KR20040095488A - Disk for gas turbine engine - Google Patents

Abstract

PURPOSE: A disk for an engine of a gas turbine is provided to reduce noise by insulating vibration from a blade with slots formed between the blades, to decrease thermal stress by buffering thermal expansion of the disk exposed at high temperature, and to prevent breakage of the disk by reducing hoop stress. CONSTITUTION: A disk(100) for an engine of a gas turbine is composed of a disk type body(110) into which a rotating shaft of a compressor or a turbine is inserted, and a blade part having plural blades(121) arranged in the outer periphery of the body. Plural slots(112) are formed between plural blades to insulate the blades extended inward from the circumference of the body. Plural penetration holes(114) are arranged circumferentially at a side(113) of the body to reduce the mass of the disk. Inertia from rotation of the disk is decreased by reducing the mass of the body, and breakage of the disk is prevented by reducing hoop stress.

Description

Disk for gas turbine engine

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine engine, and more particularly, to a disk for a gas turbine engine that receives rotational force from a rotating shaft of a compressor or turbine.

In general, a gas turbine engine mainly used as an industrial or aircraft engine includes a compressor for compressing air, a combustor for generating a gas of high temperature and high pressure by mixing air and fuel compressed from the compressor, and a gas generated from the combustor. It includes a turbine to obtain a rotational force using. In the compression unit or the turbine of such a gas turbine engine, a propulsion force is obtained by compressing air or ejecting combustion gas by rotating a disk having a plurality of blades installed on a circumference thereof.

A partial perspective view schematically showing a disk for a conventional gas turbine engine as described above is shown in FIG. 1.

Referring to the drawings, the gas turbine engine has a disk 1. The disk 1 has a main body 10 having an insertion hole 10a formed at the center thereof, and a wing 20 provided with a plurality of blades 21 along the circumferential surface 11 of the main body 10. ). A rotating shaft (not shown) of a compressor or a turbine is inserted into the insertion hole 10a of the main body 10 to transmit the rotational force to the disk 1.

By the way, the conventional gas turbine engine disk 1 comprised as mentioned above has the following problems.

First, because the disk 1 rotates at a high speed, the blade 21 of the wing 20 vibrates violently due to compressed air or ejected combustion gas, which causes excessive noise.

Second, since the disk 1, especially the disk used in the turbine, is exposed to a high temperature combustion gas, thermal stress due to thermal expansion is large, and the disk 1 is easily damaged by such thermal stress.

Third, during high-speed rotation of the disk 1, an inertial force is generated by the rotational mass of the body portion 10, and the disk 1 often breaks due to the hoop stress caused by the inertia force.

SUMMARY OF THE INVENTION The present invention has been made to solve the above problems, and an object thereof is to provide a disk for a gas turbine engine, the structure of which is improved to insulate vibrations between adjacent blades to reduce noise.

Another object is to provide a disk for a gas turbine engine that can reduce thermal stress due to thermal expansion of the disk.

Furthermore, another object is to provide a disk for a gas turbine engine in which the mass of the disk is reduced to reduce the hoop stress.

1 is a partial perspective view schematically showing a disk for a conventional gas turbine engine,

2 is a partial perspective view schematically showing a disk for a gas turbine engine according to an embodiment of the present invention;

3 is a plan view of the disk for the gas turbine engine shown in FIG. 2.

<Brief description of symbols for the main parts of the drawings>

100 ... disk 110 ... main unit

110a ... insertion hole 111 ... Circumferential surface

112 ... Slot 113 ... Side

114.Through hole 120 ... wing

121 ... blade

In order to achieve the above object, a disk for a gas turbine engine according to the present invention,

A disk-shaped main body portion into which a rotating shaft of the compressor or turbine is inserted; A blade portion provided with a plurality of blades along the outer circumferential surface of the main body portion,

The main body portion is formed with a plurality of slots between the plurality of blades to insulate the adjacent blades extending inward from the circumferential surface,

And / or the side portion of the main body portion may be formed with a plurality of through holes penetrated at equal intervals along the circumferential direction for mass reduction.

Here, the slot and the through hole are preferably in communication with each other.

Hereinafter, a disk for a gas turbine engine according to a preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings.

2 is a partial perspective view schematically illustrating a disk for a gas turbine engine according to an embodiment of the present invention, and FIG. 3 is a plan view of the disk for a gas turbine engine shown in FIG. 2.

Referring to the drawings, the gas turbine engine disk 100 according to an embodiment of the present invention is rotated by receiving a rotational force from a rotating shaft (not shown) of the compressor or turbine, the center of rotation of the compressor or turbine in the center A disk-shaped main body 110 having an insertion hole 110a inserted therein, and a wing 120 provided with a plurality of blades 121 along the outer circumferential surface 111 of the body 110. Here, as the blade 121 of the wing 120 rotates, the air is compressed or the combustion gas is ejected.

In the above-described embodiment, according to one feature of the present invention, the main body portion 110 has a circumferential surface between the plurality of blades 121 so as to insulate between adjacent blades 121. A plurality of slots 112 extending inwardly from 111 are formed.

The slots 112 formed between the blades 121 insulate the vibration generated from each blade 121 from being transmitted to the adjacent blade 121 to reduce noise.

In addition, the slots 112 serve as a buffer region for thermal expansion even when the disk 100, ie, the main body 110, which is exposed to high temperature is thermally expanded to minimize the occurrence of thermal stress.

On the other hand, in order to reduce the mass of the disk 100, the body portion 110 may be formed in the side portion 113 a plurality of through holes 114 penetrated at equal intervals along the circumferential direction.

The light through hole 114 reduces the mass of the disk 100, ie, the main body 110, to reduce the inertial force due to the rotation of the disk 100. Therefore, the hoop stress generated in the main body 110 may be reduced to prevent the disk 110 from being damaged.

2 and 3, the slot 112 and the through hole 114 may communicate with each other. In this manner, by communicating the slot 112 and the through hole 114, the effect of vibration isolation between adjacent blades 121 can be increased.

As described above, according to the gas turbine engine disk of the present invention, the following effects can be obtained.

First, slots formed between the blades reduce noise by isolating transmission of vibrations from each blade to adjacent blades.

Secondly, the slots act as a buffer zone for thermal expansion even when the disk exposed to high temperature, that is, the body portion of the disk, minimizes the occurrence of thermal stress.

Third, the through hole formed in the body portion of the disk reduces the rotational mass of the body portion, thereby reducing the inertial force due to the rotation of the disk. Therefore, the hoop stress generated in the main body portion is reduced to prevent the disk from being broken.

Although the present invention has been described with reference to the embodiments illustrated in the accompanying drawings, it is merely an example, and those skilled in the art may realize various modifications and equivalent other embodiments therefrom. Will understand. Therefore, the true scope of protection of the present invention should be defined by the technical spirit of the appended claims.

Claims (4)

A disk-shaped main body portion into which a rotating shaft of the compressor or turbine is inserted; In the gas turbine engine disk having a; Wing portion provided with a plurality of blades along the outer peripheral surface of the main body, And a plurality of slots formed between the plurality of blades so as to insulate the adjacent blades extending inwardly from the circumferential surface thereof. A disk-shaped main body portion into which a rotating shaft of the compressor or turbine is inserted; In the gas turbine engine disk having a; Wing portion provided with a plurality of blades along the outer peripheral surface of the main body, The main body portion is a disk for a gas turbine engine, characterized in that formed in the side portion through the plurality of through holes spaced at equal intervals along the circumferential direction for mass reduction. A disk-shaped main body portion into which a rotating shaft of the compressor or turbine is inserted; In the gas turbine engine disk having a; Wing portion provided with a plurality of blades along the outer peripheral surface of the main body, The main body portion is formed with a plurality of slots between the plurality of blades to insulate between the adjacent blades extending inward from the circumferential surface, The side of the main body portion gas turbine engine disk, characterized in that a plurality of through holes penetrated at equal intervals along the circumferential direction for mass reduction. The method of claim 3, And said slot and said through hole communicate with each other.