KR102156428B1 - Airfoil for turbine, turbine including the same - Google Patents

Abstract

An object of the present invention is to provide an airfoil with improved cooling performance and a turbine.
The airfoil according to an aspect of the present invention includes a sidewall forming an inner space, a turning space formed inside the wall of the sidewall to induce swirl, and a passage of the refrigerant connected to the turning space inside the wall of the sidewall. And an internal flow path connected to the orbiting space in a direction eccentric with respect to a central axis of the orbiting space, and an injection channel connected to the orbiting space and discharging the refrigerant introduced into the orbiting space.

Description

Airfoil for a turbine, and a turbine including the same TECHNICAL FIELD [AIRFOIL FOR TURBINE, TURBINE INCLUDING THE SAME}

The present invention relates to an airfoil for a turbine, and a turbine including the same.

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

Gas turbines generally include compressors, combustors and turbines. The compressor sucks in outside air, compresses it, and delivers it to the combustor. The air compressed by the compressor is in a state of high pressure and high temperature. The combustor combusts by mixing fuel and compressed air introduced from the compressor. The combustion gases generated by combustion are discharged to the turbine. The turbine blades inside the turbine are rotated by the combustion gas, and power is generated through this. The generated power is used in various fields such as power generation and driving of mechanical devices.

In recent years, in order to increase turbine efficiency, the temperature of the gas flowing into the turbine (Turbine Inlet Temperature: TIT) has been constantly increasing, and for this reason, the importance of heat resistance treatment and cooling of the turbine blades has emerged.

Methods for cooling turbine blades include film cooling and internal cooling. In the film cooling method, a coating film is formed on the outer surface of the turbine blade to prevent heat transfer from the outside to the blade. According to the film cooling method, the heat-resistant paint applied to the blade determines the heat resistance and mechanical durability of the blade.

The internal cooling method cools the blade through heat exchange between the cooling fluid and the blade. In general, turbine blades are cooled using compressed cooling air extracted from a compressor of a gas turbine. Since compressed air compressed by the compressor is produced for use in the combustor of a gas turbine, increasing the amount of compressed air extracted from the compressor for cooling the turbine blades lowers the overall efficiency of the gas turbine. Therefore, for efficient blade cooling, the entire blade must be evenly cooled with a small amount of cooling fluid. In particular, the leading edge portion of the airfoil is easy to overheat and it is difficult to cool down.

Republic of Korea Patent Publication No. 10-2015-0082944

Based on the technical background as described above, the present invention is to provide an airfoil with improved cooling performance and a turbine.

An airfoil according to an aspect of the present invention includes a side wall forming an inner space, a turning space formed inside the wall of the side wall to induce swirl, and a passage of the refrigerant formed connected to the turning space inside the wall of the side wall. And an internal flow path connected to the orbiting space in a direction eccentric with respect to a central axis of the orbiting space, and an injection channel connected to the orbiting space and discharging the refrigerant introduced into the orbiting space, and A plurality of the orbiting spaces are formed inside, and the internal flow path connects the orbiting spaces, and the internal flow path has an inlet through which refrigerant flows from the orbiting space to the internal flow path and an outlet for discharging the refrigerant into the orbiting space. And, the inlet is located higher than the outlet, and the inner flow path is formed to be inclined with respect to the height direction of the orbiting space, so that the refrigerant is supplied from the upper part of the orbiting space to transfer the refrigerant to the lower part of the orbiting space. Supply.

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In addition, the injection passage may be connected to the turning space further below the inlet.

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In addition, the cross-sectional area of the outlet may be formed smaller than the cross-sectional area of the inlet.

In addition, the turning space has a circular cross section, and the inner flow path may be connected to the turning space in a tangential direction of the turning space.

In addition, a guide protrusion may be formed in the orbiting space in a spiral manner to guide the swirl.

In addition, a guide groove may be formed in the revolving space to guide the swirl through a spiral.

In addition, a plurality of cooling channels are formed in the airfoil in a height direction and through which the refrigerant moves, and the internal flow path and the turning space may be formed only on a sidewall surrounding a cooling channel formed adjacent to the leading edge. .

In addition, a plurality of turning spaces connected by the internal flow path may be formed inside the sidewall, and an introduction flow path for supplying a refrigerant to the turning space may be formed in any one of the connected turning spaces. have.

In addition, a plurality of spray passages spaced apart in the height direction of the turning space may be connected to one of the turning spaces.

In addition, injection passages connected to one of the turning spaces may be formed to be connected in different directions.

A turbine including a rotatable rotor disk according to another aspect of the present invention and a plurality of turbine blades installed on the rotor disk, wherein the turbine blade has a blade shape and an airfoil having a leading edge and a trailing edge, the A platform portion coupled to a lower portion of the airfoil, a root portion protruding downward from the platform portion and coupled to the rotor disk, wherein the airfoil has a cooling passage inside the sidewall, and is formed inside the wall of the sidewall to swirl A revolving space that guides the revolving space, an inner flow path connected to the revolving space in a direction eccentric with respect to the central axis of the revolving space, and the revolving space connected to the revolving space inside the wall of the side wall It is connected to the space and includes an injection flow path for discharging the refrigerant introduced into the orbiting space, and a plurality of the orbiting spaces are formed inside the sidewall, and the internal flow path connects the orbiting spaces, and the internal flow path is the It has an inlet through which refrigerant flows into the inner flow path from the orbiting space and an outlet for discharging the refrigerant into the orbiting space, and the inlet is located higher than the outlet, and the inner flow path is inclined with respect to the height direction of the orbiting space. It is formed to receive a refrigerant from an upper portion of the one orbiting space and supply the refrigerant to a lower portion of the other orbiting space.

In addition, an introduction flow path connected to the inside of the airfoil to supply a refrigerant to the turning space is connected to the turning space, and the injection flow path is connected to the turning space further below the inlet, and the introduction flow path May be connected to the orbiting space further below the injection passage.

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According to the airfoil and turbine according to an aspect of the present invention, an inner flow path and a turning space are formed inside the sidewall of the leading edge, so that cooling efficiency for the leading edge portion may be improved.

1 is a view showing the interior of a gas turbine according to a first embodiment of the present invention.
FIG. 2 is a longitudinal cross-sectional view of a part of the gas turbine of FIG. 1.
3 is a perspective view showing a turbine blade according to a first embodiment of the present invention.
4 is a cross-sectional view showing an airfoil according to a first embodiment of the present invention.
5 is a view showing an inner flow path and a turning space according to the first embodiment of the present invention.
6 is a cross-sectional view showing an airfoil according to a second embodiment of the present invention.
7 is a view showing an inner flow path and a turning space according to a second embodiment of the present invention.
8 is a cut-away perspective view showing a turning space according to a second embodiment of the present invention.
9 is a cut-away perspective view showing a turning space according to a third embodiment of the present invention.
10 is a view showing an inner flow path and a turning space according to a fourth embodiment of the present invention.
11 is a view showing an inner flow path and a turning space according to a fifth embodiment of the present invention.
12 is a cross-sectional view showing a part of an airfoil according to a fifth embodiment of the present invention.

The present invention is intended to illustrate specific embodiments and to be described in detail in the detailed description, since various transformations can be applied and various embodiments can be provided. However, this is not intended to limit the present invention to a specific embodiment, it is to be understood to include all conversions, equivalents, and substitutes included in the spirit and scope of the present invention.

The terms used in the present invention are only used to describe specific embodiments, and are not intended to limit the present invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In the present invention, terms such as'comprise' or'have' are intended to designate the presence of features, numbers, steps, actions, components, parts, or combinations thereof described in the specification, but one or more other features. It is to be understood that the presence or addition of elements or numbers, steps, actions, components, parts, or combinations thereof, does not preclude in advance.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. In this case, it should be noted that in the accompanying drawings, the same components are indicated by the same reference numerals as possible. In addition, detailed descriptions of known functions and configurations that may obscure the subject matter of the present invention will be omitted. For the same reason, some components in the accompanying drawings are exaggerated, omitted, or schematically illustrated.

Hereinafter, a gas turbine according to a first embodiment of the present invention will be described.

1 is a view showing the interior of a gas turbine according to an embodiment of the present invention, and FIG. 2 is a longitudinal cross-sectional view of a part of the gas turbine of FIG. 1.

Referring to FIGS. 1 and 2, the thermodynamic cycle of the gas turbine 1000 according to the present embodiment may ideally follow the Brayton cycle. The Brayton cycle can consist of four processes leading to isentropic compression (thermal compression), static pressure rapid heating, isentropic expansion (thermal expansion), and static pressure heat dissipation. In other words, after inhaling atmospheric air and compressing it to high pressure, it burns fuel in a static pressure environment to release thermal energy, expands the high-temperature combustion gas and converts it into kinetic energy, and then releases exhaust gas containing residual energy into the atmosphere. I can. That is, the cycle can be performed in four processes of compression, heating, expansion, and heat dissipation.

The gas turbine 1000 realizing the above Brayton cycle may include a compressor 1100, a combustor 1200, and a turbine 1300, as shown in FIG. 1. Although the following description will refer to FIG. 1, the description of the present invention can be widely applied to a turbine engine having a configuration equivalent to that of the gas turbine 1000 illustrated in FIG. 1 by way of example.

Referring to FIG. 1, a compressor 1100 of a gas turbine 1000 may suck air from the outside and compress it. The compressor 1100 may supply compressed air compressed by the compressor blade 1130 to the combustor 1200, and may also supply cooling air to a high temperature region requiring cooling in the gas turbine 1000. At this time, since the sucked air undergoes an adiabatic compression process in the compressor 1100, the pressure and temperature of the air passing through the compressor 1100 are increased.

The compressor 1100 is designed as centrifugal compressors or axial compressors. While a centrifugal compressor is applied in a small gas turbine, a large gas turbine 1000 as shown in FIG. 1 is a large amount of air. It is common to apply the multi-stage axial compressor 1100 because it must be compressed. At this time, in the multi-stage axial compressor 1100, the blade 1130 of the compressor 1100 rotates according to the rotation of the center tie rod 1120 and the rotor disk, compressing the introduced air, and compressing the compressed air into the rear compressor vane ( 1140). As the air passes through the blades 1130 formed in multiple stages, it is compressed with more and more high pressure.

The compressor vane 1140 is mounted inside the housing 1150, and a plurality of compressor vanes 1140 may be mounted to form stages. The compressor vane 1140 guides the compressed air moved from the compressor blade 1130 at the front to the blade 1130 at the rear end. In one embodiment, at least some of the plurality of compressor vanes 1140 may be mounted so as to be rotatable within a predetermined range for adjusting the inflow amount of air.

The compressor 1100 may be driven using a portion of the power output from the turbine 1300. To this end, as shown in FIG. 1, the rotation shaft of the compressor 1100 and the rotation shaft of the turbine 1300 may be directly connected by a torque tube 1170. In the case of the large gas turbine 1000, almost half of the output produced by the turbine 1300 may be consumed to drive the compressor 1100.

On the other hand, the combustor 1200 may mix compressed air supplied from the outlet of the compressor 1100 with fuel and burn at an isostatic pressure to produce a high-energy combustion gas. In the combustor 1200, the introduced compressed air is mixed with fuel and combusted to produce high-energy high-temperature and high-pressure combustion gas, and the combustion gas temperature is raised to the heat resistance limit that the combustor and turbine parts can withstand through the iso-rolling process. .

A number of combustors 1200 may be arranged in a housing formed in a cell shape, and a burner including a fuel injection nozzle, etc., a combustor liner forming a combustion chamber, and a connection portion between the combustor and the turbine It is configured to include a transition piece (Transition Piece).

Meanwhile, the high-temperature, high-pressure combustion gas from the combustor 1200 is supplied to the turbine 1300. As the supplied high-temperature and high-pressure combustion gas expands, impulses and reaction forces are applied to the turbine blades 1400 of the turbine 1300 to generate rotational torque, and the obtained rotational torque is passed through the torque tube 1170 and the compressor 1100. Power that is transmitted to and exceeds the power required to drive the compressor 1100 is used to drive a generator or the like.

The turbine 1300 includes a rotor disk 1310 and a plurality of turbine blades 1400 and vanes radially disposed on the rotor disk 1310. The rotor disk 1310 has a substantially disk shape, and a plurality of grooves are formed in its outer circumferential portion. The groove is formed to have a curved surface, and the turbine blade 1400 and vanes are inserted into the groove. The turbine blade 1400 may be coupled to the rotor disk 1310 in a manner such as a dovetail. The vane is fixed so as not to rotate and guides the flow direction of the combustion gas passing through the turbine blade 1400.

3 is a perspective view showing a turbine blade according to a first embodiment of the present invention, Figure 4 is a cross-sectional view showing an airfoil according to the first embodiment of the present invention, and Figure 5 is a first embodiment of the present invention It is a view showing the inner flow path and the turning space according to.

Referring to Figures 3 to 5, the turbine blade 1400 is lower than the platform portion 1420 and the platform portion 1420 coupled to the lower portion of the airfoil 1410 and the airfoil 1410 in the shape of a wing. It includes a root portion 1430 protruding and coupled to the rotor disk. The airfoil 1410 may be formed of a curved surface plate in the shape of a wing, and may be formed to have an optimized airfoil shape according to the specifications of the gas turbine 1000.

The platform part 1420 is located between the airfoil 1410 and the root part 1430 and may be formed in a substantially square plate or square pillar shape. The platform unit 1420 serves to maintain a gap between the turbine blades 1400 by contacting the platform unit 1420 of the adjacent turbine blade 1400 and its side surfaces.

The root portion 1430 has a substantially fir-shaped bent portion, which is formed to correspond to the shape of the bent portion formed in the slot of the rotor disk 1310. Here, the coupling structure of the root portion 1430 does not necessarily have a fir shape, and may be formed to have a dovetail shape. An inlet port for supplying cooling air may be formed at the lower end of the root part 1430.

The airfoil 1410 may include a leading edge LE disposed on an upstream side and a trailing edge TE disposed on a downstream side based on the flow direction of the combustion gas. In addition, the airfoil 1410 has a convexly curved surface on the front surface of the airfoil 1410 and a protruding suction surface (S1), and a pressure surface that forms a curved surface concavely toward the suction surface on the rear surface of the airfoil. (S2) is formed. A pressure difference between the suction surface S1 and the pressure surface S2 of the air foil 1410 is generated, so that the turbine 1300 rotates.

A plurality of cooling holes 1411 are formed on the surface of the airfoil 1410, and the cooling holes 1411 communicate with a cooling passage formed inside the airfoil 1410 to transfer refrigerant to the surface of the airfoil 1410. Supply.

The airfoil 1410 comprises a side wall 1470 forming an outer shape, an inner flow path 1510 formed inside the side wall 1470, a refrigerant flowing into the turning space 1520 connected to the inner flow path 1510, and the turning space 1520 An injection flow path 1540 for injecting the air may include an introduction flow path 1530 connected to the interior of the airfoil 1410 to receive a refrigerant. Here, the refrigerant may be made of air, but the present invention is not limited thereto. The inner flow path 1510, the turning space 1520, the injection flow path 1540, and the introduction flow path 1530 are formed between the inner surface and the outer surface of the side wall 1470, that is, inside the wall of the side wall 1470.

Inside the airfoil 1410, a first cooling channel C11 connected to the leading edge LE, a second cooling channel C12 connected to the trailing edge TE, and a first cooling channel C11 and second cooling A third cooling passage C13 formed between the passages C12 is formed. In addition, the airfoil 1410 may include a first partition plate 1412 and a second partition plate 1413 that are connected in the height direction of the airfoil 1410 and divide the inner space of the airfoil 1410. The first partition plate 1412 and the second partition plate 1413 are connected in the height direction of the airfoil 1410 to divide the space, and the first cooling passage C11, the second cooling passage C12, and the third cooling A flow path C13 is formed.

On the other hand, the inner flow path 1510 and the turning space 1520 are formed inside the side wall 1470, the side wall 1470 is a double wall 1471 with a flow path formed therein and a single wall 1472 with no flow path formed therein. ). The double wall 1471 is positioned between the first partition plate 1412 and the leading edge LE, and the single wall 1472 is positioned between the first partition plate 1412 and the trailing edge TE. The double wall 1471 is formed only on the side wall 1470 surrounding the first cooling passage C11 disposed adjacent to the leading edge LE.

The inner flow path 1510 is formed by being connected in a direction perpendicular to the thickness direction of the side wall 1470 in parallel with the direction in which the side wall 1470 is connected. A plurality of internal flow paths 1510 are formed inside the sidewall 1470, and the internal flow paths 1510 connect the turning space 1520. The turning space 1520 is connected to at least one internal flow path 1510 and has a cylindrical shape having a circular cross section.

Inside the sidewall 1470, a plurality of turning spaces 1520 and an inner flow path 1510 may be spaced apart in the circumferential direction of the sidewall 1470, and a plurality of turning spaces 1520 may also be formed in the height direction of the sidewall 1470. ) And the inner flow path 1510 may be formed to be spaced apart.

The inner flow path 1510 may be connected to the turning space 1520 in a direction eccentric with respect to the central axis X1 of the turning space 1520. Here, the eccentric direction means that the direction is not toward the central axis X1 from the outer surface, and means a direction closer to the tangent direction among the tangent direction and the normal direction. An angle formed by the tangential direction of the turning space 1520 and the inner flow path 1510 may be within 30 degrees. In more detail, the internal flow path 1510 is connected to the revolving space 1520 in a tangential direction of the revolving space 1520 to supply a refrigerant into the revolving space 1520 and receive the refrigerant.

The inner flow path 1510 has an inlet 1512 through which air is introduced from the orbiting space 1520 and an outlet 1513 through which air is discharged into the orbiting space 1520. Accordingly, the refrigerant flowing through the swirl is supplied to the internal flow path 1510 through the inlet 1512, and the outlet 1513 induces the swirl by injecting the refrigerant into the turning space 1520. The inlet 1512 and the outlet 1513 of the inner flow path 1510 may be connected in a tangential direction to the turning space 1520, but the present invention is not limited thereto, and only the outlet 1513 is in the turning space 1520. It is connected in a tangential direction, and the inlet 1512 may be connected eccentrically with respect to the central axis X1.

On the other hand, the inlet 1512 is located higher than the outlet 1513, the inlet 1512 is located higher than the center in the height direction of the turning space 1520, the outlet 1513 is the height of the turning space 1520 It can be located further below the directional center.

An introduction passage 1530 connected to the first cooling passage C11 to receive a refrigerant is connected to the turning space 1520. The introduction passage 1530 is connected to the first cooling passage C11 to supply air as a refrigerant to the turning space. The introduction passage 1530 is connected to the orbiting space 1520 in the tangential direction of the orbiting space 1520 to supply the refrigerant to the orbiting space 1520, but allows the refrigerant to swirl inside the orbiting space 1520.

In the turning space 1520, a spray flow path 1540 for discharging the refrigerant introduced into the turning space 1520 to the outside of the airfoil 1410 is connected and formed, and the spray flow path 1540 is also a central axis of the turning space 1520 It is formed by connecting in an eccentric direction with respect to (X1). The injection passage 1540 is connected to the turning space 1520 further below the inlet 1512 of the inner passage 1510. In addition, the injection flow path 1540 is connected to the turning space 1520 above the introduction flow path 1530 and the outlet 1513. The air discharged from the jet passage 1540 moves along the surface of the airfoil 1410 to cool the film.

In the first embodiment, three orbiting spaces 1520 are connected by two internal flow paths 1510, and injection flow paths 1540 may be connected to each of the orbiting spaces 1520. Also, the introduction passage 1530 may be connected to only one turning space 1520 disposed farthest from the leading edge LE. However, the present invention is not limited thereto, and it is sufficient if the plurality of turning spaces 1520 are connected by one or more internal flow paths 1510.

The refrigerant introduced into the revolving space 1520 through the internal flow path 1510 or the introduction flow path 1530 moves to the upper part of the revolving space 1520 while swirling, and some refrigerants are airfoiled through the injection flow path 1540. (1410) The refrigerant is discharged to the outside, and the remaining refrigerant may move to another orbiting space 1520 through the internal flow path 1510.

The refrigerant cools the inner flow path 1510 and the turning space 1520 during the moving process, so that the sidewall adjacent to the leading edge LE can be efficiently cooled. In particular, since the refrigerant swirls along the inner wall of the turning space 1520 in the turning space 1520, the contact time and the contact area are extended, so that cooling efficiency can be maximized. In the inner flow path 1510, the refrigerant moves in a direction toward the leading edge LE, and since this movement direction is opposite to the movement direction of the combustion gas, cooling efficiency may be further improved.

Hereinafter, an airfoil according to a second embodiment of the present invention will be described. 6 is a cross-sectional view showing an airfoil according to a second embodiment of the present invention, FIG. 7 is a view showing an inner flow path and a turning space according to a second embodiment of the present invention, and FIG. 8 is a first embodiment of the present invention. 2 is a cutaway perspective view showing a turning space according to the embodiment.

6 to 8, the airfoil 2410 according to the second exemplary embodiment has the same structure as the airfoil according to the first exemplary embodiment, except for the turning space 2520. Duplicate description of the configuration will be omitted.

The airfoil 2410 comprises a side wall 2470 forming an outer shape, an inner flow path 2510 formed inside the side wall 2470, a refrigerant flowing into the turning space 2520 connected to the inner flow path 2510, and the turning space 2520 It may include an injection flow path 2540 for injecting.

Inside the airfoil 2410, a first cooling passage C21 connected to the leading edge LE, a second cooling passage C22 connected to the trailing edge TE, and a first cooling passage C21 and second cooling. A third cooling flow path C23 formed between the flow paths C22 is formed. In addition, the airfoil 2410 may include a first partition plate 2412 and a second partition plate 2413 that are connected in the height direction of the airfoil 2410 to divide the revolving space of the airfoil 2410.

Meanwhile, the internal flow path 2510 and the turning space 2520 are formed inside the sidewall 2470, and the internal flow path 2510 and the turning space 2520 are a first cooling flow path arranged adjacent to the leading edge LE. It is formed only on the side wall 2470 forming (C21). A plurality of cooling holes 2411 connected to the second cooling passage C22 and the third cooling passage C23 are formed in the side wall 2470.

The inner flow path 2510 is formed to be connected in a direction perpendicular to the thickness direction of the side wall 2470 in parallel with the direction in which the side walls 2470 are connected. A plurality of internal flow paths 2510 are formed inside the sidewall 2470, and the internal flow path 2510 connects the turning spaces 2520.

The internal flow path 2510 is connected to the orbiting space 2520 in a tangential direction of the orbiting space 2520 to supply a refrigerant into the orbiting space 2520 and receive the refrigerant. The inner flow path 2510 has an inlet 2512 through which air is introduced from the orbiting space 2520 and an outlet 2513 through which air is discharged into the orbiting space 2520. Accordingly, the refrigerant flowing through the swirl is supplied to the internal flow path 2510 through the inlet 2512, and the outlet 2513 of the internal flow path 2510 induces the swirl by injecting the refrigerant into the turning space 2520. The inlet 2512 is located higher than the outlet 2513, the inlet 2512 is connected to the upper end of the turning space 2520, the outlet 2513 may be formed connected to the lower end of the turning space 2520 .

In the turning space 2520, an introduction flow path 2530 connected to the first cooling flow path C21 to receive the refrigerant is formed to be connected. The introduction passage 2530 is connected to the first cooling passage C21 to supply air as a refrigerant to the turning space. The introduction flow path 2530 is connected to the orbiting space 2520 in a tangential direction of the orbiting space 2520 to supply the refrigerant to the orbiting space 2520 but allows the refrigerant to swirl inside the orbiting space 2520.

In the revolving space 2520, an injection flow path 2540 for discharging the refrigerant introduced into the revolving space 2520 to the outside of the airfoil 2410 is connected and formed, and the injection flow path 2540 is also a central axis of the revolving space 2520 It is formed by connecting in a direction eccentric with respect to.

The turning space 2520 is connected to at least one inner flow path 2510 and has a cylindrical shape having a circular cross section. A guide protrusion 2570 for guiding the movement of the refrigerant may be formed in the revolving space 2520 by connecting in a spiral direction. The guide protrusion 2570 connects in a spiral direction to induce swirl flow, and extends from the bottom to the top.

The refrigerant introduced into the turning space 2520 through the internal flow path 2510 or the introduction flow path 2530 moves upward while swirling through the guide protrusion 2570, and some air is transferred to the air through the injection flow path 2540. The foil 2410 is discharged to the outside, and the remaining air may move to another orbiting space 2520 through the inner flow path 2510.

When the guide protrusion 2570 is formed as in the second embodiment, the refrigerant moves while swirling more stably, thereby stabilizing the flow and improving cooling efficiency.

Hereinafter, an airfoil according to a third embodiment of the present invention will be described. 9 is a cut-away perspective view showing a turning space according to a third embodiment of the present invention.

Referring to FIG. 9, since the airfoil according to the third embodiment has the same structure as the airfoil according to the second embodiment, except for the turning space 3520, redundant description of the same configuration will be provided. Omit it.

The turning space 3520 according to the third embodiment is connected to at least one inner flow path 3510 and has a cylindrical shape having a circular cross section. In the turning space 3520, an injection flow path 3540 for discharging the refrigerant from the turning space 3520 and an introduction flow path for supplying the refrigerant to the turning space 3520 may be connected to each other.

A guide groove 3570 guiding the movement of the refrigerant may be formed in the revolving space 3520 to be connected in a helical direction. The guide groove 3570 is connected in a spiral direction from the bottom to the top to induce swirl flow. If the guide groove 3570 is formed as in the third embodiment, the refrigerant moves while swirling more stably, thereby stabilizing the flow and improving cooling efficiency.

Hereinafter, an airfoil according to a fourth embodiment of the present invention will be described. 10 is a view showing an inner flow path and a turning space according to a fourth embodiment of the present invention.

Referring to FIG. 10, since the airfoil according to the fourth embodiment has the same structure as the airfoil according to the first embodiment, except for the inner flow path 4510, a redundant description of the same configuration will be provided. Omit it.

The airfoil according to the fourth embodiment includes an internal flow path 4510 formed inside the sidewall, a turning space 4520 connected to the internal flow path 4510, and an injection flow path 4540 for spraying the refrigerant introduced into the turning space 4520. ), it may include an introduction passage 4530 for supplying a refrigerant to the turning space 4520.

The turning space 4520 is connected to at least one inner flow path 4510 and has a cylindrical shape having a circular cross section. The inner flow path 4510 is formed to be connected in a direction perpendicular to the thickness direction of the side wall parallel to the direction in which the side wall is connected. A plurality of internal flow paths 4510 are formed inside the sidewall, and the internal flow paths 4510 connect the turning spaces 4520. The inner flow path 4510 is connected to the turning space 4520 in the tangential direction of the turning space 4520 to supply the refrigerant into the turning space 4520 and receive the refrigerant.

The internal flow path 4510 has an inlet 4512 through which air is introduced from the orbiting space 4520 and an outlet through which air is discharged into the orbiting space 4520. Accordingly, the refrigerant flowing through the swirl is supplied to the internal flow path 4510 through the inlet 4512, and the outlet 4513 of the internal flow path 4510 injects the refrigerant into the turning space 4520 to induce the swirl.

On the other hand, the inlet (4512) is located higher than the outlet (4513), the inlet (4512) is connected to the upper end of the turning space (4520), the outlet (4513) is formed connected to the lower end of the turning space (4520). I can. In addition, the cross-sectional area of the outlet 4513 is formed to be smaller than the cross-sectional area of the inlet 4512, and the inner flow path 4510 is formed such that the inner diameter gradually decreases from the inlet 4512 to the outlet 4513.

Accordingly, the flow velocity increases from the inlet 4512 of the inner flow path 4510 to the outlet 4513, so that the refrigerant can be injected from the inner flow path 4510 into the turning space at a high speed. When the refrigerant is injected at a high speed from the internal flow path 4510, the swirl flow can be more easily induced.

The introduction passage 4530 is connected to one turning space 4520, and the introduction passage 4530 is connected to a cooling passage formed inside the airfoil to supply air as a refrigerant to the turning space. The injection flow path 4540 is connected to the turning space 4520 and is formed to be connected in a direction eccentric with respect to the central axis of the turning space 4520. The injection passage 4540 is connected to the turning space 4520 further below the inlet 4512 described above.

As in the fourth embodiment, when the outlet 4513 has a smaller cross-sectional area than the inlet 4512, and the inner flow path 4510 has a structure in which the inner diameter gradually decreases from the inlet 4512 to the outlet 4513, , The refrigerant is injected at a high speed from the inner flow path 4510 to the turning space 4520 to induce a stronger swirl.

Hereinafter, an airfoil according to a fifth embodiment of the present invention will be described.

11 is a view showing an inner flow path and a turning space according to a fifth embodiment of the present invention, and FIG. 12 is a cross-sectional view showing a part of an airfoil according to the fifth embodiment of the present invention.

11 and 12, the airfoil 5410 according to the fifth embodiment has the same structure as the airfoil according to the first embodiment, except for the injection flow paths 5540 and 5560. Therefore, redundant description of the same configuration will be omitted.

The airfoil 5410 according to the fifth embodiment contains the refrigerant introduced into the inner flow path 5510 formed inside the side wall 5470, the turning space 5520 connected to the inner flow path 5510, and the turning space 5520. It may include injection passages 5540 and 5560 for injection, and an introduction passage 5530 for supplying a refrigerant to the turning space 5520.

The turning space 5520 is connected to at least one inner flow path 5510 and has a cylindrical shape having a circular cross section. The inner flow path 5510 is formed by being connected in a direction perpendicular to the thickness direction of the side wall 5470 in parallel with the direction in which the side wall 5470 is connected. The internal flow path 5510 is connected to the orbiting space 5520 in a tangential direction of the orbiting space 5520 to supply a refrigerant into the orbiting space 5520 and receive the refrigerant. In the fifth embodiment, two orbiting spaces 5520 are connected to each other by one inner flow path 5510.

The internal flow path 5510 has an inlet 5512 through which air is introduced from the orbiting space 5520 and an outlet 5513 through which air is discharged into the orbiting space. On the other hand, the inlet (5512) is located higher than the outlet (5513), the inlet (5512) is connected to the upper end of the turning space (5520), the outlet (5513) is connected to the lower end of the turning space (5520). I can.

The introduction flow path 5530 is connected to one turning space 5520 and is connected to a cooling flow path formed inside the airfoil to supply air as a refrigerant to the turning space 5520. The introduction passage 5530 may be connected to the orbiting space 5520 in a tangential direction of the orbiting space 5520 to supply the refrigerant to the orbiting space 5520, but allow the refrigerant to swirl within the orbiting space.

The injection passages 5540 and 5560 are connected to the turning space 5520 and may be formed to be connected in an eccentric direction with respect to the central axis of the turning space 5520. The injection passages 5540 and 5560 are connected to the turning space 5520 further below the inlet 5512 described above.

Two spray flow paths 5540 and 5560 are connected to one turning space 5520 and the spray flow paths 5540 and 5560 are spaced apart in the height direction of the turning space 5520. In addition, the spray passages 5540 and 5560 connected to one turning space 5520 are formed by being obliquely connected to each other in different directions.

When a plurality of spray passages 5540 and 5560 connected in different directions are formed in one turning space 5520 as in the fifth embodiment, the film cooling effect may be further increased.

As described above, one embodiment of the present invention has been described, but those of ordinary skill in the relevant technical field add, change, delete or add components within the scope not departing from the spirit of the present invention described in the claims. Various modifications and changes can be made to the present invention by means of the like, and it will be said that this is also included within the scope of the present invention.

1000: gas turbine
1100: compressor
1130: compressor blade
1140: Bane
1150: housing
1170: torque tube
1200: combustor
1300: turbine
1310: rotor disk
1400: turbine blade
1410, 2410, 5410: airfoil
1411, 2411: cooling hole
1412, 2412: first partition
1413, 2413: second partition
1420: platform part
1430: root part
1470, 2470, 5470: side walls
1471: double wall
1472: single wall
1510, 2510, 3510, 4510, 5510: internal flow path
1512, 2512, 4512, 5512: Entrance
1513, 2513, 4513, 5513: Exit
1520, 2520, 3520, 4520, 5520: turning space
1530, 2530, 4530, 5530: introduction euro
1540, 2540, 3540, 4540, 5540, 5560: injection flow path
2570: guide protrusion
3570: Information Home
C11, C21: first cooling flow path
C12, C22: second cooling flow path
C13, C23: 3rd cooling channel
LE: leading edge
TE: Trailing Edge
S1: suction side
S2: pressure side

Claims (15)

Sidewalls forming an inner space;
A turning space formed inside the wall of the side wall to induce a swirl;
An internal flow path connected to the orbiting space in the wall of the side wall to provide a passage for moving the refrigerant, and connected to the orbiting space in a direction eccentric with respect to a central axis of the orbiting space; And
Includes; an injection passage connected to the orbiting space and discharging the refrigerant introduced into the orbiting space,
A plurality of the turning spaces are formed inside the sidewall, and the inner flow path connects the turning spaces,
The inner flow path has an inlet through which the refrigerant flows from the orbiting space into the internal flow path and an outlet through which the refrigerant discharges into the orbiting space, and the inlet is located higher than the outlet,
The inner flow path is formed to be inclined with respect to the height direction of the orbiting space, and receives refrigerant from an upper portion of the orbiting space and supplies the refrigerant to a lower portion of the orbiting space. delete delete The method of claim 1,
The injection flow path is an airfoil connected to the turning space further below the inlet. The method of claim 1,
An airfoil formed in which the cross-sectional area of the outlet is smaller than that of the inlet. The method of claim 1,
The turning space has a circular cross section, and the inner flow path is an airfoil connected to the turning space in a tangential direction of the turning space. The method of claim 1,
An airfoil in which a guide protrusion is formed in the orbiting space in a spiral manner to induce a swirl. The method of claim 1,
The airfoil is formed with a guide groove that leads to a swirl in a spiral shape in the turning space. The method of claim 1,
Inside the airfoil, a plurality of cooling channels are formed that extend in the height direction and through which the refrigerant moves,
The inner flow path and the turning space are airfoils formed only on a sidewall surrounding a cooling flow path formed adjacent to a leading edge. The method of claim 9,
An airfoil in which a plurality of turning spaces connected by the inner flow path is formed inside the sidewall, and an introduction flow path connected to the cooling flow path to supply a refrigerant to the turning space in any one of the connected turning spaces. The method of claim 1,
An airfoil in which a plurality of spray passages spaced apart in a height direction of the turning space are connected to one of the turning spaces. The method of claim 11,
Airfoils in which injection passages connected to one of the turning spaces are connected in different directions. A turbine comprising a rotatable rotor disk and a plurality of turbine blades installed on the rotor disk,
The turbine blade is formed in a wing shape and includes an airfoil having a leading edge and a trailing edge, a platform portion coupled to a lower portion of the airfoil, a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil,
Sidewalls forming a cooling passage;
A turning space formed inside the wall of the side wall to induce a swirl;
An internal flow path connected to the orbiting space in the wall of the side wall to provide a passage for moving the refrigerant, and connected to the orbiting space in a direction eccentric with respect to a central axis of the orbiting space; And
A jet passage connected to the turning space and discharging the refrigerant introduced into the turning space;
Including,
A plurality of the turning spaces are formed inside the sidewall, and the inner flow path connects the turning spaces,
The inner flow path has an inlet through which the refrigerant flows from the orbiting space into the internal flow path and an outlet through which the refrigerant discharges into the orbiting space, and the inlet is located higher than the outlet,
The inner flow path is formed to be inclined with respect to a height direction of the orbiting space to receive a refrigerant from an upper portion of the orbiting space and supply the refrigerant to a lower portion of the orbiting space. delete The method of claim 13,
An introduction flow path connected to the inside of the airfoil to supply a refrigerant to the orbiting space is formed in the turning space,
The injection flow path is connected to the turning space at a lower portion than the inlet, and the introduction flow path is connected to the turning space at a lower portion than the injection flow path.

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