KR101509383B1 - A cooling device for a turbine - Google Patents

Abstract

The present invention relates to a turbine cooling device, which consists of a blade-type unit equipped with a device containing high-temperature liquid for turbine operation and cooling tubes through which air can pass for cooling; air supply tubes that supply cooling air to the blade-type cooling tubes; and a support member with dust collection grooves that collect debris coming in with cooling air on one side of the air supply tubes. The blade-type unit is composed of rotor blades that turn the rotor driven by the turbine′s liquid while the support member is set up in ways to rotate axially with the rotor. On the exterior, the system has a rotor wheel of which rotor blades are a part while the air supply tubes include the air inflow tubes and the air outflow tubes with a certain angle between them. At the end of the air inflow tubes, there are dust collection grooves while the rotor wheel comes with the rotor blade fixing grooves on the exterior. The air inflow tubes are formed by penetrating the rotor wheel on the side. The air outflow tubes include the turbine cooling device with features that it is formed by penetration to the side of the air inflow tubes from the blade fixing grooves. In this way, the present invention can remove debris coming from air vents, thereby preventing malfunction of the system due to blocked air vents.

Description

[0001] The present invention relates to a cooling device for a turbine,

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a turbine cooling apparatus, and more particularly, to a turbine cooling apparatus that air-cools a rotor blade or a fixed blade of a turbine exposed to a high temperature fluid.

2. Description of the Related Art In general, a turbo machine such as a gas turbine or a steam turbine (hereinafter referred to as a turbomachine having a turbine including a gas turbine and a steam turbine) is a turbomachine having a power for converting heat energy of a fluid into rotational force Generating device includes a rotating body that rotates about a shaft by a fluid, and a fixed body that supports and surrounds the rotating body.

The steam turbine includes a high pressure (HP) turbine, a medium pressure (IP) turbine, and a low pressure (LP) turbine in series or in parallel. In the case of the series structure, the high pressure, medium pressure and low pressure turbines share one rotor. In steam turbines, high-pressure steam drives the rotor of a high-pressure (HP) turbine, a medium-pressure (IP) turbine, and a low-pressure (LP) turbine to rotate the rotor.

1, the gas turbine includes a combustor 110 for generating a combustion gas, a turbine 120 driven by a combustion gas discharged from the combustor 110, and a high-pressure air And a compressor 130 for supplying the refrigerant.

The compressor 130 is rotated to suck and compress the outside air to send it to the combustor 110. The combustor 110 supplies fuel to the compressed air to generate combustion gas to generate high temperature and high pressure combustion gas, And the high temperature and high pressure combustion gas discharged from the combustor 110 drives the rotor blades of the turbine 120 to rotate the rotor 140 of the turbine 120.

In the turbine 120, fixed wings 121, 123, and 125 and rotor blades 122, 124, and 126 are alternately disposed in multiple stages along the axial direction of the rotor 140.

However, there is a fear that the gas turbine and the steam turbine are deformed or damaged due to the high temperature and high pressure combustion gas or steam acting on the rotor blade. Therefore, a method of circulating air through the rotor blade of the turbine is adopted. Korean Patent Publication No. 2011-0021933 discloses an example of the technique in detail.

2 and 3, a rotor wheel 101 is provided on the outer side of the rotor 140, and a plurality of rotor blades 102 are provided on the outer circumferential surface of the rotor wheel 101 at predetermined intervals along the circumferential direction .

A cooling passage 103 is formed in the rotor blade 102 and an air supply passage 104 for supplying air for cooling by the cooling passage 103 of the rotor blade 102 is formed in the rotor wheel 101 .

However, the cooling air flowing into the conventional air supply passage 104 contains foreign substances such as dust and flows into the cooling passage 103 of the rotor blades 102. The air flow path 104 of the rotor wheel 101 and the cooling flow path 103 of the rotor blades 102 are blocked to impede the flow of air and the cooling performance is deteriorated.

The present invention has been made in order to overcome the problems of the conventional turbine cooling apparatus as described above, and it is an object of the present invention to provide a turbine cooling apparatus and a turbine cooling apparatus capable of reducing deterioration of cooling performance by trapping foreign substances flowing into a passage through which air for cooling flows, And a turbine cooling device capable of preventing the turbine cooling device from being damaged.

According to an aspect of the present invention, there is provided a turbine cooling apparatus including: an airfoil member that is exposed to a high-temperature fluid for driving a turbine and has a cooling passage through which air for cooling flows; And an air supply passage for supplying air for cooling by the cooling passage of the airflow member, and a dust collecting groove for collecting foreign matter introduced together with the cooling air is formed on one side of the air supply passage Wherein the support member is rotatably provided integrally with the rotor and the rotor wheel is coupled to the outer circumferential surface of the rotor wheel, Wherein the air supply flow path includes an air inflow path and an air discharge path which form a predetermined angle with respect to each other, a dust collecting groove is formed at the tip of the air inflow path, Wherein the air inlet flow path is formed by perforating the side surface of the rotor wheel, Characterized in that perforation is formed toward the air inlet flow path.
The airfoil member is a fixed blade for guiding the turbine driving fluid to the rotor blade, and the supporting member is a supporting ring fixed to one side of the turbine.
And the air inflow passage and the dust collecting groove are formed on the same straight line
And the dust collecting groove is formed so as to communicate with the front end of the air discharge passage.
And the air discharge passage and the dust collecting groove are formed on the same straight line.
And the dust collecting groove is formed by drilling.
And the dust collecting groove is formed by electric discharge machining.

According to another aspect of the present invention, there is provided a turbine cooling apparatus including: an airfoil member which is exposed to a high-temperature fluid for driving a turbine and has a cooling passage through which air for cooling flows; And an air supply passage for supplying air for cooling by the cooling passage of the airflow member, and a dust collecting groove for collecting foreign matter introduced together with the cooling air is formed on one side of the air supply passage Wherein the air supply flow path includes an air inflow path and an air discharge path which form a predetermined angle with respect to each other, a dust trapping groove is formed at a tip end of the air inflow path, Is formed to be inclined to the opposite side with a predetermined angle with respect to the rotation direction of the rotor.

According to another aspect of the present invention, there is provided a turbine cooling apparatus including: an airfoil member which is exposed to a high-temperature fluid for driving a turbine and has a cooling passage through which air for cooling flows; And an air supply passage for supplying air for cooling by the cooling passage of the airflow member, and a dust collecting groove for collecting foreign matter introduced together with the cooling air is formed on one side of the air supply passage Wherein the air supply flow path includes an air inflow path and an air discharge path which form a predetermined angle with respect to each other, a dust trapping groove is formed at a tip end of the air inflow path, Is formed in the radial direction of the rotor.

According to another aspect of the present invention, there is provided a turbine cooling apparatus including: an airfoil member which is exposed to a high-temperature fluid for driving a turbine and has a cooling passage through which air for cooling flows; And an air supply passage for supplying air for cooling by the cooling passage of the airflow member, and a dust collecting groove for collecting foreign matter introduced together with the cooling air is formed on one side of the air supply passage Wherein the air supply flow path includes an air inflow path and an air discharge path which form a predetermined angle with respect to each other, a dust trapping groove is formed at a tip end of the air inflow path, Is formed to be inclined along the axial direction of the rotor.

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As described above, according to the turbine cooling apparatus of the present invention, it is possible to prevent the deterioration of the cooling performance due to the clogging of the air flow path due to the foreign substances by collecting and removing the foreign matter introduced into the flow path through which the air for cooling flows, Therefore, the durability of the rotor blade can be improved.

It is possible to effectively collect the foreign matter by using the rotational force and the centrifugal force of the rotor, and to hold the collected foreign matter so as not to escape.

It is possible to easily and quickly remove the collected foreign matter by drilling, thereby reducing the maintenance cost.

1 is a schematic side cross-sectional view showing a conventional gas turbine,
FIG. 2 is a partially enlarged cross-sectional view showing the turbine cooling apparatus shown in FIG. 1,
Figure 3 is a side view of the turbine disk shown in Figure 2,
4 is a schematic side cross-sectional view of a turbine cooling apparatus according to an embodiment of the present invention,
FIG. 5 is a partial enlarged view of FIG. 4,
6 is a schematic side cross-sectional view of a turbine cooling apparatus according to another embodiment of the present invention,
FIG. 7 is a schematic cross-sectional view cut along the line AA of FIG. 6,
8 is a partially enlarged view of Fig. 7,
9 and 10 are schematic side cross-sectional views of a turbine cooling apparatus according to another embodiment of the present invention.

First, a turbine cooling apparatus according to the present invention is an apparatus for cooling an airfoil member provided in a turbine of a turbo machine.

The airfoil member includes a rotor blade and a fixed blade provided on a path through which a high-temperature fluid for driving the turbine passes. The rotor blade and the fixed blade are provided in a steam turbine and a gas turbine.

The rotor blade is driven by the turbine drive fluid to rotate the rotor, and the rotor blade guides the turbine drive fluid to the rotor blade.

A plurality of the rotor blades and the rotor blades are provided at predetermined intervals along the circumferential direction of the rotor, and the rotor blades and the rotor blades are fixedly coupled to the support members.

The support member includes a rotor wheel axially rotatable with the rotor, and a support ring fixedly coupled to the inside of the casing of the turbine.

The rotor blade is fixedly coupled to the rotor wheel and rotates together with the rotor, and the rotor blade is fixedly coupled to the support ring.

The support ring is provided at the upper and lower ends of the fixed wick to fix both ends of the fixed wick.

The support ring coupled to the upper end of the fixed wing is coupled to the inner wall of the casing and the support ring coupled to the lower end of the fixed wing is fixedly coupled to one side of the rotor housing or transition piece provided in the casing.

The high temperature fluid for turbine operation is steam in steam turbines and combustion gases in gas turbines.

Hereinafter, the case where the turbine cooling apparatus according to the present invention is provided in the rotor blade of the gas turbine and the rotor blade provided in the fixed blade will be described in detail with reference to the drawings.

First Embodiment

4 to 5, a turbine cooling apparatus according to an embodiment of the present invention includes a rotor blade 10 having a cooling passage 12 through which air for cooling flows, And a rotor wheel 20 on which dust collecting grooves 33 for collecting foreign matter are formed.

The rotor blade (10) is provided on the outer circumferential surface of the rotor wheel (20) in the radial direction of the rotor wheel (20). At the lower end of the rotor blade 10, a tapered root 11 for coupling with the rotor wheel 20 is provided. The cooling passage (12) is formed through the root (11) of the rotor blades (10).

The rotor wheel 20 is fixedly coupled to the outer circumferential surface of the rotor and rotates integrally with the rotor. The rotor wheel 20 is formed in a disk shape, and a rotor blade engaging groove 21 is formed on an outer circumferential surface thereof.

The root 11 of the rotor blade 10 is fitted in the rotor blade engagement groove 21 in the axial direction X of the rotor so that the rotor blade 10 is fixedly coupled to the rotor wheel 20.

An air supply passage 30 for supplying air for cooling to the cooling passage 12 of the rotor blade 10 is formed in the rotor wheel 20.

The cooling air flowing from the air supply passage 30 passes through the cooling passage 12 of the rotor blade 10 to cool the rotor blade 10. The cooling air can be taken out from the compressor or supplied from an external separate source.

Although the cooling passage 12 shown in FIG. 4 is formed in the radial direction of the rotor wheel 20, the cooling passage 12 may be formed in various shapes, and the discharge port may be formed at a position other than the upper end of the rotor blade 10. [ Of course.

The air supply passage 30 is composed of an air inflow passage 31 and an air discharge passage 32 communicating with each other at a predetermined angle?

The air inlet flow path 31 is formed by piercing the side surface 22 of the rotor wheel 20 toward the rotor blade engagement groove 21 and the air discharge flow path 32 is formed in the rotor blade 20, And is pierced toward the air inflow passage 31. An inlet of the air inflow passage 31 is formed in a side surface 22 of the rotor wheel 20 and an outlet of the air discharge passage 32 is formed in an inner wall of the rotor blade engaging groove 21 .

The air inflow passage 31 and the air discharge passage 32 are formed by drilling or electric discharge machining (EDM). This is because the rotor wheel 20 is manufactured through a forging process, and therefore, the method of machining the long-hole flow path such as the air inflow path 31 and the air discharge path 32 due to the rigidity of the material is extremely limited But it is also possible to process them by other processing methods.

The air inlet flow path 31 and the air discharge flow path 32 are formed in a straight line by drilling or discharging.

The dust collecting groove 33 is formed by further processing a predetermined depth beyond a point where the air inlet flow path 31 meets the air discharge flow path 32. Therefore, the air inflow passage 31 and the dust collecting groove 33 are formed on the same straight line.

The dust collecting groove 33 is formed so as to communicate with the front end of the air inflow passage 31 so that foreign matter such as dust flowing into the air inflow passage 31 enters the dust collecting groove 33. The dust-collecting groove 33 is formed in a direction different from that of the air discharge passage 32.

5, the air inflow passage 31 is formed in a radial direction R of the rotor, and is formed to be inclined at a predetermined angle? Along the axial direction X of the rotor.

Here, it is preferable that the predetermined angle? Is formed to be larger than 0 degrees and smaller than 90 degrees, and 15 degrees <? <75 degrees. is smaller than 15 degrees or larger than 75 degrees, the angle? between the air inflow passage 31 and the air discharge passage 32 becomes excessively large and the airtight bending abruptly bends at the intersection portion, .

The dust collecting groove 33 is formed on the centrifugal force acting line of the rotor wheel 20 by being formed with the air inflow passage 31 at a predetermined angle a with respect to the radial direction R of the rotor So that the centrifugal force acts on the foreign matter introduced into the dust collecting groove 33, so that it can not easily escape from the dust collecting groove 33 and can be caught.

The air supplied to the air inflow passage 31 flows through the air discharge passage 32 to the cooling passage 12 of the rotor blades 10 so that the rotor blade 10 rotates The air inflow passage 31 is formed in the radial direction R of the rotor similar to the cooling passage 12 of the rotor blades 10 so that air can be moved while minimizing frictional resistance. .

As described above, the air inflow passage 31 and the air discharge passage 32 are formed to have a predetermined angle? Between each other, and the dust collecting groove 33 is formed in a straight line with the air inflow passage 31 . Therefore, the dust-collecting groove 33 also forms an angle? Between the air discharge passage 32 and a predetermined angle?.

Here, it is preferable that the predetermined angle beta is formed to be larger than 0 degrees and smaller than 90 degrees, and 0 degrees < beta < 45 degrees. is larger than 45 degrees, the foreign matter introduced into the dust collecting groove (33) can not stay in the collected state and is affected by the flow of the flowing air, do.

If? is less than 45 degrees, particularly less than 30 degrees, the foreign matter introduced into the dust-collecting groove 33 can not easily escape and can be continuously deposited.

Second Embodiment

6 to 8, the dust collecting groove 43 and the air inflow passage 41 are formed to be inclined to the opposite side with respect to the rotational direction Y of the rotor.

The air supply passage 40 of the present embodiment is also constituted by an air inflow passage 41 and an air discharge passage 42.

6, the air inflow passage 41 and the air discharge passage 42 are formed on the same AA plane. As shown in FIG. 7, the air inflow passage 41 is formed in the rotation direction of the rotor Y with a predetermined angle? Between them.

Here, the predetermined angle? May be greater than 0 degrees and smaller than 90 degrees.

The air inflow passage 41 and the air discharge passage 42 of the present embodiment are also formed to have a predetermined angle beta with respect to each other and the dust collecting groove 43 is formed in a straight line with the air inflow passage 41. Accordingly, the dust-collecting groove 43 also forms a predetermined angle? With the air discharge passage 42. In the same way as in the first embodiment, 0 degree <? <90 degrees, 45 degrees.

The dust collecting groove 43 is inclined at a predetermined angle y opposite to the rotation direction Y of the rotor together with the air inflow passage 41, . Therefore, the reaction force in the reverse rotation direction acts on the foreign matter introduced into the dust-collecting groove 43, so that it can not easily escape from the dust-collecting groove 43 and is caught and deposited.

Third Embodiment

9, the dust collecting grooves 53 and 53 'are formed not only at the front end of the air inflow passage 51 but also at the front end of the air discharge passage 52.

In this case also, the air discharge passage 52 and the dust collecting groove 53 'are formed on the same straight line because the air discharge passage 52 and the dust collecting groove 53' are formed by drilling or electric discharge machining.

The dust collecting groove 53 'formed at the tip of the air discharging passage 52 is a modification of the second embodiment and is formed in a dust collecting groove (not shown) formed at the tip of the air inflow passage 51 with respect to the radial direction of the rotor wheel 20 53, so that collection by centrifugal force similar to that of the first embodiment is difficult, but collection by the same rotational force as in the second embodiment is possible.

When only one dust collecting groove 53 is provided by forming both the dust collecting grooves 53 and 53 'at the ends of the air inflow passage 51 and the air discharging passage 52 as shown in FIG. 9 The dust collecting effect becomes larger.

Fourth Embodiment

Referring to FIG. 10, a turbine cooling apparatus according to another embodiment of the present invention includes a fixed blade 70 having a cooling passage 71 through which air for cooling flows, and a foreign matter introduced together with the cooling air. And a support ring 80 on which dust collecting grooves 63 are formed.

The fixed blade 70 of this embodiment guides the combustion gas to the rear rotor blade 10 by the first nozzle vane provided at the discharge tip of the transition piece 111 of the combustor.

The support ring 80 is provided at the upper end and the lower end of the fixed wing 70, respectively. The plurality of fixed wings 70 are fixedly coupled between the two support rings 81 and 82 at predetermined intervals along the circumferential direction of the rotor.

An air supply passage 60 for supplying cooling air to the cooling passage 71 of the fixed blade 70 is formed in the support ring 81 at the lower end of the fixed blade 70.

The air supply passage 60 is composed of an air inflow passage 61 and an air discharge passage 62 communicating with each other at a predetermined angle β 'in the same manner as in the first embodiment.

The dust-collecting groove 63 is formed at the tip end of the air inflow path 61 so as to communicate with the air inflow path 61 in a straight line.

Since the dust collecting groove 63 of the present embodiment is formed in the fixed support ring 81, the foreign matter introduced together with the cooling air is not affected by the rotational force or the centrifugal force, unlike the case where the dust collecting groove is formed on the rotating rotor wheel. And is affected only by the angle? 'With the air discharge passage 62.

Therefore, it is possible to form various forms as long as it satisfies 0 degree <? <90 degree, particularly 0 degree <? <45 degree, which is the angle? 'Between the air inflow passage 61 and the air discharge passage 62 .

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, It is obvious that the modification or the modification is possible by the person.

It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

10: rotor blade 11: root
12: cooling flow passage 20: rotor wheel
21:
30, 40, 50, 60:
31, 41, 51, 61:
32, 42, 52, 62:
33, 43, 53, 53 ', 63:
70: fixed blade 71: cooling flow path
80,81,82: Support ring

Claims (14)

An airfoil member which is provided to be exposed to a high temperature fluid for driving the turbine and in which a cooling passage through which air for cooling flows is formed; And
And an air supply flow path for supplying air for cooling by the cooling flow path of the airfoil member and having a dust collecting groove for collecting foreign matter introduced together with the cooling air on one side of the air supply flow path, Member;
Wherein the airfoil member is a rotor blade that is driven by a turbine driving fluid to rotate the rotor, the support member is rotatably provided integrally with the rotor, and the rotor blade is coupled to an outer circumferential surface thereof,
Wherein the air supply passage includes an air inflow passage and an air discharge passage which form a predetermined angle with respect to each other, a dust groove is formed at a tip of the air inflow passage, the rotor wheel has a rotor blade engaging groove on an outer circumferential surface thereof, Wherein the air inlet flow path is formed by perforating the side surface of the rotor wheel, and the air discharge flow path is formed in the rotor blade engagement groove to the air inlet flow path.
delete The method according to claim 1,
The airfoil member is a fixed wick for guiding a turbine driving fluid to the flywheel,
Wherein the support member is a support ring fixed to one side of the turbine. delete delete The method according to claim 1,
Wherein the air inflow passage and the dust collecting groove are formed on the same straight line. The dust collecting apparatus according to claim 1,
And is connected to the front end of the air discharge passage. The method according to claim 1,
And the air discharge passage and the dust collecting groove are formed on the same straight line. The method according to claim 1,
Wherein the dust collecting groove is formed by drilling. The method according to claim 1,
Wherein the dust collecting groove is formed by electric discharge machining.
delete An airfoil member which is provided to be exposed to a high temperature fluid for driving the turbine and in which a cooling passage through which air for cooling flows is formed; And
And an air supply flow path for supplying air for cooling by the cooling flow path of the airfoil member and having a dust collecting groove for collecting foreign matter introduced together with the cooling air on one side of the air supply flow path, Member;
Wherein the air supply flow path includes an air inflow path and an air discharge path which form a predetermined angle with respect to each other, and a dust collecting groove is formed at the tip of the air inflow path, wherein the dust collecting groove and the air inflow path And is inclined to the opposite side with a predetermined angle. An airfoil member which is provided to be exposed to a high temperature fluid for driving the turbine and in which a cooling passage through which air for cooling flows is formed; And
And an air supply flow path for supplying air for cooling by the cooling flow path of the airfoil member and having a dust collecting groove for collecting foreign matter introduced together with the cooling air on one side of the air supply flow path, Member;
Wherein the air supply passage includes an air inflow passage and an air discharge passage which form a predetermined angle with respect to each other,
Wherein a dust collecting groove is formed at the tip of the air inflow path, and the dust collecting groove and the air inflow path are formed in a radial direction of the rotor. An airfoil member which is provided to be exposed to a high temperature fluid for driving the turbine and in which a cooling passage through which air for cooling flows is formed; And
And an air supply flow path for supplying air for cooling by the cooling flow path of the airfoil member and having a dust collecting groove for collecting foreign matter introduced together with the cooling air on one side of the air supply flow path, Member;
Wherein the air supply flow path includes an air inflow path and an air discharge path which form a predetermined angle with respect to each other, and a dust collecting groove is formed at the tip of the air inflow path, and the dust collecting groove and the air inflow path are formed along the axial direction of the rotor The turbine cooling apparatus comprising:

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