KR102000428B1 - Gas turbine comprising a compressor - Google Patents

Abstract

The present invention relates to a gas turbine comprising a compressor. In the compressor of the present invention, a nanoparticle-coated surface is formed in the cooling passage of the compressor disk. Compressed air passing through the cooling flow path is in contact with the nanoparticle-coated surface, and the heat is transferred to lower the temperature. Thus, the cooling performance of the turbine cooled with compressed air is improved.

Description

[0001] The present invention relates to a gas turbine comprising a compressor,

The present invention relates to a gas turbine comprising a compressor.

A gas turbine is a power engine that mixes and combusts compressed air and fuel compressed in a compressor and rotates the turbine with hot gases generated by combustion. Gas turbines are used to drive generators, aircraft, ships, trains, and so on.

Generally, a gas turbine includes a compressor, a combustor, and a turbine. The compressor sucks the external air, compresses it, and transfers it to the combustor. The compressed air in the compressor is in a state of high pressure and high temperature. The combustor mixes the fuel and the compressed air introduced from the compressor and burns them. The combustion gas generated by the combustion is discharged to the turbine. The combustion gas causes the turbine blades inside the turbine to rotate, thereby generating power. The generated power is used in various fields such as power generation, driving of machinery and the like.

Korean Patent Laid-Open No. 10-2006-0087872 (name: gas turbine device having a cooling device for air inside a compressor)

It is an object of the present invention to provide a gas turbine including a compressor for maintaining the temperature of compressed air moving from a compressor to a turbine for turbine cooling and for facilitating flow.

A compressor according to an embodiment of the present invention includes a compressor casing, a compressor disk, a tie rod, a compressor blade, and a compressor vane. The compressor disk is formed with a cooling channel through which air can move, and a nanoparticle-coated surface coated with nanoparticles is formed on the surface of the cooling channel. The compressor disk may be plural. The tie rods penetrate the plurality of compressor discs and fasten the compressor discs. The compressor blades are radially mounted on the outer circumferential surface of the compressor disk. The compressor vane is mounted inside the compressor casing. Rotation of the compressor disk causes the compressor blades to rotate and air is compressed as the compressor blades rotate. Part of the compressed air moves along the cooling flow path and comes into contact with the nanoparticle-coated surface.

The nanoparticle-coated surface of the compressor according to an embodiment of the present invention may be formed of nanoparticles having high thermal conductivity.

In the compressor according to an embodiment of the present invention, the nanoparticles coated on the nanoparticles may include at least one selected from the group consisting of Si, Au, Ag, SiOx, AlxOx, FexOx, Carbon nanotube (CNT), graphene, and a mixture thereof. The purity of the nanoparticles is preferably 80 to 99.99%. The ratio of nanoparticles can be controlled depending on the situation.

In the compressor according to an embodiment of the present invention, the thickness of the nanoparticle-coated surface is determined by the thickness of the compressor disk, the size of the cooling channel, the thermal conductivity of the nanoparticles used, the surface roughness, the size of the nanoparticles, , And temperature.

The thickness of the coated surface of the nanoparticles in the compressor according to an exemplary embodiment of the present invention is determined by the thickness of the compressor disk, the size of the hole of the cooling channel, the thermal conductivity of the nanoparticles used, the surface roughness, It depends on the temperature.

The thickness of the coated surface of the nanoparticle in the compressor according to an embodiment of the present invention may gradually become thinner in the traveling direction of the compressed air moving along the cooling channel.

In the compressor according to the embodiment of the present invention, the thickness of the coated surface of the nanoparticles may gradually increase in the direction of the compressed air moving along the cooling channel.

The thickness of the coated surface of the nanoparticles in the compressor according to an embodiment of the present invention may gradually increase in thickness in the direction of the progress of the compressed air moving along the cooling channel.

In the compressor according to the embodiment of the present invention, the thickness of the coated surface of the nanoparticles may become gradually thinner and thicker in the traveling direction of the compressed air moving along the cooling channel.

In the compressor according to an embodiment of the present invention, the nanoparticle-coated surface may be formed on a part of the surface of the cooling channel.

In the compressor according to the embodiment of the present invention, the coated surface of the nanoparticles may not have uniform thickness at the same depth of the cooling channel.

In a compressor according to an embodiment of the present invention, the nanoparticle coated surface may be in a spiral shape.

A gas turbine according to an embodiment of the present invention includes a compressor, a combustor, and a turbine. The compressor sucks the outside air and compresses it. The combustor mixes and burns the fuel in compressed air in the compressor. The turbine is equipped with a turbine blade inside, and the turbine blade is rotated by the combustion gas discharged from the combustor. The compressor includes a compressor casing, a compressor disk, a tie rod, a compressor blade, and a compressor vane. The compressor disk is provided with a cooling channel through which a part of the compressed air can move to the turbine, and a nanoparticle coated surface coated with nanoparticles is formed on the surface of the cooling channel. The compressor disk may be plural. The tie rods penetrate the plurality of compressor discs and fasten the compressor discs. The compressor blades are radially mounted on the outer circumferential surface of the compressor disk. The compressor vane is mounted inside the compressor casing. Rotation of the compressor disk causes the compressor blades to rotate and air is compressed as the compressor blades rotate. Compressed air moving along the cooling flow path is in contact with the nanoparticle coated surface to conduct heat.

The gas turbine according to one embodiment of the present invention can control the flow of the compressed air flowing into the turbine by adjusting the thickness of the nanoparticle coated surface.

The gas turbine according to one embodiment of the present invention can control the temperature of the compressed air flowing into the turbine by adjusting the thickness of the nanoparticle coated surface.

According to the embodiment of the present invention, the surface of the cooling channel of the compressor disk is coated with the nanoparticles so that the temperature of the compressed air moving from the compressor to the turbine can be maintained and the flow can be smoothly performed.

1 is a diagram illustrating an interior of a gas turbine according to an embodiment of the present invention.
2 is a conceptual illustration of a cross section of a gas turbine according to an embodiment of the present invention.
3 is a cross-sectional view of a compressor according to an embodiment of the present invention.
FIG. 4 is a view conceptually showing a compressor disk in which a nanoparticle-coated surface is formed on a cooling passage according to an embodiment of the present invention.
FIG. 5 is a diagram showing the thermal resistance and total heat flow for each material.
6 is a graph showing conduction heat transfer characteristics according to thickness.
FIG. 7 is a conceptual view illustrating various types of nanoparticle-coated surfaces according to an embodiment of the present invention.
8 is a view conceptually showing that a nanoparticle-coated surface is partially formed in a cooling channel according to an embodiment of the present invention.
FIG. 9 is a view conceptually showing that the nanoparticle-coated surface formed on the cooling channel according to an embodiment of the present invention is not uniform in thickness at the same depth.
10 is a view conceptually showing formation of a helical nanoparticle-coated surface on a cooling channel according to an embodiment of the present invention.

The present invention is capable of various modifications and various embodiments and is intended to illustrate and describe the specific embodiments in detail. It is to be understood, however, that the invention is not to be limited to the specific embodiments, but includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The singular expressions include plural expressions unless the context clearly dictates otherwise. In the present invention, terms such as "comprises" or "having" are used to designate the presence of stated features, integers, steps, operations, elements, components, or combinations thereof, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. Note that, in the drawings, the same components are denoted by the same reference symbols as possible. Further, the detailed description of known functions and configurations that may obscure the gist of the present invention will be omitted. For the same reason, some of the components in the drawings are exaggerated, omitted, or schematically illustrated.

FIG. 1 is a view showing the inside of a gas turbine according to an embodiment of the present invention, FIG. 2 conceptually showing a cross section of a gas turbine according to an embodiment of the present invention, and FIG. 1 is a cross-sectional view of a compressor according to an embodiment.

1 to 3, a gas turbine 1000 according to an embodiment of the present invention includes a compressor 1100, a combustor 1200, and a turbine 1300. The compressor (1100) sucks and compresses the outside air, and the combustor (1200) mixes and burns the fuel with compressed air in the compressor (1100). The turbine 1300 is mounted with a turbine blade 1310 therein and the turbine blade 1310 is rotated by the combustion gas discharged from the combustor 1200.

Compressor 1100 includes a compressor disk 1110, a tie rod 1120, a compressor blade 1130, a compressor vane 1140, a compressor casing 1150, an intake 1160, and a compressor diffuser 1170.

A compressor blade 1130 is mounted on the compressor disk 1110 and a tie rod 1120 is positioned through the compressor disk 1110. The compressor disk 1110 rotates in accordance with the rotation of the tie rod 1120 to rotate the compressor blade 1130. The compressor disk 1110 may be a plurality of.

A plurality of compressor discs 1110 are fastened in a manner not axially spaced apart by a tie rod 1120. Each of the compressor disks 1110 is aligned along the axial direction with the tie rod 1120 threaded therethrough. A plurality of projections (not shown) may be formed on the outer periphery of the compressor disk 1110 and a flange 1111 may be formed to rotate together with the adjacent compressor disk 1110.

A compressor disk cooling passage 1112 may be formed in at least one of the plurality of compressor disks 1110. Compressed air compressed by the compressor blade 1130 of the compressor 1100 through the compressor disk cooling flow passage 1112 can be moved to the turbine 1300 side to cool the turbine blade 1310.

The tie rod 1120 is positioned through the compressor disk 1110 and aligns the compressor disk 1110. The tie rod 1120 receives the torque generated from the turbine 1300 to rotate the compressor disk 1110. A torque tube 1400 may be disposed between the compressor 1100 and the turbine 1300 as a torque transmitting member for transmitting the rotational torque generated from the turbine 1300 to the compressor 1100. [

One end of the tie rod 1120 is fastened in the compressor disk located on the most upstream side, and the other end is inserted into the torque tube 1400. The other end of the tie rod 1120 is fastened to the pressure nut 1121 in the torque tube 1400. The pressure nut 1121 presses the torque tube 1400 toward the compressor disk 1110 to cause each compressor disk 1110 to come into tight contact.

The compressor blade 1130 is radially coupled to the outer circumferential surface of the compressor disk 1110. The plurality of compressor blades 1130 may be formed in multiple stages. The compressor blade 1130 may be formed with a compressor blade root member 1131 for fastening to the compressor disk 1110 and a compressor disk slot 1113 for insertion of the compressor blade root member 1131 into the compressor disk 1110. [ May be formed.

The compressor blade 1130 rotates in accordance with the rotation of the compressor disk 1110 to compress the introduced air while moving the compressed air to the downstream compressor vane 1140. The air is compressed to a higher pressure while passing through the multi-stage compressor blade 1130.

The compressor vane 1140 is mounted inside the compressor casing 1150, and a plurality of compressor vanes 1140 can be mounted to form an end. The compressor vane 1140 guides the compressed air moved from the compressor blade 1130 at the upstream stage to the compressor blade 1130 at the downstream stage. In one embodiment, at least some of the plurality of compressor vanes 1140 may be rotatably mounted within a predetermined range, such as for controlling the inflow of air.

The compressor casing 1150 forms the contour of the compressor 1100. The compressor casing 1150 accommodates therein a compressor disk 1110, a tie rod 1120, a compressor blade 1130, a compressor vane 1140, and the like.

The compressor casing 1150 may be provided with a connection pipe for cooling the turbine blades by flowing compressed air compressed in various stages by the multi-stage compressor blades 1130 to the turbine 1300 side.

Intake 1160 is located at the inlet of compressor 1100. The intake air 1160 introduces outside air into the compressor 1100. At the outlet of the compressor 1100 is disposed a compressor diffuser 1170 for diffusing the compressed air. The compressor diffuser 1170 rectifies the compressed air before the compressed air in the compressor 1100 is supplied to the combustor 1200 and converts some of the kinetic energy of the compressed air to static pressure. The compressed air passing through the compressor diffuser 1170 flows into the combustor 1200.

FIG. 4 is a view conceptually showing a compressor disk in which a nanoparticle-coated surface is formed on a cooling passage according to an embodiment of the present invention.

As shown in FIG. 4, the compressor disk 2110 according to an embodiment of the present invention is formed with a cooling passage 2112 through which compressed air is sent to the turbine. A nanoparticle coating surface 2113 coated with nanoparticles may be formed on the surface of the cooling passage 2112.

The compressed air having passed through the cooling passage 2112 flows into the turbine to cool the turbine blade. Therefore, the lower the temperature of the compressed air, the better the cooling of the turbine blades.

When compressed air moves along the cooling passage 2112, it contacts the nanoparticle coating surface 2113 and transfers the heat of the compressed air to the compressor disk 2210 through the nanoparticle coating surface 2113. As a result, the temperature of the compressed air is lowered, thereby improving the turbine cooling performance.

Further, when the surface of the cooling passage 2112 is coated with nanoparticles, the flow of the compressed air passing through the cooling passage 2112 becomes smooth, and it becomes easy to adjust the temperature of the air flowing into the turbine to the designed temperature.

The nanoparticles used in the coating are preferably high thermal conductivity materials. The nanoparticles may be silicon, gold, silver, silicon oxide, aluminum oxide, iron oxide, carbon nanotubes, graphene, or the like. . Preferably, silicon (Si), gold (Au), silver (Ag), silicon oxide (SiOx), aluminum oxide (AlxOx), iron oxide (FexOx), carbon nanotubes (CNT), and graphene have purity 80 to 99.99% are used to make nanoparticles.

The method of coating the nanoparticles may be various methods such as dip coating, spray coating, thermal coating and the like.

The thickness t of the nanoparticle coated surface 2113 is determined by the thickness Dt of the compressor disk 2110, the size Hd of the hole of the cooling channel 2112, the thermal conductivity Tc of the nanoparticles used, surface roughness, nanoparticle size, uniformity of nanoparticle size, temperature, and the like.

The thickness t of the nanoparticle-coated surface 2113 may vary depending on the thickness Dt of the compressor disk 2110. That is, when the thickness Dt of the compressor disk 2110 is increased, the thickness t of the nanoparticle coating surface 2113 is made thinner, and when the thickness Dt of the compressor disk 2110 is decreased, The thickness (t) This is to maintain the size of the cooling holes and to improve the thermal conductivity characteristics according to the coating thickness of the nanoparticles.

The thickness t of the nanoparticle coating surface 2113 is adjusted and coated according to the size Hd of the hole of the cooling channel 2112. That is, when the size Hd of the hole of the cooling passage 2112 is increased, the thickness t of the nanoparticle coating surface 2113 is made thinner, and when the size Hd of the hole of the cooling passage 2112 is decreased, The thickness t of the second insulating film 2113 becomes thick. This is to maintain the size of the cooling holes and to improve the thermal conductivity according to the coating thickness of the nanoparticles.

The thickness t of the nanoparticle-coated surface 2113 is adjusted according to the thermal conductivity Tc of the nanoparticle. That is, when the thermal conductivity Tc of the nanoparticles is increased, the thickness t of the nanoparticle-coated surface 2113 is made thinner, and when the thermal conductivity Tc of the nanoparticle is decreased, t) is thickened. This is to maintain the size of the cooling holes and to improve the thermal conductivity characteristics according to the coating thickness.

The contact resistance affecting the hole and hole surface can be calculated by the following equation.

Hole contact resistance

[Rth = hole contact resistance, x = hole size, k = thermal conductivity, A = area]

Contact resistance

[Rc = contact resistance, hc = contact conductance, A = area]

The total thermal resistance is the sum of the hole contact resistance and the contact resistance, which can be expressed as follows.

Using this, the overall heat flow acting on the hole can be calculated by the following equation.

[q = heat flow, T = temperature, Rth = thermal resistance]

In each equation, heat resistance and heat flow are affected by thermal conductivity, hole size, temperature, and area. FIG. 5 is a diagram showing the thermal resistance and total heat flow for each material.

Heat resistance and overall heat flow are mainly influenced by the thermal conductivity of the material. If the size and the area of the hole are changed, the shape of the cooling channel 2112 is deformed, so that various design factors are liable to be changed. However, thermal conductivity affects thermal resistance and heat flow without changing the shape. Therefore, as in the present invention, thermal conductivity can be changed through application of nanoparticles, thereby changing thermal resistance and heat flow.

에서 나노 입자 코팅면(2113)의 두께에 대한 영향성을 알 수 있다. 나노 입자 코팅면(2113)의 두께에 따른 전도 열전달 특성은 도 6에 도시되어 있다. 나노 입자 코팅면(2113)의 두께가 두꺼워질수록 전도 열전달 특성은 좋아지지만 박리 등의 우려가 있어 적절한 두께를 선택하여야 한다. 바람직하게는 나노 입자 코팅면(2113)의 두께가 10 ~ 50um이다. Fourier's law

The influence on the thickness of the nanoparticle-coated surface 2113 can be known. Conduction heat transfer characteristics depending on the thickness of the nanoparticle coated surface 2113 are shown in Fig. As the thickness of the nanoparticle-coated surface 2113 becomes thicker, the conduction heat transfer characteristic is improved, but there is a fear of peeling, and a proper thickness should be selected. Preferably, the thickness of the nanoparticle-coated surface 2113 is 10 to 50 mu m.

FIG. 7 is a conceptual view illustrating various types of nanoparticle-coated surfaces according to an embodiment of the present invention.

The flow of the compressed air moving along the cooling passage 2112 may vary depending on the shape of the nanoparticle-coated surface 2113. Thus, the shape of the nanoparticle coated surface 2113 can be modified to produce the desired compressed air flow. For example, the shape of the nanoparticle-coated surface 2113 may be modified to slow the flow rate of compressed air. If the compressed air has a low velocity, the compressed air can be in contact with the nanoparticle-coated surface 2113 for a longer time, and heat transfer can be performed well.

In an embodiment of the present invention, as shown in FIG. 7A, the nanoparticle-coated surface 2113 may be formed so that the thickness of the nanoparticle-coated surface 2113 in the direction of progress of the compressed air becomes thinner . When the thickness of the nanoparticle-coated surface 2113 gradually decreases, the cooling channel 2112 becomes wider, so that the flow of compressed air becomes slower.

In another embodiment, the nanoparticle-coated surface 2113 can be formed such that the thickness of the nanoparticle-coated surface 2113 increases in the direction of the compressed air, as shown in FIG. 7 (b). When the thickness of the nanoparticle-coated surface 2113 gradually increases, the cooling channel 2112 becomes narrower, so that the flow of compressed air becomes faster.

In another embodiment, as shown in FIG. 7C, the thickness of the nanoparticle-coated surface 2113 may become thicker and thinner in the advancing direction of the compressed air. At a portion where the thickness of the nanoparticle-coated surface 2113 becomes thicker, the speed of compressed air becomes faster, and at a portion where the thickness of the nanoparticle-coated surface 2113 becomes thinner, the velocity of the compressed air becomes slower.

The speed of the compressed air can be adjusted by adjusting the position L1 of the thickest part tmax of the nanoparticle coated surface 2113. [ The portion of the nanoparticle-coated surface 2113 that is slower than the portion where the speed of the compressed air is slower is increased as the thickest portion tmax of the nanoparticle-coated surface 2113 is closer to the inlet side of the cooling channel 2112. As a result, the speed of the compressed air as a whole slows down.

In another embodiment, as shown in FIG. 7D, the thickness of the nanoparticle-coated surface 2113 may become thinner and thicker in the advancing direction of the compressed air. Particularly, as in the present embodiment, when the compressed air stays on the nanoparticle-coated surface 2113, the contact time of the compressed air with the nanoparticle-coated surface 2113 becomes longer, and the temperature of the compressed air becomes lower.

It is possible to control the speed of the compressed air by adjusting the position L2 of the thinnest portion tmin of the nanoparticle coated surface 2113. [ As the thinnest portion tmin of the nanoparticle-coated surface 2113 is closer to the inlet side of the cooling channel 2112, the portion of the compressed air becomes faster than the portion where the velocity of the compressed air is slower, so that the speed of the compressed air as a whole increases.

8 is a view conceptually showing that a nanoparticle-coated surface is partially formed in a cooling channel according to an embodiment of the present invention.

As shown in FIG. 8, a nanoparticle coating surface 3113 may be formed in a part of the cooling passage 3112 of the compressor disk 3110 according to an embodiment of the present invention.

When forming the nanoparticle-coated surface 3113 on the cooling channel 3112, it may be costly to form the entire surface of the cooling channel 3112. Therefore, the nanoparticle-coated surface 3113 can be intensively formed in the portion where the nanoparticles are easily coated in the cooling channel 3112.

For example, the nanoparticle-coated surface 3113 is formed thick at the inlet of the cooling channel 3112 and the nanoparticle-coated surface 3113 is not formed at the center of the inner surface of the cooling channel 3112. The poor heat transfer due to the portion where the nano-particle coating surface 3113 is not formed can be compensated by thickening the nano-particle coating surface 3113 formed at the inlet portion of the cooling channel 3112.

The portion where the nanoparticle-coated surface is not formed in the cooling channel 3112 may vary depending on the nanoparticle coating method. Or the portion where the nanoparticle-coated surface is not formed in the cooling passage 3112 can be determined by the thickness Dt of the compressor disk 3110.

FIG. 9 is a view conceptually showing that the nanoparticle-coated surface formed on the cooling channel according to an embodiment of the present invention is not uniform in thickness at the same depth.

9, the nanoparticle coating surfaces 4113a and 4113b formed in the cooling channel 4112 of the compressor disk 4110 according to an embodiment of the present invention may have different thicknesses at the same depth L . The thickness t1 of the nanoparticle coating surface 4113a formed on the left side and the thickness t2 of the nanoparticle coating surface 4113b formed on the right side of the cooling channel 4112 are the same, Can be different.

Also, the thickness of the nanoparticle-coated surfaces 4113a and 4113b may vary depending on the depth of the cooling passage 4112, as described in FIG. Accordingly, the shapes of the nanoparticle-coated surfaces 4113a and 4113b can be varied, thereby changing the flow of the compressed air moving along the cooling channel 4112 variously, and also controlling the temperature of the compressed air .

10 is a view conceptually showing formation of a helical nanoparticle-coated surface on a cooling channel according to an embodiment of the present invention.

As shown in FIG. 10, the nanoparticle coating surface 5113 formed in the cooling channel 5112 of the compressor disk 5110 according to an embodiment of the present invention may have a spiral shape. If the nanoparticle coated surface 5113 has a spiral shape, the flow of compressed air may become turbulent. Thus affecting the flow of compressed air entering the turbine.

In this embodiment, the flow of the compressed air can be adjusted by adjusting the angle of helix inclination of the spiral-shaped nanoparticle-coated surface 5113. Thus affecting the cooling performance of the turbine.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit of the invention as set forth in the appended claims. The present invention can be variously modified and changed by those skilled in the art, and it is also within the scope of the present invention.

1000: gas turbine 1100: compressor
1110: Compressor disk 1111: Flange
1112, 2112, 3112, 4112, 5112:
2113, 3113, 4113a, 4113b, 5113: Nanoparticle coated surface
1120: tie rod 1130: compressor blade
1140: Compressor Vane 1150: Compressor casing
1160: INTAKE 1170: COMPRESSOR DIFFUSER
1200: Combustor 1300: Turbine

Claims (11)

A compressor for sucking and compressing outside air;
A combustor which mixes and burns fuel with compressed air in the compressor; And
And a turbine in which a turbine blade is mounted and the turbine blade is rotated by a combustion gas discharged from the combustor,
The compressor
A compressor casing,
A plurality of compressor discs having nanoparticle-coated surfaces coated with nanoparticles for enhancing thermal conductivity on a surface of the cooling channel;
A tie rod passing through the plurality of compressor discs and fastening the compressor discs;
A compressor blade radially mounted on an outer circumferential surface of the compressor disk,
And a compressor vane mounted inside the compressor casing,
The nanoparticles forming the nanoparticle-coated surface may be at least one selected from the group consisting of Si, Au, Ag, SiOx, AlxOx, FexOx, , And graphene (Graphene). The nanoparticles have high thermal conductivity,
Wherein the compressor blade is rotated by rotation of the compressor disk, the air is compressed while being moved by the rotation of the compressor blade,
The compressed air moving along the cooling passage is in contact with the nanoparticle-coated surface,
Wherein the temperature of the compressed air flowing into the turbine is controlled by adjusting the thickness of the nanoparticle-coated surface. The method according to claim 1,
Wherein the purity of the nanoparticles is 80 to 99.99%. The method according to claim 1,
The thickness of the nanoparticle-coated surface is determined by at least one of the thickness of the compressor disk, the size of the cooling channel, the thermal conductivity of the nanoparticles used, the surface roughness, the size of the nanoparticles, And the gas turbine. The method according to claim 1,
Wherein the thickness of the nanoparticle-coated surface is gradually thinned in the direction of travel of the compressed air moving along the cooling channel. The method according to claim 1,
Wherein the thickness of the nanoparticle-coated surface gradually increases in the direction of travel of the compressed air moving along the cooling channel. The method according to claim 1,
Wherein the thickness of the coating surface of the nanoparticle gradually increases and becomes thinner in the progressing direction of the compressed air moving along the cooling channel. The method according to claim 1,
Wherein the thickness of the nanoparticle-coated surface is gradually thinned and thickened in the direction of travel of the compressed air moving along the cooling channel. The method according to claim 1,
Wherein the nanoparticle-coated surface is formed on a portion of the surface of the cooling channel. The method according to claim 1,
Wherein the nanoparticle-coated surface is not uniform in thickness at the same depth of the cooling channel. The method according to claim 1,
Wherein the nanoparticle coated surface is of a spiral shape. The method according to claim 1,
Wherein the thickness of the nanoparticle-coated surface is adjusted to control the flow of compressed air flowing into the turbine.

Images