KR102087667B1 - Blade fixing structure using magnetic force and gas turbine having the same - Google Patents

Abstract

The present invention relates to a blade fixing structure using magnetic force and a gas turbine including the same. The blade fixing structure includes: a coupling groove disposed along the outer circumferential surface of a rotor disk; a coupling protrusion arranged on one end of a blade and coupled to the coupling groove; and a magnetic member disposed between the coupling groove and the coupling protrusion and receiving repulsive force between the coupling protrusion and the coupling groove to fix the position of the coupling protrusion inside the coupling groove. According to the present invention, the blade mounted on the outer circumferential surface of the rotor disk using repulsive force receives force in a radial direction to be fixed in position.

Description

Blade fixing structure using magnetic force and gas turbine having the same

The present invention relates to a blade fixing structure using a magnetic force and a gas turbine including the same, and more particularly, the blade mounted on the outer circumferential surface of the rotor disk by placing a neodymium magnet to the force (repulsive force) in the radial direction It relates to a blade fixing structure and a gas turbine to receive the position is fixed.

In general, a turbine is a power generating device that converts thermal energy of a fluid such as gas and steam into rotational force, which is mechanical energy.

Here, the gas turbine comprises a compressor section, a combustor and a turbine section, the outside air is sucked in and compressed by the rotation of the compressor section, and then sent to the combustor, where combustion occurs by mixing compressed air and fuel in the combustor. The hot, high pressure gas generated by the combustor passes through the turbine section and rotates the rotor of the turbine to drive the generator.

The rotor disks are arranged in a plurality of rows on the rotor constituting the gas turbine, and a plurality of blades are arranged along the circumferential direction of the outer circumferential surface of the rotor disk.

Referring to FIG. 1, the outer peripheral surface of the rotor disk 30 is formed with a coupling groove for mounting an arm dovetail-shaped blade, and an end portion of the blade 20 has a dovetail-shaped coupling protrusion fitted to a blade mounting portion. .

At this time, since the blade 20 is disposed in the circumferential direction on the outer circumferential surface of the rotor disk 30 during assembly, the blade 30 located below the rotor disk 30 receives a force in the outer direction of the rotor disk by gravity. In addition, the blade 30 positioned above the rotor disk 30 is urged inwardly of the rotor disk 30 due to gravity, so that the initial position of the blade 30 is not constant.

Therefore, all of the blades 20 are inserted into a root spring as shown in FIG. 1 so that the positions of the blades 20 are all uniformly constrained by radial force on the outer circumferential surface of the rotor disk 30 regardless of gravity. . By the way, in the case of using the conventional loop spring, the additional processing process as much as the H height space to the blade mounting portion of the rotor disk 30 to insert the loop spring.

United States Patent Registration Number:

An object of the present invention is to provide a blade fixing structure and a gas turbine so that the blade mounted on the outer circumferential surface of the rotor disk using the repulsive force of the neodymium magnet is fixed in position by receiving a radial force.

The present invention for achieving the above object relates to a blade fixing structure using a magnetic force and a gas turbine comprising the same, a coupling groove disposed along the outer circumferential surface of the rotor disk; A coupling protrusion disposed at one end of the blade and coupled to the coupling groove; And a magnetic member disposed between the coupling groove and the coupling protrusion to receive a repulsive force between the coupling protrusion and the coupling groove, and to fix the position of the coupling protrusion inside the coupling groove.

In addition, in the embodiment of the present invention, the magnetic force member, the first magnetic force unit disposed on one side facing the coupling groove on the coupling projection; And a second magnetic force unit disposed on the inner side facing the coupling protrusion on the coupling groove.

In addition, in the embodiment of the present invention, the first magnetic force unit may include a first magnet disposed on one side of the coupling protrusion along the rotation axis direction of the rotor disk.

In addition, in the embodiment of the present invention, the first magnetic force unit may include a first magnet that is divided into a plurality of plate shapes at one side of the coupling protrusion along the rotation axis direction of the rotor disc.

In addition, in an embodiment of the present invention, the first magnetic force unit may include: a first magnet divided into a plurality of plate shapes at one side of the coupling protrusion along the rotation axis direction and the circumferential direction of the rotor disc; Can be.

In addition, in the embodiment of the present invention, the first magnetic force unit may further include a first elastic unit disposed between the end of the first magnet and the coupling protrusion.

In addition, in the embodiment of the present invention, a first magnet channel connected to a cooling channel formed in the blade on the first magnet; is formed, the first tapered tapered in one direction on at least one side of the first magnet channel An addition can be formed.

In addition, in an embodiment of the present invention, a first magnet channel connected to a cooling channel formed in the blade is formed on the first magnet; a first curve curved in at least one side of the first magnet channel in one direction. An addition can be formed.

In addition, in the embodiment of the present invention, the second magnetic force unit may include a second magnet disposed in the inner side of the coupling groove along the rotation axis direction of the rotor disk.

In addition, in the embodiment of the present invention, the second magnetic force unit may include a second magnet that is divided into a plurality of plate shapes and disposed on an inner side of the coupling groove along a rotation axis direction of the rotor disk.

In addition, in the embodiment of the present invention, the second magnetic force unit may include a second magnet that is divided into a plurality of plate shapes and disposed in the inner side of the coupling groove along the rotation axis direction and the circumferential direction of the rotor disk. have.

In addition, the embodiment of the present invention may further include a second elastic unit disposed between the second magnet and the inner portion of the coupling groove.

In addition, in the embodiment of the present invention, a second magnet channel connected to the cooling channel formed in the rotor disk on the second magnet; is formed, the second tapered in one direction on at least one side of the second magnet channel A tapered portion can be formed.

In addition, in the embodiment of the present invention, a second magnet channel connected to the cooling channel formed in the rotor disk on the second magnet; is formed, the second magnet is curved in at least one side of the second magnet channel in one direction Curved portions may be formed.

In addition, in an embodiment of the present invention, the first magnetic force unit may include a first magnet disposed on one side of the coupling protrusion along a rotation axis direction of the rotor disc, and the second magnetic force unit may include the rotor. A second magnet disposed in the inner side of the coupling groove along the rotation axis direction of the disk; including, the first concave portion of the trapezoidal groove is formed on one side facing the second magnet on the first magnet; On the second magnet, one side portion facing the first magnet may have a second uneven portion that is a trapezoidal protrusion corresponding to the first uneven portion.

In addition, in an embodiment of the present invention, the first magnetic force unit includes a first magnet disposed in the coupling protrusion along a rotation axis direction of the rotor disc, and the second magnetic force unit includes a rotation axis of the rotor disc. A second magnet is disposed in the coupling groove along a direction, and includes a plurality of blade grooves in which the first magnet is inserted along the outer surface of the coupling protrusion, and includes a circumference of the inner surface of the coupling groove. Accordingly, a plurality of disk grooves into which the second magnet is inserted may be formed at positions corresponding to the plurality of blade grooves.

In addition, in an embodiment of the present invention, the first magnetic force unit includes a first magnet disposed in the coupling protrusion along a rotation axis direction of the rotor disc, and the second magnetic force unit includes a rotation axis of the rotor disc. A second magnet is disposed in the coupling groove in a direction, including a plurality of blade holes into which the first magnet is inserted along an outer circumference of the coupling protrusion, and along the inner circumference of the coupling groove. A disk hole into which the second magnet is inserted may be formed at a position corresponding to the plurality of blade holes.

In addition, in the embodiment of the present invention, the first magnetic force unit includes: a first magnet which is divided into a plurality of plate shapes at one side of the coupling protrusion along the rotation axis direction and the circumferential direction of the rotor disc; The second magnetic force unit may include a second magnet that is divided into a plurality of plate shapes at positions corresponding to the first magnets at an inner portion of the coupling groove along a rotation axis direction and a circumferential direction of the rotor disk. However, based on the rotation axis direction of the rotor disk, both sides of the engaging projection inclined inclined in opposite directions to each other; is formed, both sides of the coupling groove corresponding to the inclined in the direction corresponding to the inclined portion Inclination portion; may be formed.

In addition, in an embodiment of the present invention, the first magnetic force unit includes a first magnet disposed in the coupling protrusion along a rotation axis direction of the rotor disc, and the second magnetic force unit includes a rotation axis of the rotor disc. Along the direction, the second magnet disposed in the coupling groove; including, wherein the first and second magnets may be composed of a neodymium magnet having the same pole for generating a repulsive force.

In an embodiment of the present invention the gas turbine casing; A compressor section disposed inside the casing and compressing the introduced air; A combustor disposed within the casing, the combustor configured to combust compressed air; A turbine section disposed in the casing, connected to the combustor, the turbine section generating power using the combusted air; And a diffuser connected to the turbine section in the casing and discharging air to the outside; And a blade fixing structure using magnetic force disposed in at least one of the compressor section and the turbine section.

According to the present invention, the blade is fixed on the outer circumferential surface of the rotor disk by using the repulsive force of the neodymium magnet, which is fixed in the radial direction, compared to the method of inserting a conventional loop spring, the coupling of the blade and the rotor disk coupling It is easy to further process a variety of forms on the groove, and accordingly can adjust the magnetic force through the additional arrangement of the neodymium magnet, it is characterized in that the initial restraining force of the blade can be variously adjusted according to the size, weight, shape, etc. of the blade.

1 is a blade fixing structure using a conventional loop spring
Figure 2 is a side cross-sectional view showing a typical gas turbine.
Figure 3 is a side cross-sectional view showing a first embodiment of the shape of the magnetic member of the blade fixing structure of the present invention.
Figure 4 is a side cross-sectional view showing a second embodiment of the shape of the magnetic member of the blade fixing structure of the present invention.
Figure 5 is a side cross-sectional view showing a third embodiment of the shape of the magnetic member of the blade fixing structure of the present invention.
Figure 6 is a side cross-sectional view showing a fourth embodiment of the shape of the magnetic member of the blade fixing structure of the present invention.
Figure 7 is a front sectional view showing a first embodiment of the arrangement of the magnetic member of the blade fixing structure of the present invention.
Figure 8 is a front sectional view showing a second embodiment of the arrangement of the magnetic member of the blade fixing structure of the present invention.
Figure 9 is a front sectional view showing a third embodiment of the arrangement of the magnetic member of the blade fixing structure of the present invention.
Figure 10 is a front sectional view showing a fourth embodiment of the magnetic member arrangement of the blade fixing structure of the present invention.
Figure 11 is a side cross-sectional view showing a first embodiment of the linkage structure of the present invention the magnetic member and the cooling passage.
Figure 12 is a side cross-sectional view showing a second embodiment of the linkage structure of the present invention the magnetic member and the cooling passage.
13 is a view showing a fixing structure of the first magnetic force unit of the present invention.
14 is a view showing a fixing structure of the second magnetic force unit of the present invention.

Hereinafter, with reference to the accompanying drawings will be described in detail preferred embodiments of the blade fixing structure using a magnetic force and a gas turbine including the same according to the present invention.

Prior to the description of the present invention, the configuration of the gas turbine 1 will be described with reference to the drawings.

Referring to FIG. 2, the gas turbine basically includes a casing 2 for forming an appearance, a compressor section 4 for compressing air, a combustor 5 for combusting air, and a combustor. A turbine section 6 generating gas using a gas, a diffuser 7 exhausting exhaust gas, and a rotor connecting the compressor section 4 and the turbine section 6 to transmit rotational power; 3) can be configured to include.

Thermodynamically, the compressor section corresponding to the upstream side of the gas turbine receives external air and undergoes adiabatic compression. Compressed air enters the combuster section, mixes with fuel and undergoes isocombustion, and combustion gas enters the turbine section downstream of the gas turbine and undergoes adiabatic expansion. .

In the air flow direction, the compressor section 4 is located in front of the casing 2 and the turbine section 6 is provided at the rear.

Between the compressor section 4 and the turbine section 6 is provided a torque tube 3b for transmitting the rotational torque generated in the turbine section 6 to the compressor section 4.

The compressor section 4 is provided with a plurality (for example 14) of compressor rotor disks 120, and the respective compressor rotor disks 120 are fastened so as not to be spaced in the axial direction by the tie rods 3a. do.

The centers of the respective compressor rotor disks 120 are aligned in the axial direction with each other while the tie rods 3a penetrate. In the vicinity of the outer circumferential portion of the compressor rotor disk 120, a flange (not shown) coupled to a neighboring rotor disk to prevent relative rotation is formed to protrude in the axial direction.

A plurality of blades 110 (or buckets) are radially coupled to the outer circumferential surface of the compressor rotor disk 120. Each blade 110 has a dove tail portion (not shown) is fastened to the compressor rotor disk 120.

The dovetail fastening method includes a tangential type and an axial type. This may be selected according to the required structure of a commercially available gas turbine. In some cases, the compressor blade 110 may be fastened to the compressor rotor disk 120 using a fastening device other than the dovetail.

At this time, the inner circumferential surface of the compressor section 4 of the casing (2) is a vane (not shown) (or nozzle) for the relative rotational movement of the compressor blade 110 is mounted on the diaphragm (not shown) Can be.

The tie rods 3a are disposed to penetrate through the centers of the plurality of compressor rotor disks 120, one end of which is fastened in the compressor rotor disk 120 located at the most upstream side, and the other end of the tie tube 3b is disposed thereon. It is fixed to).

Since the shape of the tie rod 3a may be formed in various structures according to the gas turbine, it is not necessarily limited to the form shown in the drawings.

One tie rod 3a may have a form penetrating the central portion of the compressor rotor disk 120, or a plurality of tie rods 3a may be arranged in a circumferential shape, and a mixture thereof may be used. .

Although not shown, the compressor of the gas turbine may be provided with a vane serving as a guide vane at the next position of the diffuser to increase the pressure of the fluid and then adjust the flow angle of the fluid entering the combustor to the design flow angle. It is called a desworler.

The combustor 5 mixes and combusts the introduced compressed air with fuel to produce a high-temperature, high-pressure combustion gas of high energy, and heat resistance that the components of the combustor 5 and the turbine section 6 can withstand during the isostatic combustion process. The combustion gas temperature is raised to the limit.

The combustor 5 constituting the combustion system of the gas turbine may be arranged in the casing 2 formed in the form of a cell.

On the other hand, in the turbine section 6, the high-temperature, high-pressure combustion gas from the combustor 5 expands, and imparts impulse and reaction force to the rotor blades of the turbine section 6 to convert it into mechanical energy.

The mechanical energy obtained in the turbine section 6 is supplied with the energy required to compress the air in the compressor section 4 and the rest is used to drive the generator to produce power.

The turbine section 6 is formed by alternately arranging a plurality of vanes and rotor blades in a vehicle compartment, and rotationally drives an output shaft to which a generator is connected by driving the rotor blades by combustion gas.

To this end, the turbine section 6 is equipped with a plurality of turbine rotor disks 6a. Each turbine rotor disk 6a basically has a form similar to that of the compressor rotor disk 120.

The turbine rotor disk 6a also has a provided flange (not shown) for coupling with a neighboring turbine rotor disk 6a and includes a plurality of radially arranged turbine blades 6b (or buckets). do. The turbine blade 6b may also be coupled to the turbine rotor disk 6a in a dovetail manner.

At this time, the inner circumferential surface of the turbine section 6 of the casing 2 is mounted with a vane (not shown) (or nozzle) for relative rotational movement of the turbine blade 6b to be mounted on the diaphragm (not shown). Can be.

In the gas turbine having the structure as described above, the introduced air is compressed in the compressor section 4, combusted in the combustor 5, and then moved to the turbine section 6 to drive power generation and drive the diffuser 7. Through the atmosphere.

Here, the torque tube 3b, the compressor rotor disk 120, the compressor blade 110, the turbine rotor disk 6a, the turbine blade 6b, the tie rod 3a, and the like are integrally formed as a rotating component of the rotor ( 3) or a rotating body. The casing 2, vanes (not shown), diaphragms (not shown), etc. may be referred to as stators or fixtures integrally as non-rotating components.

One general structure of a gas turbine is as described above, and the following describes the present invention applied to such a gas turbine.

The rotor disk 120 and the blade 110 described below are limited to the compressor section 4, but this may also be applied to the rotor disk 6a and the blade 6b of the turbine section 6.

3 is a side cross-sectional view showing a first embodiment of the shape of the magnetic force member 200 of the blade fixing structure 100 of the present invention, Figure 4 is a shape of the magnetic force member 200 of the blade fixing structure 100 of the present invention 5 is a side cross-sectional view showing a second embodiment, Figure 5 is a side cross-sectional view showing a third embodiment of the shape of the magnetic member 200 of the blade fixing structure 100 of the present invention, Figure 6 is a blade fixing structure 100 of the present invention Side cross-sectional view showing a fourth embodiment of the shape of the magnetic force member 200).

First, the blade fixing structure 100 of the present invention may be configured to include a coupling groove 121, the coupling protrusion 111 and the magnetic force member 200.

A plurality of coupling grooves 121 may be disposed along the outer circumferential surface of the rotor disk 120, and in the present invention, the coupling grooves 121 may have an arm dovetail shape. The coupling protrusion 111 may be disposed at one end of the blade 110, coupled to the coupling groove 121, and fixed to the outer circumferential surface of the rotor disk 120. In the present invention, the coupling protrusion 111 may have a dovetail shape corresponding to the shape of the arm dovetail. Of course, the coupling groove 121 and the coupling protrusion 111 may be another form of the fitting structure.

The magnetic member 200 is disposed between the coupling groove 121 and the coupling protrusion 111 to receive a repulsive force between the coupling protrusion 111 and the coupling groove 121, the coupling groove 121 It may be provided to fix the position of the coupling protrusion 111 in the inner side.

The magnetic member 200 may be configured to include a first magnetic force unit 210 and the second magnetic force unit 230. The first magnetic force unit 210 may include a first magnet 211 and may be disposed on one side of the coupling protrusion 111 facing the coupling groove 121. The second magnetic force unit 230 may include a second magnet 231 and may be disposed on an inner side of the coupling groove 121 facing the coupling protrusion 111.

Referring to FIG. 3, in the first embodiment of the shape of the magnetic force member 200 of the blade fixing structure 100 of the present invention, the first magnet 211 is along the rotation axis direction of the rotor disc 120. It may be integrally disposed on one side of the coupling protrusion 111. The second magnet 231 may be integrally disposed at a position corresponding to the first magnet 211 at the inner side of the coupling groove 121 along the rotation axis direction of the rotor disc 120.

At this time, the first and second magnets 211 and 231 are made of neodymium magnets of the same polarity, and the first and second magnets 211 and 231 generate repulsive force. Accordingly, as shown by the arrow, the blade 110 is applied in the radial direction of the outer circumferential surface of the rotor disk 120, so that the position of the coupling protrusion 111 may be fixed inside the coupling groove 121.

The spacing D means the spacing between the end of the engaging projection 111 and the inner portion of the engaging groove 121, the spacing D as the blade 110 receives the force in the radial direction of the rotor disk 120 in accordance with the repulsive force generated The gap between the end of the coupling protrusion 111 and the inner portion of the coupling groove 121 is the maximum value.

Since the present invention does not need to process a separate space for inserting the conventional loop spring, the spacing D beam can be narrower than the prior art. Meaning that the spacing D is narrowed because the distance between the coupling protrusion 111 and the coupling groove 121 can be set in consideration of only the metal thermal expansion space that can be generated between the operation of the gas turbine, the coupling of the blade 110 more than the prior art The protrusion 111 and the coupling groove 121 of the rotor disc 120 may be in close contact with each other. This may improve the restraint stability of the blade 110 on the outer circumferential surface of the rotor disk 120.

Next, referring to FIG. 4, in the second embodiment of the shape of the magnetic force member 200 of the blade fixing structure 100 of the present invention, the first magnet 211 is along the rotation axis direction of the rotor disc 120. One side portion of the coupling protrusion 111 may be divided into a plurality of plate shapes. The second magnet 231 is divided into a plurality of plate shapes at positions corresponding to the first magnets 211 at an inner side of the coupling groove 121 along the rotation axis direction of the rotor disc 120. Can be.

In this divided arrangement, a space A is formed between the first and second magnets 211 and 231 arranged in a plurality of rows. Space A takes into account the thermal expansion of the first and second magnets 211 and 231 which may occur between the operation of the gas turbine. Due to the space A, the first and second magnets 211 and 231 undergo thermal expansion in the longitudinal direction, thereby preventing the problem of irregular expansion or distortion.

Next, referring to FIG. 5, in a third embodiment of the shape of the magnetic member 200 of the blade fixing structure 100 of the present invention, the first magnetic force unit 210 may include a first magnet 211 and a first elastic unit ( 215, and the second magnetic force unit 230 may include a second magnet 231 and a second elastic unit 235.

The first magnet 211 may be divided into a plurality of plate shapes on one side of the coupling protrusion 111 along the rotation axis direction of the rotor disc 120. The second magnet 231 is divided into a plurality of plate shapes at positions corresponding to the first magnets 211 at an inner side of the coupling groove 121 along the rotation axis direction of the rotor disc 120. Can be.

In this divided arrangement, a space A is formed between the first and second magnets 211 and 231 arranged in a plurality of rows. Space A takes into account the thermal expansion of the first and second magnets 211 and 231 which may occur between the operation of the gas turbine. Due to the space A, the first and second magnets 211 and 231 undergo thermal expansion in the longitudinal direction, thereby preventing the problem of irregular expansion or distortion.

In addition, the first elastic unit 215 may be disposed between the end of the first magnet 211 and the coupling protrusion 111, the second elastic unit 235 and the second magnet 231 It may be disposed between the inner portion of the coupling groove 121. The first and second elastic units 215 and 235 may be implemented in the form of a coil spring, a leaf spring, or the like.

In the third embodiment of the present invention, the repulsive force by the magnetic force member 200 and the repulsive force by the elastic unit simultaneously act to push the blade 110 more strongly in the radial direction of the rotor disc 120, You can constrain the position more strongly. That is, as shown by the arrow shown in FIG. 5, the repulsive force generated in the first and second magnets 211 and 231 and the first and second elastic units 215 and 235 connected to the first and second magnets 211 and 231 act together. It can be seen that the blade 110 is pushed more strongly in the radial direction of the rotor disk 120 to restrain the position.

Next, referring to FIG. 6, in the fourth embodiment of the shape of the magnetic force member 200 of the blade fixing structure 100 according to the present invention, the first magnet 211 has a rotation axis direction and a circumferential direction of the rotor disc 120. Accordingly, the coupling protrusion 111 may be divided and disposed in a plurality of plate shapes. The second magnet 231 has a plurality of plate shapes at positions corresponding to the first magnets 211 at the inner side of the coupling groove 121 along the rotation axis direction and the circumferential direction of the rotor disk 120. It may be divided and arranged.

In the fourth embodiment of the present invention, the first and second magnets 211 and 231 may be implemented in a disc shape, and each of the first and second magnets 211 and 231 may be end portions of the coupling protrusion 111 by the fastening bolts 214 and 234. And it may be fixed to the inner side of the coupling groove 121.

Here, the inclined portions 114 which are inclined in opposite directions to each other are formed on both sides of the coupling protrusion 111 based on the rotation axis direction of the rotor disc 120, and on both sides of the coupling groove 121. The corresponding inclined portion 124 inclined in a direction corresponding to the inclined portion 114 may be formed.

First and second magnets 211 and 231 are disposed on the inclined portion 114 and the corresponding inclined portion 124, respectively, to generate repulsive force in the inclined direction.

In this case, as shown in FIG. 6, the first and second magnets 211 and 231 disposed at the center portion generate repulsive force (see arrow) in the radial direction of the rotor disk 120 to fix the position of the blade 110, The first and second magnets 211 and 231 disposed on the inclined portion 114 and the corresponding inclined portion 124 generate a repulsive force (see arrow) in the inclined direction to fix the front and rear positions of the blade 110.

That is, in such a structure, the repulsive force may be generated in the blade 110 in multiple directions, thereby further improving the fixing force of the blade 110.

On the other hand, Figure 7 is a front sectional view showing a first embodiment of the arrangement of the magnetic force member 200 of the blade fixing structure 100 of the present invention, Figure 8 is a magnetic force member 200 arrangement of the blade fixing structure 100 of the present invention 9 is a front sectional view showing a second embodiment of the present invention, Figure 9 is a front sectional view showing a third embodiment of the arrangement of the magnetic force member 200 of the blade fixing structure 100 of the present invention, Figure 10 is a blade fixing structure of the present invention It is a front sectional view showing the fourth embodiment of the arrangement of the magnetic member 200 of (100).

Referring first to FIG. 7, a cross sectional view of the G-G portion in FIG. 3 is posted, which represents a first embodiment of the arrangement of the magnetic member 200 of the blade fixing structure 100 according to the present invention. In the first exemplary embodiment of the present invention, the blade groove 112 may be formed at the end of the coupling protrusion 111, and the first magnet 211 may be inserted into the blade groove 112. The disk groove 122 is formed at a position corresponding to the plurality of blade grooves 112 along the inner surface of the coupling groove 121, and the second magnet 231 is inserted into the disk groove 122. It may be a structure.

Referring to FIG. 8, in the second embodiment of the arrangement of the magnetic member 200 of the blade fixing structure 100 of the present invention, the first magnet 211 along the circumference of the outer surface of the coupling protrusion 111 is formed. A plurality of blade grooves 112 into which the inserts are inserted may be disposed. In addition, a plurality of disk grooves 122 into which the second magnet 231 is inserted may be disposed at positions corresponding to the plurality of blade grooves 112 along the inner circumference of the coupling groove 121.

As the plurality of blade grooves 112 and the disk grooves 122 are disposed as compared to the single blade groove 112 and the disk grooves 122 illustrated in FIG. 7, the plurality of first and second magnets 211 and 231 may be disposed. Can adjust the strength of the repulsive force.

Since the size of the actual gas turbine is varied, and thus, the size, weight, shape, etc. of the blade 110 vary, the repulsive force required by adjusting the number of the first and second magnets 211 and 231 according to each product specification. It is possible to adjust the intensity of the.

Next, referring to FIG. 9, in the third embodiment of the arrangement of the magnetic force member 200 of the blade fixing structure 100 of the present invention, the first magnet 211 is formed along the circumference of the outer surface of the coupling protrusion 111. A plurality of blade holes 113 may be inserted. In addition, a plurality of disk holes 123 into which the second magnet 231 is inserted may be disposed at positions corresponding to the plurality of blade holes 113 along the inner circumference of the coupling groove 121.

Compared to the single blade groove 112 and the disk groove 122 disclosed in FIG. 7, the plurality of first and second magnets 211 and 231 are disposed as the plurality of blade holes 113 and the disk holes 123 are disposed. I can do it and I can regulate the strength of the repulsive force.

As described above, the intensity of the repulsive force required may be adjusted by adjusting the number of the first and second magnets 211 and 231 according to each product specification such as the size, weight, and shape of the blade 110.

Next, referring to FIG. 10, in the fourth embodiment of the arrangement of the magnetic member 200 of the blade fixing structure 100 according to the present invention, the one side facing the second magnet 231 on the first magnet 211 is provided. A first concave-convex portion 219 that is a trapezoidal groove is formed, and a trapezoidal shape corresponding to the first concave-convex portion 219 is formed at one side portion facing the first magnet 211 on the second magnet 231. A second uneven portion 239 that is a protrusion may be formed.

The first and second uneven parts 219 and 239 have shapes corresponding to each other, and the coupling protrusion 111 of the blade 110 may also function as a guide when inserted into the coupling groove 121 of the rotor disc 120. In addition, by generating repulsive force between the uneven portion may also function to fix the position of the blade 110 in the radial direction of the rotor disk 120.

On the other hand, Figure 11 is a side cross-sectional view showing a first embodiment of the linkage structure of the magnetic force member 200 and the cooling channel of the present invention, Figure 12 is a second view of the linkage structure of the magnetic force member 200 and the cooling channel of the present invention Side cross-sectional view showing an embodiment.

First, referring to FIG. 11, a second magnet channel 236 connected to a cooling channel 125 formed in the rotor disk 120 is formed on the second magnet 231, and the second magnet channel ( 236 may have a second tapered portion 237 tapered in one direction. In this case, the cooling passage 125 formed in the rotor disk 120 may also be tapered in one direction.

In addition, a first magnet channel 216 is formed on the first magnet 211 to be connected to the cooling channel 115 formed in the blade 110, and the first magnet channel 216 is tapered in one direction. The first taper portion 217 may be formed. In this case, the tapered angle of the first tapered portion 217 may be proportional to the tapered angle of the second tapered portion 237.

The cooling fluid introduced into the cooling passage 125 of the rotor disc 120 enters the cooling passage 115 of the blade 110 to cool the inside of the blade 110, and thus the tapered rotor disc 120 may be cooled. It moves along the cooling flow path 125. At this time, the first and second magnets 211 and 231 are tapered at an angle corresponding to the cooling passage 125 of the rotor disk 120, so that the cooling fluid may flow smoothly to the cooling passage 115 of the blade 110 without generating turbulence. Can be. In addition, according to the law of fluid continuation, the passage gradually narrows from the cooling passage 125 of the rotor disk 120 to the cooling passage 115 of the blade 110, so that the flow velocity of the cooling fluid becomes faster.

Next, referring to FIG. 12, a second magnet channel 236 connected to the cooling channel 125 formed in the rotor disk 120 is formed on the second magnet 231, and the second magnet channel ( 236 may have a second curved portion 238 curved in one direction. In this case, the cooling passage 125 formed in the rotor disk 120 may also have a curved shape in one direction.

The first magnet channel 216 is formed on the first magnet 211 to be connected to the cooling channel 115 formed in the blade 110, and the first magnet channel 216 is curved in one direction. The first curved portion 218 may be formed. In this case, the curvature of the first curved portion 218 may be proportional to the curvature of the second curved portion 238.

The cooling fluid introduced into the cooling channel 125 of the rotor disk 120 enters the cooling channel 115 of the blade 110 and cools the inside of the blade 110. It moves along the cooling flow path 125. In this case, the first and second magnets 211 and 231 are curved at an angle corresponding to the cooling passage 125 of the rotor disk 120, so that the cooling fluid may flow smoothly to the cooling passage 115 of the blade 110 without generating turbulence. Can be. In addition, according to the law of fluid continuation, the passage gradually narrows from the cooling passage 125 of the rotor disk 120 to the cooling passage 115 of the blade 110, so that the flow velocity of the cooling fluid becomes faster.

On the other hand, Figure 13 is a view showing a fixing structure of the first magnetic force unit 210 of the present invention, Figure 14 is a view showing a fixing structure of the second magnetic force unit 230 of the present invention.

First, referring to FIG. 13, the first magnet 211 may be disposed in the blade groove 112 of the coupling protrusion 111 in one piece or in a plurality of divided shapes, and the length direction of the first magnet 211 may be adjusted. Accordingly, the first fixed beam 212 is bolted to both sides to fix the first magnet 211 at both sides, and the first cross beam 213 is bolted to the first fixed beam 212 at a predetermined interval. And may be configured to support across the first magnet 211.

Alternatively, the first cross beam 213 may be disposed between the first magnet flow paths 216 formed in the first magnet 211. At this time, the gaps G1 and G2 are formed between the blade grooves 112 and the first magnets 211 of the coupling protrusion 111, so that the thermal expansion space of the first magnets 211 due to high heat during operation of the gas turbine can be secured. .

Next, referring to FIG. 14, the second magnet 231 may be disposed in the disk groove 122 of the coupling groove 121 in one piece or in a plurality of divided shapes, and may extend in the longitudinal direction of the second magnet 231. Accordingly, the second fixed beam 232 is bolted to both sides to fix the second magnet 231 at both sides, and the second cross beam 233 is bolted to the second fixed beam 232 at a predetermined interval. And may be configured to support across the second magnet 231.

Alternatively, the second cross beam 233 may be disposed between the second magnet flow paths 236 formed in the second magnet 231. At this time, the gaps G1 and G2 are formed between the disk groove 122 and the second magnet 231 of the coupling groove 121, so that the thermal expansion space of the second magnet 231 due to high heat during operation of the gas turbine can be secured. .

The above only shows a specific embodiment of the blade fixing structure using a magnetic force and the gas turbine including the same.

Therefore, it will be apparent to those skilled in the art that the present invention may be substituted and modified in various forms without departing from the spirit of the present invention as set forth in the claims below. do.

100: blade fixed structure
110: blade 111: coupling protrusion
112: blade groove 113: blade hole
114: inclined portion 115: cooling flow path of the blade
120: rotor disc 121: coupling groove
122: disc groove 123: disc hole
124: corresponding inclined portion 125: cooling path of the rotor disk
200: magnetic member
210: first magnetic unit 211: first magnet
212: first fixed beam 213: first cross beam
214: fastening bolt 215: first elastic unit
216: first magnet euro 217: first taper portion
218: first curved portion 219: first uneven portion
230: second magnetic unit 231: second magnet
232: second fixed beam 233: second cross beam
234: fastening bolt 235: second elastic unit
236: 2nd magnet euro 237: 2nd taper part
238: second curved portion 239: second uneven portion

Claims (20)

A coupling groove disposed along an outer circumferential surface of the rotor disk;
A coupling protrusion disposed at one end of the blade and coupled to the coupling groove; And
A magnetic force member disposed between the coupling groove and the coupling protrusion and provided to fix the position of the coupling protrusion inside the coupling groove by receiving a repulsive force between the coupling protrusion and the coupling groove.
The magnetic member,
A first magnetic force unit disposed on one side of the coupling protrusion facing the coupling groove; And
And a second magnetic force unit disposed on the inner side facing the coupling protrusion on the coupling groove.
The first magnetic force unit may include a first magnet disposed on one side of the coupling protrusion along a rotation axis direction of the rotor disk, wherein the first magnet is connected to a cooling flow path formed inside the blade. 1 magnet euro; blade fixed structure using a magnetic force, characterized in that formed.
delete delete The method of claim 1,
The first magnet, the blade fixing structure using a magnetic force, characterized in that divided into a plurality of plate-shaped portion disposed on one side of the coupling projection along the rotation axis direction of the rotor disk.
The method of claim 1,
The first magnet, the blade fixing structure using a magnetic force, characterized in that divided into a plurality of plate-shaped portion on one side of the engaging projection along the rotation axis direction and the circumferential direction of the rotor disk.
delete The method of claim 1,
Blade fixing structure using magnetic force, characterized in that the first tapered portion is tapered in one direction on at least one side of the first magnet channel.
The method of claim 1,
Blade fixing structure using magnetic force, characterized in that the first curved portion curvature in one direction on at least one side of the first magnet channel.
The method of claim 1,
The second magnetic unit is,
And a second magnet disposed in an inner side of the coupling groove along a rotation axis direction of the rotor disk.
The method of claim 1,
The second magnetic unit is,
And a second magnet disposed in a plurality of plate shapes on an inner side of the coupling groove along a rotation axis direction of the rotor disk.
The method of claim 1,
The second magnetic unit is,
And a second magnet that is divided into a plurality of plate shapes on an inner side of the coupling groove along a rotation axis direction and a circumferential direction of the rotor disk.
delete The method according to any one of claims 9 to 11,
A second magnet channel connected to a cooling channel formed in the rotor disk on the second magnet; a magnetic tape, wherein at least one side of the second magnet channel is tapered in one direction Blade fixing structure
The method according to any one of claims 9 to 11,
A second magnet flow path connected to a cooling flow path formed in the rotor disk on the second magnet; and a magnetically curved second curved portion formed in at least one side of the second magnet flow path in one direction. Blade fixing structure
A coupling groove disposed along an outer circumferential surface of the rotor disk;
A coupling protrusion disposed at one end of the blade and coupled to the coupling groove; And
A magnetic force member disposed between the coupling groove and the coupling protrusion and provided to fix the position of the coupling protrusion inside the coupling groove by receiving a repulsive force between the coupling protrusion and the coupling groove.
The magnetic member,
A first magnetic force unit disposed on one side of the coupling protrusion facing the coupling groove; And
And a second magnetic force unit disposed on the inner side facing the coupling protrusion on the coupling groove.
The first magnetic force unit includes a first magnet disposed on one side of the coupling protrusion along a rotation axis direction of the rotor disc.
The second magnetic force unit, along the direction of the rotation axis of the rotor disk, a second magnet disposed on the inner side of the coupling groove; includes,
A first concave-convex portion that is a trapezoidal groove is formed in one side portion facing the second magnet on the first magnet;
The second concave-convex portion of the trapezoidal projection corresponding to the first concave-convex portion is formed on one side facing the first magnet on the second magnet; blade fixing structure using magnetic force.
A coupling groove disposed along an outer circumferential surface of the rotor disk;
A coupling protrusion disposed at one end of the blade and coupled to the coupling groove; And
A magnetic force member disposed between the coupling groove and the coupling protrusion and provided to fix the position of the coupling protrusion inside the coupling groove by receiving a repulsive force between the coupling protrusion and the coupling groove.
The magnetic member,
A first magnetic force unit disposed on one side of the coupling protrusion facing the coupling groove; And
And a second magnetic force unit disposed on the inner side facing the coupling protrusion on the coupling groove.
The first magnetic force unit includes a first magnet disposed in the coupling protrusion along a rotation axis direction of the rotor disc.
The second magnetic force unit, along the direction of the rotation axis of the rotor disk, a second magnet disposed in the coupling groove; includes,
A plurality of blade grooves are formed to be inserted into the first magnet around the outer surface of the engaging projection,
Blade fixing structure using a magnetic force, characterized in that a plurality of disk grooves are inserted in the position corresponding to the plurality of blade grooves along the inner circumference of the coupling grooves.
A coupling groove disposed along an outer circumferential surface of the rotor disk;
A coupling protrusion disposed at one end of the blade and coupled to the coupling groove; And
A magnetic force member disposed between the coupling groove and the coupling protrusion and provided to fix the position of the coupling protrusion inside the coupling groove by receiving a repulsive force between the coupling protrusion and the coupling groove.
The magnetic member,
A first magnetic force unit disposed on one side of the coupling protrusion facing the coupling groove; And
And a second magnetic force unit disposed on the inner side facing the coupling protrusion on the coupling groove.
The first magnetic force unit includes a first magnet disposed in the coupling protrusion along a rotation axis direction of the rotor disc.
The second magnetic force unit, along the direction of the rotation axis of the rotor disk, a second magnet disposed in the coupling groove; includes,
A plurality of blade holes for inserting the first magnet is formed along the outer periphery of the coupling protrusion,
And a disk hole into which the second magnet is inserted at a position corresponding to the plurality of blade holes along an inner circumference of the coupling groove.
A coupling groove disposed along an outer circumferential surface of the rotor disk;
A coupling protrusion disposed at one end of the blade and coupled to the coupling groove; And
A magnetic force member disposed between the coupling groove and the coupling protrusion and provided to fix the position of the coupling protrusion inside the coupling groove by receiving a repulsive force between the coupling protrusion and the coupling groove.
The magnetic member,
A first magnetic force unit disposed on one side of the coupling protrusion facing the coupling groove; And
And a second magnetic force unit disposed on the inner side facing the coupling protrusion on the coupling groove.
The first magnetic force unit includes: a first magnet divided into a plurality of plate shapes at one side of the coupling protrusion along a rotation axis direction and a circumferential direction of the rotor disc;
The second magnetic force unit may include a second magnet that is divided into a plurality of plate shapes at positions corresponding to the first magnets at the inner side of the coupling groove along the rotation axis direction and the circumferential direction of the rotor disc. ,
On the basis of the rotation axis direction of the rotor disk, both sides of the engaging projection inclined inclined in opposite directions to each other; is formed on both sides of the coupling groove corresponding inclined portion inclined in a direction corresponding to the inclined portion Blade fixing structure using magnetic force, characterized in that is formed.
The method according to any one of claims 9 to 11 or 15 to 18,
The first and second magnets are a blade fixing structure using magnetic force, characterized in that the neodymium magnet having the same pole for generating a repulsive force.

Casing;
A compressor section disposed inside the casing and compressing the introduced air;
A combustor disposed within the casing, the combustor configured to combust compressed air;
A turbine section disposed in the casing, connected to the combustor, the turbine section generating power using the combusted air; And
A diffuser disposed in the casing and connected to the turbine section and discharging air to the outside;
19. A blade fixing structure using magnetic force as claimed in any one of claims 1 to 15 disposed in at least one of the compressor section and the turbine section;
Gas turbine comprising a.

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