RU2530961C1 - Rotor of axial gas turbine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbine engines of aviation and ground use and may be applied in turbomachines, on the rotor of which there are blades fixed, as well as their facilities for cooling and clearance of deformations and vibrations. The rotor of the axial gas turbine comprises a rotor disc, cooled working blades arranged on the disc and a cover disc. The cover disc is installed on the rotor disc to form a circular cavity and is fixed by bayonet joints and pins. The circular cavity is connected by channels in the disc with channels in the base of the tail part of each blade. The rotor is also equipped with at least three ledges with slots made above bayonet joints. Bayonet joints are formed by hooks of the rotor disc and hooks of the cover disc. In the cover disc there are at least three holes coupled with slots. Pins are rigidly fixed in holes of the cover disc and are installed into slots of the rotor disc with a radial gap. Each hook of the cover disc is installed along the radius at the distance equal to 1.4-1.8 of the inner radius of the cover disc hub.

EFFECT: invention makes it possible to improve cooling of working blades, to increase reliability of a turbine rotor and to increase resource of a gas turbine engine.

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Description

The invention relates to gas turbine engines for aviation and ground applications and can be used mainly in turbomachines, on the rotor of which blades and means are fixed for cooling and eliminating deformations and vibrations.

The closest in technical essence and the achieved result is a gas turbine rotor containing a rotor disk, cooled rotor blades located on the disk, a cover disk mounted on the rotor disk with the formation of an annular cavity connected by channels in the disk to the channels at the base of the tail part of each blade, secured with bayonet connection and pins / RU 2378517 C1, IPC F01D 5/08, published on January 10, 2010 /

A disadvantage of the known design is its low reliability due to the increased voltage of the rim of the disk from the centrifugal forces of the cover disk due to the remote location of the pins from the bayonet connection and increased air loss due to the presence of windows in the cover disk.

The objective of the invention is to increase the reliability of the rotor and reduce losses during the supply of cooling air to the working blades.

The technical result of the claimed invention is the improvement of cooling of the working blades, increasing the reliability of the turbine rotor, increasing the resource of the gas turbine engine.

The expected technical result is achieved in that the known rotor of an axial gas turbine containing a rotor disk, cooled rotor blades located on the disk, a cover disk mounted on the rotor disk with the formation of an annular cavity connected by channels in the disk to the channels in the base of the tail part of each blade and secured with a bayonet connection and pins, according to the proposal, is equipped with at least three protrusions with grooves made over the bayonet connections, each of which is formed by hooks of the disk p ora and hooks of the casing disk, and in the casing disk made at least three holes mating with the grooves, and the pins are rigidly fixed in the holes of the casing disk and installed in the grooves of the rotor disk with a radial clearance, while each hook of the casing disk is installed radially at a distance equal to 1.4-1.8 of the inner radius of the hub of the covering disk.

To fix the cover disk in the circumferential direction, pin connections are used made on the bayonet hooks of the disk in the form of protrusions with radial grooves, holes in the cover disk and pins installed in the hole and groove. The pins are rigidly fixed in the holes of the casing disk (for example, by punching), which ensures the tightness of the connection of the pin with the disk, and in the radial grooves the pins are installed with a gap that allows it to move in radial directions, which prevents mutual temperature deformations of the turbine disk and the casing disk. The location of the pin connections on the bayonet hooks of the disc does not load the disc rim during rotation. The location of the inputs of the cooling channels for air on the cover disk at the location of the bayonet hook on the rotor at a distance selected from the condition of air supply with less loss according to the law of constant circulation, with an inner radius equal to 1.4-1.8 of the inner radius of the hub of the cover disk, reduces the loss of cooling air.

Figure 1 shows a longitudinal section of a turbine rotor.

Figure 2 shows the location of the groove in the protrusions of the disk and the position of the pin (type A).

The turbine rotor contains: a rotor disk 1 (with hooks 2), protrusions 3 with grooves 4, a cover disk 5 with hooks 6 and holes 7 in which pins 8 are installed, cooled working blades 9 located on the rotor disk 1, locks 10. Cover the disk 5 is mounted on the disk 1 of the rotor with the formation of an annular cavity connecting the channels in the disk with the channels at the base of the tail of each blade 9, while the cover disk 5 is secured with bayonet connections (each of which is formed by the hook 2 of the disk 1 of the rotor and the hook 6 of the cover disk 5 ) and pins 8.

The protrusions 3 with radial grooves 4, the holes 7 in the cover disk 5, the pins 8 installed in the holes 7, and the grooves 4 form the pin connections located on the bayonet hooks. The pins 8 are rigidly fixed in the holes 7 of the cover disk 5, while the pins 8 are installed in radial grooves 4 with a gap that allows the movement of the disk 5 in radial directions.

The inputs of the cooling channels for air on the cover disk 5 are located at the location of the bayonet joint. In this case, to reduce the loss of cooling air, the hooks 6 are arranged so that the inner radius R2 is equal to 1.4-1.8 of the inner radius R1 of the hub of the cover disk 5.

During operation, the cover disk 5 is fixed with pins 8 in the grooves 4 of the disk 1 from possible movement in the circumferential direction. In addition, the cover disk 5 freely moves in the radial direction relative to the disk 1, since between the pins 8 and the disk 1 there are gaps. In this case, the rim of the disk 1 is not loaded. And the location of the hooks 6 of the cover disk with a radius of R2 reduces the loss of cooling air.

The claimed design of the turbine rotor provides increased reliability of the rotor and reduced losses of cooled air. The application of the invention allows to improve the cooling of the working blades, increase the reliability of the turbine rotor and increase the resource of the gas turbine engine as a whole.

Claims (1)

An axial gas turbine rotor comprising a rotor disk, cooled rotor blades located on the disk, a cover disk mounted on the rotor disk to form an annular cavity connected by channels in the disk to the channels at the base of the tail of each blade and secured with bayonet joints and pins, characterized in that the rotor is equipped with at least three protrusions with grooves made over bayonet joints, each of which is formed by hooks of the rotor disk and hooks of the cover disc, and in the cover disc at least three holes mating with the grooves are made, and the pins are rigidly fixed in the holes of the cover disk and installed in the grooves of the rotor disk with a radial clearance, while each hook of the cover disk is set radially at a distance of 1.4-1.8 internal radius of the hub of the covering disk.

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