WO2015108353A1

WO2015108353A1 - Turbine cooling device

Info

Publication number: WO2015108353A1
Application number: PCT/KR2015/000439
Authority: WO
Inventors: 김기백
Original assignee: 두산중공업 주식회사
Priority date: 2014-01-15
Filing date: 2015-01-15
Publication date: 2015-07-23
Also published as: KR101509383B1

Abstract

The present invention relates to a turbine cooling device comprising: an airfoil-shaped member exposed to high-temperature fluid for driving a turbine and having a cooling passage formed therein so as to allow air for cooling to pass therethrough; and a supporting member to which the airfoil-shaped member is coupled, and which has an air supply passage for supplying the air for cooling to the cooling passage of the airfoil-shaped member and a dust collecting groove formed at one side of the air supply passage so as to collect foreign substances which flow in with the cooling air, such that the foreign substances flowing into the passage, through which the air for cooling passes, are collected and removed so as to prevent the degradation of cooling performance caused by the clogging of an air passage by the foreign substances.

Description

Turbine chiller

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine cooling device, and more particularly, to a turbine cooling device for cooling a rotary blade or fixed blade of a turbine exposed to a high temperature fluid by air cooling.

In general, turbomachines such as gas turbines and steam turbines (hereinafter, engines and devices including turbines, including gas turbines and steam turbines) are referred to as turbomachines, and power for converting the thermal energy of a fluid into rotational force, which is mechanical energy. A generator includes a rotating body axially rotated by a fluid and a fixed body supporting and wrapping the rotating body.

The steam turbine includes a high pressure (HP) turbine, an intermediate 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 the steam turbine, the high pressure steam drives the rotor blades of the high pressure (HP) turbine, the medium pressure (IP) turbine, and the low pressure (LP) turbine to rotate the rotor.

As shown in FIG. 1, the gas turbine is composed of a combustor 110 for generating combustion gas, a turbine 120 driven by the combustion gas discharged from the combustor 110, and a high pressure air to the combustor 110. It includes a compressor 130 for supplying.

The compressor 130 is rotated to intake and compress external air to be sent to the combustor 110. The combustor 110 supplies fuel to the compressed air to combust the gas to generate combustion gas having a high temperature and high pressure, and then to the turbine 120. The high-temperature, 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 blades

121, 123, 125 and

rotary blades

122, 124, 126 are alternately provided in multiple stages along the axial direction of the rotor 140.

However, gas turbines and steam turbines may be deformed or damaged by the action of hot or high pressure combustion gases or steam on the rotor blades. Thus, a method of circulating air in the rotor blades of the turbine and cooling is adopted. Korean Unexamined Patent Publication No. 2011-0021933 discloses one example of the technology in detail.

2 and 3, the rotor 140 is provided with a rotor wheel 101 on the outside, a plurality of rotor blades 102 on the outer circumferential surface of the rotor wheel 101 is a plurality of predetermined intervals along the circumferential direction Is placed.

The rotor blade 102 has a cooling passage 103 formed therein, and the rotor wheel 101 has an air supply passage 104 for supplying air for cooling to the cooling passage 103 of the rotor blade 102. It is.

The conventional air supply passage 104 configured as described above includes foreign substances such as dust in the cooling air flowing in and enters the cooling passage 103 of the rotor blade 102, thereby causing the air supply passage of the rotor wheel 101 ( When stacked inside the cooling passage 103 of the 104 and the rotor blade 102, the air supply passage 104 and the interior of the cooling passage 103 are kept closed to inhibit the flow of air, and cooling There was a problem that performance is reduced.

The present invention was created to improve the problems of the conventional turbine cooling apparatus as described above, by capturing and removing foreign matter flowing into the passage through which the cooling air passes, the air passage is blocked by the foreign matter to reduce the cooling performance. It is an object to provide a turbine cooling apparatus that can be prevented.

Technical solution

In order to achieve the above object, a turbine cooling apparatus according to the present invention includes a airfoil member having a cooling passage through which air for cooling passes and exposed to a high temperature fluid for driving a turbine, and the airfoil member is coupled thereto. And a support member having an air supply passage for supplying air for cooling into the cooling passage of the airfoil member and having a dust collecting groove formed at one side of the air supply passage to collect foreign substances introduced with cooling air. do.

In the turbine cooling apparatus according to an embodiment of the present invention, the airfoil member is a rotor blade driven by the turbine drive fluid to rotate the rotor, the support member may be a disk coupled to the rotor blades on the outer peripheral surface.

In the turbine cooling apparatus according to an embodiment of the present invention, the airfoil member is a fixed blade for guiding a turbine driving fluid to the rotary blade, the support member may be a support ring.

In the turbine cooling apparatus according to an embodiment of the present invention, the air supply passage is composed of an air inflow passage and an air discharge passage, and the dust collecting groove may be formed in communication with the front end of the air inflow passage.

Preferably, the air inflow passage and the air discharge passage are formed to form a predetermined angle to each other.

In the turbine cooling apparatus according to an embodiment of the present invention, the air inflow passage and the dust collecting groove may be formed on the same straight line, in which case the dust collecting groove is the air discharge passage and the predetermined at the end of the air inflow passage It may be formed in communication with each other forming an angle of.

In the turbine cooling apparatus according to an embodiment of the present invention, the air discharge flow path and the dust collecting groove may be formed on the same straight line, in which case the dust collecting groove is the air inflow passage and the predetermined end of the air discharge passage. It may be formed in communication with each other forming an angle of.

In the turbine cooling apparatus according to an embodiment of the present invention, the dust collecting groove may be formed by drilling or electric discharge machining.

In the turbine cooling apparatus according to an embodiment of the present invention, the disk has a rotary blade coupling groove on the outer circumferential surface, the air inlet flow passage is formed by drilling in the side of the disk, the air discharge passage is the rotary blade coupling groove In the air inlet can be formed to be perforated.

In the turbine cooling apparatus according to an embodiment of the present invention, the dust collecting groove and the air inflow passage are preferably formed to be inclined in the opposite direction with a predetermined angle with respect to the rotation direction of the rotor.

More preferably, the dust collecting grooves and the air inflow passage are formed in the radial direction of the rotor.

Preferably, the dust collecting grooves and the air inflow passage are formed to be inclined along the axial direction of the rotor.

As described above, according to the turbine cooling apparatus according to the present invention, by trapping and removing foreign substances introduced into the passage through which air for cooling passes, the air passage is blocked by the substance, thereby preventing the cooling performance from being lowered. This has the effect of improving the durability of the rotor blades.

In addition, by using the rotational force and the centrifugal force of the rotor can effectively collect the foreign matter, it is possible to hold the captured foreign matter so as not to escape.

In addition, the collected foreign matter can be easily and quickly removed by drilling, thereby reducing the maintenance cost.

1 is a schematic side cross-sectional view showing a conventional gas turbine,

2 is a partially enlarged cross-sectional view showing the turbine cooling apparatus shown in FIG. 1;

3 is a side view showing the turbine disk shown in FIG.

Figure 4 is a schematic side cross-sectional view showing a turbine cooling apparatus according to an embodiment of the present invention,

5 is a partially enlarged view of FIG. 4;

Figure 6 is a schematic side cross-sectional view showing a turbine cooling apparatus according to another embodiment of the present invention,

FIG. 7 is a schematic side cross-sectional view cut along the line A-A of FIG. 6;

8 is a partially enlarged view of FIG. 7;

9 and 10 are schematic side cross-sectional views showing a turbine cooling apparatus according to another embodiment of the present invention.

Turbine cooling device according to the invention is a device for cooling the airfoil member provided in the turbine of the turbomachine.

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

The rotor blades rotate the rotor by a driving fluid injected at high pressure inside the turbine, and the fixed blades guide the turbine driving fluid to the rotor blades.

A plurality of the rotor blades and the fixed blades are provided with a predetermined interval from each other along the circumferential direction of the rotor, the plurality of rotor blades and fixed blades are respectively coupled to the support member.

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

The rotor blade is fixedly coupled to the rotor wheel is axially rotated with the rotor, the fixed blade is fixedly coupled to the support ring.

The support ring is provided at the upper and lower ends of the fixed blade, respectively, to securely couple both ends of the fixed blade.

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

As a high temperature fluid for driving a turbine, steam is used in the case of a steam turbine, and combustion gas generated by mixing and combusting fuel and outside air is used in the case of a gas turbine.

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

제1실시예First embodiment

4 to 5, the turbine cooling apparatus according to an embodiment of the present invention is introduced into the rotary blade 10, the cooling passage 12 is formed therein through which the air for cooling passes, and the cooling air It includes a rotor wheel 20 is formed with a dust collecting groove 33 is collected foreign matter.

The rotor blade 10 is provided in the radial direction of the rotor wheel 20 on the outer circumferential surface of the rotor wheel 20. A lower end of the rotor blade 10 includes a root 11 formed in a tapered shape for coupling with the rotor wheel 20, and the cooling passage 12 is formed through the root 11 of the rotor blade 10. do.

The rotor wheel 20 is fixedly coupled to the outer circumferential surface of the rotor and axially rotated integrally with the rotor, the rotor wheel 20 is formed in a disk (disk) shape, the rotor blade coupling groove 21 is formed on the outer circumferential surface There is a mounting on the rotor blade (10).

The rotor blade 10 is coupled to the rotor wheel 20 by the root 11 and is fitted into the rotor blade coupling groove 21 in the axial direction X of the rotor to maintain a stable state.

The rotor wheel 20 has an air supply passage 30 for supplying air for cooling to the cooling passage 12 of the rotor blade 10 therein is formed in the form of a tube having a predetermined diameter, diameter, length and inclination angle The drawings are limited to the diameter, length, and inclination angle shown in the drawings.

The cooling flow path 12 is connected to the rotary blade 10 through heat exchange with high temperature heat caused by steam or combustion gas that comes into contact with the outer circumferential surface of the rotary blade 10 while the cooling air introduced from the air supply passage 30 passes. Cooling takes place. Cooling air may be supplied from external air introduced into the compressor or from a separate cooling air source (not shown) located outside the turbine for cooling.

Cooling passage 12 is formed in the radial direction of the rotor wheel 20, it is also possible to be formed in a shape other than the shape shown in the figure and the discharge port is formed at a position other than the top of the rotor blade 10 It may also be possible.

The air supply passage 30 includes an air inlet passage 31 and an air inlet passage 31 and an air outlet passage 32 communicating with each other to form a predetermined angle between the air inlet passage 31 and the air inlet passage 31. More specifically, the side of the rotor wheel 20 is formed on the side of the rotor wheel 20 to be drilled toward the rotor blade coupling groove 21 toward the inner upper side from the lower left side of the rotor wheel 20 with reference to the drawings. The flow path 32 is formed by being drilled toward the air inflow path 31 via the rotary blade coupling groove 21. Accordingly, an inlet of the air inflow passage 31 is formed at the side surface 22 of the rotor wheel 20, and an outlet of the air discharge passage 32 is formed at an inner wall of the rotor blade coupling 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 because of the rigidity of the material, a method of processing long flow paths such as the air inflow passage 31 and the air discharge passage 32 is extremely limited. Of course, it can also be processed by other processing methods.

As such, when the drilling or discharge processing is performed, the air inflow passage 31 and the air discharge passage 32 are formed in a straight line. Note that it is also possible.

The air inflow passage 31 is further processed by a predetermined depth past the point where the air discharge passage 32 meets, and a dust collecting groove 33 is formed, and the dust collecting groove 33 provides a space in which foreign matter is collected. The length and diameter may be variously changed and are not necessarily limited to the length and diameter shown in the drawings. In addition, the dust collecting groove 33 revealed that it is possible to maintain the state in which the foreign matter is attached through the roughness different from the roughness of the air supply passage 30 described above or a separate roughening process when the inner circumference of the dust collecting groove 33 improves the adhesion performance of the foreign matter. Put it.

In addition, since the air inflow passage 31 and the dust collecting groove 33 are formed on the same straight line, it is possible to more accurately check the workability and abnormality of the worker and to perform the machining work, thereby improving the workability of the worker.

The dust collecting groove 33 is formed to communicate with the tip of the air inflow passage 31 so that foreign matters such as dust flowing into the air inflow passage 31 enter the dust collecting groove 33. The dust collecting groove 33 is formed in a different direction from the air discharge passage 32 so that when foreign matter is introduced through the air inlet passage 31, the cooling passage 12 for moving the cooling air for cooling moves. It is possible to perform stable cooling for the rotor blade 10 by not partially obstructing a specific portion or preventing foreign matter located in a specific section from moving the cooling air.

As shown in FIG. 5, the air inflow passage 31 is formed in the radial direction R of the rotor and is inclined at a predetermined angle α along the axial direction X of the rotor.

Here, the predetermined angle α is, for example, a value larger than 0 degrees and smaller than 90 degrees, and is preferably formed such that 15 degrees <α <75 degrees. When α is smaller than 15 degrees or larger than 75 degrees, the angle β between the air inflow passage 31 and the air discharge passage 32 becomes excessively large and bends sharply at the intersection so that the frictional resistance during movement of air is large. You lose.

Thus, the dust collecting groove 33 is formed with a predetermined angle α with respect to the radial direction R of the rotor together with the air inflow passage 31 is located on the centrifugal force working line of the rotor wheel 20 As a result, centrifugal force acts on the foreign matter introduced into the dust collecting groove 33, and thus, the centrifugal force is not easily escaped from the dust collecting groove 33 and maintained in the dust collecting groove 33.

In addition, the air supplied to the air inflow passage 31 is moved to the cooling passage 12 of the rotor blade 10 through the air discharge passage 32, the rotor blade 10 of the rotor wheel 20 Since the air inflow passage 31 is formed in the radial direction R of the rotor, similar to the cooling passage 12 of the rotor blade 10, the air can flow while minimizing the frictional resistance because the air inflow passage 31 is coupled in the radial direction R. FIG. Will be.

As described above, the air inflow passage 31 and the air discharge passage 32 form a predetermined angle β to each other, and the dust collecting groove 33 is in line with the air inflow passage 31. Is formed. Therefore, the dust collecting groove 33 also forms a predetermined angle β with the air discharge passage 32.

Here, the predetermined angle β is a value larger than 0 degrees and smaller than 90 degrees, and is preferably formed such that 0 degrees <β <45 degrees. If β is greater than 45 degrees, foreign matters introduced into the dust collecting groove 33 do not stay in the collected state, but are affected by the flow of the flow air, so that the air may flow out into the air discharge passage 32 again. Therefore, the inclination angle within 45 degrees is preferably maintained.

If the β is smaller than 45 degrees, particularly at 30 degrees or less, foreign substances introduced into the dust collecting groove 33 may not be easily released and may be continuously deposited, thereby improving dust collection performance of the foreign substances.

The cooling passage 12 according to the present embodiment may be configured in a single form or may include a plurality of branch passages (not shown) branched from the cooling passage 12, in which case the cooling illustrated in the drawing The flow passage 12 may be a main cooling flow passage and the branch flow passage branched from the main cooling flow passage may be formed to extend outwardly from the main cooling flow passage.

제2실시예Second 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. It consists of the flow path 41 and the air discharge flow path 42.

As shown in FIG. 6, the air inflow passage 41 and the air discharge passage 42 are formed on a plane extending along the same AA line, and as shown in FIG. 7, the air inflow passage 41 is It is formed to be inclined in the opposite direction with a predetermined angle γ with respect to the rotational direction Y of the rotor.

Here, the predetermined angle γ may have a value greater than 0 degrees and less than 90 degrees.

The air inflow passage 41 and the air discharge passage 42 of the present embodiment are also formed to form a predetermined angle γ to each other, and the dust collecting groove 43 is formed in line with the air inflow passage 41. Accordingly, the dust collecting groove 43 also forms a predetermined angle γ with the air discharge passage 42. As in the case of the first embodiment, 0 degree <γ <90 degrees, in particular, 0 degree <γ < It is preferable that it is 45 degrees and the dust collection performance of the foreign matter at the inclination angle can be made stable, cooling to the rotor blade 10 in contact with the hot steam or combustion gas is made stable.

In this way, the dust collecting groove 43 is formed to be inclined with a predetermined angle γ to the opposite side of the rotation direction Y of the rotor together with the air inflow passage 41 on the rotational force working line of the rotor wheel 20. Will be located. Therefore, a reaction force in the reverse rotational direction acts on the foreign matter introduced into the dust collecting groove 43, so that it is not easily exited from the dust collecting groove 43 and is maintained in the dust collecting groove 43.

제3실시예Third 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.

Even in this case, since the air discharge passage 52 and the dust collecting groove 53 'are formed by drilling or discharging, the air discharge passage 52 and the dust collecting groove 53' are formed on the same straight line.

The dust collecting groove 53 'formed at the tip of the air discharge passage 52 is a variation of the second embodiment, and the dust collecting groove formed at the tip of the air inflow passage 51 with respect to the radial direction of the rotor wheel 20 ( It is difficult to collect by centrifugal force as in the first embodiment because it is formed in the opposite direction to 53), but it is possible to collect by rotational force as in the second embodiment.

As shown in FIG. 9, when only one dust collecting groove 53 is provided by forming both of the

dust collecting grooves

53 and 53 ′ at the ends of the air inflow passage 51 and the air discharge passage 52. Compared with the increase in number, the collection of a larger amount of foreign matter is increased, which increases the dust collection effect.

제4실시예Fourth embodiment

Referring to FIG. 10, in the turbine cooling apparatus according to another embodiment of the present invention, a fixed blade 70 having a cooling passage 71 through which air for cooling passes is collected, and foreign substances introduced together with cooling air are collected. It includes a support ring 80 is formed a dust collecting groove (63).

The fixed blade 70 of the present embodiment guides the combustion gas to the rotary blade 10 behind the first nozzle vane provided at the discharging tip of the transition piece 111 of the combustor.

The support ring 80 is provided at the upper and lower ends of the fixed blade 70, respectively. The plurality of fixed blades 70 are fixedly coupled to each other at predetermined intervals along the circumferential direction of the rotor between the two support rings 81 and 82.

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 bottom of the fixed blade 70.

As in the first embodiment, the air supply passage 60 includes an air inflow passage 61 and an air discharge passage 62 that communicate with each other to form a predetermined angle (').

The dust collecting groove 63 is formed in direct communication with the air inflow passage 61 at the tip of the air inflow passage 61.

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

Therefore, as long as it satisfies 0 degree <β <90 degrees, in particular 0 degree <β <45 degrees, which is the angle? 'Condition between the air inflow passage 61 and the air discharge passage 62, Can be.

Claims

An airfoil member exposed to a high temperature fluid for driving a turbine and having a cooling passage through which air for cooling passes; And

The airfoil member is coupled, and provided with an air supply passage for supplying air for cooling into the cooling passage of the airfoil member, a support formed with a dust collecting groove for collecting foreign matter introduced with the cooling air on one side of the air supply passage Turbine chiller comprising a member.
The method of claim 1,

The airfoil member is a rotor blade driven by the turbine driving fluid to rotate the rotor, the support member is a turbine cooling device, characterized in that the rotor wheel is provided integrally with the rotor, the rotor blade is coupled to the outer peripheral surface .
The method of claim 1,

The airfoil member is a fixed blade for guiding a turbine drive fluid to the rotary blade,

The support member is a turbine cooling apparatus, characterized in that the support ring fixed to one side of the turbine.
According to claim 2 or 3, wherein the air supply passage,

Turbine cooling apparatus comprising an air inflow passage and an air discharge passage disposed to form a predetermined angle between each other.
The method of claim 4, wherein the dust collecting groove,

Turbine cooling device, characterized in that formed in communication with the tip of the air inflow passage.
The method of claim 5,

And the air inflow passage and the dust collecting groove are formed on the same straight line.
The method of claim 4, wherein the dust collecting groove,

Turbine cooling apparatus, characterized in that formed in communication with the tip of the air discharge passage.
The method of claim 7, wherein

And the air discharge passage and the dust collecting groove are formed on the same straight line.
The method of claim 4, wherein

The dust collecting groove is a turbine cooling apparatus, characterized in that formed by drilling.
The method of claim 4, wherein

The dust collecting groove is a turbine cooling apparatus, characterized in that formed by drilling.
The method of claim 2,

The air supply passage includes an air inflow passage and an air discharge passage disposed at a predetermined angle to each other,

A dust collecting groove is formed at the tip of the air inflow passage,

The rotor wheel has a rotary blade coupling groove on the outer circumferential surface,

The air inflow passage is formed by drilling in the side of the rotor wheel,

And the air discharge passage is perforated from the rotary blade coupling groove toward the air inlet passage.
The method of claim 2,

The air supply passage includes an air inflow passage and an air discharge passage forming a predetermined angle to each other,

A dust collecting groove is formed at the tip of the air inflow passage,

And the dust collecting groove and the air inflow passage are inclined to the opposite side with a predetermined angle with respect to the rotation direction of the rotor.
The method of claim 2,

The air supply passage includes an air inflow passage and an air discharge passage forming a predetermined angle to each other,

A dust collecting groove is formed at the tip of the air inflow passage,

And the dust collecting groove and the air inflow passage are formed in the radial direction of the rotor.
The method of claim 2,

The air supply passage includes an air inflow passage and an air discharge passage forming a predetermined angle to each other,

A dust collecting groove is formed at the tip of the air inflow passage,

And the dust collecting groove and the air inflow passage are inclined along the axial direction of the rotor.