, an outer ring sidewall 150 provided on the outer peripheral side (radial direction outer side) of the blade effective portion 140, and an inner ring provided on the inner peripheral side (radial direction inner side) of the blade effective portion 140. A side wall 160 is provided. In the vane 31, each of the blade effective portion 140, the outer ring side wall 150, and the inner ring side wall 160 is integrally formed.

Although not shown, a plurality of blade effective portions 140 are disposed in the rotational direction R of the turbine rotor 32, and a space between the plurality of blade effective portions 140 aligned in the rotational direction R functions as a combustion gas passage. .

The wing effective portion 140 is configured in a wing shape. Specifically, the surface located on the leading edge side (LE) of the wing effective portion 140 is curved. The surface located on the trailing edge side (TE) of the wing effective portion 140 has a tapered shape which becomes thinner toward the tip.

A leading edge side hollow portion 141 is formed on the leading edge side (LE) of the wing effective portion 140. The leading edge side hollow portion 141 penetrates in the radial direction (the wing height direction) inside the wing effective portion 140. The front edge side hollow portion 141 is formed so that the shape of the cross section along the rotational direction R is the same as the external shape of the portion located on the front edge side (LE) in the wing effective portion 140.

A central through hole 142 is formed at a central portion of the wing effective portion 140 located between the leading edge side (LE) and the trailing edge side (TE). The central through hole 142 penetrates in the radial direction (the wing height direction) in the wing effective portion 140. Here, the central through hole 142 is formed such that the shape of the cross section along the rotational direction R is semi-elliptical.

Similarly, a trailing edge through hole 143 is formed on the trailing edge side (TE) of the wing effective portion 140. The trailing edge through hole 143 penetrates in the blade effective portion 140 in the radial direction (the blade height direction). Here, the rear edge side through hole 143 is formed so that the shape of the cross section along the rotation direction R is circular. On the trailing edge side (TE) of the blade effective portion 140, a plurality of trailing edge through holes 143 are formed. The plurality of rear edge through holes 143 are arranged at equal intervals between the front edge side (LE) and the rear edge side (TE). Here, since the blade thickness decreases from the leading edge side (LE) to the trailing edge side (TE), the plurality of trailing edge through holes 143 extend from the leading edge side (LE) to the trailing edge side (TE) Along with it, the diameter is getting smaller.

Although the front edge side hollow portion 141, the center portion through hole 142, and the rear edge side through hole 143 are illustrated in the same plane (xz plane) in FIG. 9 for convenience of illustration, from FIG. 10 and FIG. As can be seen, it is provided along the curved surface corresponding to the camber line of the blade effective portion 140.

The outer ring side wall 150 is a polygonal flat plate, and an opening groove 151 is formed on the outer peripheral side in the radial direction. At the bottom of the opening groove 151, on the front edge side (LE), a front edge side outer ring gap portion 151a is formed. The front edge side outer ring gap portion 151 a is formed in the same cross-sectional shape as the front edge side hollow portion 141 of the wing effective portion 140, and is in communication with the front edge side hollow portion 141. At the same time, at the bottom of the opening groove 151, a central outer ring gap 151b is formed at the central portion. The central outer ring gap 151 b is formed in the same cross-sectional shape as the central through hole 142 of the wing effective portion 140, and communicates with the central through hole 142.

The outer ring side wall 150 is provided with a flat plate 152. The flat plate 152 faces the portion where the trailing edge through hole 143 of the wing effective portion 140 is formed. Between the flat plate 152 of the outer ring side wall 150 and the rear edge through hole 143 of the wing effective portion 140, a rear edge outer ring gap 153 is interposed.

An engagement protrusion 157 is formed on the radially outer portion (upper portion in FIG. 9) of the outer ring side wall 150. The engagement protrusion 157 axially projects, and the stator vane 31 is fixed by being engaged with an engagement groove formed in the casing 30 (see FIG. 2). As a result, the opening groove 151 of the outer ring side wall 150 is covered with the casing 30 and is closed (see FIG. 2).

Although not shown, the opening groove 151 of the outer ring side wall 150 communicates with the supply passage of the cooling medium provided in the casing 30, and the cooling medium is introduced into the opening groove 151 from the supply passage. .

The inner ring side wall 160 is, like the outer ring side wall 150, a polygonal flat plate. A front edge side inner ring gap portion 161 is formed on the front edge side (LE) of the inner ring side wall 160. The front edge side inner ring gap portion 161 has the same cross-sectional shape as the front edge side hollow portion 141 of the wing effective portion 140, and communicates with the front edge side hollow portion 141. At the same time, on the rear edge side (TE) of the inner ring side wall 160, a rear edge side inner ring gap portion 162 is formed. The trailing edge side inner ring air gap portion 162 is interposed between the central portion through hole 142 of the wing effective portion 140 and the trailing edge side through hole 143 of the wing effective portion 140 and the flat plate 163, and the central portion through hole 142 and the rear portion It communicates with the edge side through hole 143.

In addition to the above, the vane 31 includes an insert member 170. The insert member 170 includes a plate-like portion 171 and a cylinder portion 175, and is inserted into the front edge side (LE) of the stationary blade 31.

The plate-like portion 171 of the insert member 170 is disposed at the bottom of the opening groove 151 formed in the outer ring side wall 150. Here, the plate-like portion 171 is installed at the bottom of the opening groove 151 so as to cover the front edge side outer ring gap portion 151a and the central outer ring gap portion 151b from the outer peripheral side. The plate-like portion 171 is formed with a plate-like portion front edge side opening 172 and a plate-like portion central opening 173. The plate portion front edge side opening 172 is in communication with the front edge side outer ring gap portion 151 a of the outer ring side wall 150. On the other hand, the plate-like-part central opening 173 communicates with the central-portion outer-ring gap 151 b of the outer-ring sidewall 150.

The cylindrical portion 175 of the insert member 170 is a cylindrical body in which the outer peripheral side is open and the inner peripheral side is closed. An end portion of the cylindrical portion 175 on the outer peripheral side is fixed to the plate-like portion 171. The cylindrical portion 175 is inserted into the space on the front edge side (LE) configured such that the front edge side outer ring gap portion 151a, the front edge side hollow portion 141, and the front edge side inner ring gap portion 161 communicate with each other in the vane 31 There is.

An air gap is interposed between the outer side surface 175 a of the cylindrical portion 175 and the inner wall 141 a of the portion of the wing effective portion 140 located on the front edge side (LE). Further, a plurality of jet holes 176 are formed in the outer side surface 175 a of the cylindrical portion 175. The gap between the outer side surface 175 a of the cylindrical portion 175 and the inner wall 141 a of the wing effective portion 140 is a fixed distance. Thus, when the cooling medium jetted from the jet holes 176 collides with the inner wall 141 a of the wing effective portion 140 and cools the wing effective portion 140, the entire wing effective portion 140 can be uniformly cooled. As a coolant, a working fluid (carbon dioxide) of a supercritical fluid is used.

A front edge side outer ring cooling hole 155 is formed in a portion located on the front edge side (LE) on the inner peripheral side of the outer ring side wall 150. The front edge side outer ring cooling hole 155 is formed such that the front edge side outer ring air gap portion 151 a and the outside of the outer ring side wall 150 communicate with each other. A plurality of front edge side outer ring cooling holes 155 are formed.

A rear edge side outer ring cooling hole 156 is formed in a portion located on the rear edge side (TE) on the inner peripheral side of the outer ring side wall 150. The rear edge side outer ring cooling hole 156 is formed so that the rear edge side outer ring gap portion 153 and the outside of the outer ring side wall 150 communicate with each other. A plurality of trailing edge side outer ring cooling holes 156 are formed.

A front edge side inner ring cooling hole 165 is formed in a portion located on the front edge side (LE) on the outer peripheral side of the inner ring side wall 160. The front edge side inner ring cooling hole 165 is formed such that the front edge side inner ring gap portion 161 and the outside of the inner ring side wall 160 communicate with each other. A plurality of front edge side inner ring cooling holes 165 are formed.

A rear edge side inner ring cooling hole 166 is formed in a portion located on the rear edge side (TE) on the outer peripheral side of the inner ring side wall 160. The rear edge side inner ring cooling hole 166 is formed such that the rear edge side inner ring gap portion 162 communicates with the outside of the inner ring side wall 160. A plurality of trailing edge side inner ring cooling holes 166 are formed.

In the present embodiment, the inlet-side orifice plate 301 is installed on the plate-like portion 171 of the insert member 170.

The inlet-side orifice plate 301 is a plate, and two inlet-side orifices K301 are formed. The two inlet orifices K301 are circular holes. The inlet-side orifice plate 301 is provided such that one inlet-side orifice K301 communicates with the plate-like-part front edge-side opening 172 and one inlet-side orifice K301 communicates with the plate-like-portion central opening 173.

The hole diameter of one inlet side orifice K301 is smaller than the hole diameter of the plate-like portion front edge side opening 172. Similarly, the hole diameter of the other inlet side orifice K301 is smaller than the hole diameter of the plate-like portion central opening 173. In the present embodiment, each of the two inlet orifices K201 is formed to have the same hole diameter. That is, each of the two inlet side orifices K201 is formed to have the same opening area.

Besides, in the present embodiment, the outlet side orifice plate 302 is installed on each of the outer ring side wall 150 and the inner ring side wall 160.

The outlet orifice plate 302 is a plate-like body, and an outlet orifice K302 is formed. The outlet side orifice K302 is a circular hole, and a plurality of outlet side orifice plates 302 are installed. Each of the plurality of outlet orifice plates 302 communicates with the front outer ring cooling hole 155, the rear outer ring cooling hole 156, the front inner ring cooling hole 165, and the rear inner ring cooling hole 166 with the outlet orifice K302. It is provided as.

The hole diameter of each of the plurality of outlet orifices K302 is smaller than the hole diameter of the front outer ring cooling hole 155, the rear outer ring cooling hole 156, the front inner ring cooling hole 165, and the rear inner ring cooling hole 166. In the present embodiment, the plurality of outlet orifices K 302 are formed to have the same hole diameter. That is, the plurality of outlet orifices K302 are formed to have the same opening area.

The flow of the cooling medium in the above-described vane 31 will be described.

In the stator vanes 31, the cooling medium is first introduced into the opening groove 151 from a cooling medium supply passage (not shown) formed in the casing 30.

The cooling medium introduced into the opening groove 151 flows into the plate portion front edge side opening 172 via the one inlet side orifice K301 formed in the inlet side orifice plate 301 and is formed in the inlet side orifice plate 301. It flows into the plate-like part central opening 173 via the other inlet side orifice K301. Since the opening area of the inlet-side orifice K301 is rapidly reduced, a pressure loss occurs, the flow rate of the cooling medium increases, and the flow rate of the cooling medium decreases.

The cooling medium that has flowed into the plate-like portion leading edge side opening 172 cools a portion of the inside of the vane 31 located on the leading edge side (LE).

Specifically, the cooling medium flows into the inside of the cylindrical portion 175 installed in the portion located on the front edge side (LE) of the inside of the vane 31 and proceeds from the outer peripheral side to the inner peripheral side in the radial direction. Flow. Then, the cooling medium is jetted from the jet holes 176 formed in the cylindrical portion 175 to the outside of the cylindrical portion 175. The cooling medium jetted from the jet hole 176 passes through the front edge side hollow portion 141 interposed between the outer peripheral surface of the cylindrical portion 175 and the inner wall 141a of the portion located on the front edge side (LE) in the wing effective portion 140. , Collide with the inner wall 141 a of the wing effective portion 140. The collision of the cooling medium with the inner wall 141 a of the blade effective portion 140 efficiently cools the portion of the blade effective portion 140 located on the leading edge side (LE).

Then, part of the cooling medium that has collided with the inner wall 141 a of the wing effective portion 140 flows through the front outer ring cooling hole 155 to cool a portion of the outer ring side wall 150 located on the front edge side (LE). Thereafter, the cooling medium having flowed through the front outer ring cooling hole 155 is discharged to the outside of the vane 31 via the outlet orifice K 302 formed in the outlet orifice plate 302.

Similarly, the remaining portion of the cooling medium that has collided with the inner wall 141 a of the wing effective portion 140 flows through the leading edge side inner ring cooling hole 165 to cool a portion of the inner ring side wall 160 located on the leading edge side (LE). Thereafter, the cooling medium having flowed through the front edge side inner ring cooling hole 165 is discharged to the outside of the vane 31 via the outlet side orifice K 302 formed in the outlet side orifice plate 302.

On the other hand, the cooling medium having flowed into the plate-like portion central opening 173 cools a portion of the inside of the vane 31 located on the rear edge side (TE).

Specifically, the cooling medium having flowed into the plate-like portion central opening 173 sequentially flows through the central outer ring gap 151 b and the central through hole 142. The cooling medium flows from the outer peripheral side to the inner peripheral side in the radial direction to cool the inner wall of the central through hole 142 and then flows into the rear edge inner ring gap portion 162.

Then, part of the cooling medium flowing into the rear edge side inner ring gap portion 162 flows into the rear edge side through hole 143 from the rear edge side inner ring gap portion 162. The cooling medium flows from the inner side to the outer side in the radial direction to cool the inner wall of the rear edge side through hole 143, and then flows into the rear edge side outer ring gap portion 153. Then, the cooling medium cools the outer wheel side wall 150 by flowing from the rear edge side outer ring gap portion 153 through the rear edge side outer ring cooling hole 156. Thereafter, the cooling medium having flowed through the trailing outer ring cooling hole 156 is discharged to the outside of the vane 31 via the outlet orifice K 302 formed in the outlet orifice plate 302.

In addition to this, the remaining part of the cooling medium that has flowed into the trailing edge side inner ring gap portion 162 cools the inner ring side wall 160 by flowing through the trailing edge side inner ring cooling hole 166. Thereafter, the cooling medium having flowed through the trailing edge inner ring cooling hole 166 is discharged to the outside of the vane 31 via the outlet orifice K 302 formed in the outlet orifice plate 302.

Since the opening area of the outlet-side orifice K 302 is rapidly reduced, a pressure loss occurs, the flow rate of the cooling medium increases, and the flow rate of the cooling medium decreases. Therefore, the fluid (main stream combustion gas) from the outside of the vane 31 flows back to the outlet side orifice K 302 and is prevented from flowing into the inside of the vane 31.

As described above, the plate-like portion front edge side opening 172, the plate-like portion central opening 173, the front edge side hollow portion 141, the front edge side outer ring cooling hole 155, as a cooling flow passage through which the cooling medium flows Front edge side inner ring cooling hole 165, center outer ring gap portion 151b, center portion through hole 142, rear edge side inner ring gap portion 162, rear edge side through hole 143, rear edge side outer ring gap portion 153, rear edge outer ring cooling hole 156, and rear An edge side inner ring cooling hole 166 is provided, and each part is cooled by the cooling medium.

The cooling medium discharged to the outside from the front outer ring cooling hole 155 and the front inner ring cooling hole 165 is mixed with the combustion gas flowing through the combustion gas passage 37 (see FIG. 2). Similarly, the cooling medium discharged to the outside from the trailing outer ring cooling hole 156 and the trailing inner ring cooling hole 166 is mixed with the combustion gas flowing through the combustion gas passage 37.

As described above, in the turbine 21 of the present embodiment, the turbine blades that are the stationary blades 31 and the moving blades 34 are configured to be cooled by the flow of the cooling medium in the cooling flow path. Here, the turbine blade is cooled by the cooling medium flowing into the cooling flow passage inside the turbine blade via the inlet side orifices K201 and K301 formed in the inlet

side orifice plate

201 and 301. Thereafter, in the turbine blade, the cooling medium flows out through the outlet orifices K202 and K302 formed on the

outlet orifice plates

202 and 302, respectively.

For this reason, in the present embodiment, the supply amount of the cooling medium supplied to the cooling flow passage formed inside the turbine blade is easily adjusted by the inlet side orifices K201 and K301 formed on the inlet

side orifice plate

201 and 301. can do. Further, in the present embodiment, the discharge amount from which the cooling medium flows out from the cooling flow path formed inside the turbine blade is easily adjusted by the outlet side orifices K202 and K302 formed on the outlet

side orifice plates

202 and 302. be able to.

Therefore, in this embodiment, it is possible to cool the turbine blade effectively, and the efficiency of the power generation system can be improved.

Further, in the present embodiment, the inlet

side orifice plates

201 and 301 in which the inlet side orifices K201 and K301 are formed, and the outlet

side orifice plates

202 and 302 in which the outlet side orifices K202 and K302 are formed are different from the turbine blades. Because of the body, the cooling efficiency of the turbine blade can be easily improved without redesigning the internal structure of the turbine blade. Specifically, a plurality of inlet-

side orifice plates

201 and 301 having different hole diameters of the inlet-side orifices K201 and K301 and a plurality of outlet-

side orifice plates

202 and 302 having different hole diameters of the outlet-side orifices K202 and K302 are prepared. Then, when the turbine 21 is actually operated, if the cooling is excessive, the

inlet orifice plates

201 and 301 with the smaller aperture diameters of the inlet orifices K201 and K301 and the aperture diameters of the outlet orifices K202 and K302 are smaller. At least one of the

outlet orifice plates

202 and 302 is replaced. On the other hand, when the turbine 21 is actually operated, if the cooling is insufficient, the

inlet orifice plates

201 and 301 having a large hole diameter of the inlet orifices K201 and K301 and the outlet orifices K202 and K302. It is replaced with at least one of the outlet

side orifice plates

202 and 302 having a large pore size. As a result, the improvement of the cooling efficiency of the turbine blade and the improvement of the efficiency of the power generation system can be realized.

Furthermore, in the present embodiment, the outlet side orifices K202 and K302 are provided at the outlet of the cooling flow passage formed inside the turbine blade, and the area of the hole is smaller than the inside of the turbine blade communicating with this. As a result, it is possible to prevent high temperature fluid exceeding 1000.degree. C. from entering the turbine blade from the outside to the inside. As a result, burnout can be prevented from occurring inside the turbine blade.

Although the above embodiment has described the case where the

inlet orifice plates

201 and 301 and the

outlet orifice plates

202 and 302 are installed on both the stator vanes 31 and the rotor blades 34, the invention is not limited thereto. If necessary, the inlet

side orifice plate

201, 301 and the outlet

side orifice plate

202, 302 may be installed on any one of the stator vanes 31 and the rotor blades 34.

Second Embodiment
The details of the outlet-side orifice plate 202 constituting the moving blade 34 in the second embodiment will be described with reference to FIG. 12, similarly to FIG. 6, the cross section of the X1-X2 part shown in FIG. 4 is schematically shown.

As shown in FIG. 12, the outlet-side orifice plate 202 is formed such that a plurality of outlet-side orifices K 202 are aligned in the rotational direction R, as in the case of the first embodiment. However, in the present embodiment, the hole diameters of the plurality of outlet orifices K 202 are not the same but different. Here, the plurality of outlet-side orifices K202 are formed such that the hole diameter decreases in the direction of rotation R from the front side to the rear side. That is, the outlet orifice plate 202 is configured to include a plurality of outlet orifices K 202 having different opening areas.

The detail of the inlet-side orifice plate 201 which comprises the moving blade 34 in this embodiment is demonstrated using FIG. 13, similarly to FIG. 8, a cross section of the Z3-Z4 portion shown in FIG. 4 is schematically shown.

As shown in FIG. 13, the inlet-side orifice plate 201 is formed such that a plurality of inlet-side orifices K201 are axially aligned, as in the first embodiment. However, in the present embodiment, the respective hole diameters of the plurality of inlet-side orifices K201 are not the same but different. Here, the plurality of inlet-side orifices K201 are formed such that the hole diameter decreases in the axial direction from the leading edge side (LE) to the trailing edge side (TE). That is, the inlet-side orifice plate 201 is configured to include a plurality of inlet-side orifices K 201 having different opening areas, and the plurality of inlet-side orifices K 201 go from the leading edge side (LE) to the trailing edge side (TE) Thus, the opening area is reduced.

As described above, in the present embodiment, the opening areas of the plurality of outlet orifices K 202 are different, and the opening areas of the plurality of inlet orifices K 201 are also different. The opening areas of the plurality of outlet orifices K202 and the plurality of inlet orifices K201 are appropriately set in accordance with the flow rate of the cooling medium. The inlet-side orifice plate 201 is configured to supply the cooling medium through the inlet-side orifice K 201 having a large opening area at a portion of the rotor blade 34 that needs to supply a large amount of the cooling medium. As a result, the improvement of the cooling efficiency of the turbine blade and the improvement of the efficiency of the power generation system can be further realized.

During operation of the turbine 21, the moving blades 34 generally have a temperature that tends to be higher on the leading edge side (LE) than on the trailing edge side (TE). For this reason, as described above, in the plurality of inlet side orifices K201, the opening area is larger than the inlet side orifice K201 where the inlet side orifice K201 located on the front edge side (LE) is located on the rear edge side (TE) Thus, it is preferable to configure a plurality of inlet-side orifices K201. As a result, cooling can be effectively performed on the portion of the leading edge side (LE) where the temperature of the moving blade 34 is high.

Although the above embodiment has been described with respect to the inlet side orifice plate 201 and the outlet side orifice plate 202 installed on the moving blade 34, the invention is not limited thereto. A similar configuration may be employed for the inlet-side orifice plate 301 and the outlet-side orifice plate 302 installed on the stator vanes 31 as needed.

Third Embodiment
The details of the outlet-side orifice plate 202 constituting the moving blade 31 according to the third embodiment will be described with reference to FIG. 14, similarly to FIG. 6, the cross section of the X1-X2 portion shown in FIG. 4 is schematically shown.

In the present embodiment, as shown in FIG. 14, the outlet-side orifice plate 202 includes a first outlet-side orifice plate member 202a and a second outlet-side orifice plate member 202b, unlike the first embodiment. . Each of the first outlet-side orifice plate member 202a and the second outlet-side orifice plate member 202b is a rectangular parallelepiped plate-like body, and is arranged to be aligned in the radial direction. A slit-like outlet orifice K 202 extending in the rotational direction R is interposed between the first outlet orifice plate member 202 a and the second outlet orifice plate member 202 b.
The detail of the inlet-side orifice plate 201 which comprises the moving blade 31 which concerns on 3rd Embodiment is demonstrated using FIG. In FIG. 15, similarly to FIG. 8, a cross section of the Z3-Z4 portion shown in FIG. 4 is schematically shown.

In the present embodiment, as shown in FIG. 15, the inlet-side orifice plate 201 includes a first inlet-side orifice plate member 201a and a second inlet-side orifice plate member 201b, unlike the case of the first embodiment. . The first inlet-side orifice plate member 201 a and the second inlet-side orifice plate member 201 b are plate-like members having a rectangular parallelepiped shape, and are arranged in the rotational direction R. Between the first inlet side orifice plate member 201a and the second inlet side orifice plate member 201b, a slit-like inlet side orifice K201 extending in the axial direction is interposed.

As described above, in the present embodiment, in the inlet-side orifice plate 201, the first inlet-side orifice plate member 201a and the second inlet-side orifice plate member 201b are aligned via the inlet-side orifice K201. The inlet-side orifice K201 is a slit-like hole. In the inlet-side orifice plate 201 of this embodiment, the distance between the first inlet-side orifice plate member 201a and the second inlet-side orifice plate member 201b can be easily changed. The width of the can be easily adjusted. Further, in the present embodiment, in the outlet side orifice plate 202, the first outlet side orifice plate member 202a and the second outlet side orifice plate member 202b are arranged via the outlet side orifice K202. The outlet side orifice K202 is a slit-like hole. In the outlet-side orifice plate 202 of the present embodiment, the distance between the first outlet-side orifice plate member 202a and the second outlet-side orifice plate member 202b can be easily changed. The width of the can be easily adjusted.

For this reason, in the present embodiment, it is easy to adjust the flow rate of the cooling medium. As a result, the improvement of the cooling efficiency of the turbine blade and the improvement of the efficiency of the power generation system can be further realized.

Fourth Embodiment
The essential parts of the turbine 21 according to the fourth embodiment will be described with reference to FIG. In FIG. 16, a part of the turbine stage is shown enlarged, and the lateral direction corresponds to the axial direction along the rotation axis AX, and the longitudinal direction corresponds to a part in the radial direction.

As shown in FIG. 16, in the turbine 21 of the present embodiment, the inlet side orifice plate 201 d is installed on the side surface of the rotor disk 33 formed on the outer peripheral surface of the turbine rotor 32 located on the rear edge side (TE). . Except for this point, the present embodiment is configured in the same manner as the case of the first embodiment, and thus the description will be appropriately omitted.

In the present embodiment, the cooling medium flows from the inlet-side orifice K 201 d of the inlet-side orifice plate 201 d installed in the rotor disk 33 into the flow path P 33 formed in the rotor disk 33. Thereafter, as in the case of the first embodiment, the cooling medium flows into the cooling passage P34 formed inside the moving blade 34, and the moving blade 34 is cooled (the cooling passage P34 in FIG. 16). Although it is simplified and illustrated, it corresponds to the blade effective portion cooling hole 44, the snubber cooling hole 50, the implantation cooling hole 52 and the like shown in FIG. 4).

Details of the inlet-side orifice plate 201d according to the present embodiment will be described with reference to FIG. In FIG. 17, the direction orthogonal to the paper surface corresponds to the axial direction (FIG. 17 is a side view but hatched).

As shown in FIG. 17, the inlet-side orifice plate 201d is a ring-shaped plate-like body, and a plurality of inlet-side orifices K201d are formed. The plurality of inlet-side orifices K 201 d are circular holes, and are formed to be spaced apart along the rotational direction R.

The hole diameter of the plurality of inlet-side orifices K 201 d is smaller than the hole diameter of the flow path P 33 formed in the rotor disk 33. In the present embodiment, the plurality of inlet-side orifices K 201 d are formed to have the same hole diameter.

As described above, in the turbine 21 of the present embodiment, the turbine blade as the moving blade 34 has the cooling medium provided inside the turbine blade via the inlet-side orifice K 201 d formed in the inlet-side orifice plate 201 d. It is cooled by flowing into the cooling channel P34. For this reason, in the present embodiment, as in the case of the first embodiment, an inlet formed in the inlet-side orifice plate 201d for supplying a cooling medium to the cooling flow passage P34 formed inside the turbine blade. It can be easily adjusted by the side orifice K201d. Therefore, in this embodiment, it is possible to cool the turbine blade effectively, and the efficiency of the power generation system can be improved.

Further, in the present embodiment, the inlet side orifice plate 201 d is installed on the rotor disk 33. Therefore, it is not necessary to attach the inlet-side orifice plate 201d to the moving blade 34 after the moving blade 34 is taken out of the rotor disk 33 as in the first embodiment. As a result, since the flow rate of the cooling medium can be easily adjusted, it is possible to easily realize the improvement of the cooling efficiency of the turbine blade and the improvement of the efficiency of the power generation system.

While certain embodiments have been described, these embodiments have been presented by way of example only, and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other forms, and various omissions, substitutions, and modifications can be made without departing from the scope of the invention. These embodiments and modifications thereof are included in the scope and the gist of the invention, and are included in the invention described in the claims and the equivalents thereof.

DESCRIPTION OF SYMBOLS 10 ... Gas turbine installation, 20 ... Combustor, 21 ... Turbine, 22 ... Heat exchanger, 23 ... Heat exchanger, 24 ... Piping, 25 ... Generator, 26 ... Compressor, 30 ... Casing, 31 ... Stator vane, 32: turbine rotor, 33: rotor disk, 34: moving blade, 35: shroud segment, 36: air gap portion, 37: combustion gas passage, 40: blade effective portion, 41: snubber, 42: platform, 43: implantation portion , 44: wing effective part cooling hole, 45: leading edge side cooling hole, 46: central part cooling hole, 47: trailing edge side cooling hole, 48: leading edge side cavity, 49: trailing edge side cavity, 50: snubber cooling hole, 51 ... Snubber cavity, 52: Implantation cooling hole, 53: Implantation cavity, 140: Wing effective part, 141: Front edge side hollow part, 141a: Inner wall, 142: Central part through hole, 143: Rear edge side through hole, 15 ··· Outer ring side wall, 151 · · · Opening groove, 151a · · · front edge side outer ring gap portion, 151b · · · central portion outer ring gap portion, 152 · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · Cooling hole 157: Engaging projection portion 160: Inner ring side wall 161: Front edge side inner ring gap portion 162: Rear edge side inner ring gap portion 163: Flat plate 165: Front edge side inner ring cooling hole 166: Rear edge side inner ring cooling hole 170: Insert member 171: plate-like portion 172: plate-like portion front edge side opening 173: plate-like portion central opening 175: cylindrical portion 175a: outer surface 176: jet hole 201: inlet side orifice Plate, 201a: first inlet side orifice plate member, 201b: second inlet side orifice plate member, 201d: inlet side orifice plate, 202: outlet side orifice plate 202a: first outlet side orifice plate member 202b: second outlet side orifice plate member 301: inlet side orifice plate 302: outlet side orifice plate AX: rotation shaft K201: inlet side orifice K201d: Inlet side orifice, K202: outlet side orifice, K301: inlet side orifice, K302: outlet side orifice, LE: leading edge side, P33: flow path, P34: cooling flow path, R: rotation direction, TE: trailing edge side.

Claims

A cooling blade is formed inside, and a turbine blade cooled by flowing a cooling medium in the cooling flow passage,
An inlet orifice plate formed with an inlet orifice for supplying a cooling medium to the cooling passage;
And an outlet orifice plate having an outlet orifice for discharging the cooling medium after cooling the turbine blade from the cooling passage.
Turbine blade.
The inlet side orifice plate is formed with a plurality of the inlet side orifices,
The plurality of inlet side orifices include inlet side orifices having different opening areas,
The turbine blade according to claim 1.
The inlet-side orifice plate is formed such that the plurality of inlet-side orifices line up from the leading edge side to the trailing edge side in the turbine blade,
The plurality of inlet side orifices have a smaller opening area from the leading edge side to the trailing edge side,
The turbine blade according to claim 2.
The outlet side orifice plate is formed with a plurality of the outlet side orifices,
The plurality of outlet orifices include outlet orifices having different opening areas,
The turbine blade according to any one of claims 1 to 3.
The inlet side orifice plate is
A first inlet side orifice plate member;
And a second inlet side orifice plate member;
The inlet-side orifice is interposed between the first inlet-side orifice plate member and the second inlet-side orifice plate member,
The inlet side orifice is in the form of a slit,
The turbine blade according to claim 1.
The outlet orifice plate is
A first outlet orifice plate member;
And a second outlet orifice plate member,
The outlet side orifice is interposed between the first outlet side orifice plate member and the second outlet side orifice plate member,
The outlet orifice is in the form of a slit,
The turbine blade according to claim 1 or 5.
A cooling channel is formed inside, and a moving blade is cooled by flowing a cooling medium in the cooling channel;
And a turbine rotor having a rotor disk formed on an outer peripheral surface, and the moving blades provided on the rotor disk,
Provided on the rotor disc,
A turbine having an inlet-side orifice plate formed with an inlet-side orifice for the cooling medium to flow into an inlet of the cooling channel.