KR100921324B1 - Structure of medium turbocharger bearing part through arrangement and selection of bearing - Google Patents

Abstract

The present invention relates to a structure of a bearing portion of a medium turbocharger (supercharger) used in a 4-stroke internal combustion engine, and an object thereof is fixed to a rotor shaft and a housing of a bearing portion between a turbine wheel and a compressor wheel. By selecting and arranging a number of bearings, it is to provide a structure that is effective in improving performance, maintenance and production.

The present invention is a structural improvement of the bearing portion through the effective selection and arrangement of a plurality of bearings provided for smooth rotation of the rotor shaft across the rotor shaft and the housing inside the turbocharger, the selection and arrangement of the bearing is the rotor shaft A radial bearing for supporting the radial reaction force of the shaft on the turbine shaft of the rotor, a labyrinth ring for maintaining the airtightness on the compressor shaft of the rotor shaft, and an exile for supporting the axial reaction force by reducing a portion of the rotor shaft diameter It is a summary that a thrust bearing is provided and a thrust bearing is provided which supports a bidirectional and radial reaction force of a shaft simultaneously in the outer side of the said eccentric bearing.

supercharger. 4-stroke, Turbocharger, Bearing, Array, Turbocharger, 4-Stroke, Bearing, Arrangement

Description

The Bearing Type and Arrangement for Turbocharger Bearing Part Structure}             

1 is an exemplary view illustrating a conventional bearing part structure consisting of one thrust bearing, two radial bearings and one distance sleeve, and one thrust ring;

2 is an exemplary view illustrating a conventional bearing part structure consisting of one thrust bearing, two radial bearings and one excile (secondary) bearing, and one thrust bearing;

Figure 3 is an exemplary view illustrating a conventional bearing structure consisting of one radial bearing, l radial / thrust composite bearing and one feather key, one thrust ring

4 is an exemplary view illustrating the present invention.

<Description of the symbols for the main parts of the drawings>

(1): Compressor Wheel

(2): labyrinth ring

(3): Distance sleeve

(4): Thrust Bearing

(5): Thrust Ring                 

(6): Radial Bearing

(7): Turbine Wheel

(8): Rotor Shaft

(9): Axial Bearing

(10): Feather Key

(11): Thrust & Radial Bearing

(12): Auxiliary Bearing

(13): labyrinth & thrust ring

The present invention relates to the selection and arrangement of bearings in a bearing housing part of a turbocharger for a medium-to-large machine. A structure of a series of bearings fixed to a rotor shaft and a housing is provided.

A conventionally configured turbocharger is largely a compressor Part, Bearing Part, Turbine Part, and more specifically, Compressor Housing, Compressor Wheel, Bearing, Bearing Housing, Rotor It consists of a shaft (Rotor Shaft), turbine housing (Turbine Housing), turbine wheel (Turbine Wheel).

It is fixed to the rotor shaft or the housing inside the double bearing housing part, and a series of bearings are used for smooth operation during the operation of the turbocharger. It also has a lot of influence in repair and production.

According to the drawings, for example, a labyrinth ring (2) is installed to maintain airtightness on the compressor wheel (1) side installed in the rotor shaft (8) as shown in FIG. The thrust bearing 4 and the thrust ring 5 which support the reaction force of the axial direction of 8) are provided. A distance sleeve 3 is installed between the thrust ring 5 and the labyrinth ring 2 to maintain the clearance between the two, and the radial bearing is provided with a compressor wheel to support the axial reaction force of the rotor shaft 8. On the compressor wheel side, the thrust ring is positioned and the turbine wheel side is positioned before the turbine wheel. In the above configuration, one labyrinth ring, two radial bearings, one thrust bearing, one thrust ring, and a distance sleeve are used to take a total of six parts. The distance sleeve maintains the clearance between the thrust ring and the labyrinth ring, but consequently increases the number of parts and induces slip, which adversely affects the mounting of the compressor wheel.

As another example, referring to FIG. 2, a labyrinth ring 2 is installed to maintain the airtightness of the compressor wheel 1 installed on the rotor shaft 8, and a radial bearing 6 to support the radial reaction force of the shaft. ), And the outer diameter of the rotor shaft is smaller than the opposite side of the compressor wheel (1), which causes the radial bearing (6) and the rotor shaft (8) to prevent the inner diameter of the radial bearings installed on both sides from being different. An eccentric (auxiliary) bearing 12 serving as an auxiliary role therebetween is provided, and a thrust bearing 4 and a thrust ring 5 are installed to support the reaction force in the axial direction. Finally, one radial bearing 6 is installed on the turbine wheel 7 side to support the radial reaction force of the shaft. In the above configuration, one labyrinth ring, two radial bearings, one axial (secondary) bearing, one thrust bearing, and one thrust ring are written on the bearing part, and six parts are used. And the thrust bearings behind them, eliminating the distance sleeves that led to slip, reducing slip and the overall size of the turbocharger. However, the outer diameter of the rotor shaft is reduced toward the compressor wheel. In this case, if the inner diameters of the radial bearings used on both sides are different, the overall performance will be reduced, so that the inner diameter of the radial bearings is equal to the inner diameter of the radial bearing. The bearings were installed to maintain the same inner diameter of the radial bearings on both sides of the turbine wheel and the compressor wheel.

Lastly, as an example, thrust / installing a labyrinth ring (2) to maintain airtightness on the compressor wheel (1) side of the rotor shaft (8), and simultaneously supporting both the bidirectional and radial reaction forces of the shaft. The radial bearing 11 and the thrust ring 5 for supporting the reaction force in the axial direction are provided. At the portion where the rotor shaft 8 and the thrust ring 5 come into contact with each other, a feather key 10 is provided to span the rotor shaft 8 and the thrust ring 5 to prevent slippage, and a radius is provided on the turbine wheel 7 side. A radial bearing 6 supporting the reaction force in the direction is provided. In the above configuration, one labyrinth ring, one radial bearing, one thrust / radial bearing, one feather key, and one thrust ring were used, reducing the number of parts compared to the two examples described above, but the thrust ring and labyrinth Since it was impossible to fix the friction between the rings, Feder key was inevitably added, which reduced the outer diameter of the rotor shaft. The inner diameter was different, resulting in performance loss.

The present invention is created to solve the above-mentioned problems, which is due to the reduction of the number of parts used in the selection and arrangement of the effective bearing and the performance of the radial bearings used on both sides of the turbine wheel and the compressor wheel. It is an object to provide a method for preventing degradation.

The present invention for achieving the above object is composed of a compressor wheel and a turbine wheel provided at each end of the rotor shaft and a plurality of bearings and rings of the rotor shaft.                     

In detail, the bearing part consisting of a rotor shaft 8 for rotating the compressor wheel 1 and the turbine wheel 7 and a series of bearings for supporting the rotor shaft 8 as shown in FIG. 1) the rotor shaft 8 of the type having a relatively small outer diameter of the compressor wheel 1 side compared to the turbine wheel 7 side due to the installation of a plurality of bearings,

The radial bearing 6 is installed on the turbine wheel 7 side of the rotor shaft 8 to support radial reaction force and the compressor wheel 1 side of the rotor shaft 8 to maintain airtightness. A labyrinth / thrust ring 13 supporting an axial reaction force applied from the compressor wheel 1 toward the turbine wheel 7;

The shaft coming from the turbine wheel 2 without compensating the outer diameter of the rotor shaft by compensating the outer diameter of the rotor shaft on the compressor wheel 1 side which is located next to the labyrinth / thrust ring 13 and whose outer diameter is smaller than the turbine wheel 7 side. An exile (secondary) bearing 12 supporting directional reaction force and radial reaction force,

Installed on the outside of the exile (secondary) bearing 12 and located next to the labyrinth / thrust ring 13, the axial reaction force and the radial reaction force applied from both the turbine wheel 7 and the compressor wheel 1 are applied. It is characterized by consisting of the supporting thrust / radial bearing (11).

When describing the operation of the present invention in the above configuration, the number of parts used is related to bearings: one labyrinth / thrust ring, one thrust / radial bearing, one exile (secondary) bearing, and one radial bearing. The total number of parts is 4, which uses 1 radial bearing and 1 thrust / radial bearing and 2 thrust bearings and labyrinth rings. With a labyrinth / thrust ring that combines the functionality into a single component, another component count is reduced, and the slip that occurs in conventional configurations is eliminated by the use of distance sleeves, and the wear between the two components is also eliminated.

In addition, due to the use of a number of different bearings, it is necessary to change the outer diameter of the rotor shaft supporting the bearing. This change causes the inner diameter of the radial bearing on the turbine wheel side and the inner diameter of the thrust / radial bearing on the compressor wheel side. Makes a difference. When radial bearings with different inner diameters are used in this way, the performance will be degraded. As a result of the installation of the eccentric (auxiliary) bearing as described above, the inner diameters of the radial bearings used on both sides of the compressor wheel and the turbine wheel will be the same. Prevented.

The present invention is not limited to the above-described specific preferred embodiments, and various modifications can be made by any person having ordinary skill in the art without departing from the gist of the present invention claimed in the claims. Of course, such changes will fall within the scope of the claims.

The effect of the present invention, which can be expected by the above-described configuration and action, is that the number of bearing-related parts to be used preferentially is smaller than that of the conventional method exemplified, and the inner diameter of the radial bearing is not changed to the turbine wheel because there is no change in the inner diameter of the radial bearings. Sophisticated boring work to fit has been reduced from 2 to 1. Due to the same inner diameter of the radial bearings used as described above, they have the same stiffness coefficient and attenuation coefficient between the radial bearings, which contributes to the stability of the shaft system, thereby enabling overall stable operation. The reduced number of parts and the reduced number of processes as described above are expected to improve convenience and performance in manufacturing, maintenance, and use.

Claims (1)

In the configuration of the rotor shaft 8 for rotating the compressor wheel 1 and the turbine wheel 7 and a series of bearings for supporting the rotor shaft 8, A radial bearing 6 installed on the turbine wheel 7 side of the rotor shaft 8 having a smaller diameter on the compressor wheel 1 side than the turbine wheel 7 side to support radial reaction force; A labyrinth / thrust ring (13) installed on the compressor wheel (1) side of the rotor shaft (8) so as to be in close contact with one side of the compressor wheel (1) to support an axial reaction force while maintaining airtightness; One side of the labyrinth / thrust ring 13 is in close contact with the other side, and the other side and one side of the rotor shaft 8 having a larger diameter than the compressor wheel 1 side are in close contact with the compressor wheel 1 side. Exile is installed on the other side of the located rotor shaft 8 to compensate for the outer diameter of the rotor shaft 8 on the compressor wheel 1 side so that there is no change in the outer diameter of the rotor shaft 8 and support the axial and radial reaction forces. Roller (secondary) bearing 12; And One side of the labyrinth / thrust ring 13 and the other end surface of the one end end of the exile (auxiliary) bearing 12 is built in the exile (auxiliary) bearing 13 so that the turbine wheel ( 7) and a thrust / radial bearing (11) for supporting an axial reaction force and a radial reaction force applied from both sides of the compressor wheel (1).

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