RU92694U1 - AXIAL COMPRESSOR ROTOR DISC CONNECTOR ASSEMBLY OF A GAS TURBINE ENGINE - Google Patents

Abstract

The hub connection of the rotor disks of the axial compressor of a gas turbine engine, including drum sections of adjacent disks contacting each other on end surfaces, characterized in that a thread contacting a reciprocal thread made on a drum section of an adjacent disk is made on a part of the drum section adjacent to the end surface and at the end of the drum section there is a centering belt in contact with a centering belt made on an adjacent disk, and the direction of the thread turns with Rhone input to the compressor rotor coincides with the direction of rotation.

Description

The utility model relates to the field of aircraft engine manufacturing, namely, to the design of rotors of gas turbine engine compressors (GTE).

A known node of the connection of the rotor disks of the axial compressor of the gas turbine engine, including drum sections of adjacent disks in contact with each other along the end surfaces and fastened with pins (G.S. Skubachevsky, "Aviation gas turbine engine", M., "Engineering", 1974, p. 61 )

A disadvantage of the known device is the significant mass of the structure, due to the presence of many elements, as well as the need to make belts for holes and a significant mass of the disk as a whole to ensure its strength properties.

The problem to which the claimed solution is directed is to reduce the mass of the disks and the total mass of the device.

The technical result is achieved by the fact that in the known node connecting the rotor disks of the axial compressor of the gas turbine engine, including the drum sections of adjacent disks contacting each other along the end surfaces, on the part of the drum section adjacent to the end surface, a thread is made in contact with a mating thread made on the drum a section of the adjacent disk, and at the end of the drum section there is a centering belt in contact with a centering belt made on the neighboring disk, the direction of the turns of p The thread on the compressor inlet side coincides with the direction of rotation of the rotor.

This embodiment of the device eliminates the need to make additional holes in the disk and increase in this regard, its size and weight. An exception to the connection of fasteners also reduces its weight.

Figure 1 shows a General view of the node connecting two adjacent disks of the rotor of the axial compressor of the gas turbine engine;

figure 2 - arrangement of the elements of the connection.

The connection node of the adjacent disks 1 and 2 of the rotor of the axial compressor contains drum sections 3 and 4 of these disks contacting each other along the end surfaces 5. On the part of the drum section 3, the disks 1 adjacent to the end surface 5 have a thread 6 in contact with the reciprocal thread, made on the drum section 4 of the disk 2. At the end of the drum section 3 of the disk 1, a centering belt 7 is made in contact with the centering belt made on the adjacent disk 2.

The disks 1 and 2 are interconnected by means of a threaded connection 6. The discs are centered relative to each other due to the fit of the centering belts 7 with an interference fit. The axial dimension of the connection and the tolerance on the end runout of the disks relative to each other is maintained due to the stop on the end surface 5.

During engine operation, a torque is transmitted between the disks, which is carried out by abutting the threaded connection 6 to the end surface 5. The direction of the thread turns from the compressor inlet side must coincide with the direction of rotation of the rotor, so that when transmitting torque, the thread works for tightening. A part of the torque is transmitted due to friction forces in conjunction with an interference fit along the girdle 7. Due to the action of centrifugal forces, the discs are “pulled out”, while the “picking up” girdle 7 of the disk of one stage has a larger hood than the “covering” girdle 7 of the disk of another stage due to the difference in distance from the center of mass of the disk and the geometry of the rim. This allows you to save interference on the centering belt 7 in operation. Thus, the connection maintains integrity and geometric properties when working at high speeds.

The proposed device can significantly reduce the mass of disks and their connections. In addition, increases the manufacturability of the manufacture and assembly of the connection, as well as maintainability of the rotor due to the possibility of its multiple disassembly and assembly.

Claims (1)

The hub connection of the rotor disks of the axial compressor of a gas turbine engine, including drum sections of adjacent disks contacting each other on end surfaces, characterized in that a thread contacting a reciprocal thread made on a drum section of an adjacent disk is made on a part of the drum section adjacent to the end surface and at the end of the drum section there is a centering belt in contact with a centering belt made on an adjacent disk, and the direction of the thread turns with Rhone input to the compressor rotor coincides with the direction of rotation.