KR101682639B1 - Gas Turbine Vane and Blade Having Cooling Passage Added on Outermost Surface - Google Patents

Abstract

A gas turbine vane and a blade including an outermost flow path are disclosed. The gas turbine vane and the blade 100 according to the embodiment of the present invention are a vane and a blade 100 applied to a gas turbine, and a flow path 110 through which a cooling fluid can flow can be formed inside the vane and the blade 100, A plurality of micro flow paths 122 are formed on the inner surface of the flow path at a predetermined angle on a side surface thereof. After the cooling fluid flows into the flow path 110, the micro flow paths 122 are discharged to the outside through the micro flow path 122. To be the point of composition.
According to the gas turbine vane and the blade of the present invention, a flow path in which a cooling fluid can flow can be formed inside, a microfluidic path can be formed on the inner surface of the flowpath, and the supercritical fluid can be cooled By using it as a fluid, it is possible to improve the cooling efficiency of the vanes and blades of the gas turbine, and consequently to improve the energy efficiency of the power generation system. Further, according to the gas turbine vane and the blade of the present invention, by using the supercritical fluid as the cooling fluid, the cooling efficiency of the gas turbine system can be remarkably improved.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a gas turbine vane and a blade including an outermost channel having a porous microstructure,

The present invention relates to a gas turbine vane and a blade, and more particularly, to a gas turbine vane and a blade including an outermost flow passage.

The gas turbine used in the power generation system is composed of a combustor and a turbine. Specifically, the gas turbine compresses air with a compressor to supply compressed air to the combustion chamber, and injects fuel into the combustion chamber to burn. The high-temperature, high-pressure gas generated at this time is blown into the turbine while expanding to rotate the turbine.

Generally, the compressor and the turbine are directly or indirectly connected in one axis, and the power for operating the compressor uses 25 to 30% of the output generated by the turbine.

Therefore, the output for rotating the generator, the propeller, and the like with the gas turbine is obtained by subtracting the output required for operating the compressor from the output generated from the turbine.

FIG. 1 is a schematic view showing a method of cooling a combustor and a turbine in a gas turbine power generation system according to the prior art (Korean Patent Laid-Open Publication No. 10-1990-0011968, published on Aug. 02, 1990).

Referring to FIG. 1, a conventional gas turbine power generation system 10 uses compressed air for cooling high temperature components (combustion chamber, vane, blade, casing, etc.) Respectively.

However, since a part of the compressed cooling fluid is sent to the combustor 13 and the turbine 12 for cooling, there has been a problem of lowering the efficiency of the entire gas turbine power generation system.

On the other hand, thermal load is applied to the vane and the blade in the gas turbine, and the efficiency of operation of the gas turbine can be improved only by efficiently cooling the vane and the blade.

The vane and the blade of the gas turbine according to the related art are provided with a coolant passage through which the cooling fluid can flow, and the cooling fluid can flow through the coolant passage to cool the vane and the blade.

However, the refrigerant flow path formed in the gas turbine vane and the blade according to the prior art has a technical limitation to further improve the cooling efficiency.

It is an object of the present invention to provide a gas turbine vane and a blade that can improve the cooling efficiency of vanes and blades of a gas turbine used in a power generation system and consequently improve the energy efficiency of the power generation system.

According to one aspect of the present invention, there is provided a gas turbine vane and a blade, comprising: a vane and a blade to be applied to a gas turbine, in which a flow path is formed through which supercritical fluid can flow, The shape of the vane and the blade is a shape in which the outer shape of the vane and the blade is reduced to a predetermined ratio and a porous microstructure is formed in the thickness portion formed by the vane and the blade surface and the inner wall of the flow path, And the trailing edge is defined by a partition wall having a plurality of flow paths in a leading edge direction and a trailing edge direction and a surface connecting the leading edge and the trailing edge along the surface of the vane and the blade, , The flow path partitioned through the partition wall is provided with a plurality of support members which penetrate the thickness portion and connect the upper surface and the lower surface opposite to each other, Wherein the supercritical fluid is introduced into the flow path and then discharged to the outside through the porous microstructure or the supercritical fluid flows into the porous microstructure after the supercritical fluid is introduced into the flow path, And the gas turbine vane and the blade may be a gas turbine vane and a blade.

In this case, the supercritical fluid flowing in the flow path and the microfluidic passage may be heated by absorbing heat from the gas turbine vane and the blade, and then being discharged to the outside. The gas turbine vanes and blades may also include a supercritical fluid turbine driven using an externally vented supercritical fluid and a supercritical fluid compressor including a supercritical fluid compressor compressing a supercritical fluid through the supercritical fluid turbine. Turbine systems.

In one embodiment of the present invention, a microstructure composed of a plurality of layers is formed in the vane, the blade surface, and the thickness portion formed by the inner wall of the flow path, and each of the microstructures has a micro- .

In one embodiment of the present invention, a microstructure composed of a plurality of layers is formed in the vane and the thickness portion formed by the inner wall of the flow path and the blade surface, and the microstructure is inclined at a predetermined angle on the side surface And the minute concavo-convex structures formed in the microstructure are in contact with each other to form a microfluidic channel.

At this time, the microfluidic channels formed in each layer of the microstructure may be formed to intersect with each other at a predetermined angle.

According to another aspect of the present invention, there is provided a gas turbine vane and a blade, comprising: a vane and a blade to be applied to a gas turbine, in which a flow path is formed through which a cooling fluid can flow, A plurality of microfluidic channels are formed in a direction parallel to the direction of formation of the flow path or in a direction perpendicular to the direction of formation of the flow path in the thickness portion formed by the inner surface of the flow path and the vane and the blade surface. The microfluidic channel is in communication with one another to form one flow path. After the cooling fluid flows into the flow path, the microfluidic channel is discharged to the outside through the microfluidic channel, or the supercritical fluid flows into the microfluidic channel And then discharged to the outside through a flow path.

In this case, the supercritical fluid flowing in the flow path and the microfluidic passage may be heated by absorbing heat from the gas turbine vane and the blade, and then being discharged to the outside. The gas turbine vanes and blades may also include a supercritical fluid turbine driven using an externally vented supercritical fluid and a supercritical fluid compressor including a supercritical fluid compressor compressing a supercritical fluid through the supercritical fluid turbine. Turbine systems.

According to an embodiment of the present invention, a microstructure composed of one layer is formed in the vane and the thickness portion formed by the inner surface of the blade and the inner wall of the flow path, and a fine flow path is formed inside the microstructure .

In one embodiment of the present invention, the flow path may be divided into two sections, a leading edge direction and a trailing edge direction.

In this case, an impinging jet hole may be further formed in the microfluidic channel formed on the inner surface of the flow path partitioned in the leading edge direction.

According to another aspect of the present invention, there is provided a gas turbine vane and a blade, comprising: a vane and a blade to be applied to a gas turbine, in which a flow path is formed through which a cooling fluid can flow, The outer shape of the blade is reduced to a predetermined ratio, and a porous microstructure is formed in the thickness portion formed by the vane and the blade surface and the inner wall of the flow path. After the supercritical fluid flows into the flow path Or may be discharged to the outside through the porous microstructure, or may be a structure in which the supercritical fluid is introduced into the porous microstructure and then discharged to the outside through the flow path.

In this case, the supercritical fluid flowing in the flow path and the porous microstructure can be heated by absorbing heat from the gas turbine vane and the blade, and then being discharged to the outside. The gas turbine vanes and blades may also include a supercritical fluid turbine driven using an externally vented supercritical fluid and a supercritical fluid compressor including a supercritical fluid compressor compressing a supercritical fluid through the supercritical fluid turbine. Turbine systems.

In an embodiment of the present invention, the flow path may be divided into a plurality of flow paths in a leading edge direction and a trailing edge direction.

According to an embodiment of the present invention, the flow path may be provided with a plurality of support members that maintain a distance between the inner surfaces facing each other.

In one embodiment of the present invention, the cooling fluid may be a supercritical fluid. At this time, the supercritical fluid may be carbon dioxide.

In an embodiment of the present invention, the shape of the flow path may be a shape in which the outer shape of the vane and the blade is reduced by 50 to 95%.

Also, the microchannel may be a tubular microchannel, and the inner diameter of the microchannel may be 200 to 3,000 micrometers.

As described above, according to the gas turbine vane and the blade of the present invention, a flow path in which a cooling fluid can flow can be formed inside, a micro flow path can be formed on the inner surface of the flow path, By using supercritical fluid as the cooling fluid, it is possible to improve the cooling efficiency of the vanes and blades of the gas turbine, and consequently to improve the energy efficiency of the power generation system.

Further, according to the gas turbine vane and the blade of the present invention, supercritical carbon dioxide having a density and a specific heat of the supercritical region higher than that of the compressed air and having no physical phase change in the supercritical region is used as a cooling fluid, A higher cooling effect can be obtained as compared with compressed air, and as a result, a sufficient cooling effect can be obtained without applying a film cooling method applied to a high-load part.

Further, according to the gas turbine vane and the blade of the present invention, by using the supercritical fluid as the cooling fluid, the cooling efficiency of the gas turbine system can be remarkably improved.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic diagram showing a method for cooling a combustor and a turbine in a gas turbine power generation system according to the prior art; FIG.
2 is a configuration diagram illustrating a cooling system for cooling a gas turbine vane and a blade in accordance with an embodiment of the present invention.
3 is a perspective view showing a structure of a gas turbine vane and a blade according to an embodiment of the present invention.
Fig. 4 is a perspective view showing the gas turbine vane and the blade of Fig. 3 partially exploded. Fig.
5 is a perspective view showing a structure of a gas turbine vane and a blade according to an embodiment of the present invention.
Figure 6 is a top view of the gas turbine vane and blade of Figure 5;
7 is a front view showing the microfluidic channel shown in FIG. 5 in more detail.
8 is a plan view showing a structure of a gas turbine vane and a blade according to an embodiment of the present invention.
Figure 9 is a front cross-sectional view of the gas turbine vane and blade of Figure 8;

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the drawings. Prior to the description, terms and words used in the present specification and claims should not be construed as limited to ordinary or dictionary meanings and should be construed in accordance with the technical concept of the present invention.

Throughout this specification, when a member is "on " another member, it includes the case where there is another member between the two members as well as when the member is in contact with the other member.

Throughout this specification, when an element is referred to as "including" an element, it is understood that it may include other elements as well, without departing from the other elements unless specifically stated otherwise.

FIG. 2 is a block diagram illustrating a cooling system for cooling a gas turbine vane and a blade in accordance with an embodiment of the present invention.

2, a cooling system 10 for cooling a gas turbine vane and a blade according to the present embodiment may be a configuration including a main power generation system 11 and a supercritical fluid turbine system 15. [

Specifically, the main power generation system 11 includes a compressor 12 for compressing air, a combustor 13 for burning fuel and air exhausted from the compressor 12, and a turbine driven by a combustion gas discharged from the combustor 13 (14). At this time, the main power generation system 11 can cool the vanes of the gas turbine and the blades of the gas turbine by flowing the compressed air and the supercritical fluid as the cooling fluid. In this case, a supercritical fluid can be used as the cooling fluid.

On the other hand, the supercritical fluid turbine system 15 flows supercritical fluid as a cooling fluid through the cooling passage 18 provided in the combustor 13 and the turbine 14, flows through the cooling passage 18, A supercritical fluid turbine 16 driven using a supercritical fluid and a supercritical fluid compressor 17 compressing a supercritical fluid through the supercritical fluid turbine 16. At this time, the above supercritical fluid may be carbon dioxide.

Generally, the compressed air used as a gas turbine vane and blade cooling fluid is about 400 degrees Celsius (the temperature in the case of compressed air extracted from a compressor). Supercritical carbon dioxide can be applied to existing gas turbine vanes and blade cooling fluids because the critical point temperature of carbon dioxide is above 31 degrees Celsius and the operating temperature of the supercritical turbine can be varied depending on the supercritical fluid turbine system capacity. The gas turbine vane and blade cooling system according to the present embodiment is a system in which a portion of the cooling fluid required for existing gas turbine cooling is obtained from a supercritical system (15-25% of the total flow rate) The turbine system efficiency reduction can be reduced.

Supercritical fluid refers to a fluid at a point where it can not distinguish a liquid from a gas by reaching a state exceeding a certain high temperature and a high pressure limit. The density of the molecule is close to the liquid, but the viscosity is low.

At normal temperature and pressure, the gas and the liquid become a state where the vapor and the liquid can not be distinguished from each other because the evaporation process does not occur when the gas and the liquid become beyond a certain high temperature and high pressure limit called a critical point. The state of matter is called supercritical fluid. Among the supercritical fluids having such properties, carbon dioxide is relatively close to the room temperature, and in the present invention, carbon dioxide is used as an embodiment of the supercritical fluid.

1, in the embodiment of the present invention, the cooling passage 18 is provided in the combustor 13 and the turbine 14 that require cooling, so that the compressed air is not compressed by the compressor 12 It is possible to increase the power generation efficiency by cooling by using a separate supercritical fluid.

In some cases, the power generation system 10 according to the present embodiment may further include a carbon dioxide collecting unit for collecting carbon dioxide from the exhaust gas discharged after driving the turbine 14. [ At this time, the carbon dioxide captured by the carbon dioxide capture unit can be recovered as a supercritical fluid and recycled.

Therefore, according to the power generation system of the present invention, the carbon dioxide emitted from the combustion gas in the power generation system can be collected and recycled as a supercritical fluid, thereby preventing an environmental problem that may be generated due to the carbon dioxide exhaust gas.

FIG. 3 is a perspective view showing a structure of a gas turbine vane and a blade according to an embodiment of the present invention, and FIG. 4 is a perspective view showing a gas turbine vane and a blade of FIG. 3 partially exploded.

3 and 4 show the structure of a gas turbine vane and a blade according to a first embodiment of the present invention.

Referring to these drawings, the gas turbine vane and the blade 100 according to the present embodiment may have a structure in which a flow path 110 through which a cooling fluid can flow is formed. At this time, the shape of the flow path 110 is a shape in which the outer shape of the vane and the blade is reduced to a predetermined ratio, and may be a shape reduced preferably at a ratio of 50 to 95%. When the reduction ratio is less than 50%, the size of the flow path 110 is small and the cooling fluid can not flow sufficiently, and when the reduction ratio exceeds 95%, the stiffness of the vane and the outer periphery of the blade is remarkably decreased.

In addition, in the thickness portion formed by the inner surface of the vane and the blade and the inner surface of the flow path 110, a number of microfluidic paths 122 inclined at a predetermined angle on the side surface are formed. And may be discharged to the outside through the microfluidic channel 122 after the fluid is introduced. Here, the microfluidic channel 122 refers to a microchannel formed in a tubular shape, and means a flow channel having an inner diameter or an inner width within a range of 200 to 3,000 micrometers. When the inner diameter or inner width of the microfluidic passage 122 is less than 200 micrometers, the size of the microfluidic passage 122 is small and the cooling fluid can not sufficiently flow. When the inner diameter or inner width of the microfluidic passage 122 is 3,000 If it exceeds micrometer, a sufficient cooling effect by the cooling fluid can not be achieved, which is undesirable.

Specifically, as shown in FIG. 3, a microstructure 120 composed of a plurality of layers is formed in the thickness portion of the vane and blade surface and the inner wall of the flow path 110, and the microstructure 120 A microfluidic channel 122 may be formed inside each of the microfluidic channels 122.

4, the microstructure 120 formed of a plurality of layers is formed in the thickness of the vane and the blade surface and the inner wall of the flow path 110, The micro concavo-convex structure 121 may be formed by being inclined at a predetermined angle on the side surface. At this time, the micro concavo-convex structures 121 formed on the microstructure 120 are in contact with each other to form the microfluidic channel 122. In addition, the microfluidic channels 122 formed in the respective layers of the microstructure 120 may be formed to intersect with each other at a predetermined angle.

The gas turbine vanes and blades according to this embodiment including this structure can effectively cool the vanes and blade surfaces exposed to high thermal loads through the forced convection effect through which the cooling fluid flows through the microfluidic path 122 .

In addition, a high cooling effect can be obtained by the friction between the cooling fluid generated by the flow path formed in the diagonal direction and the effect of accelerating the flow of the cooling fluid due to the shape of the sloped micro flow path (swirler shape) have.

FIG. 5 is a perspective view showing the structure of a gas turbine vane and a blade according to an embodiment of the present invention, and FIG. 6 is a plan view showing the gas turbine vane and the blade of FIG. 5, There is shown a front view showing in more detail the microfluidic channel shown in Fig.

5 to 7 show a structure of a gas turbine vane and a blade according to a second embodiment of the present invention.

Referring to these drawings, the gas turbine vane and the blade 100 according to the present embodiment may have a structure in which a flow path 110 through which a cooling fluid can flow is formed. At this time, the shape of the flow path 110 is a shape in which the outer shape of the vane and the blade is reduced to a predetermined ratio, and may be a shape reduced preferably at a ratio of 50 to 95%. When the reduction ratio is less than 50%, the size of the flow path 110 is small and the cooling fluid can not flow sufficiently, and when the reduction ratio exceeds 95%, the stiffness of the vane and the outer periphery of the blade is remarkably decreased.

In addition, in the thickness portion formed by the vane and the blade surface and the inner wall of the flow path 110, a number of micro flow paths 132 are formed in a direction parallel to the forming direction of the flow path 110, May be a structure communicating with each other to form one flow path. At this time, the cooling fluid may flow into the flow path and then be discharged to the outside through the fine flow path.

Here, the microfluidic channel 132 refers to a microchannel formed in a tubular shape, and means a flow channel having an inner diameter or an inner width within a range of 200 to 3,000 micrometers. When the inner diameter or inner width of the microfluidic channel 132 is less than 200 micrometers, the size of the microfluidic channel 132 is so small that the cooling fluid can not sufficiently flow and the inner diameter or inner width of the microfluidic channel 132 is 3,000 If it exceeds micrometer, a sufficient cooling effect by the cooling fluid can not be achieved, which is undesirable.

Specifically, a microstructure 130 composed of one layer is formed in the thickness of the vane and blade surface and the thickness of the inner wall of the flow path 110, and the microstructure 130 has a micro- (131) may be formed.

5 and 6, the flow path 110 may be divided into two sections 111 and 112 in the leading edge direction and the trailing edge direction.

The cooling fluid flows into the vanes and the blades through the two flow paths 111 and 112 formed in the gas turbine vane and the blade according to the present embodiment, flows along the flow path of the micro flow path 131, . The vanes and the blades can be effectively cooled by the cooling fluid flowing through the microfluidic passage 131. [

7, the impinging jet holes 132 may be further formed in the microfluidic channel 131 formed on the inner surface of the flow path 111 defined in the leading edge direction, Can be improved.

FIG. 8 is a plan view showing the structure of a gas turbine vane and a blade according to an embodiment of the present invention, and FIG. 9 is a front sectional view showing the gas turbine vane and the blade of FIG.

8 and 9 show the structure of a gas turbine vane and a blade according to a first embodiment of the present invention.

Referring to these drawings, the gas turbine vane and the blade 100 according to the present embodiment may have a structure in which a flow path 110 through which a cooling fluid can flow is formed. At this time, the shape of the flow path 110 is a shape in which the outer shape of the vane and the blade is reduced to a predetermined ratio, and may be a shape reduced preferably at a ratio of 50 to 95%. When the reduction ratio is less than 50%, the size of the flow path 110 is small and the cooling fluid can not flow sufficiently, and when the reduction ratio exceeds 95%, the stiffness of the vane and the outer periphery of the blade is remarkably decreased.

The porous microstructure 140 is formed in the thickness of the vane and the blade surface and the inner wall of the flow path 110. After the cooling fluid flows into the flow path 110, ). ≪ / RTI >

Specifically, as shown in FIG. 8, the flow path 110 can be partitioned into a plurality of flow paths 113 in the leading edge direction and the trailing edge direction.

The cooling fluid flows from the vane and the blade tip to the vane and to the surface of the blade surface to create a forced convection effect, which can effectively cool the vane and blade surface.

It is possible to increase permeability and diffusibility of the cooling fluid by applying the vane and the flow path-shaped flow path to the porous layer as a porous layer, thereby improving the cooling efficiency.

In some cases, the flow path 110 may be provided with a plurality of support members 150 for maintaining a distance between the inner surfaces facing each other.

Specifically, in order to improve the structural strength, a fin-shaped fin or a guide may be provided in the flow path 110 to which the cooling fluid is supplied, thereby improving the structural strength and obtaining an additional cooling effect by heat conduction.

In the above description of the present invention, only specific embodiments thereof are described. It is to be understood, however, that the invention is not to be limited to the specific forms thereof, which are to be considered as being limited to the specific embodiments, but on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention as defined by the appended claims. .

That is, the present invention is not limited to the above-described specific embodiment and description, and various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims. And such variations are within the scope of protection of the present invention.

1: Conventional gas turbine power generation system
2: Compressor
3: Turbine
4: Combustor
10: Gas Turbine Vane and Blade Cooling System
11: Main power generation system
12: Compressor
13: Combustor
14: Turbine
15: Supercritical Fluid Turbine System
16: supercritical fluid turbine
17: Supercritical fluid compressor
18:
100: Vane and blade
110:
111: flow path in the leading edge direction
112: flow path in the direction of the trailing edge
113: a plurality of partitioned flow paths
120: microstructure
121: fine concave and convex structure
122:
130: microstructure
131: microfluidic channel
132: Impinging jet hole
140: Porous microstructure
150: Support member

Claims (5)

A vane and blade (100) for use in a gas turbine,
A flow path 110 through which a supercritical fluid can flow is formed inside,
The shape of the flow path 110 is a shape in which the outer shape of the vane and the blade is reduced to a predetermined ratio,
A porous microstructure 140 is formed in the thickness of the vane and blade surface and the inner wall of the flow path 110,
The flow path 110 is divided through the partition so as to have a plurality of flow paths 113 in the leading edge direction and the trailing edge direction,
When a surface connecting the leading edge and the trailing edge along the vane and blade surface is referred to as an upper surface and a lower surface,
A plurality of support members 150 are provided in the flow path 110 partitioned through the partition walls to connect the upper surface and the lower surface of the flow path 110 to each other through the thick portion. ),
The supercritical fluid is introduced into the flow path 110 and then discharged to the outside through the porous microstructure 140 or the supercritical fluid is introduced into the porous microstructure 140, And the gas turbine vanes and blades are discharged to the outside. The method according to claim 1,
Wherein the supercritical fluid flowing in the flow path (110) and the porous microstructure (140) is heated by being absorbed heat from the gas turbine vane and the blade, and then discharged to the outside. 3. The method of claim 2,
The gas turbine vane and blade include a supercritical fluid turbine 16 driven using an externally vented supercritical fluid and a supercritical fluid compressor 17 compressing a supercritical fluid through the supercritical fluid turbine 16 Wherein the gas turbine vanes and blades are applied to a supercritical fluid turbine system (15) including a gas turbine (10). delete delete

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