KR102025148B1 - Gas turbine including pre-swirl system - Google Patents

Abstract

The present invention relates to a gas turbine including a free swirl system for preventing flow disturbance in a gas turbine in which an air inlet duct for introducing air to a pre-swirl system includes a plurality of partial ducts. And a compressor disposed in the casing, the compressor for sucking air and compressing the air at high pressure, a combustor for mixing the compressed air by the compressor with fuel, and a high-temperature, high-pressure combustion gas discharged from the combustor. A turbine for generating power by rotating a plurality of turbine blades, a free swirl system for swirling cooling air flowing into a lower end of the turbine blade, and a supply of cooling air discharged from the compressor to the free swirl system. An air inlet duct, the air inlet ducts having a plurality of The gas turbine is formed of a partial duct, characterized in that the position or area of the air flow in which the cooling air flows in the free swirl system corresponding to the position or area where the cooling air flows through the air inlet duct is provided. do.

Description

Gas turbine with free swirl system {GAS TURBINE INCLUDING PRE-SWIRL SYSTEM}

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine comprising a free swirl system, and more particularly to a flow turbine in a gas turbine in which an air inlet duct for introducing air into a pre-swirl system is composed of a plurality of partial ducts. The invention relates to a gas turbine comprising a free swirl system.

In general, a turbine is a machine that converts the energy of a fluid such as water, gas, steam, etc. into mechanical work, usually by planting several feathers or vanes on the circumference of a rotating body and exhaling steam or gas thereon to produce high-speed impulse or reaction force. A turbo-type machine that rotates is called a turbine.

Such turbine types include a hydro turbine using energy of high water, a steam turbine using energy of steam, an air turbine using energy of high pressure compressed air, and a gas using energy of high temperature and high pressure gas. Turbine and the like.

In general, a gas turbine is a type of internal combustion engine that converts thermal energy into mechanical energy by injecting and rotating a high temperature and high pressure combustion gas generated by mixing fuel with air compressed at high pressure in a compressor and rotating it.

Since the gas turbine does not have a reciprocating mechanism such as a piston of a four-stroke engine, there is no mutual friction portion such as a piston-cylinder, so the consumption of lubricating oil is extremely low, and the amplitude characteristic of the reciprocating machine is greatly reduced. There is an advantage.

In order to form such a turbine, the structure which makes the said high-temperature, high-pressure combustion gas pass through a turbine blade by constructing several turbine rotor disk in which several turbine blades are arrange | positioned on the outer peripheral surface in multiple stages is used widely.

However, with the recent trend toward larger and more efficient gas turbines, cooling devices for the turbine blades are commonly employed to withstand high temperature combustion gases as the combustor outlet temperature gradually increases.

To this end, a pre-swirl system is provided on a cooling passage in which cooling air is supplied to the turbine blades, and the free swirl system induces a vortex to improve flow characteristics of air supplied to the turbine blades. Therefore, efficient air can be delivered and pressure loss can be reduced to increase the efficiency of the flow.

In this case, the inlet duct for introducing air into the free swirl system may be made of one full duct, but may be made of a plurality of partial ducts.

However, in the related art, the free swirl system is formed to have a uniform flow area at equal intervals regardless of the location and area where air is introduced into the free swirl system by the plurality of partial ducts, thereby causing a flow disturbance.

In particular, the conventional free swirl system has a problem that the efficiency of the gas turbine is lowered because the flow is blocked at the position facing the flange to which the plurality of partial ducts are connected.

The present invention is to solve the above problems, the pre-swirl system to prevent the flow disturbance in the gas turbine consisting of a plurality of ducts of the air inlet duct for introducing air to the pre-swirl system An object is to provide a gas turbine comprising a.

The present invention for solving the above problems is, a casing, a compressor disposed in the casing, a compressor for sucking air and compressing it to a high pressure, a combustor for mixing and combusting the air compressed by the compressor with fuel, A turbine for generating electric power by rotating a plurality of turbine blades by using high-temperature and high-pressure combustion gas discharged from the combustor, a free swirl system for swirling cooling air flowing into a lower end of the turbine blade, and discharge from the compressor And an air inlet duct for supplying cooling air to the free swirl system, wherein the air inlet duct is formed of a plurality of partial ducts, and corresponds to a position or an area in which cooling air is introduced through the air inlet duct. The position of the air flow section where the cooling air flows in the free swirl system or It provides a gas turbine characterized in that the area is formed.

The apparatus may further include a cooling air chamber in which cooling air discharged from the compressor is stored, and the air inlet duct may connect the cooling air chamber and the free swirl system.

The apparatus may further include a cooler installed on a line for extracting cooling air from the compressor to the cooling air chamber.

In each of the plurality of partial ducts, at least one air inlet for introducing air from the cooling air chamber may be formed.

Flanges are formed on both sides of each of the plurality of partial ducts, and adjacent partial ducts may be coupled to each other by coupling the flanges.

The free swirl system includes a plurality of swirl units for swirling the cooling air, wherein each swirl unit includes an air foil part, a first coupling part formed on one side of the air foil part, and the air foil part. It may include a second coupling portion formed on the other side of the.

The first coupling portion and the second coupling portion of each swirl unit may be formed differently according to the position or area where the cooling air is introduced through the air inlet duct.

The free swirl system may further include a plurality of connecting parts arranged between the adjacent plurality of swirl units to connect the plurality of swirl units in a circular shape, wherein each of the plurality of connecting parts is in a circumferential direction of the plurality of swirl units. It can be stretched along.

Each of the plurality of connection parts may include a first connection part connecting each first coupling part of the adjacent swirl unit and a second connection part connecting each second coupling part of the adjacent swirl unit.

The first connection part and the second connection part may include expansion and contraction parts for adjusting the distance between each of the first coupling part and the second coupling part of the adjacent swirl unit, and the expansion part of the first connection part and the second connection part. It may further include a driving unit for driving at least one of the.

The expansion unit may include a first slide unit coupled to one swirl unit of the adjacent swirl unit and another swirl unit coupled to another one of the adjacent swirl units and slidable with respect to the first slide unit. It may include wealth.

A guide part for guiding the slide may be provided between the first slide part and the second slide part.

Alternatively, the stretchable portion may be made of bellows or a flexible material.

The apparatus may further include a fixing part for fixing each of the expansion and contraction units to the adjacent swirl unit.

According to the present invention, even if the air inlet duct for introducing air into the free swirl system is composed of a plurality of partial ducts, even if the position or area where the air is introduced into the free swirl system is not uniform, in the free swirl system The position or area of air flow can be adjusted to prevent flow disturbance and ultimately improve the efficiency of the gas turbine.

The effects of the present invention are not limited to the above-described effects, but should be understood to include all the effects deduced from the configuration of the invention described in the detailed description or claims of the present invention.

1 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.
FIG. 2 is an enlarged cross-sectional view of a portion of the gas turbine of FIG. 1. FIG.
3 is a cross-sectional view based on line A of FIG. 2.
4 is a side view showing a free swirl system according to the first embodiment;
FIG. 5 is a perspective view illustrating the swirl unit of the free swirl system of FIG. 4 separately; FIG.
6 is a side view showing a free swirl system according to the second embodiment.
FIG. 7 is an enlarged perspective view of a connection part of the free swirl system of FIG. 6. FIG.
8 is a perspective view illustrating a state after driving of the connection of FIG. 7;
9 is an enlarged perspective view illustrating a connection part of the free swirl system according to the third embodiment;
10 is a perspective view illustrating a state after driving of the connecting unit of FIG. 9;

Hereinafter, a preferred embodiment of a gas turbine including a free swirl system of the present invention will be described with reference to FIGS. 1 to 10.

In addition, terms to be described below are terms defined in consideration of functions in the present invention, which may vary according to intentions or customs of users or operators, and the following embodiments do not limit the scope of the present invention. It is merely illustrative of the components set forth in the claims.

In order to clearly describe the present invention, parts irrelevant to the description are omitted, and like reference numerals designate like elements throughout the specification. Throughout the specification, when a part is said to "include" a certain component, it means that it may further include other components, without excluding the other components unless otherwise stated.

1 is a cross-sectional view illustrating a schematic structure of a gas turbine according to an embodiment of the present invention, FIG. 2 is an enlarged cross-sectional view of a portion of the gas turbine of FIG. 1, and FIG. 3 is based on the line A of FIG. 2. 4 is a side view illustrating the free swirl system according to the first embodiment, FIG. 5 is a perspective view of a swirl unit separately of the free swirl system of FIG. 4, and FIG. 6 is a free view according to the second embodiment. A side view of the swirl system, FIG. 7 is an enlarged perspective view of the connecting portion of the free swirl system of FIG. 6, FIG. 8 is a perspective view showing a state after driving the connecting portion of FIG. 7, and FIG. 9 is a third embodiment according to the third embodiment. It is a perspective view which shows the connection part of a free swirl system on an enlarged scale, and FIG. 10 is a perspective view which shows the state after driving of the connection part of FIG.

Hereinafter, a gas turbine according to an embodiment of the present invention will be described with reference to FIG. 1.

The gas turbine 1 according to an embodiment of the present invention includes a casing 10, a compressor 20 that is disposed in the casing 10, and compresses air at high pressure and compresses the compressor 20. By rotating the plurality of turbine blades by using a plurality of combustors 30 for mixing and combusting the air compressed by the fuel and the high-temperature, high-pressure combustion gas discharged from the combustor 30 to produce power It may be made including a turbine (40).

The casing 10 includes a compressor casing 12 in which the compressor 20 is accommodated, a combustor casing 13 in which the combustor 30 is accommodated, and a turbine casing 14 in which the turbine 40 is accommodated. can do. However, the present invention is not limited thereto, and the compressor casing, the combustor casing, and the turbine casing may be integrally formed.

Here, the compressor casing 12, the combustor casing 13 and the turbine casing 14 may be arranged sequentially from the upstream side to the downstream side in the fluid flow direction.

A rotor (center shaft) 50 is rotatably provided inside the casing 10, and a generator (not shown) is interlocked with the rotor 50 for power generation, and the turbine is downstream of the casing 10. A diffuser for discharging the combustion gas passed through the 40 may be provided.

The rotor 50 is accommodated in the compressor rotor disk 52 accommodated in the compressor casing 12, the turbine rotor disk 54 accommodated in the turbine casing 14 and the combustor casing 13 and the compressor. Tie rods for fastening the torque tube 53 connecting the rotor disk 52 and the turbine rotor disk 54, the compressor rotor disk 52, the torque tube 53, and the turbine rotor disk 54. 55 and fastening nut 56.

The compressor rotor disk 52 may be formed in plural, and the plurality of compressor rotor disks 52 may be arranged along the axial direction of the rotor 50. That is, the compressor rotor disk 52 may be formed in multiple stages.

In addition, each of the compressor rotor disks 52 may be formed in a substantially disk shape, and a compressor blade coupling slot may be formed at an outer circumferential portion thereof to be coupled with the compressor blade 22 to be described later.

The turbine rotor disk 54 may be formed similarly to the compressor rotor disk 52. That is, the turbine rotor disk 54 may be formed in plural, and the plurality of turbine rotor disks 54 may be arranged along the axial direction of the rotor 50. That is, the turbine rotor disk 54 may be formed in multiple stages.

In addition, each of the turbine rotor disk 54 is formed in a substantially disk shape, the outer peripheral portion may be formed with a turbine blade coupling slot coupled to the turbine blade 42 to be described later.

The torque tube 53 is a torque transmission member that transmits the rotational force of the turbine rotor disk 54 to the compressor rotor disk 52, and has one end thereof in the flow direction of air among the plurality of compressor rotor disks 52. It may be engaged with the compressor rotor disk located at the downstream end, and the other end may be engaged with the turbine rotor disk located at the most upstream end in the flow direction of the combustion gas of the plurality of turbine rotor disk 54. Here, a protrusion is formed at each of the one end and the other end of the torque tube 53, and each of the compressor rotor disk 52 and the turbine rotor disk 54 is formed with a groove that is engaged with the protrusion, the torque tube 53 may be prevented from rotating relative to the compressor rotor disk 52 and the turbine rotor disk 54.

In addition, the torque tube 53 may be formed in a hollow cylinder shape so that air supplied from the compressor 20 may flow through the torque tube 53 to the turbine 40.

In this case, the torque tube 53 is strongly formed due to the deformation and distortion of the gas turbine that is continuously operated for a long time, and can be easily assembled and dismantled for easy maintenance.

The tie rod 55 is formed to penetrate through the plurality of compressor rotor disks 52, the torque tube 53, and the plurality of turbine rotor disks 54, and one end thereof is provided with the plurality of compressor rotor disks 52. The other end is fastened in the compressor rotor disk located at the most upstream end in the flow direction of the air, the other end of the plurality of turbine rotor disks 54 of the turbine rotor disk is located on the most downstream end in the flow direction of the combustion gas It can protrude to the opposite side of the compressor 20 and can be fastened with the fixing nut 56.

Here, the fixing nut 56 presses the turbine rotor disk 54 located at the downstream end to the compressor 20 side, and the compressor rotor disk 52 and the downstream end located at the most upstream end. As the spacing between the turbine rotor disks 54 being located decreases, a plurality of the compressor rotor disks 52, the torque tube 53 and the plurality of turbine rotor disks 54 are in the axial direction of the rotor 50. Can be compressed. Accordingly, axial movement and relative rotation of the plurality of compressor rotor disks 52, the torque tube 53, and the plurality of turbine rotor disks 54 may be prevented.

Meanwhile, in the present embodiment, one tie rod is formed to penetrate through the centers of the plurality of compressor rotor disks, the torque tube, and the plurality of turbine rotor disks, but is not limited thereto. That is, separate tie rods may be provided on the compressor side and the turbine side, respectively, and a plurality of tie rods may be disposed radially along the circumferential direction, and these may be mixed.

Both ends of the rotor 50 according to this configuration are rotatably supported by a bearing, and one end may be connected to the drive shaft of the generator.

The compressor 20 is a compressor vane 24 fixed to the casing 10 so as to align the flow of air flowing into the compressor blade 22 and the compressor blade 22 with the rotor 50. ) May be included.

The compressor blades 22 are formed in plural, the plurality of compressor blades 22 are formed in plural stages along the axial direction of the rotor 50, and the plurality of compressor blades 22 are formed in each stage. It may be formed radially along the rotation direction of the rotor 50.

That is, the root portion 22a of the compressor blade 22 is coupled to the compressor blade coupling slot of the compressor rotor disk 52, and the root portion 22a is such that the compressor blade 22 has its compressor blade coupling slot. It may be formed in the shape of a fir (fir-tree) to prevent the deviation from the radial direction of rotation of the rotor 50 from.

In this case, the compressor blade coupling slot may be formed in a fir shape so as to correspond to the root portion 22a of the compressor blade.

In the present embodiment, the compressor blade root portion 22a and the compressor blade coupling slot are formed in a fir shape, but are not limited thereto and may be formed in a dove tail shape or the like. Alternatively, the compressor blade may be fastened to the compressor rotor disk by using a fastener such as a key or bolt other than the above type.

Here, the compressor rotor disk 52 and the compressor blade 22 are typically combined in a tangential type or an axial type. In the present embodiment, the compressor blade root portion 22a As described above, is formed in a so-called axial type that is inserted into the compressor blade engaging slot along the axial direction of the rotor 50. Accordingly, the compressor blade coupling slot according to the present embodiment may be formed in plural, and the plurality of compressor blade coupling slots may be arranged radially along the circumferential direction of the compressor rotor disk 52.

The compressor vanes 24 may be formed in plural, and the plurality of compressor vanes 24 may be formed in plural stages along the axial direction of the rotor 50. Here, the compressor vanes 24 and the compressor blades 22 may be alternately arranged along the air flow direction.

In addition, the plurality of compressor vanes 24 may be radially formed along the rotation direction of the rotor 50 at each stage.

The combustor 30 mixes and combusts the air flowing from the compressor 20 with fuel to produce a high-temperature, high-pressure combustion gas of high energy, and burns to the heat-resistant limit that the combustor and the turbine can withstand by the isostatic combustion process. It can be formed to increase the gas temperature.

Specifically, the combustor 30 may be formed in plural, and the plurality of combustors 30 may be arranged along the rotational direction of the rotor 50 in the combustor casing.

In addition, each of the combustors 30, the liner to which the air compressed by the compressor 20 is introduced, a burner for injecting and burning fuel into the air flowing into the liner, and the combustion gas generated by the burner to the turbine It may include guiding transition pieces.

The liner may include a flame barrel forming a combustion chamber and a flow sleeve forming an annular space surrounding the flame barrel.

The burner may include a fuel injection nozzle formed at a front side of the liner to inject fuel into the air flowing into the combustion chamber, and a spark plug formed at a wall of the liner to ignite the air and fuel mixed in the combustion chamber. Can be.

The transition piece may be formed such that the outer wall portion of the transition piece is cooled by the air supplied from the compressor so as not to be damaged by the high temperature of the combustion gas.

That is, the transition piece is formed with a cooling hole for injecting air therein, the air can cool the main body therein through the cooling hole.

Meanwhile, air that cools the transition piece flows into the annular space of the liner, and air is supplied to cooling air through a cooling hole provided in the flow sleeve on the outer wall of the liner to collide with the outer wall of the liner. have.

Here, although not separately shown, a de-swirler that serves as a guide vane between the compressor 20 and the combustor 30 to adjust a flow angle of air flowing into the combustor 30 to a design flow angle. ) May be formed.

Next, the turbine 40 may be formed similarly to the compressor 20. That is, the turbine 40 is a turbine vane that is fixed to the casing 10 so as to align the flow of the air flowing into the turbine blade 42 and the turbine blade 42 rotates with the rotor 50. And (44).

The turbine blades 42 are formed in plural, the plurality of turbine blades 42 are formed in plural stages along the axial direction of the rotor 50, and the plurality of turbine blades 42 are formed in each stage. It may be formed radially along the rotation direction of the rotor 50.

In other words, the root portion 42a of the turbine blade 42 is coupled to the turbine blade coupling slot of the turbine rotor disk 54, and the root portion 42a is the turbine blade coupling slot thereof. It may be formed in the shape of a fir (fir-tree) to prevent the deviation from the radial direction of rotation of the rotor 50 from.

In this case, the turbine blade coupling slot may be formed in a fir shape so as to correspond to the root portion 42a of the turbine blade.

In the present embodiment, the turbine blade root portion 42a and the turbine blade coupling slot are formed in a fir shape, but are not limited thereto and may be formed in a dove tail shape or the like. Alternatively, the turbine blade can be fastened to the turbine rotor disk by using a fastener such as a key or a bolt other than the above-described form.

Here, the turbine rotor disk 54 and the turbine blade 42 are typically combined in a tangential type or an axial type. In the present embodiment, the turbine blade root portion 42a. As described above, is formed in a so-called axial type that is inserted into the turbine blade coupling slot along the axial direction of the rotor 50. Accordingly, the turbine blade coupling slot according to the present embodiment may be formed in plural, and the plurality of turbine blade coupling slots may be arranged radially along the circumferential direction of the turbine rotor disk 54.

The turbine vanes 44 may be formed in plural, and the plurality of turbine vanes 44 may be formed in plural stages along the axial direction of the rotor 50. Here, the turbine vanes 44 and the turbine blades 42 may be alternately arranged along the air flow direction.

In addition, the plurality of turbine vanes 44 may be radially formed along the rotation direction of the rotor 50 at each stage.

Here, since the turbine 40 contacts the combustion gas of high temperature and high pressure unlike the compressor 20, the turbine 40 needs cooling means to prevent damage such as deterioration.

Accordingly, the gas turbine according to the present embodiment may further include a cooling flow path for extracting air compressed at a part of the compressor 20 and supplying the compressed air to the turbine 40.

The cooling passage may extend from the outside of the casing 10 (outside passage), or may extend through the inside of the rotor 50 (inside passage), and may include both the outer passage and the inner passage. Can also be used.

At this time, the cooling passage is in communication with the turbine blade cooling passage formed in the turbine blade 42, the turbine blade 42 may be cooled by the cooling air.

In addition, the turbine blade cooling passage is in communication with the turbine blade film cooling hole formed in the surface of the turbine blade 42, the cooling air is supplied to the surface of the turbine blade 42, the turbine blade 42 is The so-called membrane can be cooled by cooling air.

In addition, the turbine vane 44 may also be formed to be cooled by receiving cooling air from the cooling passage, similar to the turbine blade 42.

In addition, the cooling passage is formed to communicate with the inside of the turbine blade 42 through the lower end of the turbine blade 42 so that the cooling air flowing through the cooling passage flows through the lower end of the turbine blade 42. do.

At this time, as shown in Figure 2, in order to increase the flow efficiency of the cooling air flowing into the turbine blade 42, free swirl on the inlet or the flow path of the cooling flow path to which the cooling air is supplied to the turbine blade 42 (pre-swirl) system 1000 is provided. The free swirl system 1000 supplies cooling air to the turbine blade 42 to supply a flow rate required for cooling and operation of the turbine blade 42 that maintains a high temperature state to ensure stable operation of the turbine. do.

In the present invention, the air inlet duct 400 forming the cooling passage consists of a plurality of partial ducts (420). That is, as shown in FIG. 3, the air inlet duct 400 is connected to each other such that the plurality of partial ducts 420 form a circle.

Specifically, the air inlet duct 400 connects the cooling air to the lower end of the turbine blade 42 in the cooling air chamber 60 in which the compressed air discharged from the compressor 20 is stored. . The free swirl system 1000 is disposed at the rear end of the air inlet duct 400, and the cooling air supplied through the air inlet duct 400 passes through the free swirl system 1000 and the turbine blade 42. Flows into the bottom of the

The cooling air chamber 60 may be formed at various positions such as the inside of the compressor casing 12 or the inside of the combustor casing 13.

In addition, a cooler 70 may be further installed on a line for adding compressed air from the compressor 20 to the cooling air chamber 60, and discharged from the compressor 20 by the cooler 70. Compressed air may be supplied to the cooling air chamber 60 in a more cooled state.

At least one air inlet passage 440 may be formed in each of the plurality of partial ducts 420 to introduce air from the cooling air chamber 60.

In this case, the area of the air inlet passage 440 and the space between the air inlet passage 440 are different for each of the plurality of partial ducts 420, or a connection portion for connecting the adjacent partial ducts 420 is formed. As formed, the location or area where the cooling air is introduced through the air inlet duct 400 may not be uniformly formed.

In the present embodiment, as shown in Figure 3, the space between the air inlet passage 440 and the area of the air inlet passage 440 adjacent to the air in each of the partial duct 420 is formed uniformly The spacing between the air inlet passages 440 facing each other in the adjacent partial ducts 420 by the connecting portion for connecting the adjacent partial ducts 420 is not uniformly formed.

That is, between the first air inlet passage 441 formed in one partial duct 420 and the second air inlet passage 442 adjacent thereto is spaced apart by A, while formed in different partial ducts 420. The space between the second air inlet passage 442 and the third air inlet passage 443, which is disposed between the gap is spaced by B.

The plurality of partial ducts 420 may be coupled by various methods such as welding and bolting. In the present embodiment, flanges 420a are formed at both sides of each partial duct 420, and the flanges 420a The bolts are coupled to each other so that the adjacent partial ducts 420 are engaged.

Accordingly, since the cooling air is not supplied from the connection portion between the plurality of partial ducts 420 and the coupling portion of the flange 420a in this embodiment, the free swirl system at a position corresponding thereto, as will be described later. Likewise, when the air flow portion is located in the free swirl system, the flow is blocked, thereby lowering the efficiency of the gas turbine.

To this end, in the present invention, a portion through which the air flows in the free swirl system 1000 may be formed to correspond to a position or an area where cooling air is introduced through the plurality of air inlet passages 440, and the free The swirl system 1000 will be described in detail below.

In the gas turbine 1 according to this configuration, the air flowing into the casing 10 is compressed by the compressor 20, and the air compressed by the compressor is mixed with fuel by the combustor 30. After combustion, the combustion gas is generated, the combustion gas generated in the combustor flows into the turbine 40, and the combustion gas introduced into the turbine 40 passes through the rotor blades 42 through the turbine blades 42. After the rotation, the rotor 50 discharged to the atmosphere through the diffuser and rotated by the combustion gas may drive the compressor 20 and the generator. That is, some of the mechanical energy obtained from the turbine can be supplied to the energy required to compress air in the compressor, and the rest can be used to produce power with the generator.

Here, the gas turbine is only one embodiment of the present invention, the free swirl system of the present invention to be described in detail below can be applied to all the general gas turbine.

Hereinafter, the free swirl system 1000 according to the first embodiment of the present invention will be described with reference to FIGS. 4 and 5.

The free swirl system 1000 according to the first embodiment of the present invention includes a plurality of swirl units 100 for swirling cooling air supplied through the air inlet duct 400, and the plurality of swirl units ( 100, each of the air foil part 120, the first coupling part 140 formed on one side of the air foil part 120, and the second coupling part formed on the other side of the air foil part 120 ( 160).

As shown in FIG. 4, the plurality of swirl units 100 are coupled to each other to form a circle, and in this embodiment, adjacent swirl units 100 may be fixedly coupled by welding or the like.

In addition, as shown in FIG. 5, the airfoil unit 120 may be formed to have a general airfoil shape including a leading edge and a trailing edge, and have a predetermined height. It is formed to have.

The first coupling part 140 and the second coupling part 160 are respectively formed above and below the air foil part 120, and the first coupling part 140 and the first coupling part 140 of the swirl unit 100 adjacent to each other. Each of the two coupling parts 160 is fixedly coupled to form a portion in which air flows therebetween.

Hereinafter, one swirl unit 100a of the plurality of swirl unit units 100 and another swirl unit unit 100b adjacent thereto will be described.

The swirl unit 100a includes an airfoil unit 120a, a first coupling unit 140a, and a second coupling unit 160a, and the other swirl unit 100b includes an airfoil unit 120b. ), A first coupling part 140b and a second coupling part 160b, and the adjacent first coupling parts 140a and 140b and the second coupling parts 160a and 160b are fixedly coupled to each other. An air flow part 180 through which cooling air flows is formed between adjacent air foil parts 120a and 120b.

In this case, as described above, the spaces between the plurality of air inlet passages 440 are not uniformly formed so as to correspond to the position or area where the cooling air is introduced through the plurality of air inlet passages 440. There is a need to form the air flow unit 180.

To this end, the circumferential length L of the first coupling part 140 and the second coupling part 160 may be adjusted. That is, as the circumferential lengths of the first coupling part 140 and the second coupling part 160 are adjusted, the distance between the adjacent air foil parts 120a and 120b may be adjusted. The position or area of the flow unit 180 may be adjusted.

Specifically, as shown in FIG. 3, the gap between the second air inlet passage 442 and the third air inlet passage 443 by a flange 420a for connecting the adjacent partial duct 420. Since it is formed wider, the air flow of the swirl unit 100 is disposed corresponding to the second air inlet passage 442 and the third air inlet passage 443 as shown in FIG. Eastern part 180 may also be formed wide.

That is, as shown in FIG. 5, one swirl unit different from the circumferential length L1 of the first coupling unit 140a and the second coupling unit 160a of the swirl unit 100a described above ( The circumferential length L2 of the first coupling part 140b and the second coupling part 160b of 100b may be longer, and thus air formed between the adjacent swirl units 100a and 100b. The area of the flow unit 180 may be formed to be wide.

Accordingly, it is possible to prevent the clogged flow from occurring so that no flow disturbance occurs and the efficiency of the gas turbine can be prevented from being lowered.

Next, the free swirl system according to the second embodiment of the present invention will be described with reference to FIGS. 6 to 8.

The free swirl system 1000 according to the second embodiment of the present invention is largely disposed between a plurality of swirl units 100 for swirling air and the adjacent swirl units 100, and the plurality of swirls. It may include a plurality of connecting portion 200 for connecting the unit 100 in a circular shape.

That is, as shown in FIG. 6, the plurality of swirl unit bodies 100 and the plurality of connection units 200 are alternately arranged and connected in a circle.

Since the plurality of swirl units 100 are the same as in the first embodiment, description thereof will be omitted.

In this case, each of the connection parts 200 may be stretched along the circumferential direction of the plurality of swirl unit bodies 100. That is, each of the connection parts 200 may adjust the distance between the swirl units 100 connected thereto.

Each of the connection parts 200 may include a first connection part 240 connecting the first coupling parts 140 of the adjacent swirl units and a second connection part 160 of the adjacent swirl units. 2 includes a connector 260.

Hereinafter, the description will be made based on the connection unit 200 connecting one swirl unit 100a of the plurality of swirl unit units 100 and the other swirl unit unit 100b adjacent thereto. That is, the one swirl unit 100a includes an airfoil unit 120a, a first coupling unit 140a, and a second coupling unit 160a, and the other swirl unit 100b includes an airfoil unit. And a first coupling part 140b and a second coupling part 160b, wherein the first connection part 240 connects the adjacent first coupling parts 140a and 140b to each other. The second connection part 260 connects the adjacent second coupling parts 160a and 160b.

In this case, the first connecting portion 240 and the second connecting portion 260, for adjusting the distance between each of the first coupling portion (140a, 140b) and the second coupling portion (160a, 160b) connected to each other In this embodiment, the expansion unit, the first slide unit 241, 261 and the second slide unit 242, 262 and the first slide unit which are coupled to the adjacent swirl unit respectively and slideable with each other. It may include a guide portion (243, 263) for guiding the slide between the (241, 261) and the second slide portion (242, 262).

In detail, the first slide parts 241 and 261 are coupled to any one swirl unit 100a of the adjacent swirl units, that is, the first coupling unit 140a and the second coupling unit 160a, respectively. The second slide parts 242 and 262 are coupled to another swirl unit 100b of the adjacent swirl units, that is, the first coupling unit 140b and the second coupling unit 160b, respectively. .

The apparatus may further include a driving unit 300 for driving the expansion and contraction unit. In this embodiment, the driving unit 300 includes a driving unit 300 for driving the expansion and contraction unit of the first connection unit 240. However, the present invention is not limited thereto, and may further include a driving unit for driving the expansion and contraction unit of the second connection unit 260. The drive unit 300 may be variously formed as long as it is for driving, including an actuator using electricity, hydraulic pressure, compressed air, and the like.

7 and 8, in the present exemplary embodiment, the first slide parts 241 and 261 are formed in a c-shape to form the space parts 241a and 261a of which one side is open. The slide parts 242 and 262 may be formed to have protrusions 242a and 262a disposed in the space parts 241a and 261a through one open side of the first slide parts 241 and 261.

Accordingly, as the protrusions 242a and 262a slide outward from the spaces 241a and 261a, the distance between the adjacent swirl units 100, that is, the area of the air flow unit 180 is adjusted. Can be.

In this case, the widths of the first slide parts 241 and 261 and the second slide parts 242 and 262 are preferably the same.

The driving unit 300 may be disposed in the space portion 241a where the protrusion 242a is disposed and remains. Accordingly, space can be secured and driving is easy.

In addition, the guide parts 243 and 263 are provided between the first slide parts 241 and 261 and the second slide parts 242 and 262 to provide the first slide parts 241 and 261 and the second slide. The friction between the slide surfaces of the parts 242 and 262 is reduced and the slide is smoothly performed.

The guide parts 243 and 263 may be formed of various kinds of bearings or LM guides.

As such, the first slide unit 241 and 261 and the second slide unit 242 and 262 are slid by the driving unit 300 and the distance between the adjacent swirl unit 100 is reduced or increased. An area of the air flow unit 180 between adjacent swirl units 100 may be adjusted. Accordingly, the position or area of the air flow unit 180 may be adjusted to correspond to the position or area where air is introduced through the air inlet duct 400 as described above.

However, the structure of the expansion and contraction portion is not limited thereto, and the expansion and contraction portion may be formed so that the first slide portion and the second slide portion are each formed in a plate shape and overlap and slide to be unfolded. May be

Finally, a free swirl system according to a third embodiment of the present invention will be described with reference to FIGS. 9 and 10.

The free swirl system according to the third exemplary embodiment of the present invention is disposed between the plurality of swirl unit units 100 and the adjacent swirl unit units 100 for swirling air as in the second embodiment. It includes a plurality of connecting unit 1200 for connecting a plurality of swirl unit 100 in a circular shape, the structure of the swirl unit 100 is not different from the embodiment, the connection unit 1200 and for driving the same Only the structure of the driving unit 1300 is different. Hereinafter, only the different parts from the above embodiment will be described.

Each connection part 1200 may include a first connection part 1240 connecting each of the first coupling parts 140 of the adjacent swirl units and a second connection part 160 of the adjacent swirl units. 2 includes a connector 1260.

However, the first connection portion 1240 and the second connection portion 1260 are for adjusting the distance between each of the first coupling portion (140a, 140b) and the second coupling portion (160a, 160b) connected to each other. Including a stretch portion, in the present embodiment, the stretch portion is made of bellows (1244, 1264).

In addition, fixing parts 1245 and 1265 may be provided to fix the stretchable part to the adjacent swirl unit 100, respectively.

Specifically, as shown in FIG. 7, the fixing parts 1245 and 1265 are different from the first fixing parts 1245a and 1265a coupled to the swirl unit 100a side of any one of the adjacent swirl units. Second fixing parts 1245b and 1265b coupled to one swirl unit body 100b are disposed side by side, and the bellows is disposed between the first fixing parts 1245a and 1265a and the second fixing parts 1245b and 1265b. 1244 and 1264 are arrange | positioned.

The apparatus may further include a driving unit 1300 for driving the expansion and contraction unit. In this embodiment, the driving unit 1300 for driving the expansion and contraction unit of the first connection unit 1240 is further included. However, the present invention is not limited thereto, and may further include a driving unit for driving the expansion and contraction unit of the second connection unit 1260. The drive unit 1300 may be variously formed as long as it is for driving, including an actuator using electric, hydraulic, compressed air, and the like.

The driving unit 1300 is disposed in the bellows 1244. Specifically, in the present embodiment, the driving unit 1300 is disposed in the bellows 1244 so that the first fixing unit 1245a and the second fixing unit ( Adjust the bellows 1244 by adjusting the distance between 1245b).

That is, one end of the driving unit 1300 is respectively fixed to the first fixing unit 1245a and the second fixing unit 1245b so that the distance between the fixing units can be adjusted, and the driving unit 1300 controls the distance between the fixing units. When the distance between the fixing part is far away, the bellows 1244 and 1264 are unfolded, and the distance between the adjacent swirl units becomes farther, and when the distance between the fixing parts is reduced, the bellows 1244 and 1264 are folded and the adjacent The distance between swirl units is reduced.

Accordingly, similarly, the position or area of the air flow unit 180 may be adjusted to correspond to the position or area where air is introduced through the air inlet duct 400.

However, the present invention is not limited thereto, and the fixing part may be omitted, and the elastic part may be made of a flexible material as well as a bellows shape.

According to the present invention, even if the air inlet duct for introducing air into the free swirl system is composed of a plurality of partial ducts, even if the position or area where the air is introduced into the free swirl system is not uniform, in the free swirl system The position or area of air flow can be adjusted to prevent flow disturbance and ultimately improve the efficiency of the gas turbine.

The present invention is not limited to the above-described specific embodiments and descriptions, and various modifications can be made by those skilled in the art without departing from the gist of the present invention claimed in the claims. Such variations are within the protection scope of the present invention.

1: gas turbine 10: casing
12: compressor casing 13: combustor casing
14 turbine casing 20 compressor
22: compressor blade 22a: compressor blade root portion
24: compressor vane 30: combustor
40: turbine 42: turbine blade
42a: turbine blade root portion 44: turbine vane
50: rotor 52: compressor rotor disk
53: torque tube 54: turbine rotor disk
55: tie rod 56: fixing nut
60: cooling air chamber 70: cooler
100: a plurality of swirl unit 120: air foil part
140: first coupling portion 160: second coupling portion
180: air flow portion
200, 1200: connection portion 240, 1240: first connection portion
260 and 1260: second connection part 241 and 261: first slide part
241a and 261a: space portion 242 and 262: second slide portion
242a and 262a: protrusions 243 and 263: guide portions
1244, 1264: Bellows 1245, 1265: Fixed part
1245a and 1265a: first fixing part 1245b and 1265b: second fixing part
300, 1300: drive unit
400: air inlet duct 420: plural partial ducts
420a: flange 440: air inlet passage

Claims (14)

Casing;
A compressor disposed in the casing and configured to suck air and compress the air at high pressure;
A combustor for mixing and combusting air compressed by the compressor with fuel;
A turbine which rotates a plurality of turbine blades and generates electric power by using high temperature and high pressure combustion gas discharged from the combustor;
A free swirl system for swirling cooling air flowing into the lower end of the turbine blade; And
And an air inlet duct for supplying cooling air discharged from the compressor to the free swirl system.
The free swirl system includes a plurality of swirl units for swirling the cooling air,
Each swirl unit is
An airfoil portion;
A first coupling part formed at one side of the air foil part; And
And a second coupling part formed at the other side of the air foil part.
An air flow portion through which cooling air flows is formed between the air foil portions of the adjacent swirl units,
The air inlet duct is composed of a plurality of ducts, the gas turbine, characterized in that the position or area of each of the air flow portion is formed corresponding to the position or area where the cooling air flows through the air inlet duct. The method of claim 1,
And a cooling air chamber in which cooling air discharged from the compressor is stored.
The air inlet duct connecting the cooling air chamber and the free swirl system. The method of claim 2,
And a cooler installed on a line for extracting cooling air from the compressor to the cooling air chamber. The method of claim 2,
Each of the plurality of partial ducts, characterized in that at least one air inlet passage for introducing air from the cooling air chamber is formed. The method of claim 1,
A flange is formed at both sides of each of the plurality of partial ducts, and the adjacent partial ducts are coupled to each other as the flanges are coupled to each other. delete The method of claim 1,
Gas turbine, characterized in that the first coupling portion and the second coupling portion of each swirl unit may be formed differently depending on the position or area where the cooling air is introduced through the air inlet duct. The method of claim 1,
The free swirl system may further include a plurality of connecting units disposed between the plurality of adjacent swirl units to connect the plurality of swirl units in a circular manner.
Each of the plurality of connection parts may be stretchable along the circumferential direction of the plurality of swirl units. The method of claim 8,
Each of the plurality of connection portions,
A first connection part connecting each first coupling part of the adjacent swirl unit; And
A second connection part connecting each second coupling part of the adjacent swirl unit;
Gas turbine comprising a. The method of claim 9,
And the first connection part and the second connection part, an expansion and contraction part for adjusting a distance between each of the first coupling part and the second coupling part of the adjacent swirl unit.
A driving unit for driving at least one of the expansion and contraction units of the first connection unit and the second connection unit;
Gas turbine further comprising a. The method of claim 10,
The stretching portion,
A first slide unit coupled to any one swirl unit of the adjacent swirl unit; And
A second slide unit coupled to another swirl unit of the adjacent swirl unit and slidable relative to the first slide unit;
Gas turbine comprising a. The method of claim 11,
Gas turbine, characterized in that the guide portion for guiding the slide is provided between the first slide portion and the second slide portion. The method of claim 10,
The stretching portion,
Gas turbine, characterized in that it is made of bellows or flexible material. The method of claim 13,
A fixing part for fixing the elastic part to the adjacent swirl unit respectively;
Gas turbine further comprising a.

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