KR101771216B1 - complex sealing apparatus for turbine - Google Patents

Abstract

The present invention relates to a complex sealing device for a turbine, which includes a sealing unit mounted on the inner peripheral surface of a casing in order to seal the flow of a fluid discharged between the casing of a turbine and a rotor rotating inside the casing, thereby improving sealing performance against the fluid flowing between the casing and the rotor. The complex sealing device for turbine comprises: a first honeycomb sealing unit where a plurality of first section units are arranged in a honeycomb structure in a radial direction in order to decompress a fluid in the inner peripheral surface of the casing; and a second honeycomb sealing unit which is formed to be stepped from the inner peripheral surface of the first honeycomb sealing unit and where a plurality of second section units are arranged in a honeycomb structure in a radial direction. The complex sealing device includes a pair of honeycomb sealing units where the first honeycomb sealing unit is placed at the back side of the second honeycomb sealing unit so that throttling can be performed along the flowing direction of the fluid. In addition, a first sealing gap between the first honeycomb sealing unit and the rotor is formed larger than a second sealing gap between the second honeycomb sealing unit and the rotor. A brush unit is placed between the pair of honeycomb sealing units. The brush unit includes a plurality of Bristol plates of which one end is fixed at the center of the sealing unit and the other end is separated from the outer peripheral surface of the rotor by corresponding to a preset first gap. The first gap is formed smaller than a gap between the honeycomb sealing unit and the rotor.

Description

Complex sealing apparatus for turbine

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a hybrid sealing device for a turbine, and more particularly, to a combined sealing device for a turbine with improved sealability against fluid flowing between the casing and the rotating body.

Generally, a turbine is a machine that converts the energy of a fluid such as water, gas or steam into rotational force. That is, a turbo type machine in which a rotary body formed with blades along the outer periphery is rotatably disposed inside a casing, and high-temperature steam or gas is blown to the blades to rotate at a high speed.

In this turbine, the fluid leaking between the rotating body and the fixed casing becomes a main cause of increasing the fuel cost by lowering the efficiency of the turbine, so that the importance of design technique of a seaing device for reducing fluid leakage is increasing, And it plays an important role in reducing vibration generation of the rotating body due to abnormal behavior of the fluid.

1 is a cross-sectional view showing a state where a conventional labyrinth-type sealing apparatus is mounted on a turbine, and Fig. 2 is a sectional view showing a conventional labyrinth-type sealing apparatus.

As shown in Figs. 1 and 2, a conventional labyrinth type sealing apparatus 5 is installed in the outer ring and the inner ring of the diaphragm 3 mounted on the casing 2. [ Here, the labyrinth type sealing device 5 is a non-contact type sealing device that uses a throttling process of fluid passing through a sharp tooth 6 to reduce the leakage flow rate.

In detail, the fluid flows along the space between the tooth 6 and the rotating body 1, which are arranged in order along the fluid flow direction, and the pressure drop effect generated in the process of repeating the throttling and the enlarging, The leakage flow rate can be reduced.

However, the labyrinth-type sealing device 5 has to have a plurality of the teeth 6 in order to increase the efficiency of the pressure drop. Further, in the above case, the pressure reducing effect is increased. However, as the leakage flow rate is rapidly reduced, the vibration of the rotating body 1 is caused and the teeth 6 are contacted to wear. In addition, there is a problem that loss of rotational force occurs due to vibration of the rotating body 1, and efficiency of the turbine is lowered.

3 is a cross-sectional view of a conventional brush sealing apparatus.

3, the conventional brush sealing apparatus includes a brush portion 7 for sealing the gap between the rotary body 1 and the diaphragm 3, and a brush portion 7 for covering and supporting the front and rear sides of the brush portion 7 And a bristle plate (8, 9).

Here, the brush part 7 is provided in a densely packed form with a plurality of bristles, and can divide the high-pressure area and the low-pressure area to reduce the leakage of the fluid.

At this time, the leakage flow of the fluid can be reduced as compared with the labyrinth type sealing device 5 as the lower ends of the bristles come into contact with the outer circumference of the rotating body 1 with the upper end fixed, The frame is flexed flexibly and the rotation movement loss amount is reduced by supporting the outer periphery of the rotating body 1. [

However, since the bristle sealing device has a large area exposed to the lower portion of the bristle plates 8 and 9 and the substantial reduction in the pressure reduction efficiency due to the abrasion due to the direct contact with the rotating body 1, the sealing performance is somewhat deteriorated .

Korean Patent Publication No. 10-2000-0016885

SUMMARY OF THE INVENTION In order to solve the above problems, the present invention provides a combined sealing device for a turbine having improved sealability against fluid flowing between a casing and a rotating body.

In order to solve the above problems, the present invention provides a turbine composite sealing apparatus comprising a turbine casing and a sealing portion mounted on an inner circumferential surface of the casing to seal a flow of fluid flowing between the turbine casing and a rotating body rotated from the inside of the casing A first honeycomb sealing portion having a plurality of first compartment portions arranged in a radial direction as a honeycomb structure so that the fluid is decompressed on the inner circumferential surface of the casing; a plurality of second honeycomb sealing portions formed stepwise from the inner circumferential surface of the first honeycomb sealing portion, And a second honeycomb sealing portion disposed radially as a honeycomb structure, wherein the honeycomb sealing portion is disposed on a rear side of the second honeycomb sealing portion along the flow direction of the fluid so that the first and second honeycomb- Wherein the first sealing interval between the first honeycomb sealing portion and the rotating body is shorter than the first sealing interval between the second honeycomb sealing portion and the rotating body And the other end of the honeycomb sealing portion is fixed to the center of the sealing portion and the other end of the honeycomb sealing portion is fixed to the outer circumferential surface of the rotating body by a predetermined amount Wherein the first gap is formed to be smaller than the gap between the honeycomb sealing portion and the rotating body, wherein the first gap is smaller than the gap between the honeycomb sealing portion and the rotating body .

Here, the honeycomb sealing portion may be formed of a nickel-chrome alloy steel.

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Preferably, the partition is formed to be inclined along the flow direction of the fluid radially outward by a predetermined angle unit such that the flow direction of the fluid is changed and the flow distance is increased.

Meanwhile, a guide portion, which is coupled to one side of the sealing portion and is disposed between the first and second honeycomb sealing portions and is spaced apart from the outer circumferential surface of the rotating body by a predetermined second interval, And the guide portion is formed of a metal material having a lower hardness than the metal material forming the rotating body.

The present invention provides the following effects through the above-mentioned solution.

First, the fluid reduced in pressure by the honeycomb sealing portion disposed at the front side of the brush portion is reduced in speed by the brush portion to facilitate diffusion into the flow area, and the pressure reducing effect of the honeycomb sealing portion disposed at the rear side of the brush portion A sealing effect can be remarkably improved.

Second, since the second honeycomb sealing portion, the guide portion, and the first honeycomb sealing portion are provided to increase and decrease the flow area, the reduced pressure due to the throttling action and the reduced pressure using the diffusion of the fluid due to the difference in area, Can be further improved.

Thirdly, since the honeycomb sealing part is provided so that the fluid introduced into the partition part is changed in direction by the vortex phenomenon and the pressure acts as a reaction force to be depressurized, there is no contact with the rotating body and a direct influence on the high- The durability can be further improved.

1 is a cross-sectional view showing a state where a conventional labyrinth type sealing device is mounted on a turbine.
2 is a side sectional view showing a conventional labyrinth type sealing apparatus.
3 is a side cross-sectional view of a conventional brush seal device;
4 is a cross-sectional view illustrating a state in which a hybrid sealing apparatus for a turbine according to an embodiment of the present invention is mounted on a turbine.
5 is a cross-sectional view of a composite sealing apparatus for a turbine according to an embodiment of the present invention.
6 is a cross-sectional view of a first compartment of a turbine composite sealing apparatus according to an embodiment of the present invention.
7 is a sectional view showing a modified example of a honeycomb sealing portion of a turbine composite sealing apparatus according to an embodiment of the present invention.
8 is a cross-sectional view of a composite sealing apparatus for a turbine according to another embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a hybrid sealing apparatus for a turbine according to a preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings.

FIG. 4 is a cross-sectional view showing a state in which a hybrid sealing apparatus for a turbine according to an embodiment of the present invention is mounted on a turbine, FIG. 5 is a sectional view showing a hybrid sealing apparatus for a turbine according to an embodiment of the present invention, Sectional view of a first compartment of a hybrid sealing apparatus for a turbine according to an embodiment of the present invention.

4, the hybrid sealing apparatus 100 for a turbine according to an embodiment of the present invention is mounted to seal the flow of the fluid f leaking between the casing 20 of the turbine and the rotating body 10 .

Here, it is preferable that the rotor 10 includes a rotor portion having a plurality of blades 27a coupled to the outer periphery thereof. At this time, the turbine composite sealing apparatus 100 may be provided in a ring shape, and may be disposed along the circumferential direction between the outer circumference of the rotating body 10 and the inner circumference of the casing 20.

The term sealing the flow of the fluid f means that the flow of the fluid f in the forward high pressure region of the blade 27a of the rotary body 10 is blocked so that the rotation of the rotary body 10 can be smoothly performed It is desirable to understand that the leakage fluid f is minimized.

Of course, the turbine composite sealing apparatus 100 is disposed between the casing 20 and the end of the blade 27a and between the casing 20 and the cylindrical body of the rotor section, Can be reduced. In addition, it may be installed at any place where sealing is required between the rotating body 10 rotated in the casing 20 and the casing 20 fixed thereto.

4, the blade 27a is provided with a fluid f, such as a vapor or a gas, which flows into the casing 20 and then passes through the partition 27 of the diaphragm fixed to the casing 20, . Then, the fluid (f) is discharged to the outside through the step of rotating the next blade (27a) according to the guidance of the partition (27).

Through this process, the generator receives the rotational force through the rotor portion rotated together with the respective blades 27a, and the rotational force can be converted into electrical energy.

5, the turbine composite sealing apparatus 100 includes a sealing unit 110, a brush unit 140, and a honeycomb sealing unit 130. As shown in FIG.

The sealing part 110 may be formed in the casing 20 so as to seal the flow of the fluid f discharged between the casing 20 and the rotating body 10 rotated inside the casing 20 And is coupled to the inner peripheral surface.

In detail, the sealing portion 110 is formed in a ring shape so that the fluid f can be sealed by covering the circumferential surface of the rotating body 10 and the inner circumferential surface of the casing 20 in the circumferential direction. At this time, the sealing part 110 may be provided in a complete ring shape, but it is preferably formed in a ring shape through assembly by being divided at a predetermined angle for convenience of mounting.

A coupling groove 21 is formed on an inner circumferential surface of the casing 20 to mount the sealing portion 110 and a coupling groove 21 is formed on an outer end of the coupling portion 21 to correspond to the coupling groove 21. The engaging projections 111 are projected.

Here, the inner side is preferably understood as the direction of the rotating body 10, and the outer side is preferably understood as the direction of the casing 20.

At this time, it is preferable that an elastic member 111a is provided between the coupling groove 21 and the coupling protrusion 111. The coupling protrusion 111 of the sealing portion 110 is formed by the elastic member 111a And can be elastically supported radially inward.

Accordingly, excessive contact with the outer circumferential surface of the rotating body 10 due to vibration and expansion is prevented, so that abrasion and damage are minimized, and the rotational force loss of the rotating body 10 Can be minimized.

Of course, the elastic member 111a may be further provided on the rear surface of the coupling protrusion 111, as the case may be. In this case, the end portion where the coupling protrusion 111 and the sealing portion 110 are connected to each other is damped by the load applied by the high-pressure fluid f flowing from the front side, thereby improving durability.

Here, the front side is preferably understood as a direction in which the fluid f flows, and the rear side is preferably understood as a direction in which the fluid f is exhausted.

The brush 140 is fixed to the central portion of the sealing portion 110 at one end thereof and has a plurality of bristles spaced apart from the outer circumference of the rotary body 10 at a predetermined first interval A, And a frame 141. At this time, the bridges 141 are brought into contact with or spaced from the rotary body 10 according to the setting of the first interval A.

Each of the bristles 141 may be formed of a flexible material having elasticity and heat resistance and may be closely packed with the adjacent bristles 141. The bristles 141 may have one end 141b, Can be fixed by electric beam welding (EBW) or by an adhesive material which is stable at high temperatures.

At this time, each of the bristles 141 is directly fixed to the brush groove 112 formed at the center of the sealing part 110. It is also possible that the brush plate 142 is fixed to the brush groove 112 while being fixed to a separate member such as a brush plate 142 or the like.

The ends of the bridges 141 are connected to the outer circumference of the rotator 10 and the other end of the bridges 141, And a length having a predetermined first spacing (A).

The brush 140 may further include a shock preventing portion 142a covering the front of each of the bristles 141 and a supporting portion 142b supporting the rear of each of the bristles 141 have. The shock preventing portion 142a and the support portion 142b may be integrally formed with the brush plate 142 to which the bristles 141 are coupled.

In detail, the shock-preventing portion 142a covers the front surface of the bristles 141 to prevent the high-pressure fluid f flowing at high speed from coming into direct contact with the bristles 141. In addition, wear and damage of the bristles 141 due to foreign matter in the fluid f and the pressure of the fluid f itself can be minimized.

The support portion 142b supports the rear surface of the bristles 141 and supports the bristles 141 along the flow direction of the fluid f when the fluid f passes between the bristles 141. [ 141 can be prevented from being bent backward.

That is, even if a high-pressure fluid f presses and passes through the bristles 141, the ends of the bristles 141 do not move away from the outer periphery of the rotary body 10, Performance can be improved.

Meanwhile, it is preferable that the honeycomb sealing parts 130 are provided as a pair. In detail, the honeycomb sealing part 130 is provided at a front side of the brush part 140 so that the fluid f is in contact with the bristles 141 under reduced pressure. The honeycomb sealing part 130 is provided on the rear side of the brush part 140 so that the fluid f whose pressure is lowered by the brush part 140 flows smoothly and the fluid f is decompressed .

That is, the honeycomb sealing parts 130 are substantially provided as a pair, and the brush part 140 is provided between the pair of honeycomb sealing parts 130.

Here, the honeycomb sealing part 130 is continuously provided along the circumferential direction on the inner circumferential surface of the sealing part 110 and may be fixed by welding or adhesion.

As a matter of course, a groove may be formed in the sealing part 110 and protrusions may be formed on the outer end of the honeycomb sealing part 130, so that the sealing part 110 may be inserted into the sealing part 110. Alternatively, As shown in FIG.

In addition, the honeycomb sealing part 130 may be arranged in a radial direction so that the fluid f is decompressed, and the compartment is disposed perpendicularly to the rotating body 10. At this time, as the inlet of the partition faces the outer circumferential surface of the rotary body 10, the fluid f flowing in can be introduced in the inlet direction.

The honeycomb sealing part 130 may be made of nickel-chromium alloy steel (Ni-Cr alloy steel). Here, the honeycomb sealing portion 130 may be formed of iron, nickel, or cobalt alloy having a low thermal expansion coefficient so as to have heat resistance to the high-temperature fluid (f).

Of course, since it may be made of other kinds of heat-resistant alloys depending on the case, it is preferable that it is made of a material which is not limited in material but has heat resistance and is easy to use in the process.

Meanwhile, the honeycomb sealing part 130 includes a first honeycomb sealing part 131 in which a plurality of first compartments 131a are disposed in a honeycomb structure, and a plurality of second compartments 132a in a honeycomb structure And a second honeycomb sealing portion 132 formed on the second honeycomb sealing portion 132.

In detail, since the plurality of first compartments 131a and the plurality of second compartments 132a are provided in a honeycomb structure, a maximum space can be ensured without using a minimum amount of material. At this time, the cross sections of the first partition 131a and the second partition 132a are preferably formed in a regular hexagonal shape corresponding to the honeycomb structure. Each of the partitioning parts 131a and 132a is open at one side to form an inlet port, and a space part into which the fluid f can flow can be formed.

Here, if a honeycomb structure is formed by a cross section of a regular hexagon, a plurality of sides are formed to be supported at various angles so that a buffering effect against an external impact can be reinforced. Of course, the sections of the partitioning parts 131a and 132a may be formed in various shapes such as a square shape and a circular shape.

In addition, it is preferable that the sectional shape of each of the partitioning parts 131a and 132a substantially corresponds to the shape and size of the cross section of the partitioning parts 131a and 132a, . When the shape or size of each of the dividing sections 131a and 132a is different from that of the dividing sections 131a and 132a, the reduced pressure of the fluid f due to the difference in area of the inlet port through which the fluid f flows in correspondence to the shape or size of the cross- .

5 to 6, the fluid f is discharged to the inside of the second honeycomb sealing portion 132, that is, between the second honeycomb sealing portion 132 and the rotating body 10 And flows into the two sealing intervals (C2). At this time, the flow area of the fluid (f) formed at the second sealing interval (C2) is sharply lower than the flow area formed at the front side of the turbine composite sealing apparatus (100) .

At this time, a part of the fluid f is diffused in the outer direction of the second honeycomb sealing portion 132, that is, in the direction of the inlet port of the second partitioning portion 132a by the reduced flow area, 132a.

Here, the fluid f flowing into the second compartment 132a flows into the second compartment 132a and a reaction force opposing to the fluid f discharged therefrom is applied to generate a reduced pressure . That is, since the pressure of the fluid f is generated in the plurality of second compartments 131a, the pressure of the fluid f passing through the second honeycomb sealing part 132 becomes lower toward the rear side from the front side .

The fluid f passed through the second honeycomb sealing portion 132 is discharged through the first honeycomb sealing portion 131 and the rotating body 130 disposed on the rear side of the second honeycomb sealing portion 132 10).

 At this time, the second honeycomb sealing portion 132 is formed to be stepped from the inner circumferential surface of the first honeycomb sealing portion 131 so that the flow area of the fluid f is different.

In detail, the second honeycomb sealing portion 132 is further protruded inward than the first honeycomb sealing portion 131, so that the first honeycomb sealing portion 131 and the rotating body 10 A gap between the first sealing interval C1 formed and the second sealing interval C2 occurs. At this time, since the first sealing interval C1 is formed to be larger than the second sealing interval C2, the flow area of the fluid f can be further increased.

Accordingly, the fluid f can be flown toward the inlet of the first compartment 131a after passing through the second honeycomb sealing part 132 by the diffusion due to the difference in flow area.

At this time, the pressure reducing action of the fluid f is generated in the first partition 131a so as to correspond to the depressurizing action of the second compartment 132a. That is, the fluid f passing through the second honeycomb sealing portion 132 and the second honeycomb sealing portion 131 may be continuously decompressed. Therefore, the second honeycomb sealing portion 132 and the first honeycomb sealing portion 131 (see FIG. 3) are formed so as to perform the diaphragm operation by using the gap between the first sealing interval C1 and the second sealing interval C2. Are arranged along the flow direction of the fluid f.

Further, the brush 140 is disposed on the rear side of the second honeycomb sealing part 132 and the first honeycomb sealing part 131. Since the fluid f is in contact with the brush 140 in a state where the fluid f is depressurized by the second honeycomb sealing part 132 and the first honeycomb sealing part 131, Wear and damage can be minimized.

As the second honeycomb sealing portion 132 and the first honeycomb sealing portion 131 are disposed on the rear side of the brush portion 140, the brush portion 140 140 can be reduced.

That is, since the flow area of the fluid f is drastically reduced and increased by the second honeycomb sealing part 132, the first honeycomb sealing part 131 and the brush part 140, So that the pressure can be reduced.

Accordingly, the fluid f reduced by the honeycomb sealing part 130 disposed on the front side of the brush part 140 is decelerated by the brush part 140 and is easily diffused into the flow area The synergistic effect of increasing the depressurizing effect of the honeycomb sealing part 130 disposed at the rear side of the brush part 140 is provided and the sealing ability can be remarkably improved.

The first honeycomb sealing part 131 and the second honeycomb sealing part 132 are provided so that a part of the pressure of the fluid f acts as a reaction force to generate a reduced pressure so that there is no contact with the rotating body, It has less direct influence on high-pressure fluids, and wear and damage of the components due to high pressure is minimized, so that the durability can be improved.

Of course, depending on the size of the sealing part 110, the brush part 140 may be provided in plurality, and the second honeycomb sealing part 132, The sealing portion 131 may be disposed on the front side and the rear side of the brush portion 140.

7 is a cross-sectional view showing a modified example of a honeycomb sealing portion of a turbine composite sealing apparatus according to an embodiment of the present invention. In the present modified example, the basic configuration except for the honeycomb sealing portion is the same as that of the above-described embodiment, so a detailed description of the constitution will be omitted.

7, the partitioning portion 331 of the honeycomb sealing portion 330 is formed so that the flow direction of the fluid f is changed and the flow of the fluid f is radially outward by a predetermined angle unit such that the flow distance is increased. As shown in Fig.

Here, since the partition 331 is formed in a substantially diagonal direction, the length of the partition defined by the inlet is greater than the length of the partition formed by the vertical direction. The partitioning portion 331 is formed to be inclined along the flow direction of the fluid f toward the radially outer side and corresponds to the traveling direction of the fluid f flowing from the flow area formed by the first gap A So that the fluid f can be easily introduced.

At this time, as the fluid f easily flows into the inside of the partitioning portion 331, the flow distance of the fluid f increases and the pressure is lowered, so that the pressure reducing effect can be further improved.

When the vortex phenomenon is generated from the inside of the partitioning portion 331 and the fluid f is discharged from the partitioning portion 331 and the fluid f is switched to be substantially opposite to the traveling direction of the fluid f, It is possible to provide a reaction force against the traveling direction of the vehicle. Therefore, as the fluid f is partitioned into the plurality of partitioning sections 331, the reaction force is increased and the pressure of the fluid f is further lowered, so that the sealing performance can be improved.

Of course, the partition 331 may be inclined radially outwardly in the circumferential direction corresponding to the induction angle in the flow direction of the fluid f, as the case may be. In this case, since the induction angle is formed to correspond to the rotating direction of the rotating body 10, the fluid f can easily flow into the rotating body 10, and a reaction force opposite to the rotating direction of the rotating body 10 The resonance phenomenon can be minimized.

Further, the partitioning part 331 is inclined along the flow direction of the fluid f radially outward corresponding to the predetermined angle, and corresponds to the induction angle of the flow direction of the fluid f in the circumferential direction As shown in FIG. At this time, in the above case, the sealing property is reinforced and the resonance phenomenon is minimized, and such modifications are within the scope of the present invention.

8 is a cross-sectional view of a hybrid sealing apparatus for a turbine according to another embodiment of the present invention. In this embodiment, the basic configuration except for the sealing portion is the same as that of the above-described embodiment, so a detailed description of the configuration will be omitted.

8, the sealing portion 210 is formed at the outer end of the sealing portion 210 so as to be mounted on the coupling groove 21 formed in the casing 20, corresponding to the above- The projection 211 can be projected. An elastic member 211a may be provided between the coupling groove 21 and the coupling protrusion 211. The coupling protrusion 211 of the sealing portion 210 may be formed by the elastic member 211a, It can be elastically supported inward in the direction.

The sealing part 210 is provided with a first honeycomb sealing part 231 in which a plurality of first compartments 231a are arranged in a honeycomb structure so as to substantially correspond to the above embodiment, A honeycomb sealing portion 230 including a second honeycomb sealing portion 232 having a honeycomb structure 232a may be provided.

At this time, the honeycomb sealing parts 230 are provided in a pair, and the first honeycomb sealing part 231 and the second honeycomb sealing part 232 are disposed along the flow direction of the fluid f . The second honeycomb sealing portion 232 may be formed to be stepped from the inner circumferential surface of the first honeycomb sealing portion 231.

Meanwhile, the sealing part 210 may further include a guide part 220. At this time, the guide part 220 may be coupled to one side of the sealing part 210 while the sealing part 210 is adjacent to the rotating body 10.

In detail, the guide part 220 is continuously connected to the inner circumferential surface of the sealing part 210 along the circumferential direction, and can be fixed by welding or a stable adhesive material at a high temperature. As a matter of course, a mounting groove may be formed in the sealing portion 210, and the guide portion 220 may be inserted and then coupled by means of interference fit or caulking.

Preferably, the guide portion 220 is spaced apart from the outer circumferential surface of the rotating body 10 by a predetermined second interval B. At this time, the fluid f flows into the gap formed at the second gap B, and the flow area through which the fluid f flows into the guide portion 220 is sharply reduced, have.

In addition, the flow rate of the fluid f passing through the guide portion 220 increases, but the pressure decreases rapidly. Here, at the rear side of the guide part 220, the fluid f may flow through the entire area of the flow area which is rapidly expanded again by diffusion.

Therefore, it is preferable that the guide part 220 is provided between the first honeycomb sealing part 231 and the second honeycomb sealing part 232 to increase the pressure reducing effect .

In detail, the fluid (f) flowing into the turbine composite sealing apparatus 200 is reduced in pressure as the flow area of the fluid f is rapidly reduced by the second honeycomb sealing portion 232 disposed at the front side .

Here, the fluid f may flow into the second gap B formed on the inner side in the radial direction of the guide portion 220 disposed on the rear side of the second honeycomb sealing portion 232. At this time, the second gap B may be smaller than the gap between the second honeycomb sealing portion 232 and the rotating body 10, and the flow area formed by the second gap B may be The pressure of the fluid (f) decreases and the speed increases rapidly.

In addition, since the first honeycomb sealing portion 231 is provided on the rear side of the guide portion 220, the flow area of the fluid f increases rapidly, and the efficiency of the throttle operation can be further increased. In addition, the sealing part 21 is provided with a pair of honeycomb sealing parts 230 and the guide part 233 disposed between the second honeycomb sealing part 232 and the first honeycomb sealing part 231, The fluid (f), which is continuously generated by the diaphragm (220) and is caused to flow, can be decompressed.

Accordingly, since the guide 220 is disposed between the second honeycomb sealing part 232 and the first honeycomb sealing part 231, the combined sealing device 200 for a turbine can increase and decrease the flow area And the efficiency of the throttling operation is increased, so that a synergy effect between the respective components can be provided and the sealing performance can be improved.

Of course, the plurality of guide portions 220 may be appropriately disposed and fixed at positions where the pressure reduction is required.

The guide 220 may be made of a metal having a lower hardness than that of the rotor. At this time, the guide part 220 may be made of a flexible material having low hardness such as brass or copper alloy.

Of course, since the guide part 220 may be made of copper or a nickel alloy, the guide part 220 may be made of a metal having a low hardness so as not to be damaged by the high pressure fluid f .

In detail, the guide part 220 is subjected to the pressure of the fluid f directly flowing from the front side to the front part. Therefore, since the guide part 220 is made of a metal material having a low hardness, the guide part 220 can flexibly cope with a high pressure because deformation and breakage may be caused by a high pressure.

In addition, the guide part 220 may be linearly contacted to the end of the blade 27a by vibration or the like and may be in contact with the blade 27a and the sealing part 210, Wear or breakage can be prevented.

Further, the guide part 220 may be provided so that the other end thereof becomes narrower toward the inside. In this case, since the flow area is gradually narrowed while the fluid f flows into the gap formed by the second gap B in the above case, the damage of the guide part 220 due to the sudden high pressure is prevented .

The guide part 220 may be provided with a plurality of switching holes along the circumferential direction so that the flow direction of the fluid f is easily switched. The flow of the fluid f in the direction of the honeycomb sealing part 230 can be easily switched, although the switching hole is inclined from the inside toward the outside and the pressure reducing effect can be reduced.

As described above, the present invention is not limited to the above-described embodiments, and variations and modifications may be made by those skilled in the art without departing from the scope of the present invention. And these modifications fall within the scope of the present invention.

10: rotating body 20: casing
27: partition 27a: blade
110, 210: sealing part 111, 211:
130, 230, 330: Honeycomb sealing part 131, 231: First honeycomb sealing part
132,232: Second honeycomb sealing part 140: Brush part
220: guide part 100, 200: composite sealing device for turbine

Claims (5)

And a sealing portion mounted on an inner circumferential surface of the casing for sealing a flow of fluid flowing between a casing of the turbine and a rotating body rotated inside the casing,
A first honeycomb sealing portion in which a plurality of first compartment portions are arranged in a radial direction as a honeycomb structure so that the fluid is decompressed on the inner circumferential surface of the casing and a plurality of second compartment sealing portions formed stepwise from the inner circumferential surface of the first honeycomb sealing portion, And a second honeycomb sealing portion disposed radially as a honeycomb structure, wherein a honeycomb sealing portion having the first honeycomb sealing portion disposed on the rear side of the second honeycomb sealing portion along the flow direction of the fluid so as to perform the diaphragm action Including,
Wherein a first sealing gap between the first honeycomb sealing portion and the rotating body is formed to be larger than a second sealing gap between the second honeycomb sealing portion and the rotating body,
Wherein the honeycomb sealing portions are provided in a pair and one end portion of the honeycomb sealing portion is fixed to a central portion of the sealing portion and the other end portion of the plurality of viscous sealing portions is spaced apart from the outer circumferential surface of the rotating body by a predetermined first interval, Wherein the first gap is formed to be smaller than the gap between the honeycomb sealing portion and the rotating body. delete The method according to claim 1,
Wherein the honeycomb sealing portion is formed of a nickel-chromium alloy steel material. The method according to claim 1,
Wherein the first and second compartments are formed such that the first and second compartments are inclined along the fluid flow direction radially outward by a predetermined angle unit such that the flow direction of the fluid is changed and the flow distance is increased. The method according to claim 1,
And a guide portion coupled to one side of the sealing portion and disposed between the first and second honeycomb sealing portions and spaced apart from the outer circumferential surface of the rotating body by a predetermined second interval, ,
Wherein the guide portion is formed of a metal material having a lower hardness than a metal material forming the rotating body.

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