KR101408330B1 - lubricating and cooling test apparatus for high temperature turbines air foil bearing - Google Patents

Abstract

The present invention relates to a device for testing the lubricating and cooling performances of an air foil bearing by simulating a turbo charger in which a high temperature turbine is embedded. The present invention comprises a rotation driving part for generating rotation force; a rotary body having a shaft connected to a rotary shaft of the rotation driving part to rotate, and a circular disc for a high-temperature turbine and a circular disc for low-temperature compression formed on the front and rear ends of the shaft; a housing including a turbine chamber which has an inflow port formed on one side to introduce air, and in which the disc for a high-temperature turbine is accommodated, a compression chamber which has a supply port formed on the other side to supply the air, and in which the disc for low-temperature compression is accommodated, and hollow parts which connect the compression chamber and the turbine chamber, and through which the shaft penetrates, and in which multiple outlets communicating with the outside to introduce external air or discharge internal air are formed; radial air foil bearings interposed between the shaft and the hollow parts of the housing; and compressors for supplying the compressed air to the inflow port and the supply port of the housing.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a lubricating and cooling test apparatus for an airfoil bearing for a high temperature turbine,

The present invention relates to a lubrication and cooling test apparatus for an airfoil bearing for a high temperature turbine, and more particularly to a device for simulating a turbocharger with a high temperature turbine and for testing the lubrication and cooling performance of the airfoil bearing.

BACKGROUND ART So-called 'gas bearings', which bear rotating shafts of high-speed rotating equipments such as compressors, turbines, superchargers and the like, and use air or gaseous fluid as a working fluid without using lubricating oil, And dynamic pressure bearings.

A hydrostatic bearing is a type in which air or gas pressurized by an external compressor is fed between bearings to obtain a load bearing capacity. Instead of requiring a pressure source (external pressurizing device), the shaft can be lifted Therefore, it is possible to avoid bearing damage due to solid friction.

On the other hand, the dynamic pressure bearing is a type that obtains the load capacity by pulling the air or gas around the bearing between the bearings by the rotation of the shaft to increase the pressure. It does not require a separate pressure source, As solid friction occurs, bearing life is shortened. To prevent this, it is necessary to coat the bearing surface with a solid lubricant.

Among the hydrodynamic bearings, Air Foil Bearing (Air Foil Bearing) is a type of air bearing which uses air as lubricant for supporting rotation. It supports rotating body and load by dynamic pressure generated by relative motion between rotating body and foil do. Airfoil bearings can be used for small or light turbomachine bearings because they can rotate at high speed and can be used in various fields such as turbocharger, gas compressor, turbo blower, air cycle machine and so on.

Since Air Foil Bearing uses low viscosity air as a lubricant, it can be supplemented by applying a solid lubricant coating on the friction surface to prevent damage to the low viscosity of the lubricant during solid contact.

In particular, unlike conventional hydrodynamic bearings, airfoil bearings can actively change the shape of the foil according to the pressure distribution generated inside and external load conditions. Therefore, it can be used not only as a high-speed rotation but also as an air bearing with a high load condition.

Such an airfoil bearing generates a lot of heat during operation because the rotating shaft rotates at a high speed and the air pressure gradient changes abruptly in a small gap between the rotating shaft and the bearing sleeve.

At this time, if the generated heat is not properly cooled, stable and smooth rotation of the rotating shaft can not be guaranteed, and the materials coated on the surface of the product can be damaged.

Therefore, in the prior art, a method of supplying air for cooling to the space between the rotating shaft and the bearing sleeve has been applied, but in this case, since the cooling of the rotating shaft is not smooth, the rotation stability of the rotating shaft is deteriorated. There is a problem in that it is difficult to evaluate the bearing performance, especially the durability life, such as lubrication and cooling of the airfoil bearing used in a high-speed rotating device.

As a result, it is required to develop a device capable of evaluating the performance of the airfoil bearing by simulating the condition of the turbocharger with the high temperature turbine, but a reliable test device has not been developed yet.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and it is an object of the present invention to more accurately evaluate the lubrication and cooling performance of an airfoil bearing by simulating a high temperature turbine device such as a turbocharger, etc., in which an airfoil bearing used in a high- The present invention has been made to solve the above problems.

According to an aspect of the present invention, there is provided a turbine for a high-temperature turbine, comprising: a rotary driving unit for generating a rotating force; a shaft connected to the rotary shaft of the rotary driving unit to rotate; A turbine chamber in which the high temperature turbine disk is accommodated and a supply port through which air is supplied are formed on the other side of the turbine chamber, And a hollow portion that connects the compression chamber and the turbine chamber and passes through the shaft and communicates with the outside to form external air or a plurality of outlets through which the internal air escapes, A radial airfoil bearing interposed between the hollow portions of the housing; And a compressor for supplying.

According to an embodiment of the present invention, the plurality of radial airfoil bearings are spaced apart from each other, and the entrance is formed on both sides of the respective radial airfoil bearings.

According to an embodiment of the present invention, the housing includes a tip member forming a turbine chamber and a hollow portion therein, a tip member forming a flange along a circumferential direction on an outer side formed with the hollow portion, A rear end member forming a flange along a circumferential direction on the other side formed with the hollow portion, and a ring-shaped connecting member sandwiched between flanges of the front end member and the rear end member to connect the front end member and the rear end member And the front end member and the hollow portion of the rear end member are connected in a straight line.

According to an embodiment of the present invention, a thrust disk accommodated between the flange of the leading end member and the trailing end member is formed in the shaft, and a thrust airfoil bearing is interposed between the flange of the leading end member and the trailing end member and the thrust disc. do.

According to an embodiment of the present invention, the connecting member is provided with an inlet for supplying external air to the thrust airfoil bearing or for discharging internal air to the outside.

The airfoil bearing used in the high-speed rotating high-temperature turbine is tested under the same conditions as the actual high temperature turbine by the lubrication and cooling test apparatus of the airfoil bearing for high temperature turbine of the present invention as described above, The lubrication and cooling performance of the compressor can be evaluated.

In addition, in order to smoothly operate the shaft rotating at a high speed, radial airfoil bearings installed in the radial direction as well as axially mounted thrust airfoil bearings supporting the axial load of the shaft can be evaluated There is also.

1 is a perspective view of a lubrication and cooling test apparatus for an airfoil bearing for a high temperature turbine according to an embodiment of the present invention,
FIG. 2 is a sectional view showing an example of a path through which external air is introduced and internal air is discharged in the configuration of FIG. 1;
FIG. 3 is a cross-sectional view showing another example of a path through which external air is injected and internal air is discharged in the configuration of FIG. 1;
Fig. 4 is a perspective view showing the radial airfoil bearing of Fig. 1 taken as an excerpt. Fig.
5 is a perspective view of a lubrication and cooling test apparatus for an airfoil bearing for a high temperature turbine according to another embodiment of the present invention.

The present invention will now be described in detail with reference to the accompanying drawings. Here, the same reference numerals are used for the same components, and repeated descriptions and known functions and configurations that may obscure the gist of the present invention will not be described in detail. Embodiments of the present invention are provided to more fully describe the present invention to those skilled in the art. Accordingly, the shapes and sizes of the elements in the drawings and the like can be exaggerated for clarity.

FIG. 1 is a perspective view of a lubrication and cooling test apparatus for an airfoil bearing for a high-temperature turbine according to an embodiment of the present invention. FIG. 2 shows an example of a path through which external air is introduced and internal air is discharged Sectional view.

An apparatus for lubricating and cooling an airfoil bearing for a high temperature turbine according to an embodiment of the present invention is a device for testing a lubricating and cooling performance of an airfoil bearing by simulating a turbocharger with a high temperature turbine built therein, A housing 300 accommodating the rotating body 200 in an inner space of the housing 300; a housing 300 housed in the inner space of the housing 300; Air foil bearings 410 and 420 interposed between the rotating body 300 and the rotating body 200 for reducing frictional force and a compressor 500 for supplying compressed air to the front and rear ends of the housing 300.

The rotation driving unit 100 is connected to the shaft 210 to provide a rotating force and functions as a turbine for rotating the shaft 210 in the actual apparatus. Or a motor that directly rotates the motor. When the rotation driving unit 100 is provided as a motor, a separate inverter may be provided to control the rotational speed and output of the motor.

The rotary body 200 includes a shaft 210 connected to the rotary shaft of the rotary drive unit 100 to rotate and a disk 221 for a high temperature turbine formed in the circumferential direction at the front and rear ends of the shaft 210, And a low-temperature compression disk 222. The shaft 210 rotates in conjunction with the rotation shaft of the rotary drive unit 100 and functions as a shaft connected to the turbine and the impeller in an actual turbocharger. The high-temperature turbine disk 221 and the low-temperature compression disk 222 are connected to the shaft 210 and rotate at the same time. The turbine chamber 311 and the compression chamber 321 of the housing 300, And serves as a turbine and an impeller in the actual turbocharger.

The housing 300 includes an inlet 312 through which air flows and a turbine chamber 311 in which the high temperature turbine disk 221 is received and a supply port 322 through which air is supplied, A compression chamber 321 in which the low temperature compression disk 222 is accommodated and a compression chamber 321 in which the compression chamber 321 and the turbine chamber 311 are connected and the shaft 210 is passed, And hollow portions 313 and 323 for forming a plurality of outlets 314 and 324 through which the inner air escapes.

The housing 300 may have a cylindrical shape in which a turbine chamber 311, a compression chamber 321 and hollow portions 313 and 323 are formed and an inlet 312 for communicating with the outside of the turbine chamber 311, And a supply port 322 for communicating with the outside of the compression chamber 321 is formed on the other side. At this time, a shaft connecting hole 323 through which the shaft 210 is inserted may be formed at the center of the shaft receiving hole 322.

The diameters of the turbine chamber 311 and the compression chamber 321 are the same or similar to the diameters of the high temperature turbine disk 221 and the low temperature compression disk 222. The diameters of the hollow portions 313, Is larger than the diameter of the shaft (320). This is to ensure a space in which the radial airfoil bearing 410 described later is fitted. The diameters of the hollow portions 313 and 323 are smaller than the diameters of the turbine chamber 311 or the compression chamber 321. Meanwhile, the housing 300 may have a plurality of outlets 314 and 324 for allowing the hollows 313 and 323 to communicate with the outside. The outlets 314 and 324 can act as a passage for introducing outside air into the hollow portions 313 and 323 or discharging the air in the hollow portions 313 and 323 to the outside.

FIG. 3 is a cross-sectional view illustrating another example of a path through which external air is introduced and internal air is discharged in the configuration of FIG. 1, and FIG. 5 is a schematic view of a lubrication and cooling test apparatus for an airfoil bearing for a high temperature turbine according to another embodiment of the present invention FIG. As shown in the drawing, the lower housing 300 and the housing 300 can be supported by a separate mounting frame 600, and a ring 340 for lifting with a wire or the like can be formed at the upper end.

According to an embodiment of the present invention, a pump (not shown) for generating compressed air to be supplied to the housing 300 and compressed air generated from the pump are transferred to the entrance ports 314, 324, and 334 of the housing 300 (Not shown). The injection means may be provided with a hose or the like, and high pressure air generated by the pump may be injected into the outlets 314, 324, and 334 of the housing 300 to cool the airfoil bearings 410 and 420. Meanwhile, when the compressed air generated in the pump is injected into the outlets 314, 324, and 334 of the housing 300, the pressure and temperature of the air to be injected are adjusted, and the cooling performance and the lubrication performance thereof are evaluated, Pressure and temperature with performance and lubrication performance can be measured.

The radial airfoil bearing 410 is interposed between the shaft 210 and the hollow portions 313 and 323 of the housing 300. The radial airfoil bearing 410 serves to support a radial load of the shaft 210. That is, in order to smoothly operate the shaft 210 rotating at high speed, a radial airfoil bearing 410 is installed in the radial direction, and a thrust airfoil bearing 420, which will be described later, is installed in the axial direction.

Fig. 4 is a perspective view showing the radial airfoil bearing of Fig. 1 taken as an excerpt. Fig. For example, the radial airfoil bearing 410 includes a hollow bearing housing 411 into which the shaft 210 is inserted, a foil 420 inserted between the inner surface of the bearing housing 411 and the shaft 210, And a plurality of slots 413 formed on the inner surface of the bearing housing 411 so as to be bent inwardly and press-fit inwardly in an end portion 412a of the foil 412. The radial airfoil bearing 410 according to the present invention has been described as including the bearing housing 411 and the foil 412 and the slot 413 but is not limited thereto and other known And can be adopted as any one of airfoil bearings having various structures.

The compressor 500 supplies compressed air to the inlet 312 and the inlet 322 of the housing 300. In order to simulate the high-pressure state of the turbocharger in which the high-temperature and high-pressure exhaust gas flows into the turbine chamber 311 and the turbine rotates, the turbine rotates the shaft 210, To simulate the situation of the compression chamber 321 in which the impeller is rotated to introduce external air and then compress it to a high pressure. In the case of the turbine chamber 311, a separate heating means for heating the compressed air to be supplied to the compressor 300 or the housing 300 adjacent to the compressor 500 or the turbine chamber 311, Or a conveyance pipe connecting the compressor 500 and the turbine chamber 311. In addition,

According to an embodiment of the present invention, a vibration sensor and a temperature sensor 800 may be mounted inside or outside the housing 300 or the radial airfoil bearing 410. First, when the vibration sensor is provided, a rotational force is generated through the rotation driving unit 100, and the vibration generated in the housing 300 or the radial airfoil bearing 410 when the shaft 210 rotates at a high speed The lubrication performance of the radial airfoil bearing 410 can be evaluated and the temperature of the air discharged through the outlets 314 and 324 can be measured when the temperature sensor 800 is mounted It is possible to evaluate the cooling performance of the radial airfoil bearing 410 by sensing the temperature inside or outside the radial airfoil bearing 410.

According to an embodiment of the present invention, the plurality of radial airfoil bearings 410 are spaced apart from each other, and the outlets 314 and 324 are formed on both sides of the respective radial airfoil bearings 410 . When a plurality of radial airfoil bearings 410 are installed as described above, the load in the radial direction of the shaft 210 can be more stably supported. When a plurality of outlets 314 and 324 are formed in the housing 300, external air for cooling can be uniformly injected into both sides of the radial airfoil bearing 410, and the radial airfoil bearing 410, So that the cooling efficiency can be enhanced. The position and number of the outlets 314 and 324 can be adjusted by analyzing the temperature change of the air discharged from the outlets 314 and 324.

According to an embodiment of the present invention, the housing 300 includes the turbine chamber 311 and a hollow portion 313 formed therein. The hollow portion 313 is formed on one side of the housing 300 in a circumferential direction A flange 315 and a compression chamber 321 and a hollow portion 323 formed in the compression chamber 321. The compression chamber 321 and the hollow portion 323 are formed on the other side of the hollow portion 323, And a rear end member 320 which is inserted between flanges 315 and 325 of the front end member 310 and the rear end member 320 to connect the front end member 310 and the rear end member 320, And includes a connecting member 330 and the front end member 310 and the hollow portions 313 and 323 of the rear end member 320 are connected in a straight line. The housing 300 may be formed as a single body, but may be formed of a front end member 310, a rear end member 320, and a connecting member 330 as described above. Therefore, the thrust disk 223 and the thrust airfoil bearing 420, which will be described later, can be positioned inside the housing 300. The front end member 310 and the rear end member 320 are disposed such that the flanges 315 and 325 face each other and the connecting member 330 is inserted between the flanges 315 and 325 and the flanges 315 and 325 The housing 300 can be formed by fastening the connecting member 330.

According to an embodiment of the present invention, the shaft 210 is provided with a thrust disc 223 accommodated between the front end member 310 and the flanges 315 and 325 of the rear end member 320, A thrust air foil bearing 420 is interposed between the thrust disk 223 and the flanges 315 and 325 of the rear end member 320 and the thrust disk 223. Therefore, it is possible to face the thrust disk 223 to cope with the thrust. That is, a radial airfoil bearing 410 is installed in the radial direction and a thrust airfoil bearing 420 is installed in the axial direction for smooth operation of the shaft 210 rotating at high speed.

According to an embodiment of the present invention, the connecting member 330 is provided with an inlet 334 for supplying external air to the thrust airfoil bearing 420 or discharging internal air to the outside. The entrance 334 may serve as a passage for introducing outside air into the connecting member 330 or discharging the air inside the connecting member 330 to the outside. As a result, external air for cooling can be uniformly injected into the thrust airfoil bearing 420 due to the entrance 334 formed in the connecting member 330, and the internal air of the thrust airfoil bearing 420 is discharged to the outside So that the cooling efficiency can be improved. Thereafter, the position and number of the entrance 334 can be adjusted by analyzing the temperature change of the air discharged from the entrance 334.

According to the present invention as described above, the airfoil bearing used for the high-speed rotating high-temperature turbine is tested under the same conditions as the actual high temperature turbine by the lubrication and cooling test apparatus for the airfoil bearing for the high temperature turbine, The advantage of being able to evaluate the lubrication and cooling performance of the foil bearing.

It will be apparent to those skilled in the art that various modifications, substitutions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. will be. Therefore, the embodiments disclosed in the present invention and the accompanying drawings are intended to illustrate and not to limit the technical spirit of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments and the accompanying drawings . The scope of protection of the present invention should be construed according to the following claims, and all technical ideas falling within the scope of the same shall be construed as falling within the scope of the present invention.

100:
200: rotating body
210: shaft
221: Disc for high temperature turbine
222: Low-temperature compression disk
223: Thrust disc
300: housing
310:
311: Turbine room
312: inlet
313, 323: hollow part
314, 324, 334:
315,325: Flange
320: rear end member
321: compression chamber
322: Supply port
323:
330: connecting member
410: Radial airfoil bearing
420: Thrust airfoil bearing
500: Compressor

Claims (5)

The present invention relates to an apparatus for testing an optimum performance condition of an airfoil bearing mounted on a high-speed turbine rotating at high speed,
A rotation driving unit for generating a rotation force;
A shaft rotatably connected to the rotary shaft of the rotary drive unit; a rotary disk including a disk for a high temperature turbine and a disk for low temperature compression, the disk being formed at a front end and a rear end of the shaft;
A turbine chamber in which an air inlet is formed at one side and a turbine chamber in which the high temperature turbine disk is accommodated and a supply port through which air is supplied, And a hollow portion through which the shaft passes and which communicates with the outside to introduce outside air or a plurality of outlets through which the inside air escapes;
A radial airfoil bearing interposed between the shaft and the hollow portion of the housing;
And a compressor for supplying compressed air to the inlet and the supply port of the housing. The method according to claim 1,
Wherein the plurality of radial airfoil bearings are spaced apart from each other and the entrance is formed on both sides of each of the radial airfoil bearings. The apparatus of claim 1, wherein the housing comprises:
A tip member forming a turbine chamber and a hollow portion therein and forming a flange in a circumferential direction on an outer side of the hollow portion;
A rear end member forming a compression chamber and a hollow portion therein and forming a flange in a circumferential direction on the other side formed with the hollow portion;
And a ring-shaped connecting member which is inserted between flanges of the distal end member and the rear end member and connects the distal end member and the rear end member, and the hollow member of the distal end member and the rear end member are connected in a straight line. Bearing lubrication and cooling test equipment. The method of claim 3,
Wherein a thrust disk accommodated between the flange of the front end member and the rear end member is formed in the shaft and a thrust airfoil bearing is interposed between the flange of the front end member and the rear end member and the thrust disk. Lubricating and cooling test equipment for foil bearings. The method of claim 4, wherein
Wherein the connecting member is provided with an inlet for supplying external air to the thrust airfoil bearing or for discharging internal air to the outside.

Images