Rotor disk for an exhaust turbocharger, exhaust turbocharger and method for balancing a rotor assembly for an exhaust turbocharger

Abstract

A rotor disk for an exhaust turbocharger is mounted in a housing of the exhaust turbocharger able to rotate about an axis of rotation. The rotor disk has a disk hub comprising a disk back and a disk front remote from the disk back. A plurality of rotor disk blades are formed on the disk hub in a manner extending between the disk back and the disk front. A balancing mark is arranged in a blade channel formed between a first blade of the plurality of rotor disk blades and a second blade, arranged adjacent to the first blade, of the plurality of rotor disk blades. A width of the balancing mark is less than a length of the balancing mark. The disclosure also relates to an exhaust turbocharger comprising such a rotor disk and to a method for balancing a rotor assembly for such an exhaust turbocharger.

Claims

1. A rotor disk for an exhaust turbocharger, wherein the rotor disk has a disk hub with a plurality of rotor disk blades formed on the disk hub, and wherein a balancing mark is arranged in a blade channel formed between a first blade of the plurality of rotor disk blades and a second blade, arranged adjacent to the first blade, of the plurality of rotor disk blades, and wherein a radially extending width of the balancing mark is less than a circumferentially extending length of the balancing mark, and wherein the width of the balancing mark is substantially constant over the length of the balancing mark, and wherein the balancing mark is curved.

2. The rotor disk as claimed in claim 1, wherein the balancing mark extends circumferentially on an arc at a constant radius from a center of the disk hub.

3. A method for balancing a rotor assembly which is mounted rotatably in a housing of an exhaust turbocharger, wherein the rotor assembly comprises a rotor disk which has a plurality of rotor disk blades on a disk hub of the rotor disk, and wherein formed between at least one first blade of the plurality of rotor disk blades and a second blade, adjacent to the first blade, of the plurality of rotor disk blades is a blade channel comprising a channel base, comprising: forming a balancing mark in the channel base, the balancing mark having a circumferentially extending length greater than a radially extending width with the width of the balancing mark being substantially constant over the length of the balancing mark, by moving a tool in circumferential direction of the rotor disk.

4. The method as claimed in claim 3, wherein the balancing mark is produced by material removal.

5. A method for balancing a rotor assembly which is mounted rotatably in a housing of an exhaust turbocharger, wherein the rotor assembly comprises a rotor disk which has a plurality of rotor disk blades on a disk hub of the rotor disk, and wherein formed between at least one first blade of the plurality of rotor disk blades and a second blade, adjacent to the first blade, of the plurality of rotor disk blades is a blade channel comprising a channel base, the method comprising: forming a balancing mark in the channel base, the balancing mark having a circumferentially extending length greater than a radially extending width with the width of the balancing mark being substantially constant over the length of the balancing mark, by circumferentially moving the rotor disk.

6. The method as claimed in claim 5, wherein the balancing mark is produced by material removal using a stationary milling tool.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 shows a perspective view of a detail of a rotor disk according to the prior art.

(2) FIG. 2 shows a perspective view of a detail of a rotor disk in accordance with the invention.

DETAILED DESCRIPTION

(3) A rotor disk 1 of a rotor assembly 2 for an exhaust turbocharger 3 according to the prior art is formed as shown in FIG. 1. The rotor disk 1 is designed in the form of a compressor wheel. The rotor assembly 2 comprises the compressor wheel 1 and a turbine wheel, not illustrated in greater detail, which is connected via a shaft, not illustrated in greater detail, to the compressor wheel 1 for conjoint rotation therewith.

(4) The rotor assembly 2 is mounted in a bearing portion, not illustrated in greater detail, of the exhaust turbocharger 3 so as to be able to rotate about an axis of rotation 4 of the rotor assembly 2. The turbine wheel is accommodated in a rotatable manner in an exhaust gas conducting section, not illustrated in greater detail, of the exhaust turbocharger 3, said exhaust gas conducting section being capable of having a flow pass therethrough. Exhaust gas from an internal combustion engine, which engine is not illustrated in greater detail and is connected to the exhaust turbocharger 3 so as to be capable of having a flow pass therethrough, is applied via an inlet channel, not illustrated in greater detail, of the exhaust gas conducting section, to the turbine wheel, causing said turbine wheel to rotate.

(5) By means of the conjoint-rotation connection, established with the aid of the shaft, to the compressor wheel 1, the compressor wheel 1 which is rotatably accommodated in an air conducting section, not illustrated in greater detail, is likewise caused to perform a rotational movement, wherein it takes in air and compresses it. The compressed air is supplied to the internal combustion engine via an outlet channel, not illustrated in greater detail, of the air conducting section.

(6) The compressor wheel 1 comprises a plurality of rotor disk blades 5, by means of which it takes in air, which blades are arranged on a disk hub 6 of the compressor wheel 1. The disk hub 6 has a disk back 7 and a disk front, not illustrated in greater detail and remote from the disk back 7, of the disk hub 6. The plurality of rotor disk blades 5 are arranged on the disk hub 6 in a manner extending from the disk front to the disk back 7. Formed between in each case two blades of the plurality of rotor disk blades 5, a first blade 8 and a second blade 9, is a blade channel 10 comprising a channel base 11, along which the air flows.

(7) In order to produce a particularly calm rotational movement of the rotor assembly 2, a balancing mark 12 is formed on the channel base 11 of the compressor wheel 1. The balancing mark 12 which is produced with the aid of a milling method is point-shaped, wherein a width B of the balancing mark 12 corresponds substantially to a length L of the balancing mark 12.

(8) FIG. 2 illustrates a rotor disk 1 in accordance with the invention which is likewise designed in the form of a compressor wheel. Likewise, the rotor disk 1 can also be designed in the form of a turbine wheel.

(9) The balancing mark 12 is configured so as to extend over its circumferential extension direction U in the circumferential direction of the rotor disk 1 and is formed generally in the shape of a racetrack. The racetrack shape of a linear balancing mark 12 is formed by two semi-circles which are connected by a rectangle. The racetrack shape of a curved balancing mark 12 is formed by two semi-circles which are connected by an annular sector. The balancing mark 12 is notch-like, i.e. in other words it has been produced with material removal. Likewise, the balancing mark 12 can also be linear. The balancing mark 12 of the rotor disk 1 in accordance with the invention has a length L which is greater than the width B.

(10) In order to produce the balancing mark 12 in so-called high-speed balancing, on the one hand the material-removing tool can be moved or on the other hand the rotor disk 1 or the rotor assembly 2 itself can be moved. The linear balancing mark 12 can be produced preferably by a moving tool, whereas the curved balancing mark 12 can be produced preferably with a moving rotor disk 1 or moving rotor assembly 2.

(11) In order to effect sufficient removal of material which reduces the imbalance, a depth of the balancing mark 12 can also be increased, wherein it is necessary to take into account that the depth does not exceed a thickness D of the rotor disk 1 required for the strength of the rotor disk 1.

(12) The advantage of the curved balancing mark 12 can be seen in the fact that a maximum equalization radius, and thus a maximum imbalance-related effect, of a rotor disk mass to be removed are ensured. However, in the case of the linear balancing mark 12, a straight racetrack segment is removed in the circular rotor disk 1, whereby the maximum equalization radius is achieved typically only at end points of the balancing mark 12.

(13) In order to produce the balancing mark 12, basically any material-removing method can be used, in other words any material removal. In particular, grinding is feasible if the rotor disk 1 is designed in the form of a turbine wheel. Likewise, the material removal can also be achieved with the aid of a laser method. The balancing mark 12 could also be produced on an outer edge of the rotor disk 1 with the aid of a cutting method. The advantage of milling can be seen in terms of a possible surface treatment and cost advantage over other methods because milling can be used cost-effectively and flexibly.

(14) In one exemplified embodiment, not illustrated in greater detail, the balancing mark 12 is configured extending at least partially in a radial direction over its length L. It is also possible for the balancing mark 12 to extend completely in a radial manner over its length L.