JP2003148106A - Structure between cascades for axial flow turbine stator and rotor blades and gas turbine using it - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve aerodynamic performance of a axial flow turbine blade. SOLUTION: In the structure 10 between cascades for the axial flow turbine stator and rotor blades, suppressing plates 50 attached to an inner circumferential ring 30 of the stator blade is protruded into cavity 60. A plurality of the suppressing plates 50 are provided in an arrangement pitch P of the stator blade 20 so as to correspond to a flow flowing into the cavity 60 and a flow flowing out from the cavity 60. Since a vortex like flow 66 caused by an inflow and an outflow is efficiently reduced by providing the suppressing plates 50, energy loss of a working fluid mainstream 65 is reduced.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an axial flow turbine blade, and more particularly to reducing loss when a working fluid passes through a portion of a cavity formed between a row of stationary blades and a row of moving blades. The present invention relates to an inter-blade structure of axial flow turbine stationary blades capable of improving aerodynamic performance of an axial flow turbine and a gas turbine using the same.

[0002]

2. Description of the Related Art An axial-flow turbine machine such as an axial-flow compressor, a steam turbine, or a gas turbine is one in which a working fluid enters and exits in the axial direction, and is often used as a typical fluid machine. . One way to increase the thermal efficiency of these gas turbines and steam turbines and further improve the performance of the axial compressor is to reduce the energy loss of the working fluid and improve the aerodynamic performance of the axial turbine blades. There is a way to raise it.

FIG. 11 is an explanatory view showing an inter-blade structure stationary blade of an axial-flow turbine stationary blade that has been used so far.
The vane 920 is attached to the inner circumferential ring 930 of the vane, and constitutes a vane row 925. The rotor blades 940 are attached to the rotor disc 942, and
Are configured. Here, in an axial flow turbine machine that is exposed to high temperatures such as a gas turbine and a steam turbine, it is necessary to absorb thermal expansion of a turbine main shaft (not shown), a rotor disk 942, and the like. For this reason, a space is provided between the stationary blade row 925 and the moving blade row 945, and the cavity 9
Forming 60.

[0004]

However, in the conventional axial flow turbine machine, the working fluid is the stationary blade row 925.
From the cavity 960 as it flows from the
As a result, the main flow of the working fluid was affected, resulting in energy loss. Although this loss is not so large, in order to further improve the performance of the axial flow turbine machine, it is necessary to minimize the energy loss of the working fluid main flow in the cavity 960 to improve the aerodynamic performance of the axial flow turbine blade. There is.

Therefore, the present invention has been made in view of the above, and reduces the energy loss when the working fluid passes through the cavity portion formed between the stationary blade row and the moving blade row. SUMMARY OF THE INVENTION It is an object of the present invention to provide an inter-blade structure of an axial flow turbine stationary / moving blade capable of improving the aerodynamic performance of the axial flow turbine blade and a gas turbine using the same.

[0006]

In order to achieve the above object, an interblade structure of an axial flow turbine stationary blade according to a first aspect of the present invention is provided between a stationary blade row and a moving blade row of an axial flow turbine. A suppressing plate protruding into the cavity formed in the inner peripheral ring of the vane, and the suppressing plates are spaced from each other in the direction in which the stationary vanes are arranged, and the stationary vanes are arranged. It is characterized in that a plurality of them are arranged in the pitch.

The inter-blade structure of this axial flow turbine static blade is
A plurality of suppressing plates are projected into a cavity formed between the stationary blade row and the moving blade row of the axial flow turbine. In turbines used for axial flow turbine machines exposed to high temperatures such as gas turbines and steam turbines, a space called a cavity between the stationary blade row and the moving blade row to absorb thermal expansion of the main shaft and rotor disk. Is provided. The working fluid such as combustion gas or steam that has passed through the stationary blades is injected to the moving blades on the downstream side, and at this time, a part of the main working fluid flows into this cavity. Then, after forming a flow in which the center of the vortex is directed in the mainstream direction of the working fluid in this cavity, it flows out of the cavity again and joins with the mainstream. It has been newly found that the flow of fluid that flows into and out of the cavity causes energy loss in the main working fluid flow, thereby reducing the aerodynamic performance of the axial turbine blade.

In view of this, in the inter-blade structure of the axial flow turbine stationary / moving blade, the suppressing plate is provided so as to protrude into the cavity to suppress the flow having the vortex center in the direction of the main working fluid flow. As a result, the energy loss of the main working fluid can be reduced, and the aerodynamic performance of the axial turbine blade can be improved. When the inter-blade structure of this axial flow turbine stationary blade is applied to a gas turbine or a steam turbine, the energy of the working fluid can be effectively converted into rotational energy etc. by improving the aerodynamic performance of the blade. The heat efficiency can be improved.

Further, in the inter-blade structure of the axial-flow turbine stationary blade according to claim 2, the suppressing plate is further arranged such that a curve parallel to the circumferential direction of the inner peripheral ring passes through the plate surface. It is characterized in that it is provided on the inner peripheral ring of the stationary blade. In the inter-blade structure of the axial flow turbine stationary / moving blade, the suppressing plate is provided so as to project into the cavity so as to prevent the flow of the inner peripheral ring of the stationary blade in the circumferential direction. As a result, the flow of the working fluid, in which the vortex center is directed toward the main flow direction, can be hindered and efficiently reduced, so that the aerodynamic performance of the axial flow turbine blade can be improved and the performance of the axial flow turbine machine can be improved.

Further, the inter-blade structure of the axial flow turbine stationary / moving blade according to a third aspect of the present invention is configured so as to entirely block the opening of the cavity formed between the stationary blade and the moving blade of the axial flow turbine. The projecting overhanging portion is provided on the inner peripheral ring of the stationary blade. In the cavity provided between the stationary blade row and the moving blade row, in addition to the flow in which the vortex center is directed in the direction of the working fluid main flow described above, a flow in which the vortex center is directed in the circumferential direction of the inner peripheral ring of the stationary blade is provided. Inflow. The inter-blade structure of this axial-flow turbine static blade has an overhanging portion provided in the inner circumferential ring of the static blade so as to block the opening of the cavity, so not only the flow of the vortex center in the direction of the mainstream of the working fluid It is also possible to reduce the flow in which the vortex center is directed in the circumferential direction of the inner peripheral ring of the vane. As a result, the energy loss of the working fluid can be further reduced and the aerodynamic performance of the axial turbine blade can be improved.

Further, according to a fourth aspect of the present invention, there is provided an inter-blade structure of an axial flow turbine stationary blade, wherein a restraint plate protruding from a cavity formed between a stationary blade row and a moving blade row of an axial flow turbine and an overhang. Are provided in the inner circumferential ring of the vane, and the suppressing plates are arranged in a plurality in the array pitch of the vanes with an interval in the array direction of the vanes, and the overhang portion. Are arranged so as to cover the opening of the cavity as a whole. In the inter-blade structure of this axial flow turbine stationary / moving blade, the suppressing plate and the overhanging portion are provided on the inner peripheral ring of the stationary blade. Therefore, it is possible to reduce the flow in which the vortex center is directed in the direction of the mainstream of the working fluid and the flow in which the vortex center is directed in the circumferential direction of the stator blade inner peripheral ring. As a result, the energy loss of the working fluid can be reduced and the aerodynamic performance of the axial flow turbine blade can be improved.

According to a fifth aspect of the present invention, there is provided an inter-blade structure of axial flow turbine stationary blades, wherein the inter-blade structure of the axial flow turbine static blades has a structure in which the open end of the suppressing plate rotates the rotary blades. It is characterized in that it is inclined toward the opposite direction.
In the inter-blade structure of the axial turbine turbine moving blade in which the suppressing plate is provided on the inner peripheral ring of the stationary blade described above, in the region surrounded by the suppressing plate due to the rotation of the moving blade, a vortex is generated in the radial direction of the inner peripheral ring of the stationary blade. A vortex with a center is generated. This vortex interferes with the main flow of the working fluid and causes energy loss of the working fluid. In the inter-blade structure of this axial flow turbine stationary blade, the open end of the suppression plate is inclined toward the direction opposite to the rotating direction of the blade, so this vortex itself is destroyed and interference with the main working fluid flow is reduced. can do. As a result, the energy of the main working fluid can be used more effectively, and the aerodynamic performance of the blade can be improved.

A gas turbine according to a sixth aspect of the present invention is an axial flow type compressor having a stationary blade and a moving blade, a combustor for supplying fuel to the air compressed by the compressor to burn the air. And a turbine driven by combustion gas from the combustor, wherein at least one of the compressor and the turbine is an inter-blade structure of the axial turbine stator blade. It is characterized by having. In this gas turbine, at least one of the compressor and the turbine is provided with the above-described inter-blade structure of the axial flow turbine stationary blades. Therefore, the energy loss of the working fluid can be reduced to improve the aerodynamic performance of the axial turbine blades provided in the compressor and the turbine, so that the thermal efficiency of the entire gas turbine can be further improved.

[0014]

BEST MODE FOR CARRYING OUT THE INVENTION The present invention will be described below in detail with reference to the drawings. The present invention is not limited to this embodiment. In addition, constituent elements in the following embodiments include those that can be easily assumed by those skilled in the art or those that are substantially the same.

(First Embodiment) FIG. 1 is an explanatory view showing a gas turbine to which an inter-blade structure of an axial flow turbine stationary blade according to a first embodiment of the present invention is applied. Also, in FIG.
It is explanatory drawing which shows the structure between blade rows of the axial-flow turbine static-blade which concerns on Embodiment 1 of this invention. The inter-blade structure of this axial-flow turbine static blade is provided with a suppression plate protruding in a cavity provided between the static blade row and the dynamic blade row on the inner peripheral ring of the static blade, whereby the main working fluid flow It is characterized in that it suppresses the vortices whose vortex centers go in the flow direction of. In addition, in this embodiment, a moving blade of a gas turbine will be described as an example, but the scope of application of the present invention is not limited to the gas turbine. For example, the present invention can be applied to an axial flow machine such as a steam turbine or an axial flow compressor in which a cavity for absorbing thermal expansion is provided between a moving blade and a stationary blade.

First, the operation of the gas turbine 100 will be briefly described. The air taken in from the air intake 101 is compressed by the compressor 102 to become high-temperature / high-pressure compressed air and is sent to the combustor 103. Combustor 10
In 3, a gas fuel such as natural gas or a liquid fuel such as light oil or light heavy oil is supplied to the compressed air to burn the fuel and generate high-temperature and high-pressure combustion gas as a working fluid. Then, the combustion gas of high temperature and high pressure is supplied to the turbine 10
It is injected into the first-stage stationary blade 20 provided in No. 4.

The combustion gas injected from the combustor 103 to the first-stage vane 20 is rectified here, and then the first-stage rotor blade 4
The turbine 104 is driven in the process of flowing into 0 from the second stage to the fourth stage of the stationary blades / moving blades. Then, the combustion gas that has finished flowing through the turbine 104 is discharged to the outside of the gas turbine 100. The first embodiment of the present invention is provided between the first-stage stationary blade row composed of the plurality of stationary blades 20 and the first-stage stationary blade array composed of the plurality of moving blades 40.
The inter-blade structure of the axial-flow turbine stationary blade according to is applied. Next, the inter-blade structure will be described with reference to FIG.

An outer peripheral ring 35 is provided on the outer peripheral side of the stationary blade 20, and an inner peripheral ring 30 is provided on the inner peripheral side. Then, the stationary blade 2 including the inner peripheral ring 30 and the outer peripheral ring 35
A plurality of 0s are connected to form the stationary blade row 25. A moving blade 40 is arranged on the downstream side (B side in the figure) of the stationary blade 20, and a plurality of moving blades 40 are attached to a rotor disk 42 attached to a rotating shaft (not shown), A row 45 is formed.

Generally, the turbine of the gas turbine is operated in a high temperature environment, so that the main shaft of the turbine, the rotor disk, etc. are thermally expanded. A certain clearance is required in order to prevent the stationary blade row 25 and the moving blade row 45 from coming into contact with each other due to this thermal expansion. Therefore, the stationary blade row 25 and the moving blade row 45
A cavity 60 is provided between and as a constant clearance to absorb thermal expansion of the turbine main shaft and the like. Next, the flow in the cavity 60 will be described.

FIG. 3 is an explanatory diagram showing the flow in the cavity in the inter-blade structure of the conventional axial flow turbine stationary blade. As shown in the figure, it was newly found that a vortex-shaped flow 66 whose vortex center is directed in the mainstream flow direction (direction D in the figure) is formed. The + in FIG. 3A indicates the cavity 6
The inflow of the combustion gas from 0 toward the main working fluid flow 65 is shown. Further, -in the figure indicates the outflow flow of the combustion gas that branches from the working fluid main flow 65 into the cavity 60. Due to these two flows, the spiral flow 6
6 occurs. As described above, since a part of the combustion gas forming the working fluid main flow 65 becomes the spiral flow 66 and enters and leaves the cavity 60, energy loss occurs in the working fluid main flow 65.

Therefore, in the inter-blade structure 10 of the axial-flow turbine stationary blade according to the first embodiment, the suppressing plate 50 attached to the inner peripheral ring 30 of the stationary blade in the cavity 60 as shown in FIG. Is sticking out. And this suppression plate 5
0 suppresses the spiral flow 66 in which the center of the vortex is directed in the mainstream flow direction (direction D in FIG. 3). Here, a plurality of the suppression plates 50 are provided within the arrangement pitch P of the stationary blades 20 so as to correspond to the positions of the inflow flow and the outflow flow described above (see FIG. 2A).

Further, as shown in FIG. 2 (c), the inner peripheral ring 3
The suppression plate 50 is provided on the inner peripheral ring 30 so that a curve 49 parallel to the circumferential direction of 0 passes through the plate surface of the suppression plate 50. The inclination α at this time is 90 degrees, but the angle of the inclination α is not limited to 90 degrees. By providing the suppression plate 50, the spiral flow 66 caused by the inflow flow and the outflow flow can be efficiently reduced, so that the energy loss of the working fluid main flow 65 can be reduced. As a result, the aerodynamic performance of the rotor blade 40, which is an axial turbine blade provided in the turbine 104, can be improved, so that the thermal efficiency of the gas turbine 100 can be improved.

Further, the compressor 102 of the gas turbine 100
The inter-blade structure of the axial flow turbine stationary / moving blade according to Embodiment 1 may be applied to the moving / static blades provided in the above. in this case,
Since it is possible to improve the aerodynamic performance of the moving blade that is the axial turbine blade in the compressor 102, the efficiency of the compressor 102 can be increased. Then, the compressor 102 is driven by the turbine 104, but the efficiency of the compressor 102 becomes higher than in the conventional case, so that the amount of energy that can be extracted as the shaft output of the turbine 104 increases. Thereby, the thermal efficiency of the gas turbine 100 can be further improved.

It should be noted that the number of the suppression plates 50 is as shown in FIG.
The arrangement pitch P between the stationary blades shown in (a) is not limited to three, and an appropriate number can be selected according to the situation of the spiral flow 66. And the suppression plate 50
In consideration of the thermal expansion of the rotary shaft and the rotor disk 42, it is preferable to install at a position where the interval between the stationary blade row 25 and the moving blade row 45 widens during operation.

The restraint plate 50 may be integrally formed with the inner peripheral ring 30 by means such as cutting or casting. In this case, it takes time to manufacture, but sufficient strength can be provided. Alternatively, the inner ring 30 may be manufactured and attached as a separate component. If they are separate parts, they can be easily manufactured and the cost can be reduced. Furthermore, this suppression plate 50
Since it is exposed to high-temperature combustion gas, it is desirable to provide a cooling flow path inside and to cool it by flowing a cooling medium such as air or steam. The material of the suppressing plate 50 is Ni-based or C.
It is preferable to use a heat-resistant alloy such as o-based alloy (the same applies hereinafter).

(Modification 1) FIG. 4 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to a first modification of the first embodiment. The inter-blade structure 10a of the axial-flow turbine static blade according to this modification has substantially the same configuration as the inter-blade structure 10 (see FIG. 2) of the axial-flow turbine static blade according to the first embodiment. However, the suppressing plate 50a is arranged so that the plate surface of the suppressing plate 50a is in contact with a curve parallel to the circumferential direction of the inner peripheral ring 30.
The difference is that it is set to 0. Since other configurations are similar to those of the first embodiment, the description thereof will be omitted and the same components will be denoted by the same reference numerals.

The inner peripheral ring 30 is provided with a plurality of restraining plates 50a at intervals between blade pitches P. And
The plate surface of the suppressing plate 50a is in contact with a curved line 49 parallel to the circumferential direction of the inner ring 30. Even if the suppression plate 50a is attached in this manner, the flow branched from the main working fluid 65 flows into the cavity 60,
It is possible to prevent the flow that has flowed out from within 0 from joining the working fluid main flow 65. Thereby, the energy loss of the working fluid main flow 65 can be suppressed and the aerodynamic performance of the blade can be improved. The suppressing plate 50a is not only a vortex 66 (see FIG. 3) whose vortex center is directed in the direction of the working fluid main flow 65, but also a vortex-like flow whose vortex center is directed in the circumferential direction of the inner peripheral ring 30 as shown in FIG. The inflow of 68 can be suppressed. As a result, the energy loss of the working fluid main flow 65 can be further reduced, so that the aerodynamic performance of the axial turbine blade can be further improved.

(Modification 2) FIG. 5 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to a second modification of the first embodiment. The inter-blade structure 11 of the axial flow turbine static / blade according to this modification has substantially the same structure as the inter-blade structure 10 (see FIG. 2) of the axial flow turbine static / blade according to the first embodiment. However, the difference is that the open end 51a of the suppression plate 51 is tilted in the direction opposite to the rotation direction of the moving blade row 45 (the direction of the arrow Y in FIG. 5A). Since other configurations are similar to those of the first embodiment, the description thereof will be omitted and the same components will be denoted by the same reference numerals.

FIG. 6 is an explanatory view showing the flow in the cavity in the blade row structure of the axial flow turbine stationary blade according to the second modified example and the first embodiment. Here, FIG.
1 shows a flow in a blade row structure of an axial turbine stationary blade according to Embodiment 1. As shown in FIG. 6B, in this case, in the region surrounded by the suppression plate 50 due to the rotation of the moving blade row 45, a vortex-shaped flow in which the vortex center is directed in the radial direction of the inner peripheral ring 30 of the stationary blade 20. 67 occurs. The spiral flow 67 interferes with the working fluid main flow 65 of the combustion gas as the working fluid, and the energy loss of the working fluid main flow 65 increases.

FIG. 6 (a) shows a flow in the cavity in the blade row structure of the axial flow turbine stationary blade according to the second modification. In this way, since the open end 51a of the suppressing plate 51 is inclined in the direction opposite to the rotating direction of the moving blade row 45, the suppressing plate 51 can break the spiral flow 67. As a result, the generation of the vortex-like flow 67 is reduced to suppress the interference with the main working fluid flow 65, and further, the action and effect of the blade row structure of the axial flow turbine stationary blade according to the first embodiment can be obtained. . When the blade row structure of the axial flow turbine blade is applied to the gas turbine, the aerodynamic performance of the rotor blade 40 of the axial flow turbine blade is further improved to further improve the thermal efficiency of the gas turbine. Can be made. The angle θ at which the suppression plate 51 is tilted is preferably 0 degree or more and 45 degrees or less.

(Modification 3) FIG. 7 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to a third modification of the first embodiment. The inter-blade structure 12 of the axial flow turbine stationary / moving blade according to this modification has substantially the same configuration as the inter-blade structure 10 (see FIG. 2) of the axial flow turbine stationary / moving blade according to the first embodiment. However, the difference is that the suppression plate 52 is inclined with respect to the meridian plane. Since other configurations are similar to those of the first embodiment, the description thereof will be omitted and the same components will be denoted by the same reference numerals. Here, the meridional plane means a plane including the axis Z, and in this example, a plane perpendicular to the paper surface and including the axis Z in FIG. 7B. As shown in FIG. 7, although there are a plurality of suppressing plates 52, there is a meridional surface corresponding to each suppressing plate 52.

As shown in FIG. 7, in the cavity 60, a vortex 66 (FIG.
In addition to the above, a spiral flow 68 having a vortex center directed in the circumferential direction of the inner peripheral ring 30 of the stationary blade 20 flows in. In the inter-blade structure of the axial turbine stationary / moving blade according to the first embodiment, the action of preventing the spiral flow 68 from flowing into the cavity 60 is not sufficient. However, in the inter-blade structure of this axial-flow turbine static blade, as shown in FIG.
Since 2 is inclined with respect to the meridian plane, the inflow of the spiral flow 68 can be suppressed by the suppressing plate 52. As a result, the aerodynamic performance of the moving blade 40 can be further improved, and the thermal efficiency of the gas turbine can be further increased.

Although not shown, the suppressing plate 52 may be tilted in the direction opposite to the direction shown in FIG. In addition, the second modified example is applied to the third modified example, the restraint plate 52 is tilted with respect to the meridian plane, and the open end 52 of the restraint plate 52 is applied.
You may incline a in a direction opposite to the rotating direction of the moving blade row 45. By doing so, it is possible to suppress the spiral flow 67 (see FIG. 6) generated in the region surrounded by the suppression plate 52, in which the vortex center is directed in the radial direction of the inner peripheral ring 30, and thus the aerodynamic performance of the axial turbine blade is further increased. Can be improved.

(Second Embodiment) FIG. 8 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary / moving blade according to a second embodiment. The inter-blade structure 13 of the axial flow turbine stationary / moving blade according to this modification moves over the entire circumference of the inner peripheral ring of the stationary blade so as to close the cavity formed between the stationary blade row and the moving blade row. It is characterized by the formation of overhangs toward the wings. Since other configurations are similar to those of the first embodiment, the description thereof will be omitted and the same components will be denoted by the same reference numerals.

Inter-blade structure 13 of this axial-flow turbine static blade
In the above, the inner peripheral ring 30 of the stationary blade 20 is provided with the overhanging portion 53 toward the moving blade 40. The projecting portion 53 is formed so as to close the opening of the cavity 60. The projecting portion 53 is attached slightly inward in the radial direction with respect to the radially outer surface 30a of the inner peripheral ring 30. This is because, as shown in FIG. 8B, the radially outer surface 40a of the root of the inlet portion of the moving blade 40 has a curved surface for smoothly flowing the working fluid main flow 65. This is because the working fluid main flow 65 is allowed to flow smoothly to the root portion.

As described in the first embodiment, the working fluid main flow 65 of the combustion gas, which is the working fluid, is stored in the cavity 60.
Flow 66 (see FIG. 3) in which the vortex center goes in the direction of and the vortex flow 6 in which the vortex center goes in the circumferential direction of the inner circumferential ring 30.
8 (see FIG. 7) flows in. However, in the inter-blade structure 13 of the axial turbine stationary / moving blade, almost no flow flows into the cavity 60 due to the overhang portion 53.
Further, when the suppression plate described in the first embodiment is used, the spiral flow 67 (see FIG. 6) is generated in the region surrounded by the suppression plate due to the rotation of the rotor blade row 45, and the working fluid main flow is generated. 6
5 may interfere. However, since there is no region surrounded by the suppression plate in the overhang portion 53, the spiral flow 67 is hardly generated, and the interference between this flow and the main working fluid 65 can be reduced.

Due to these actions, in the inter-blade structure 13 of the axial-flow turbine stationary blade, the aerodynamic performance of the axial-flow turbine blade can be further improved, and the performance of the axial-flow turbine machine can be improved. In particular, when applied to a gas turbine, the thermal efficiency can be further improved, and when applied to an axial compressor, the same compression performance can be exhibited with less energy, so that the energy saving effect can be enhanced.

The overhang portion 53 may be formed integrally with the inner peripheral ring 30 by cutting or casting, or may be formed by providing an annular integral member on the inner peripheral ring 30. Alternatively, arc-shaped split rings may be connected to each other and attached to the inner peripheral ring 30. This is preferable because the individual parts can be made smaller and manufacturing and assembling are easy. Further, a plurality of plate members are connected to each other to form a projecting portion 53 having a polygonal cross section.
The inner ring 30 may be formed. In this case, since the overhanging portion 53 can be formed of a plate material, curved surface processing is not required, processing is easy, and manufacturing cost can be reduced, which is preferable. Further, since the overhanging portion 53 is exposed to high-temperature combustion gas, a cooling flow path is provided inside to allow a cooling medium such as air or steam to flow, or a cooling medium is injected from the inside of the cavity 60 for cooling. Is desirable. Then, it is preferable to use a heat-resistant alloy such as Ni-base or Co-base as the material of the overhang portion 53 (the same applies hereinafter).

(Modification 1) FIG. 9 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to a first modification of the second embodiment. In the inter-blade structure 14 of the axial flow turbine stationary / moving blade according to this modification, the suppression plate described in the first embodiment is used in combination with the inter-blade structure of the axial flow turbine stationary / moving blade according to the second embodiment. The point is characteristic. Other configurations are the same as those of the second embodiment.
Therefore, the description thereof will be omitted and the same components will be denoted by the same reference numerals.

Inter-blade structure 14 of this axial-flow turbine static blade
Is attached to the inner peripheral ring 30 so as to extend toward the moving blade 40 attached to the inner peripheral ring 30 of the stationary blade 20 so as to close the cavity 60, and to intersect the protruding portion 54 at a substantially right angle. And a suppression plate 55. The overhang portion 54 suppresses the inflow of the vortex whose vortex center is directed in the circumferential direction of the inner peripheral ring 30, and the suppression plate 55 suppresses the inflow of the vortex whose vortex center is directed in the flow direction of the working fluid main flow 65. . By these actions, a flow that is separated from the working fluid main flow 65 and enters the cavity 60, and a flow that flows out of the cavity 60 and joins the working fluid main flow 65 can be suppressed. As a result, the energy loss of the working fluid main flow 65 can be reduced and the aerodynamic performance of the turbine blade can be improved.

In place of the suppressing plate 55, the first embodiment is used.
The suppression plate 51 according to the second modification (see FIG. 4) or the suppression plate 52 according to the third modification (see FIG. 7) may be applied. In particular, when the suppressing plate 51 (see FIG. 5) is used, it is possible to suppress a vortex, which is generated in the region surrounded by the suppressing plate 51 and has its vortex center radially outward of the inner circumferential ring 30, so that the working fluid main flow is further increased. The energy loss of 65 can be reduced.

(Modification 2) FIG. 10 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to a second modification of the second embodiment. In the inter-blade structure 15 of the axial turbine stationary / moving blade according to this modification, in the inter-blade structure of the axial flow turbine stationary / moving blade according to the second embodiment, the radially outer surface 54a of the overhanging portion 54 is The radially outer surface 30a of the inner peripheral ring 30 and the radially outer surface 40 at the root of the moving blade 40
It is characterized in that it is formed flush with a. Since other configurations are similar to those of the second embodiment, description thereof will be omitted and the same components will be denoted by the same reference numerals.

Inter-blade structure 15 of this axial-flow turbine static blade.
Then, the radially outer surface 54a of the overhanging portion 54 and the inner peripheral ring 3
The surface 30a on the outer side in the radial direction of 0 and the surface 40a on the outer side in the radial direction at the root portion of the moving blade 40 are substantially the same surface. Note that, in order to do so, unlike the inter-blade structure 13 (see FIG. 8) of the axial-flow turbine stationary blade according to the mobile phone 2 of the embodiment, the root portion 40 at the entrance of the blade 40 is provided.
a is formed linearly.

With such a structure, in the inter-blade structure 15 of this axial flow turbine stationary blade, a vortex flow 66, etc. (see FIG. 3).
(See the like) does not easily flow into the cavity 60, and the main working fluid flow 65 of the combustion gas, which is the working fluid, smoothly flows over the cavity 60 toward the moving blade 40. Thereby, the energy loss of the working fluid main flow 65 when passing over the cavity 60 can be made extremely small, so that the aerodynamic performance of the moving blade 40, which is an axial turbine blade, can be further enhanced. When the structure of the axial flow turbine static blades is applied to the gas turbine, the aerodynamic performance of the axial flow turbine blades can be further improved.
The thermal efficiency of the entire gas turbine can be further improved. Further, when applied to other axial flow machines, the performance of each can be further improved.

[0045]

As described above, in the inter-blade structure of the axial flow turbine stationary / moving blade according to the present invention (claim 1), the suppressing plate is formed between the stationary blade row and the moving blade row. It is provided so as to project into the existing cavity to suppress the flow having a vortex center in the direction of the main working fluid flow. As a result, the energy loss of the main working fluid can be reduced, and the aerodynamic performance of the axial turbine blade can be improved. The performance of the axial flow turbine machine can be improved by improving the aerodynamic performance of the blade.

Further, in the inter-blade structure of the axial flow turbine stationary blade according to the present invention (claim 2), the suppressing plate is projected into the cavity so as to prevent the flow of the inner peripheral ring of the stationary blade in the circumferential direction. I decided to provide it. As a result, the flow in which the vortex center is directed toward the main flow direction of the working fluid is blocked, so that the energy loss of the working fluid main flow can be reduced more efficiently. As a result, the aerodynamic performance of the axial turbine blade can be further improved and the performance of the axial turbine machine can be enhanced.

Further, in the inter-blade structure of the axial flow turbine stationary blade according to the present invention (claim 3), since the overhanging portion is provided in the inner peripheral ring of the stationary blade so as to close the opening of the cavity, the working fluid It is possible to reduce not only the flow in which the vortex center is directed in the direction of the main flow, but also the flow in which the vortex center is directed in the circumferential direction of the inner peripheral ring of the vane. This can further reduce the energy loss of the working fluid and further improve the aerodynamic performance of the axial flow turbine blade.

Further, in the inter-blade structure of the axial flow turbine stationary blade according to the present invention (claim 4), the suppressing plate and the overhanging portion are provided on the inner peripheral ring of the stationary blade. Therefore, it is possible to reduce the flow in which the vortex center is directed in the direction of the mainstream of the working fluid and the flow in which the vortex center is directed in the circumferential direction of the stator blade inner peripheral ring. As a result, the energy loss of the working fluid can be reduced and the aerodynamic performance of the axial flow turbine blade can be improved.

Further, in the inter-blade structure of the axial flow turbine stationary blade according to the present invention (claim 5), the open end of the suppressing plate is inclined toward the direction opposite to the rotating direction of the moving blade. For this reason, it is possible to reduce the interference with the main working fluid flow by breaking the vortices that are generated in the region surrounded by the suppression plate and in which the vortex center is directed in the radial direction of the stator blade inner peripheral ring. As a result, the energy of the main working fluid can be used more effectively, so that the aerodynamic performance of the blade can be further improved.

Further, in the gas turbine according to the present invention (claim 6), at least one of the compressor and the turbine is provided with the inter-blade structure of the above axial flow turbine stationary blades. Therefore, the energy loss of the working fluid can be reduced to improve the aerodynamic performance of the axial turbine blades provided in the compressor and the turbine, so that the thermal efficiency of the entire gas turbine can be further improved.

[Brief description of drawings]

FIG. 1 is an explanatory diagram showing a gas turbine to which an inter-blade structure of axial flow turbine stationary / moving blades according to a first embodiment of the present invention is applied.

FIG. 2 is an explanatory diagram showing an inter-blade structure of the axial flow turbine stationary / moving blade according to the first embodiment of the present invention.

FIG. 3 is an explanatory view showing a flow in a cavity in a conventional inter-blade structure of an axial turbine stationary blade.

FIG. 4 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary / moving blade according to a first modified example of the first embodiment.

FIG. 5 is an explanatory diagram showing an inter-blade structure of an axial flow turbine stationary / moving blade according to a second modified example of the first embodiment.

FIG. 6 is an explanatory view showing a flow in a cavity in the blade row structure of the axial flow turbine stationary blade according to the second modified example and the first embodiment.

FIG. 7 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to a third modified example of the first embodiment.

FIG. 8 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to the second embodiment.

FIG. 9 is an explanatory diagram showing an inter-blade structure of an axial flow turbine stationary blade according to a first modified example of the second embodiment.

FIG. 10 is an explanatory view showing an inter-blade structure of an axial flow turbine stationary blade according to a second modified example of the second embodiment.

FIG. 11 is an explanatory view showing an inter-blade structural vane of an axial flow turbine vane that has been used so far.

[Explanation of symbols]

10, 10a, 11, 12, 13, 14, 15, inter-blade structure 20 stationary blade 25 stationary blade row 30 inner peripheral ring 35 outer peripheral ring 40 moving blade 42 rotor disk 45 moving blade row 49 curves 50, 50a, 51, 52 , 55 suppression plates 51a, 52a open ends 53, 54 overhang 60 cavity 65 working fluid mainstream 100 gas turbine 101 air intake 102 compressor 103 combustor 104 turbine

Continued front page    (72) Inventor Yoshinori Tanaka             2-5-3 Marunouchi, Chiyoda-ku, Tokyo             Hishi Heavy Industries Ltd. (72) Inventor Takashi Nakano             2-1-1 Niihama, Arai-cho, Takasago, Hyogo Prefecture             Takasago Works, Mitsubishi Heavy Industries, Ltd. F-term (reference) 3G002 GA15 GB05                 3H034 AA02 AA16 BB03 BB08 BB17                       CC03 DD07 EE08 EE18

Claims (6)

[Claims] 1. A suppressing plate protruding into a cavity formed between a stationary blade row and a moving blade row of an axial turbine is provided on an inner peripheral ring of the stationary blade, and the suppressing plates are provided with each other. An inter-blade structure of an axial flow turbine stationary blade, wherein a plurality of the stationary blades are arranged in an array pitch of the stationary blades at intervals in the array direction of the stationary blades. 2. The suppressing plate is further provided on the inner peripheral ring of the vane so that a curve parallel to the circumferential direction of the inner peripheral ring passes through the plate surface. An inter-blade structure of the axial flow turbine stationary / moving blade according to 1. 3. An overhanging portion projecting so as to cover the entire opening of a cavity formed between the stationary blade and the moving blade of the axial turbine is provided on the inner peripheral ring of the stationary blade. An inter-blade structure of an axial-flow turbine static blade, characterized in that 4. A suppressing plate and an overhanging portion protruding into a cavity formed between a stationary blade row and a moving blade row of an axial turbine are provided on an inner peripheral ring of the stationary blade, and the suppressing blade is provided. A plurality of plates are arranged within the arrangement pitch of the stationary blades with an interval in the arrangement direction of the stationary blades, and the projecting portions are arranged so as to block the opening of the cavity as a whole. The inter-blade structure of the characteristic axial flow turbine blades. 5. The axial flow according to claim 1, wherein the open end of the suppressing plate is inclined in a direction opposite to the rotating direction of the moving blade. Inter-blade structure of turbine turbine blades. 6. An axial flow type compressor having a stationary blade and a moving blade, a combustor for supplying fuel to air compressed by the compressor to burn the air, and a stationary blade and a moving blade. And a turbine driven by combustion gas from the combustor, wherein at least one of the compressor and the turbine is a blade of an axial-flow turbine stationary blade according to any one of claims 1 to 5. A gas turbine having an inter-row structure.