KR101828474B1

KR101828474B1 - Turbine disk including bore groove

Info

Publication number: KR101828474B1
Application number: KR1020150085056A
Authority: KR
Inventors: 정성철
Original assignee: 두산중공업 주식회사
Priority date: 2015-06-16
Filing date: 2015-06-16
Publication date: 2018-02-12
Also published as: KR20160148274A

Abstract

According to an aspect of the present invention, there is provided an annular disk including a hole coupled to a rotary shaft, the disk including a bore which is an inner circumferential surface contacting the rotation axis, and a hub connecting the bore portion and the outer circumferential surface of the disk And at least one groove starting from the bore section and extending toward the outer circumferential surface may be a gas turbine disk formed in the hub.
The turbine disk according to the present invention has a structure in which the rotary shaft and the disk assembly are combined with each other to absorb shocks due to heat, vibration, and natural vibration due to heat, thereby preventing damage and breakage of the bore portion.
In addition, it is a structure that can reduce processing and maintenance costs while appropriately dispersing the stress generated in the borehole, and it is proposed a structure that can absorb stress, vibration and impact due to heat load properly.

Description

[0001] The present invention relates to a turbine disk including a bore groove,

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine disk installed in a gas turbine, and more particularly, to a turbine disk including a bore portion groove in the disk.

A gas turbine is a rotary type heat engine that drives a turbine with high-temperature, high-pressure combustion gas. Generally, it consists of compressor, combustor and turbine. The rotor portion of the compressor and the rotor portion of the turbine are coupled to a rotating shaft to form a rotor assembly.

The rotary shaft is restrained at both ends of the turbine, and the middle portion is not supported or restrained separately, and there is a problem in durability against vibration and natural vibration. In order to solve this problem, the problem of durability of the rotating shaft is solved by inserting a disk without a blade between the compressor rotor part and the turbine rotor part and by coupling the disk with the rotating shaft.

However, according to the related art, there is a disadvantage that the rotation shaft and the disk are very tightly coupled, the tolerance is small, and the assembled part is strongly constrained. In addition, since the stress is concentrated on the bore portion, there is a real problem that the area of the bore portion must be increased.

In order to solve this problem, there has been an attempt to use a bore portion having two hubs and an attempt to change the shape of the maximum stress point of the bore portion. However, this has a problem that additional machining cost and maintenance cost are increased.

Accordingly, the present invention proposes a turbine disk which can reduce the processing and maintenance costs while appropriately dispersing the stress generated in the bore portion.

Korean Patent Publication No. 1999-0030089 (published on April 26, 1999)

An object of the present invention is to provide a structure capable of appropriately absorbing stress, vibration, and impact due to thermal load by suggesting a structure capable of reducing processing and maintenance costs while adequately dispersing stress generated in a turbine disk bore portion.

According to an aspect of the present invention, there is provided an annular disk including a hole coupled to a rotary shaft, the disk including a bore which is an inner circumferential surface contacting the rotation axis, and a hub connecting the bore portion and the outer circumferential surface of the disk And at least one groove starting from the bore section and extending toward the outer circumferential surface may be a gas turbine disk formed in the hub.

Wherein the gas turbine disk according to one aspect is a first groove and a second groove formed on both sides of the symmetry plane with respect to a symmetry plane of the disk which is perpendicular to the longitudinal direction of the rotary shaft, Lt; / RTI >

The gas turbine disk according to one aspect may further comprise a third groove formed along the symmetry plane of the disk.

The gas turbine disk according to one aspect of the present invention may be a gas turbine disk, wherein the first groove and the second groove are inclined toward the third groove.

The gas turbine disk according to one aspect may be a gas turbine disk characterized in that the first groove and the second groove are symmetrical with respect to the third groove.

The gas turbine disk according to one aspect of the present invention may further comprise at least one or more of a fourth groove formed on the bore portion in parallel with the rotation axis.

The gas turbine disk according to one aspect of the present invention may be a gas turbine disk in which two or more of the fourth grooves are formed to be equally spaced.

According to another embodiment of the present invention, there is provided an annular disk including a hole coupled with a rotation axis, wherein the disk includes a bore which is an inner circumferential surface contacting the rotation axis, and a hub connecting the bore portion and the outer circumferential surface of the disk And at least one groove starting from the bore section and extending toward the outer circumferential surface may be a gas turbine disk formed in the hub.

The gas turbine disk according to one aspect of the present invention may be a gas turbine disk, wherein the grooves are formed on at least one or more of the bore portions in parallel with the rotation axis.

Wherein the gas turbine disk according to one aspect is formed such that two or more of the grooves are equally spaced.

The turbine disk according to the present invention has a structure in which the rotary shaft and the disk assembly are combined with each other to absorb shocks due to heat, vibration, and natural vibration due to heat, thereby preventing damage and breakage of the bore portion.

In addition, it is a structure that can reduce processing and maintenance costs while appropriately dispersing the stress generated in the borehole, and it is proposed a structure that can absorb stress, vibration and impact due to heat load properly.

1 shows a disk of a gas turbine.
2 shows a turbine disk according to the prior art.
3 shows a groove of a turbine disk according to an embodiment of the present invention.
FIG. 4 illustrates a modification of a groove of a turbine disk according to an embodiment of the present invention.
FIG. 5 shows a modification of a groove of a turbine disk according to an embodiment of the present invention.

Hereinafter, some embodiments of the present invention will be described in detail with reference to exemplary drawings. It should be noted that, in adding reference numerals to the constituent elements of the drawings, the same constituent elements are denoted by the same reference symbols as possible even if they are shown in different drawings. In the following description of the embodiments of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the difference that the embodiments of the present invention are not conclusive.

In describing the components of the embodiment of the present invention, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; may be "connected," "coupled," or "connected. &Quot;

A typical gas turbine disk is shown in FIG. In a typical gas turbine disk, the thickness of the part that joins with the rotating shaft is thick and the thickness becomes thinner toward the outer circumferential surface. Reference numeral 10 denotes a rotating shaft, and a description will be made below with reference to a cross section cut along the line A-B, if necessary.

2 shows a cross section of a gas turbine disk according to the prior art. 2 (a), 2 (b) and 2 (c) are cross-sectional views showing a conventional gas turbine disk. The rotational axis of the gas turbine is contracted in the axial direction as the gas turbine is operated. As a result, the bore portion of the disk coupled with the rotating shaft is also subjected to stress that is compressed in the longitudinal direction of the rotating shaft. A method of increasing the area of the bore portion in order to appropriately disperse such stress has been studied, and accordingly, a form corresponding to Fig. 2 (a) has been proposed. However, this type has a problem that the maximum stress is concentrated at the center of the bore and the stress distribution is uneven.

In FIG. 2 (b), the bore portion is cut along the stress curve. As a result, it was possible to change the maximum stress point at the center of the bore, but the area of the bore portion was reduced, and the average stress was relatively increased.

In FIG. 2 (c), a form in which the hub of the disk is divided into two and the two hubs are combined by reaching the outer circumferential surface of the disk has been proposed. 1 (b), there is an advantage in that the reduction of the cross-sectional area of the bore portion is smaller, but a process of attaching the two hubs to each of the two hubs is additionally required. There was a real problem.

3 shows a gas turbine disk according to an embodiment of the present invention. 3 (a) is a perspective view of a gas turbine disk, and FIG. 3 (b) is a cross-sectional view taken along line A-B of FIG. 3 (a).

Referring to FIG. 3, the disk shown in FIG. 3 is widened toward the hub 30 of the disk as in the conventional technique. The cross-sectional shape of the disk is symmetrical with respect to the reference numeral 20 and the symmetry plane 20 is shown.

The groove 40 is also shown on the symmetry plane 20. The grooves 40 are located on the bore along the symmetry plane 20. The depth of the groove 40 is not particularly limited, and various applications are possible depending on the required situation.

Referring to FIG. 3 (a), in the entire disk, the groove appears in a circle on the bore. In FIG. 3 (b), the dashed line in the left-right symmetry about the groove 40 schematically shows the stress distribution. The higher the height of the dotted line from the borehole, the greater the stress is. If the groove 40 is not present, the stress distribution will be distributed in the shape of the disc bore portion shown in FIG. 2 (c) as a shaved shape and will reach the symmetry plane 20 to exhibit the maximum stress.

However, by creating the grooves 40 on the symmetry plane 20 as in FIG. 3 (b), the stress distribution is minimized at the symmetry plane 20 and symmetrically distributed with respect to the grooves 40. This results in minimal stress at both ends of the bore and in the groove (40), with maximum stress at the midpoint between the ends of the bore and the groove (40). As a result, the generation of the grooves 40 makes it possible to disperse the stress distribution broadly while reducing the decrease in the area of the bore section to a minimum compared to when the groove 40 is absent.

Referring to FIG. 3, an embodiment of the present invention will be described. An annular disk including a hole coupled with a rotary shaft 10, the disk having a bore portion that is an inner circumferential surface contacting the rotary shaft 10, And a hub 30 connecting the outer circumferential surface of the disk.

Characterized in that at least one groove starting from the bore section and extending toward the outer circumferential surface is formed in the hub and the groove further comprises a third groove (40) formed along the symmetry plane (20) of the disk. Disk.

Figure 4 shows various forms of grooves according to embodiments of the present invention. Fig. 4 (a) shows two grooves 40 in the bore section, and Fig. 4 (b) shows this along the section A-B. 4 (c) shows three grooves 40 in the bore section, and Fig. 4 (d) shows this along the section A-B. Fig. 4 (e) shows four grooves 40 in the bore section, and Fig. 4 (f) shows this along the section A-B.

Referring to Figures 4 (a) and 4 (b), two grooves 40 divide the bore into three parts. In this case, the two grooves 40 are symmetrical with respect to the symmetry plane 20, but are not formed in the circumferential direction in the bore section but are inclined toward the symmetry plane 20, respectively. This is because the groove 40 is inclined corresponding to the shape in which the turbine disk is gradually widened from the rim to the hub 30 and the bore portion. As a result, the stress distribution is minimized at both ends of the bore and each groove (40), and the maximum stress appears at the center of each section divided by the bore. This results in a more uniform stress distribution than when the groove 40 is single.

4 (c), 4 (d), 4 (e), and 4 (f) show three and four grooves 40, respectively. Grooves 40 located at the center of the groove have symmetrical surfaces 20 The grooves 40 which are formed in the circumferential direction of the disk rotating shaft 10 but not are formed obliquely toward the symmetry plane 20. [ In addition, as the groove 40 is increased, the stressed points are dispersed as a whole, thereby distributing the stress distribution throughout the entire bore portion.

Compared with the case where two grooves 40 are provided, since the two grooves 40 are inclined toward the symmetry plane, the stress concentrates in the vicinity of the symmetry plane 20 as they enter the inside of the hub. Therefore, if the third groove 40 formed along the symmetry plane 20 is formed, there is a sense of dispersing the stress concentration in the hub. Likewise, if four grooves 40 are formed, a more uniform stress distribution can be obtained than when three grooves 40 are present.

In FIG. 4, only four grooves 40 are shown. However, more grooves 40 can be formed if necessary, and the depth and inclination of the grooves 40 can be variously modified.

4 (a) and 4 (b), an embodiment of the present invention is an annular disk including a hole coupled with a rotary shaft, wherein the disk has a bore portion that is an inner circumferential surface contacting the rotation shaft, And a hub connecting the outer circumferential surface of the disk.

The disk includes at least one groove that starts from the bore section and extends toward the outer circumferential surface. The groove is formed on both sides of the symmetry plane with respect to the symmetry plane of the disk that is perpendicular to the longitudinal direction of the rotation axis. 1 < / RTI > groove and a second groove.

4 (c) and 4 (d), an embodiment of the present invention is an annular disk including a hole coupled with a rotation shaft, wherein the disk has a bore portion that is an inner circumferential surface contacting the rotation shaft, And a hub connecting the outer circumferential surface of the disk.

The disk includes at least one groove that starts from the bore section and extends toward the outer circumferential surface. The groove is formed on both sides of the symmetry plane with respect to the symmetry plane of the disk that is perpendicular to the longitudinal direction of the rotation axis. Further comprising a groove and a second groove and a third groove formed along the symmetry plane of the disk.

5 (a), 5 (b) and 5 (c) show the case where three, four, and five grooves 50 are formed in the bore portion of the turbine disk, respectively. The grooves 40 shown in Figs. 3 and 4 and the grooves 50 shown in Fig. 5 cross each other at right angles.

The disk rotating shaft 10 not only shrinks and pulls in the axial direction, but also vibrates in a direction perpendicular to the axial direction to generate shrinkage and tension perpendicular to the axial direction. Therefore, it is possible to generate the grooves 50 in correspondence with this, so that stress and vibrational impact perpendicular to the axial direction can be appropriately absorbed.

5 (a) is a groove 50 formed by three straight lines parallel to the longitudinal direction of the rotary shaft 10, and is formed so as to extend in the circumferential direction or the radial direction of the rotary shaft. 5 (b) is a groove 50 formed by four straight lines parallel to the longitudinal direction of the rotary shaft 10, and is formed so as to extend in the circumferential direction or the radial direction of the rotary shaft. 5 (c) is a groove 50 formed by five straight lines parallel to the longitudinal direction of the rotating shaft 10, and is formed so as to extend in the circumferential direction or the radial direction of the rotating shaft. The grooves 50 of (a), (b), and (c) may be equally spaced from each other.

Although only three to five grooves 50 are shown in the drawing, the grooves 50 can be extended to a larger number if necessary, and the depth at which the grooves 50 are formed is not limited. The direction in which the grooves 50 are formed can also be extended or applied starting from the bore section and extending toward the hub 30.

The grooves 50 formed in FIG. 5 can be simultaneously implemented in combination with the embodiment shown in FIG. 3 or FIG. So the combination will be myriad.

While the present invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiments. That is, within the scope of the present invention, all of the components may be selectively coupled to one or more of them. Furthermore, the terms "comprises", "comprising", or "having" described above mean that a component can be implanted unless otherwise specifically stated, But should be construed as including other elements. All terms, including technical and scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. Commonly used terms, such as predefined terms, should be interpreted to be consistent with the contextual meanings of the related art, and are not to be construed as ideal or overly formal, unless expressly defined to the contrary.

The foregoing description is merely illustrative of the technical idea of the present invention, and various changes and modifications may be made by those skilled in the art without departing from the essential characteristics of the present invention. Therefore, the embodiments disclosed in the present invention are intended to illustrate rather than limit the scope of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

10: disk rotating shaft 20:
30: hub 40: groove
50: Groove

Claims

Wherein the disk includes a bore which is an inner circumferential surface contacting the rotation axis and a hub which connects the bore portion and the outer circumferential surface of the disk,
At least one groove starting from the bore section and extending toward the outer circumferential surface is formed in the hub,
And the groove is a fourth groove formed on the bore portion in parallel with the rotation axis.

The method according to claim 1,
Further comprising a first groove and a second groove formed on both sides of the symmetry plane with respect to a symmetry plane of the disk which is perpendicular to the longitudinal direction of the rotary shaft.

3. The method of claim 2,
Further comprising a third groove formed along the symmetry plane of the disk.

The method of claim 3,
Wherein the first groove and the second groove are inclined toward the third groove.

5. The method of claim 4,
Wherein the first groove and the second groove are symmetrical with respect to the third groove.

delete

The method according to claim 1,
Wherein at least two of the fourth grooves are formed to be equally spaced.