CN112594068B

CN112594068B - Disc drum sealing mechanism of aircraft engine and aircraft engine

Info

Publication number: CN112594068B
Application number: CN202110078748.3A
Authority: CN
Inventors: 胡淑慧; 邢丽民; 刘洋; 曹传军; 吴志青; 陆晓锋; 况成玉
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-01-21
Filing date: 2021-01-21
Publication date: 2021-05-28
Anticipated expiration: 2041-01-21
Also published as: CN112594068A

Abstract

The invention provides a disc drum sealing mechanism of an aircraft engine, which comprises: a rotor disc (1); the comb tooth ring (2) is detachably arranged on the outer peripheral surface of the rotor disc (1), and comb teeth are arranged on the outer peripheral surface of the comb tooth ring (2); and a groove (7) formed on the outer circumferential surface of the rotor disk (1); and a baffle ring (3) which is located in the groove (7) and is divided into a plurality of sections (10, 11) independent of each other, and one side of which abuts against the grate ring (2) in the axial direction of the rotor disk (1) to axially restrain the grate ring (2), the cost and time of the grate maintenance being reduced by using the baffle ring (3) including a plurality of sections. The invention also provides an aircraft engine with the disc drum sealing mechanism.

Description

Disc drum sealing mechanism of aircraft engine and aircraft engine

Technical Field

The invention relates to the field of aircraft engines, in particular to a disc drum sealing mechanism of an aircraft engine and the aircraft engine.

Background

The labyrinth seal is a non-contact seal structure in the field of aeroengines. The non-contact sealing structure is applied, and the air flow leakage amount is reduced by reducing the clearance between the rotating part and the static part. When the air flow passes through the grid teeth, the air flow is throttled and accelerated for many times, the pressure energy is converted into kinetic energy, and the kinetic energy is converted into heat energy under the action of turbulent flow and viscous dissipation and is consumed, and finally the sealing effect is achieved. The high-quality labyrinth structure can effectively reduce the leakage of a sealing system, increase the thrust-weight ratio of the engine and obviously improve the efficiency of the engine.

The traditional rotor design of the rotary machine is that the grid tooth is taken as a part of the disk drum, and the grid tooth and the disk drum are designed into a whole, but the inventor finds that the following problems are caused: the grid teeth and the disc drum are integrally designed, so that the whole disc drum cannot be used due to the fact that a small part of grid teeth are damaged, and great difficulty is brought to maintenance of the grid teeth. Because the grate is often in an inclined grate structure, the feed direction may interfere with other characteristics such as the disc edge or the blades during processing, and the integrally designed grate brings great inconvenience to the processing.

Disclosure of Invention

The invention provides a disc drum sealing mechanism of an aircraft engine, which is used for reducing the cost and time of repairing a grate.

The invention provides a disc drum sealing mechanism of an aircraft engine, which comprises:

a rotor disk;

the comb tooth ring is detachably arranged on the outer peripheral surface of the rotor disc, and comb teeth are arranged on the outer peripheral surface of the comb tooth ring; and

a groove formed on an outer circumferential surface of the rotor disk; and

a baffle ring located in the groove and divided into separate sections and one side of which abuts against the grate ring in the axial direction of the rotor disk to axially restrain the grate ring.

In some embodiments, an end of the grate ring remote from the baffle ring bears axially against a circumferential flange on the outer circumferential surface of the rotor disk.

In some embodiments, the disc drum sealing mechanism comprises a radially inwardly projecting protrusion disposed at the other end of the grate ring adjacent the slinger and axially abutting the other side of the slinger.

In some embodiments, the number of the protrusions is multiple, and the central angle beta of each section is smaller than the central angle alpha of the grate ring between two adjacent protrusions.

In some embodiments, the number of the plurality of segments is equal to the number of the projections, and each segment of the retainer ring axially abuts a corresponding one of the projections.

In some embodiments, a stop is disposed in the groove and circumferentially blocks the retaining ring.

In some embodiments, the baffle ring is open.

In some embodiments, the baffle ring comprises a plurality of long sections and two short sections, the two short sections are respectively positioned at two ends of the opening of the baffle ring, and the bent free ends of the two short sections are abutted against the corresponding protrusions along the circumferential direction so as to circumferentially limit the baffle ring.

In some embodiments, the barrel of the rotor disk on which the grate ring is disposed is frustoconical, the baffle ring being closer to the smaller dimension end of the barrel relative to the larger dimension end of the barrel.

The invention further provides an aircraft engine which comprises the disc drum sealing mechanism of the aircraft engine.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 shows a schematic partial cross-sectional view of a disc drum sealing mechanism of an aircraft engine according to an embodiment of the invention.

Fig. 2 shows a schematic structural view of the retainer ring 3 in another embodiment of the present invention.

Fig. 3 shows a partial schematic view of the catch ring 3 and the projections 9 mounted on the rotor disk 1, seen from the right side of fig. 1.

Fig. 4 shows a partial schematic view of the rotor disk 1 of fig. 1 from above, wherein the labyrinth ring 2 and the baffle ring 3 are omitted.

Fig. 5 shows a partial schematic view from the upper right in fig. 1 with the blocking ring 3 shown in fig. 2 installed, wherein the grate ring 2 is omitted.

Fig. 6 shows a schematic structural view of a rotor disc 1 and a retainer ring 3 according to a further embodiment of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature.

One embodiment of the invention provides a disc drum sealing mechanism of an aircraft engine, which comprises a rotor disc 1, a labyrinth ring 2 and a baffle ring 3, as shown in fig. 1 and 2. The grate ring 2 is detachably mounted on the outer circumferential surface 4 of the rotor disc 1, the grate ring 2 being provided with grate teeth on the outer circumferential surface, the grate ring 2 being generally concentric with the rotor disc 1. A ring of grooves 7 is provided in the outer circumferential surface 4 of the rotor disc 1. The baffle ring 3 is arranged in the groove 7 and is divided circumferentially into a plurality of segments, each of which is independent, one side of the baffle ring 3 axially abutting against the tooth ring 2, axially retaining the tooth ring 2 on the rotor disk 1.

As shown in fig. 3, the segments of the baffle ring 3 are moved axially into the groove 7 in turn from the end of the rotor disk 1 adjacent to the groove 7 (in this embodiment there is no protrusion 9), the side of the baffle ring 3 located in the groove 7 abuts against the grate ring 2, thereby axially limiting the movement of the grate ring 2. By using a plurality of segments with the baffle ring 3, each segment can be mounted in turn, so that it is more convenient to detachably mount the grate ring 2 on the rotor disk 1, reducing the maintenance cost and time of the grate ring 2.

In another embodiment of the invention, as shown in fig. 1, a circumferential flange 101 is formed on the outer circumferential surface 4 of the rotor disk 1, one end of the grate ring 2 remote from the baffle ring 3 abuts against the circumferential flange 101, and the other end of the grate ring 2 adjacent to the baffle ring 3 abuts against the baffle ring 3, so that the grate ring 2 is axially retained on the rotor disk 1.

In a further embodiment of the invention, as shown in fig. 3, the end of the grate ring 2 adjacent to the retainer ring 3 is provided with a plurality of projections 9 protruding radially inwards, the projections 9 abutting against the other side of the retainer ring 3 in the axial direction of the rotor disc 1. The central angle beta of each section is smaller than the central angle alpha of the grate ring 2 between two adjacent bulges 9. The axial bidirectional positioning of the grate ring 2 on the rotor disk 3 can be achieved by the projections 9 and the baffle ring 3.

Alternatively, as shown in fig. 3, the number of the plurality of segments of the retainer ring 3, each of which abuts against a corresponding one of the projections 9, is equal to the number of the plurality of projections 9.

In still another embodiment of the present invention, as shown in fig. 4, in order to prevent the retainer ring 3 from moving circumferentially in the groove 7, a stopper 6 is provided in the groove 7, and the stopper 6 blocks the retainer ring 3 circumferentially so that the circumferential movement of the retainer ring 3 is restricted.

In yet another embodiment of the present invention, as shown in fig. 2, the retainer ring 3 may be opened, so that the retainer ring 3 is easily detached. As shown in fig. 2 and 5, the plurality of segments includes a plurality of long segments 10 and two short segments 11, the two short segments 11 are respectively located at both ends of the opening of the retainer ring 3, and the bent respective ends 8 of the two short segments 11 respectively abut against two adjacent corresponding protrusions 9 in the circumferential direction, so that the movement of the retainer ring 3 along the circumferential direction is restricted.

It should be noted that the end of the grate ring 2 remote from the baffle ring 3 is optional for the fixation of the rotor disk 1, as long as the baffle ring 3 is able to axially position the grate ring 2. The embodiment shown in fig. 6 differs from the embodiment shown in fig. 1 mainly in that the outer surface of the cylinder of the rotor disc 1 is frustoconical and the inner surface of the corresponding labyrinth ring 2 is also frustoconical. The baffle ring 3 is closer to the small-size end of the frustoconical cylinder of the rotor disc 1 with respect to the large-size end of the frustoconical cylinder of the rotor disc 1. One side of the baffle ring 3 abuts against the tooth ring 2 and the inner surface of the tooth ring 2 axially abuts against the outer surface of the cylinder of the rotor disk 1, so that an axial bidirectional positioning of the tooth ring 2 on the rotor disk 1 is achieved.

The invention also provides an aircraft engine which comprises the disc drum sealing mechanism.

The above description is only exemplary of the present invention and should not be taken as limiting the invention, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A disc drum sealing mechanism for an aircraft engine, comprising:

a rotor disc (1);

the comb tooth ring (2) is detachably arranged on the outer peripheral surface of the rotor disc (1), and comb teeth are arranged on the outer peripheral surface of the comb tooth ring (2);

a groove (7) formed on the outer circumferential surface of the rotor disk (1);

a baffle ring (3) which is located in the groove (7) and is divided into a plurality of individual segments (10, 11) and which bears with one side in the axial direction of the rotor disk (1) against the grate ring (2) in order to axially limit the grate ring (2), and

a radially inwardly protruding protrusion (9), said protrusion (9) being arranged at one end of the grate ring (2) adjacent to the shield ring (3) and axially abutting against the other side of the shield ring (3);

wherein the baffle ring (3) is open, the baffle ring (3) comprising a plurality of long sections (10) and two short sections (11), the two short sections (11) being located at respective ends of the opening of the baffle ring (3), the bent respective ends (8) of the two short sections (11) abutting against the respective protrusions (9) in the circumferential direction to circumferentially restrain the baffle ring (3).

2. The aircraft engine disc drum sealing mechanism according to claim 1, wherein an end of the grate ring (2) remote from the baffle ring (3) axially abuts against a circumferential flange (101) on the outer circumferential surface of the rotor disc (1).

3. The disc drum sealing mechanism of an aircraft engine according to claim 1, wherein the number of the projections (9) is plural, and the central angle β of each segment is smaller than the central angle α of the grate ring (2) between two adjacent projections (9).

4. The disc-drum sealing mechanism of an aircraft engine according to claim 3, wherein the number of segments (10, 11) is equal to the number of projections (9), each segment of the baffle ring (3) axially abutting against a respective one of the projections (9).

5. The disc-drum sealing mechanism of an aircraft engine according to claim 1, wherein a stop (6) is provided in the groove (7), the stop (6) circumferentially blocking the retainer ring (3).

6. The aircraft engine disc drum seal mechanism according to claim 1, wherein the cylinder of the rotor disc (1) on which the grate ring (2) is provided is frustoconical, the baffle ring (3) being adjacent to the small dimension end of the cylinder.

7. An aircraft engine comprising a disc drum seal mechanism of an aircraft engine as claimed in any of claims 1 to 6.