KR20200114638A - Air foil bearing - Google Patents

Abstract

An object of the present invention is to improve the cooling performance of an airfoil bearing by increasing heat exchange efficiency of the surrounding air. To this end, the present invention provides an airfoil bearing comprising: first and second airfoil plates disposed on both sides of a rotor disk and supporting rotation of the rotor disk in both directions; and an air cooling means for cooling air which has passed through the first airfoil plate and introducing the same into the second airfoil plate.

Description

Air foil bearing

The embodiment relates to an airfoil bearing.

A bearing is a mechanical element that fixes a rotating shaft at a certain position and supports the shaft's own weight and load applied to the shaft so as to rotatably support it. For example, a ball bearing or journal bearing is a method of supporting a shaft using an oil film, and a foil bearing is a bearing of a method of supporting the shaft by forming a high-pressure air layer between the top foil and the shaft.

When the rotor rotates at high speed, air, a viscous fluid, is introduced between the rotor or the bearing disk and the contacting foil to form pressure to support the axial load.

Since the airfoil bearing is effective in supporting a rotating shaft rotating at a high speed, it can be applied to a rotating shaft rotating at a high speed in rotating equipment such as a turbo compressor, a turbo cooler, a turbo generator, and an air compressor.

The airfoil bearing includes a plate, a bump foil disposed on the plate and elastically deformable, and a top foil on the bump foil in contact with the rotating portion. At this time, the bump foil and the top foil are joined on the plate by welding, which requires additional press processing and welding processing processes, and an effort such as welding quality control is required, which increases the product cost of the bearing. Accordingly, an airfoil bearing having a structure that can be assembled without a welding process has been proposed.

In this regard, Korean Patent Registration No. 10-1558489 (registered on October 1, 2015) discloses an assembly-type airfoil bearing, and according to the disclosed contents, the airfoil bearing includes a lower plate having a coupling part and a lower plate of the lower plate. A bump foil plate provided with a bump foil disposed on an upper surface to be elastically deformable and coupled to the coupling portion, and an air foil plate coupled to the coupling portion by having a top foil disposed on the upper surface of the bump foil plate and in contact with the rotating portion. Include.

When the airfoil bearing is driven, overheated internal air is discharged to one side, and the overheated air is cooled by heat exchange from the outside and introduced to the other side. In this case, when the air flow is not smooth or the heat exchange of the flowing air is insufficient, the cooling function is deteriorated, causing deformation of the airfoil bearing, thereby deteriorating the bearing performance.

Korean Patent Registration No. 10-1558489 (registered on October 1, 2015)

An object of the present invention is to improve the cooling performance of an airfoil bearing by increasing the heat exchange efficiency of the surrounding air. In particular, the present invention is characterized by improving heat exchange efficiency by flowing air that has passed through the bearing in an air foil bearing manufactured by simply laminating without welding foil plates (top foil, bump foil, etc.).

The problem to be solved by the present invention is not limited to the problems mentioned above, and other problems that are not mentioned herein will be clearly understood by those skilled in the art from the following description.

The embodiment includes: first and second airfoil plates disposed on both sides of a rotor disk and supporting rotation of the rotor disk in both directions; And air cooling means for cooling the air that has passed through the first airfoil plate and then flowing it into the second airfoil plate.

Preferably, the air cooling means may be disposed outside the rotor disk between the first and second airfoil plates.

Preferably, the air cooling means cools the air by forming a turbulent flow in the air that has passed between the rotor disk and the first airfoil plate, and forms a laminar flow in the cooled air to form a laminar flow between the rotor disk and the first airfoil plate. 2 It can flow through the airfoil plate.

Preferably, the air cooling means may have a plurality of air through-holes extending in a radial direction of rotation of the rotor disk on a side thereof and inclined toward a radial direction.

Preferably, the plurality of air through holes may be inclined in a direction opposite to the rotation direction of the rotor disk.

Preferably, the air cooling means may include first and second ring plates spaced apart from each other, and a plurality of vanes connecting the first and second ring plates and forming the plurality of air through holes. have.

Preferably, the vanes are disposed to be inclined in a direction opposite to the rotation direction of the rotor disk, so that air moving outward from the rotor disk collides with the vanes to form turbulent flow.

Preferably, the vanes are disposed to form an angle of attack with respect to a reference line extending in a radial direction from the center of rotation of the rotor disk, and the angle of attack may be greater than 0° and less than 90°.

Preferably, a plurality of layers of turbulent flow are formed in the air passing between the rotor disk and the first airfoil plate to cool the air, and a plurality of layers of laminar flow are formed in the cooled air to form the rotor disk and the first airfoil plate. 2 It can flow through the airfoil plate.

Preferably, the air cooling means may have a plurality of air through-holes extending in a radial direction of rotation of the rotor disk and forming a plurality of layers that are inclined toward the radial direction.

Preferably, the plurality of air through holes may be inclined in a direction opposite to the rotation direction of the rotor disk.

Preferably, the air cooling means may include a plurality of ring plates of at least three or more spaced apart from each other, and a plurality of vanes disposed between the plurality of ring plates to form a plurality of layers of air through holes. have.

Preferably, the vanes are disposed to be inclined in a direction opposite to the rotation direction of the rotor disk, so that air moving outward from the rotor disk collides with the vanes, thereby forming turbulence.

Preferably, the vanes are arranged to form an angle of attack with respect to a reference line extending in a radial direction from the center of rotation of the rotor disk, and the angle of attack may be greater than 0° and less than 90°.

Preferably, the vanes may be characterized by forming different angles of attack for each stage.

Preferably, the first and second airfoil plates include first and second bumpfoil plates spaced apart from each other on each side of the rotor disk, and each of the first and second bumpfoil plates and the rotor disk. It may include first and second top foil plates respectively disposed between both surfaces.

According to the embodiment, turbulent or laminar flow is formed in the air passing through the airfoil plates on both sides of the rotor disk, effectively cooling the overheated air, and providing the cooled air smoothly in the airfoil bearing, Cooling performance can be improved.

According to an embodiment, air passing through a plurality of air through holes may generate a plurality of layers of turbulent or laminar flow, thereby further enhancing the air heat exchange efficiency of the airfoil bearing, thereby improving the airfoil bearing cooling performance. .

1 is a cross-sectional view showing an air compressor for a vehicle equipped with an airfoil bearing according to an embodiment of the present invention.
2 is a perspective view of an airfoil bearing according to an embodiment of the present invention.
3 is an exploded perspective view of an airfoil bearing according to an embodiment of the present invention.
4 is a side cross-sectional view of an airfoil bearing according to an embodiment of the present invention.
5 is a plan view of a first ring plate and vanes shown in FIG. 1;
Figure 6 is a bottom view of the second ring plate and vane shown in Figure 1;
7 is a perspective view of an airfoil bearing according to another embodiment of the present invention.
8 is an exploded perspective view of an airfoil bearing according to another embodiment of the present invention.
9 is a cross-sectional view of an airfoil bearing according to another embodiment of the present invention.
10 is a side cross-sectional view of an air cooling means of an airfoil bearing according to another embodiment of the present invention.
11 is a cross-sectional view taken along AA′ of FIG. 10.
12 is a cross-sectional view taken along BB′ of FIG. 10.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

However, the technical idea of the present invention is not limited to some embodiments to be described, but may be implemented in various different forms, and within the scope of the technical idea of the present invention, one or more of the constituent elements may be selectively selected between the embodiments. It can be combined with and substituted for use.

In addition, terms (including technical and scientific terms) used in the embodiments of the present invention are generally understood by those of ordinary skill in the art, unless explicitly defined and described. It can be interpreted as a meaning, and terms generally used, such as terms defined in a dictionary, may be interpreted in consideration of the meaning in the context of the related technology.

In addition, terms used in the embodiments of the present invention are for describing the embodiments and are not intended to limit the present invention.

In the present specification, the singular form may include the plural form unless specifically stated in the phrase, and when described as "at least one (or more than one) of A and (and) B and C", it is combined with A, B, and C. It may contain one or more of all possible combinations.

In addition, terms such as first, second, A, B, (a), and (b) may be used in describing the constituent elements of the embodiment of the present invention.

These terms are only for distinguishing the component from other components, and are not limited to the nature, order, or order of the component by the term.

And, when a component is described as being'connected','coupled' or'connected' to another component, the component is not only directly connected, coupled or connected to the other component, but also the component and It may also include the case of being'connected','coupled' or'connected' due to another component between the other components.

In addition, when it is described as being formed or disposed in the "top (top) or bottom (bottom)" of each component, the top (top) or bottom (bottom) is one as well as when the two components are in direct contact with each other. It also includes a case in which the above other component is formed or disposed between the two components. In addition, when expressed as "upper (upper) or lower (lower)", the meaning of not only an upward direction but also a downward direction based on one component may be included.

1 is a cross-sectional view showing an air compressor for a vehicle equipped with an airfoil bearing according to an embodiment of the present invention. Below. The inside represents the direction toward the axis center based on the radial direction of the motor, and the outside represents the opposite direction of the inside.

Referring to FIG. 1, an air foil bearing 1 according to an embodiment of the present invention is installed in a mechanical device having a rotating shaft rotating at high speed. In the present embodiment, an example in which the airfoil bearing 1 is installed to support the rotational shaft 65 of the blower motor mounted on the air compressor will be described as an example.(However, this description is only an example, a mechanical device having a rotating shaft. It can be applied anywhere).

An air compressor for a vehicle includes a housing (H) forming an exterior, an impeller 40 coupled to the front of the housing (H) to compress air, an impeller receiving portion 20 accommodating the impeller 40, and an impeller housing ( 30), a rear cover 50 coupled to the rear of the housing H, and a blower motor 60 installed inside the housing H to rotate and drive the impeller 40.

An air inlet 31 through which external air is introduced is formed in the front center of the impeller housing 30, and air discharge ports 33 are formed on both sides of the front side. The impeller 40 is installed inside the impeller housing 30, and the rotation shaft 65 of the blower motor 60, which will be described later, is coupled to the hollow penetrating the impeller 40. That is, the impeller 40 is supported by the rotation shaft 65. The air sucked through the air inlet 31 by the impeller 40 is compressed by the impeller 40 and discharged to the air outlet 33.

The blower motor 60 is inserted into the motor housing 60a inserted inside the housing H. The blower motor 60 is installed adjacent to the inner circumferential surface of the motor housing 60a and has a stator 63 having a hollow (not shown), a rotation shaft 65 installed through the hollow of the stator 63, and a rotation shaft ( It consists of a rotor that is coupled to the outer peripheral surface of 65).

The rotary shaft 65 can be rotated inside the housing (H) by the airfoil bearing (1) and journal bearing (75) installed at the rear of the impeller (40) with one end coupled to the hollow of the impeller (40) And the rear end is also rotatably supported by the rear bearing 80.

Hereinafter, with reference to the accompanying drawings will be described in detail with respect to the airfoil bearing 1 according to the embodiment.

Figure 2 is a perspective view of an airfoil bearing according to a first embodiment of the present invention, Figure 3 is an exploded perspective view of the airfoil bearing according to the first embodiment of the present invention, and Figure 4 is a first embodiment of the present invention. It is a side view of the airfoil bearing according to this.

2 to 4, the airfoil bearing 1 according to an embodiment of the present invention is installed on the rotor disk R to support the rotation of the rotor disk R. The airfoil bearing 1 includes first and second airfoil plates 100a and 100b and air cooling means 200.

The first and second airfoil plates 100a and 100b are disposed on both sides of the rotor disk R and serve to support the rotation of the rotor disk R in both directions.

Referring to FIG. 3, the first and second airfoil plates 100a and 100b may include first and second bump foil plates 110a and 110b and first and second top foil plates 120a and 120b. I can.

The first and second bump foil plates 110a and 110b may be spaced apart from each other on both sides of the rotor disk R. At this time, the first and second bump foil plates 110a and 110b can be elastically deformed in the axial direction of the rotor disk R. In this case, the first and second bump foil plates 110a and 110b may include bump foil plate portions 111a and 111b and bump foil portions 112a and 112b.

The bump foil plate portions 111a and 111b are formed in a circular disk shape. In this case, the bump foil plate portions 111a and 111b may include first members 1111a and 1111b, second members 1112a and 1112b, and third members 1113a and 1113b.

The first members 1111a and 1111b are formed in a ring shape to form a hollow through which the shaft portion of the rotor disk R passes.

The second members 1112a and 1112b are formed in a ring shape having a larger diameter than the first members 1111a and 1111b, and are spaced apart from the first members 1111a and 1111b in the radial direction. In this case, a plurality of first fasteners h1 may be formed in the second members 1112a and 1112b. Here, the first fixture h1 may be disposed to be spaced apart at 120° intervals with respect to the center of the rotor disk R.

The third members 1113a and 1113b are disposed radially with respect to the axis of rotation of the rotor disk R to connect the first members 1111a and 1111b and the second members 1112a and 1112b.

The bump foil portions 112a and 112b are plural, and are radially disposed in the space between the third members 1113a and 1113b. The plurality of bump foil portions 112a and 112b are spaced apart from each other at equal intervals. The bump foil portions 112a and 112b have a trapezoidal planar shape, and have a wave shape in which a plurality of peaks and valleys are alternately connected so as to be elastically deformed in the axial direction of the rotor disk R.

In this case, the first and second bump foil plates 110a and 110b may be manufactured by pressing a thin metal plate.

The first and second top foil plates 120a and 120b are disposed between the first and second bump foil plates 110a and 110b and both surfaces of the rotor disk R, respectively. In this case, the first and second top foil plates 120a and 120b may include top foil plate portions 121a and 121b and top foil portions 122a and 122b.

The top foil plate portions 121a and 121b are formed in a circular disk shape. In this case, the top foil plate portions 121a and 121b may include fourth members 1211a and 1211b, fifth members 1212a and 1212b, and sixth members 1213a and 1213b.

The fourth members 1211a and 1211b are formed in a ring shape to form a hollow through which the shaft portion of the rotor disk R passes. At this time, the fourth members 1211a and 1211b are disposed to face the first members 1111a and 1111b of the bump foil plate portions 111a and 111b.

The fifth members 1212a and 1212b are formed in a ring shape having a larger diameter than the fourth members 1211a and 1211b, and are spaced apart from the fourth members 1211a and 1211b in the radial direction. Also, the fifth members 1212a and 1212b are disposed to face the second members 1112a and 1112b of the bump foil plate portions 111a and 111b. In this case, the fifth members 1212a and 1212b may have a plurality of second fasteners h2 corresponding to the first fasteners h1.

The sixth members 1213a and 1213b are arranged radially with respect to the rotational axis of the rotor disk R, and the sixth members 1213a and 1213b connect the fourth members 1211a and 1211b and the fifth members 1212a and 1212b. do. At this time, the sixth members 1213a and 1213b are disposed to face the third members 1113a and 1113b of the bump foil plate portions 111a and 111b.

The top foil portions 122a and 122b are disposed between the sixth members 1213a and 1213b. One of the four sides of the top foil portions 122a and 122b is connected to the top foil plate portions 121a and 121b, and the other three sides are formed as free ends.

In this case, the first and second top foil plates 120a and 120b may be manufactured by pressing a thin metal plate.

The air cooling means 200 cools the air that has passed through the first airfoil plate 100a and then introduces it into the second airfoil plate 100b.

The air cooling means 200 is disposed between the first and second airfoil plates 100a and 100b, and may be disposed outside the rotor disk R.

The air cooling means 200 cools the air by forming a turbulent flow in the air that has passed between the rotor disk R and the first airfoil plate 100a, and forms a laminar flow in the cooled air to form the rotor disk ( It may be introduced between R) and the second airfoil plate 100b.

The air cooling means 200 may have a hollow 201 in which the rotor disk R is disposed, and may have a plurality of air through holes 202 extending in a radial direction by communicating with the hollow 201. At this time, the air through hole 202 extends in the radial direction of the rotor disk R, and may be formed to be inclined toward the radial direction. Preferably, the air through-hole 202 may be inclined in a direction opposite to the rotation direction of the rotor disk R.

The air cooling means 200 may include first and second ring plates 210 and 220 and a plurality of vanes 230.

5 is a plan view of the first ring plate and vanes shown in FIG. 1, and FIG. 6 is a bottom view of the second ring plate and vanes shown in FIG. 1.

The first and second ring plates 210 and 220 may be disposed on opposite surfaces of the first and second airfoil plates 100a and 100b, respectively, and may be spaced apart from each other. In this case, the separation distance H1 between the first and second ring plates 210 and 220 may be greater than the thickness H2 in the axial direction of the rotor disk R.

The first and second ring plates 210 and 220 may be arranged for an interview on the fifth members 1212a and 1212b. The first and second ring plates 210 and 220 may have a third fastener h3 corresponding to the second fastener h2.

The plurality of vanes 230 connect the first and second ring plates 210 and 220. The plurality of vanes 230 form an air through hole 202 and guide air passing through the air through hole 202. At this time, the vanes 230 are arranged to be inclined in a direction opposite to the rotation direction of the rotor disk R, so that the air passing through the air through holes 202 from the rotor disk R side collides with the vanes 230 and turbulent flow. Can be formed. That is, as shown in the figure, when the rotor disk R rotates in a clockwise direction, the vanes 413 are inclined to be inclined counterclockwise toward the outside. More preferably, each vane 230 may be disposed to form an angle of attack (∠a) with respect to a reference line extending in the radial direction from the rotation center of the rotor disk R. Here, the angle of attack (∠a) may be greater than 0° and less than 90°.

Referring to FIG. 5, air heated by the first airfoil plate 100a while the rotor disk R rotates passes through the top foil portion 122a of the first airfoil plate 100a. At this time, the air that has passed through the top foil part 122a exits to the outside through the air through hole 202 and collides with the inner surface of the vane 230 to form turbulence. In this case, the heated air is cooled through heat exchange with the surrounding air, and the heat exchange time may be extended due to turbulence.

In addition, referring to FIG. 6, the cooled air forms a laminar flow along the inclination of the vane 230 and is introduced between the rotor disk R and the second airfoil plate 100b to cool the second airfoil plate 100b. do. At this time, the cooled air increases the moving speed due to the laminar flow, and the contact with the second airfoil plate 100b may be more smooth.

With the same principle, the heated air that first passed between the rotor disk R and the second airfoil plate 100b is cooled by turbulence, and the cooled air is cooled by the rotor disk R and the first airfoil plate 100a. It is also possible to cool the first airfoil plate 100a while being sucked into.

When the airfoil plates are arranged on both sides of the rotor disk R, when the airfoil plate on one side is cooled and the heated air directly flows into the airfoil plate on the other side, the air temperature is overheated and the other side is The airfoil plate may not be cooled or, conversely, the temperature may increase. The airfoil bearing according to the present invention prevents the air from being overheated and provides the cooled air smoothly, thereby increasing the cooling efficiency of the airfoil bearing.

In the airfoil bearing according to the present invention, turbulent or laminar flow is formed while the surrounding air flows through the air through hole when the rotor is rotated, thereby increasing the heat exchange efficiency of the flowing air and improving the cooling performance of the airfoil bearing. .

The coupling means 400 couples the first and second airfoil plates 100a and 100b and the air cooling means 200. In this case, the coupling means 400 may include first and second airfoil plates 100a and 100b and a plurality of coupling pins 410 passing through the air cooling means 200. In this case, the plurality of coupling pins 410 may be spaced apart at 120° intervals based on the center of the rotor disk R. In more detail, the air cooling means 200 may have a plurality of third fasteners h3 extending in the axial direction corresponding to the second fastener h2. At this time, the coupling pin 410 passes through the first fastener h1, the second fastener h2, and the third fastener h3 arranged to overlap.

Hereinafter, with reference to the accompanying drawings will be described in detail with respect to the airfoil bearing 2 according to another embodiment.

7 is a perspective view of an airfoil bearing according to another embodiment of the present invention, Figure 8 is an exploded perspective view of an airfoil bearing according to another embodiment of the present invention, and Figure 9 is an airfoil according to another embodiment of the present invention A side cross-sectional view of the bearing, and FIG. 10 is a side cross-sectional view of an air cooling means of an airfoil bearing according to another embodiment of the present invention.

Referring to FIGS. 7 to 10, the airfoil bearing 2 may include an air cooling means 300 for generating a plurality of layers of turbulent or laminar flow.

The air cooling means 300 cools the air by forming a plurality of layers of turbulent flow in the air that has passed between the rotor disk R and the first airfoil plate 100a, and creates a plurality of layers of laminar flow in the cooled air. It may be formed to be introduced between the rotor disk R and the second airfoil plate 100b.

The air cooling means 300 may have a hollow 301 in which the rotor disk R is disposed, and may have a plurality of air through holes 302 extending in a radial direction by communicating with the hollow 301. Accordingly, the rotor disk R is disposed inside the air cooling means 300, and air around the rotor disk R may be discharged or introduced through the air through hole 302.

The air through-hole 302 extends in the radial direction of the rotor disk R and may be inclined toward the radial direction. At this time, the air through-hole 302 may be inclined in a direction opposite to the rotation direction of the rotor disk R.

The air cooling means 300 may include a plurality of ring plates 310, 320, 330 and vanes 340.

At least three or more ring plates 310, 320, and 330 may be provided. At this time, the plurality of ring plates 310, 320, 330 are spaced apart at equal intervals. Here, the sum (H3) of the separation distances of the plurality of ring plates (310, 320, 330) is formed larger than the axial thickness (H2) of the rotor disk (R). In this case, among the plurality of ring plates 310, 320, and 330, the plate 320 disposed in the middle may be formed thicker than the ring plates 310 and 330 disposed on both sides.

The plurality of vanes 340 are disposed between the plurality of ring plates 310, 320, and 330. At this time, the plurality of vanes 340 form a plurality of layers in the direction of the rotation axis of the rotor disk R. That is, in the case of the three ring plates 310, 320, and 330 as shown in the drawing, they may be arranged in two stages between the three ring plates 310, 320, and 330. For example, assuming that the plurality of plates 310, 320, and 330 are sequentially first, second and third plates, the plurality of vanes 340 are disposed between the first plate 310 and the second plate 320. A first vane 341 and a second vane 342 disposed between the second plate 320 and the third plate 330 may be included. Here, the first vane 341 and the second vane 342 may be disposed on the same line in the axial direction. Meanwhile, the first vane 341 and the second vane 342 may be disposed at alternate positions in the axial direction.

The plurality of vanes 340 form a plurality of air through holes 302 and guide air passing through the air through holes 302. Each vane 340 may be disposed to be inclined in a direction opposite to the rotation direction of the rotor disk R. At this time, turbulence may occur while air moving outward from the rotor disk R collides with the vanes 230. That is, when the rotor disk R rotates in a clockwise direction, the vanes 340 are inclined to face counterclockwise toward the outside. Here, the first vane 341 and the second vane 342 may have different inclinations.

11 is a cross-sectional view taken along line AA' of FIG. 10, and FIG. 12 is a cross-sectional view taken along line BB' of FIG.

11 and 12, the plurality of vanes 340 form an angle of attack (∠b) (∠c) based on a reference line extending in the radial direction from the rotation center of the rotor disk R. Here, the angle of attack (∠b) (∠c) may be greater than 0° and less than 90°. In this case, the vanes 413 are arranged in a plurality of layers, and may be arranged at different slopes for each stage. That is, the vanes 340 may form different angles of attack for each stage. For example, the angle of attack ∠b of the first vane 341 and the angle of attack ∠c of the second vane 342 may be different from each other.

According to the airfoil bearing 2 according to the present invention, while the rotor disk R rotates, the first airfoil plate 100a is cooled and the heated air passes through the air through hole 302. As turbulence is formed, the heat exchange time between the heated air and the outside air is extended, and the air can be cooled more quickly. In addition, while the cooled air flows back into the second airfoil plate 100b, a plurality of layers of laminar flow are formed by the inclination of the vane 340, thereby increasing the flow rate of the cooled air and a larger amount of cooling air. May flow into the second airfoil plate 100b.

The airfoil bearing according to the present invention forms a turbulent or laminar flow in the air passing through the airfoil plates on both sides of the rotor, effectively cooling the overheated air, and smoothly providing the cooled air in the airfoil bearing, It can improve the cooling performance of the foil bearing.

Although the above has been described with reference to preferred embodiments of the present invention, those skilled in the art will variously modify and change the present invention within the scope not departing from the spirit and scope of the present invention described in the following claims. You will understand that you can do it.

R: rotor disc
100a, 100b: first and second airfoil plates
110a, 110b: first and second bump foil plates
120a, 120b: first and second top foil plates
200,300: air cooling means
210,220,310,320,330: ring plate
230,340: Bain
341: first vane
342: second vane
400: coupling means
410: coupling pin

Claims (16)

First and second airfoil plates 100a and 100b disposed on both sides of the rotor disk R to support rotation of the rotor disk R in both directions; And
An airfoil bearing comprising an air cooling means (200) (300) for cooling the air that has passed through the first airfoil plate (100a) and introducing it into the second airfoil plate (100b). The method of claim 1,
The air cooling means (200) (300) is disposed between the first and second airfoil plates (100a, 100b), and is disposed outside the rotor disk (R). The method of claim 1,
The air cooling means 200,
Turbulent flow is formed in the air that has passed between the rotor disk R and the first airfoil plate 100a to cool the air, and a laminar flow is formed in the cooled air to form a laminar flow between the rotor disk R and the second airfoil plate 100a. An airfoil bearing, characterized in that flowing through the airfoil plate (100b). The method of claim 1,
The air cooling means 200,
An airfoil bearing having a plurality of air through-holes 202 extending in a radial direction of rotation of the rotor disk R on a side thereof and inclined toward a radial direction. The method of claim 4,
The plurality of air through holes 202 are inclined in a direction opposite to the rotation direction of the rotor disk R. The method of claim 4,
The air cooling means 200,
First and second ring plates 210 and 220 disposed spaced apart from each other,
An airfoil bearing comprising a plurality of vanes (230) connecting the first and second ring plates (210, 220) and forming the plurality of air through holes (202). The method of claim 6,
The vane 230 is disposed to be inclined in a direction opposite to the rotation direction of the rotor disk R,
Airfoil bearing, characterized in that turbulent flow is formed by the air passing through the air through hole (202) from the rotor disk (R) side collides with the vane (230). The method of claim 6,
The vanes 230 are arranged to form an angle of attack (∠a) with respect to a reference line extending in a radial direction from the rotation center of the rotor disk R,
Airfoil bearing, characterized in that the angle of attack (∠a) is greater than 0° and less than 90°. The method of claim 1,
The rotor disk (R) and the first airfoil plate (100a) form a plurality of layers of turbulent flow in the air to cool the air, and form a plurality of layers of laminar flow in the cooled air to form the rotor disk ( R) and the airfoil bearing, characterized in that inflow between the second airfoil plate (100b). The method of claim 9,
The air cooling means 300,
An airfoil bearing having a plurality of air through holes 302 extending in a radial direction of rotation of the rotor disk R and forming a plurality of layers inclined toward a radial direction. The method of claim 9,
The plurality of air through holes 302 are inclined in a direction opposite to the rotation direction of the rotor disk R. The method of claim 9,
The air cooling means 300,
At least three or more plurality of ring plates 310, 320, 330 spaced apart from each other, and
An airfoil bearing comprising a plurality of vanes (340) disposed between the plurality of ring plates (310, 320, 330) to form a plurality of layers of air through holes (302). The method of claim 12,
The vane 340 is disposed to be inclined in a direction opposite to the rotation direction of the rotor disk R,
Airfoil bearing, characterized in that turbulent flow is formed by the air passing through the air through hole (202) from the rotor disk (R) side collides with the vane (230). The method of claim 13,
The vanes 340 are arranged to form an angle of attack (∠b) (∠c) with respect to a reference line extending in the radial direction from the rotation center of the rotor disk R,
Airfoil bearing, characterized in that the angle of attack (∠b) (∠c) is greater than 0° and less than 90°. The method of claim 14,
The vane 340 is an airfoil bearing, characterized in that forming a different angle of attack (∠b) (∠c) for each stage. The method according to any one selected from claims 1 to 15,
The first and second airfoil plates 100a and 100b,
First and second bump foil plates 110a and 110b spaced apart from each other on both sides of the rotor disk R,
An airfoil bearing comprising first and second top foil plates 120a and 120b disposed between the first and second bump foil plates 110a and 110b and both surfaces of the rotor disk R, respectively.

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