KR20190096641A - Combuster and gas turbine having the same - Google Patents

Abstract

The present invention relates to a combustor and a gas turbine including the same. According to the present invention, the combustor comprises: a nozzle plate in which a plurality of nozzle shrouds for fuel injection nozzles to be mounted are integrally formed; a first heat deformation compensation unit which is formed along the circumference of the nozzle shrouds and provided to compensate for a heat deformation space of the nozzle shrouds in a high temperature environment; and a second heat deformation compensation unit which is formed at the boundary between the nozzle shrouds and the nozzle plate and provided to compensate for a heat deformation space of the boundary at a high temperature environment. According to the present invention, by manufacturing the nozzle plate and the nozzle shrouds integrally, it is possible to shorten the assembly time and reduce the manufacturing costs. The combustor is designed to compensate for the heat deformation space, thereby preventing heat deformation in a high temperature operating environment.

Description

COMBUSTER AND GAS TURBINE HAVING THE SAME}

The present invention relates to a combustor and a gas turbine including the same. More particularly, the nozzle plate and the nozzle shroud are integrally manufactured to reduce weight, reduce assembly time, and reduce manufacturing cost, and to compensate for heat deformation space. The present invention relates to a combustor and a gas turbine including the same, which prevent thermal deformation in a high temperature operating environment.

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, and includes a rotor including a plurality of buckets to be axially rotated by the fluid. rotor and a casing installed around the rotor and provided with a plurality of diaphragms.

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 is 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.

1 shows an assembled state of a nozzle plate 9a and a nozzle shroud 9b of a conventional combustor. As shown in Fig. 1, when there are six fuel injection nozzles to be mounted, the nozzle shrouds 9b are disposed on the opening holes of the nozzle plate 9a, respectively, and the brackets 9c are fastened by bolts 9d to fasten the nozzle shrouds. (9b) is fixed. The number of parts required is 1 nozzle plate, 6 nozzle shrouds, 5 brackets, and the number of bolts is 15.

As the conventional combustor is required to match the assembly positions of several parts, and bolted respectively, as described above, the operator's work load is high, the assembly takes a long time, and the production cost is increased by applying a plurality of parts have.

Korean Patent Publication No.:10-2014-0035415

The present invention has been made to solve the problems in the related art as described above, an object of the present invention is to produce a nozzle plate and a nozzle shroud integrally to reduce the weight, shorten the assembly time and reduce the manufacturing cost, heat The present invention provides a combustor and a gas turbine including the same, which are designed to compensate the deformation space and prevent thermal deformation in a high temperature operating environment.

The present invention for achieving the above object relates to a combustor and a gas turbine comprising the same, in the combustor of the gas turbine, a nozzle plate and the nozzle shroud is formed integrally a plurality of nozzle shroud to which the fuel injection nozzle is mounted. And a first heat deformation compensation part provided along the perimeter of the nozzle shroud and provided at the boundary between the nozzle shroud and the nozzle plate to compensate for the heat deformation space of the nozzle shroud in a high temperature environment, and the heat deformation of the boundary part in a high temperature environment. It may include a second heat distortion compensation unit provided to compensate for the space.

In addition, in the embodiment of the present invention, the first heat distortion compensating part is formed along a circumference of the nozzle shroud, and includes a dividing part dividing the nozzle shroud into a plurality of unit shroud blocks in a circumferential direction. In order to compensate for a widthwise heat deformation space of the unit shroud block in a high temperature environment, the unit shroud blocks may be spaced apart from each other by a predetermined distance, and may be formed along the length direction of the unit shroud block.

In addition, in the embodiment of the present invention, the first heat distortion compensation unit is formed in at least one along the width direction of the unit shroud block, and is provided to compensate for the longitudinal heat deformation space of the unit shroud block in a high temperature environment. It may further include one slot.

In addition, in the exemplary embodiment of the present invention, the first slot may be formed to extend in the width direction of the unit shroud block in the division part.

In addition, in the embodiment of the present invention, the first heat distortion compensation unit may include a second slot formed at an inner end of the division part and provided to compensate for the heat deformation space at the joint portion between the unit shroud blocks in a high temperature environment. It may further include.

In addition, in the embodiment of the present invention, the first heat distortion compensation unit is formed along the width direction of the unit shroud block, and further includes a rounding groove provided to compensate for the longitudinal heat deformation space of the unit shroud block in a high temperature environment. It may include.

In addition, in the embodiment of the present invention, the second heat deformation compensating part is formed in a boundary portion between the nozzle shroud and the nozzle plate, and is provided in a form recessed in the opposite direction (-Z) of the nozzle shroud at the boundary portion. It may include a depression.

In addition, in the embodiment of the present invention, the depression may be curved in the direction opposite to the protrusion (-Z) of the nozzle shroud along the circumference of the boundary portion.

In addition, in the embodiment of the present invention, the second heat deformation compensator may include an auxiliary groove formed in the opposite direction (-Z) of the nozzle shroud on the depression to compensate for the heat deformation space of the depression in a high temperature environment. It may further include.

In addition, in the embodiment of the present invention, the second heat distortion compensation part may further include an auxiliary protrusion formed on the opposite side of the auxiliary groove in the depression so that the rigidity of the depression is improved.

The gas turbine of the present invention is disposed in the casing and the casing and the compressor section for compressing the introduced air and connected to the compressor section in the casing, the combustor for combusting the compressed air and the combustor inside the casing And a turbine section disposed in connection with the turbine section to generate power using the combusted air, and a diffuser connected to and disposed in the casing and connected to the turbine section, and configured to discharge air to the outside. A first heat deformation compensation unit and a nozzle shroud formed along a circumference of the nozzle shroud and the nozzle shroud in which a plurality of nozzle shrouds are integrally formed, and provided to compensate for the heat deformation space of the nozzle shroud in a high temperature environment; It is formed in the boundary of the nozzle plate, the heat deformation hole of the boundary in a high temperature environment The provided so that compensation may include a second heat distortion compensation.

In addition, in the embodiment of the present invention, the first heat distortion compensating part is formed along a circumference of the nozzle shroud, and includes a dividing part dividing the nozzle shroud into a plurality of unit shroud blocks in a circumferential direction. In order to compensate for a widthwise heat deformation space of the unit shroud block in a high temperature environment, the unit shroud blocks may be spaced apart from each other by a predetermined distance, and may be formed along the length direction of the unit shroud block.

In addition, in the embodiment of the present invention, the first heat distortion compensation unit is formed in at least one along the width direction of the unit shroud block, and is provided to compensate for the longitudinal heat deformation space of the unit shroud block in a high temperature environment. It may further include one slot.

In addition, in the exemplary embodiment of the present invention, the first slot may be formed to extend in the width direction of the unit shroud block in the division part.

In addition, in the embodiment of the present invention, the first heat distortion compensation unit may include a second slot formed at an inner end of the division part and provided to compensate for the heat deformation space at the joint portion between the unit shroud blocks in a high temperature environment. It may further include.

In addition, in the embodiment of the present invention, the first heat distortion compensation unit is formed along the width direction of the unit shroud block, and further includes a rounding groove provided to compensate for the longitudinal heat deformation space of the unit shroud block in a high temperature environment. It may include.

In addition, in the embodiment of the present invention, the second heat deformation compensating part is formed in a boundary portion between the nozzle shroud and the nozzle plate, and is provided in a form recessed in the opposite direction (-Z) of the nozzle shroud at the boundary portion. It may include a depression.

In addition, in the embodiment of the present invention, the depression may be curved in the direction opposite to the protrusion (-Z) of the nozzle shroud along the circumference of the boundary portion.

In addition, in the embodiment of the present invention, the second heat deformation compensator may include an auxiliary groove formed in the opposite direction (-Z) of the nozzle shroud on the depression to compensate for the heat deformation space of the depression in a high temperature environment. It may further include.

In addition, in the embodiment of the present invention, the second heat distortion compensation part may further include an auxiliary protrusion formed on the opposite side of the auxiliary groove in the depression so that the rigidity of the depression is improved.

According to the present invention, by integrally manufacturing the nozzle plate and nozzle shroud of the combustor through a mold, it is possible to remove the bracket and bolt to fasten the nozzle plate and nozzle shroud used in the past, thereby reducing the assembly time The manufacturing cost can be lowered.

In addition, in consideration of the high temperature operating environment of the combustor, the nozzle shroud is divided along the circumferential direction, and the boundary between the nozzle plate and the nozzle shroud is formed to be bent, so that the heat deformation space is compensated, and due to thermal expansion of the metal material in the high temperature operating environment. It is possible to prevent thermal deformation of the part.

1 is a view showing a fastening structure of a conventional nozzle plate and a nozzle shroud.
Figure 2 is a side cross-sectional view showing the structure of the gas turbine.
3 is a cross-sectional perspective view showing the structure of the combustor.
Figure 4 is a view showing the structure of the nozzle plate and nozzle shroud in the combustor of the present invention.
Figure 5 is a side view showing a first form of the first heat deformation compensation unit of the combustor according to the present invention.
Figure 6 is a side view showing a second form of the first heat deformation compensation unit of the combustor according to the present invention.
Figure 7 is a side view showing a third form of the first heat deformation compensation unit of the combustor according to the present invention.
8 is a side view showing a fourth form of the first heat deformation compensation unit in the combustor according to the present invention;
9 is a side view showing a first form of a second heat distortion compensation unit in the combustor of the present invention;
10 is a side view showing a second form of the second heat deformation compensation unit in the combustor according to the present invention;

Hereinafter, preferred embodiments of the combustor and the gas turbine including the same according to the present invention will be described in detail with reference to the accompanying drawings.

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 10 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. .

Referring to the flow direction of the air, the compressor section 4 is located in front of the casing 10, 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 4a, and each of the compressor rotor disks 4a is 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 4a 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 4a, 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 4b (or buckets) are radially coupled to the outer circumferential surface of the compressor rotor disk 4a. Each blade 4b has a dove tail portion (not shown) and is fastened to the compressor rotor disk 4a.

The dovetail part may be of 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 4b can be fastened to the compressor rotor disk 4a using a fastening device other than the dovetail.

At this time, the inner circumferential surface of the compressor section 4 of the casing 2 has vanes (or nozzles) for relative rotational movement of the compressor blade 4b mounted on the diaphragm (not shown). Can be.

The tie rods 3a are arranged to penetrate through the centers of the plurality of compressor rotor disks 4a, one end of which is fastened in the compressor rotor disk 4a located at the most upstream side, and the other end thereof is the torque tube 3b. It is fixed to).

Since the tie rod 3a may be formed in various structures according to gas turbines, the tie rod 3a 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 4a, and 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 10 mixes and combusts the introduced compressed air with fuel to produce high energy, high pressure, high pressure combustion gas, and heat resistance that the components of the combustor 10 and the turbine section 6 can withstand during the isostatic combustion process. The combustion gas temperature is raised to the limit.

The combustor 10 constituting the combustion system of the gas turbine may be arranged in the casing 2 formed in the form of a cell.

The structure of the combustor 10 will be described in detail below with reference to FIG. 3.

On the other hand, in the turbine section 6, the high-temperature, high-pressure combustion gas from the combustor 10 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 the compressor rotor disk 4a.

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 a vane (or nozzle) for the relative rotational movement of the turbine blade (6b) is 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 10, and then moved to the turbine section 6 to drive power generation, and the diffuser 7 is driven. Through the atmosphere.

Here, the torque tube 3b, the compressor rotor disk 4a, the compressor blade 4b, the turbine rotor disk 6a, the turbine blade 6b, the tie rods 3a, and the like are integrally formed as a rotating component. 3) or a rotating body. The casing 2, vanes (not shown), diaphragms (not shown), etc. may be referred to as stators or fixtures as a non-rotating component.

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

3 is a longitudinal cut perspective view of the combustor. The combustor 10 includes the fuel injection nozzles 15 and 17 constituting the burner 10a, the burner casing 11 surrounding the fuel nozzles 15 and 17, and a liner 31 forming the combustion chamber 31a. A flow sleeve 35 annularly enclosing the liner 31 and the annularly enclosed transition piece 3 and the transition piece 33 serving as a connection between the combustor 100 and the turbine 20. A sleeve 35 is configured.

The liner 31 provides a combustion chamber 31a in which fuel injected by the fuel nozzles 15 and 17 is mixed with and combusted with compressed air introduced through. The liner 31 may cool the liner 31 through the compressed air flow path 32 by the flow sleeve 35 forming an annular space on the outer circumference. The fuel nozzles 15 and 17 are coupled to the front end of the liner.

On the other hand, the transition piece 33 is connected to the rear end of the liner 31 so that the combustion gas combusted by the spark plug can be sent to the turbine side. The liner 31 and the transition piece 33 are annular spaces formed by the flow sleeve 35 wrapped around the liner 31 and the transition piece 33 to prevent damage due to high temperature of the combustion gas, that is, the compressed air flow path ( It is cooled by the compressed air supplied to 32,34.

The plurality of fuel nozzles 18 are annularly enclosed in the burner casing 11 serving as a housing and connected to the liner 31. A cylindrical member having a plurality of openings may be inserted into a portion in which the plurality of fuel nozzles 18 is connected to the liner 31. The cylindrical member may include a nozzle tube including a plurality of fuel nozzles 18. 13). The plurality of openings formed in the nozzle tube 13 function as a fuel nozzle 18, and the fuel nozzle 18 may be composed of a central nozzle 17 and a plurality of peripheral nozzles 15 surrounding the nozzle nozzle 13. .

The fuel nozzle 18 is configured to enclose a center body 14 extending in the combustor front-back direction at the center of the cylindrical space. One end of the center body 14 is connected to and supplied with fuel from a fuel nozzle base 12, the fuel being formed around the center body 14 and / or the center body 14. It is injected through the fuel injection opening 21 formed in the swirl vane 20 may be mixed with compressed air. It should be noted that the position and shape of the fuel nozzle to which fuel is supplied is not limited to the form shown in FIG. 2, and the drawing is merely an example.

The nozzle base 12 is connected to the end cover 22, and the end cover 22 may comprise a configuration for receiving fuel at least partially.

4 is a view showing the structure of the nozzle plate 50 and the nozzle shroud 60 in the combustor 10 of the present invention.

Referring to FIG. 4, the combustor 10 of the present invention may include a nozzle plate 50, a nozzle shroud 60, a first heat deformation compensation unit 70, and a second heat deformation compensation unit 80. have.

 A plurality of openings 50a are formed in the nozzle plate 50, and in the present invention, six nozzles 50a may be formed. This means that six fuel injection nozzles 15 and 17 are mounted on the nozzle plate 50.

The nozzle shroud 60 may be integrally formed on each of the openings 50a of the nozzle plate 50. Unlike the related art, in the present invention, the nozzle plate 50 and the nozzle shroud 60 may be integrally manufactured through a mold design.

When the integrated nozzle plate 50 and the nozzle shroud 60 are applied, the assembly time of the combustor 10 can be shortened, and the number of parts such as a separate bracket and bolt for fastening can be shortened. It can reduce the manufacturing cost can be expected to be reduced.

Next, the first heat deformation compensation unit 70 may be formed along the circumference of the nozzle shroud 60, and may be provided to compensate for the heat deformation space of the nozzle shroud 60 in a high temperature environment.

The second heat deformation compensator 80 is formed at the boundary A between the nozzle shroud 60 and the nozzle plate 50 and provides a compensation for the heat deformation space of the boundary A in a high temperature environment. Can be.

In general, the nozzle plate 50 and the nozzle shroud 60 are made of a metal material in which thermal expansion occurs in a high temperature operating environment of the combustor 10. Therefore, if a separate thermal deformation compensation space is not provided, thermal deformation of the component may occur due to thermal expansion during manufacturing as a single piece, which may cause thermal damage of the component, which may shorten the life of the combustor 10 and deteriorate its function. Can

The first and second thermal deformation compensation units 70 and 80 form a thermal deformation compensation space between the nozzle plate 50 and the nozzle shroud 60 that are integrally manufactured to prevent the thermal damage problem described above.

Specifically, first, various embodiments of the first heat distortion compensation unit 70 will be described.

5 is a side view showing a first form of the first heat distortion compensation unit 70 of the combustor 10 according to the present invention.

Referring to FIG. 5, the nozzle shroud 60 protrudes in one direction and is integrally formed on the nozzle plate 50, and the division part 71 is formed on the nozzle shroud 60.

The division part 71 is formed along the circumference of the nozzle shroud 60 and divides the nozzle shroud 60 into a plurality of unit shroud blocks 61 in the circumferential direction.

At this time, the division part 71 is spaced apart a predetermined interval between the unit shroud block 61, to compensate for the width direction heat deformation space of the unit shroud block 61 in a high temperature environment, the unit shroud block 61 It may be formed along the longitudinal direction.

In the high temperature operating environment of the combustor 10, the nozzle shroud 60 may undergo thermal expansion along the circumferential direction, which may cause distortion of the nozzle shroud 60. Therefore, in order to prevent this, in the present invention, the nozzle shroud 60 is divided into a plurality of unit shroud blocks 61.

Since the division part 71 is formed, a space that can be thermally expanded even in a high temperature environment is formed, which can prevent distortion and thermal deformation of the nozzle shroud 60 in the circumferential direction. This is to prevent the distortion heat deformation in the width direction in the unit shroud block.

Next, Figure 6 is a side view showing a second form of the first heat distortion compensation unit 70 of the combustor 10 of the present invention.

Referring to FIG. 6, the first heat distortion compensating part 70 may further include a first slot 73 and a second slot 75 in addition to the dividing part 71.

At least one first slot 73 is formed along the width direction of the unit shroud block 61, and may be provided to compensate for a longitudinal heat deformation space of the unit shroud block 61 in a high temperature environment.

In the high temperature operating environment of the combustor 10, the nozzle shroud 60 may generate thermal expansion not only in the circumferential direction but also in the longitudinal direction. In this case, the thermal expansion in the circumferential direction compensates for the thermal deformation space in the division part 71, and the thermal expansion in the longitudinal direction compensates for the thermal deformation space in the first slot 73.

Only one first slot 73 is formed in the unit shroud block 61 in FIG. 6, but a plurality of first slots 73 may be arranged along a length direction according to a design. Can also be produced. Therefore, it is not necessarily limited to the structure posted in FIG.

In addition, the second slot 75 may be formed at the inner end of the dividing portion 71 and may be provided to compensate for the heat deformation space at the joint portion between the unit shroud blocks 61 in a high temperature environment.

In the high temperature operating environment of the combustor 10, the thermal expansion of the nozzle shroud 60 may occur at joints between the plurality of shroud blocks 61. At this time, the thermal expansion in the width direction of the unit shroud block 61 is the division portion 71, the thermal expansion in the longitudinal direction compensates the heat deformation space in the first slot 73, the unit shroud block 61 Thermal expansion at the joint between the holes compensates for the heat deformation space in the second slot 75.

The second slot 75 is formed in an elliptical shape and a track shape in FIG. 6, but may be manufactured in other sizes and shapes according to design. Therefore, it is not necessarily limited to the structure posted in FIG.

Next, FIG. 7 is a side view illustrating a third form of the first heat deformation compensation unit 70 of the combustor 10 according to the present invention.

Referring to FIG. 7, unlike the first slot 73 posted in FIG. 6, the first slot 73 posted in FIG. 7 is disposed in the width direction of the unit shroud block 61 in the splitter 71. It may be formed in an elongated form. That is, in a form associated with the division part 71, a thermal expansion compensation space in the longitudinal direction of the unit shroud block 61 is formed.

At least one first slot 73 is formed along the width direction of the unit shroud block 61, and may be provided to compensate for a longitudinal heat deformation space of the unit shroud block 61 in a high temperature environment.

Only one first slot 73 is formed in the unit shroud block 61 in FIG. 7, but a plurality of first slots 73 may be arranged along a length direction according to a design. Can also be produced. Therefore, it is not necessarily limited to the structure posted in FIG.

8 is a side view showing a fourth form of the first heat distortion compensation unit 70 of the combustor 10 according to the present invention.

Referring to FIG. 8, the first heat deformation compensating part 70 may further include a rounding groove 77 in addition to the dividing part 71. The rounding groove 77 may be formed along the width direction of the unit shroud block 61, and may be provided to compensate for a longitudinal heat deformation space of the unit shroud block 61 in a high temperature environment.

In the high temperature operating environment of the combustor 10, the nozzle shroud 60 may generate thermal expansion not only in the circumferential direction but also in the longitudinal direction. In this case, the thermal expansion in the circumferential direction compensates for the thermal deformation space in the division part 71, and the thermal expansion in the longitudinal direction compensates for the thermal deformation space in the rounding groove 77.

In the present invention, the rounding groove 77 may be formed in two stages on the unit shroud block 61 at predetermined intervals as shown in FIG. 8, but may be arranged along the length direction in different stages according to design. If the dog is placed, it can also be manufactured in different sizes and shapes. Therefore, it is not necessarily limited to the structure posted in FIG.

Next, various forms of the second heat distortion compensator 80 will be described with reference to FIGS. 9 and 10. Prior to description, the protruding direction (forward direction) of the nozzle shroud 60 shown in Figs. 9 and 10 is defined by the direction reference Z, and the radial direction of the nozzle plate 50 is defined by the direction reference X. Therefore, the direction opposite to the protrusion of the nozzle shroud 60 may be interpreted as -Z.

9 is a side view showing a first form of the second heat distortion compensation unit 80 of the combustor 10 according to the present invention.

First, referring to FIG. 9, the second heat distortion compensator 80 may include a recess 81. The depression 81 is formed at the boundary A between the nozzle shroud 60 and the nozzle plate 50 and is recessed in the opposite direction (-Z) of the nozzle shroud 60 at the boundary A. It may be provided in the form.

The depression 81 may have a curved shape in a direction opposite to the nozzle shroud 60 along the circumference of the boundary portion A.

If the depression 81 is not formed at the boundary A between the nozzle plate 50 and the nozzle shroud 60, the nozzle plate 50 may be opened at a high temperature operating environment of the combustor 10. Since thermal expansion occurs in the 50a and the nozzle shroud 60 radially expands in a radial direction, thermal deformation spaces are not formed therebetween, and thermal damage may occur at the boundary A. FIG.

At this time, when the depression 81 is formed in the boundary portion A, thermal expansion of the nozzle plate 50 into the opening 50a inside is directed toward the nozzle shroud 60 from the upper side of the depression 81. Since the thermal expansion of the nozzle shroud 60 is made in the direction of the nozzle plate 50 from the upper side of the recess 81, a thermal deformation space is secured, and thermal damage is prevented.

In addition, since the thermal expansion in the longitudinal direction of the nozzle shroud 60 is made in the downward direction of the depression 81, the thermal deformation space is also secured, and thus the longitudinal thermal damage of the nozzle shroud 60 can be prevented. have.

Next, FIG. 10 is a side view showing a second form of the second heat distortion compensation unit 80 of the combustor 10 according to the present invention.

Referring to FIG. 10, the second heat deformation compensating part 80 may further include an auxiliary groove 83 and an auxiliary protrusion 85 in addition to the recessed part 81.

The auxiliary groove 83 may be formed in the opposite direction (-Z) of the nozzle shroud 60 on the depression 81. The auxiliary groove 83 provides a space to compensate for the thermal deformation of the depression 81 in the high temperature operating environment of the combustor 10. The auxiliary groove 83 may be formed in the circumferential direction along the depression 81.

In addition, the auxiliary protrusion 85 may have weakened rigidity of the depression 81 as the auxiliary groove 83 is formed, such that the rigidity of the depression 81 is improved. 81 may be formed at an opposite side of the auxiliary groove 83.

In the high temperature environment, the auxiliary protrusion 85 is thermally deformed in the opposite direction (-Z) of the auxiliary groove 83 in the high temperature environment, thereby hindering the function of the depression 81 and the auxiliary groove 83. Without doing so, the rigidity of the depression 81 can be maintained.

Meanwhile, the gas turbine 1 of the present invention includes a casing 2, a compressor section 4 arranged in the casing 2 and compressing the air introduced therein, and the compressor section inside the casing 2. Combustor 10 connected and disposed in connection with 4) and combusted compressed air, and turbine section connected and disposed in the casing 2, connected to the combustor 10 and producing power using combusted air. (6) and a diffuser (7) connected to the turbine section (6) and disposed inside the casing (2) and for discharging air to the outside.

Here, the combustor 10 is formed along the circumference of the nozzle plate 50 and the nozzle shroud 60 in which a plurality of nozzle shrouds 60 on which fuel injection nozzles are mounted are integrally formed, and the nozzles in a high temperature environment. The first thermal deformation compensator 70 is provided to compensate for the heat deformation space of the shroud 60 and the boundary A between the nozzle shroud 60 and the nozzle plate 50 and the boundary part in a high temperature environment. A second heat distortion compensation unit 80 may be provided to compensate for the heat deformation space of (A).

The foregoing merely shows specific embodiments of the combustor 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.

1: gas turbine
2: casing
3: rotor
4: compressor section
6: turbine section
7: Diffuser
10: burner
15, 17: fuel injection nozzle
50: Nozzle board
60: Nozzle shroud
61: unit shroud block
70: first heat distortion compensation unit
71: Division
73: first slot
75: second slot
77: rounding groove
80: second heat distortion compensation unit
81: depression
83: auxiliary groove
85: auxiliary protrusion
A: Border

Claims (20)

In the combustor of the gas turbine,
A nozzle plate in which a plurality of nozzle shrouds on which the fuel injection nozzles are mounted are integrally formed;
A first heat distortion compensation unit formed along a circumference of the nozzle shroud and provided to compensate for the heat deformation space of the nozzle shroud in a high temperature environment; And
A second heat deformation compensation unit formed at a boundary between the nozzle shroud and the nozzle plate and provided to compensate for a heat deformation space of the boundary in a high temperature environment;
Combustor comprising a.
The method of claim 1,
The first heat deformation compensation unit includes a partition unit formed along a circumference of the nozzle shroud and divides the nozzle shroud into a plurality of unit shroud blocks in a circumferential direction.
The division unit is spaced apart a predetermined interval between the unit shroud block, to compensate for the width direction heat deformation space of the unit shroud block in a high temperature environment, the combustor formed along the longitudinal direction of the unit shroud block.
The method of claim 2,
The first heat distortion compensation unit,
And at least one first slot formed along the width direction of the unit shroud block and provided to compensate for a longitudinal heat deformation space of the unit shroud block in a high temperature environment.
The method of claim 3,
And the first slot is formed to extend in the width direction of the unit shroud block in the division part.
The method of claim 2,
The first heat distortion compensation unit,
And a second slot formed at an inner end of the dividing portion and provided to compensate for a heat deformation space at a joint between the unit shroud blocks in a high temperature environment.
The method of claim 2,
The first heat distortion compensation unit,
And a rounding groove formed along the width direction of the unit shroud block and provided to compensate for a longitudinal heat deformation space of the unit shroud block in a high temperature environment.
The method of claim 1,
The second heat distortion compensation unit,
And a depression formed in a boundary portion of the nozzle shroud and the nozzle plate and provided in a form recessed in the opposite direction (-Z) of the nozzle shroud at the boundary portion.
The method of claim 7, wherein
And the depression is curved along the periphery of the boundary in the direction opposite the protrusion (-Z) of the nozzle shroud.
The method of claim 7, wherein
The second heat distortion compensation unit,
And an auxiliary groove formed on the depression in the opposite direction (-Z) of the nozzle shroud on the depression to compensate for the heat deformation space of the depression in a high temperature environment.
The method of claim 8,
The second heat distortion compensation unit,
And an auxiliary protrusion formed at an opposite side of the auxiliary groove in the depression so that the rigidity of the depression is improved.
A compressor section disposed inside the casing and compressing the introduced air, and a combustor connected to the compressor section within the casing and combusting compressed air; and connected to the combustor inside the casing. And disposed, 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.
The combustor
A nozzle plate in which a plurality of nozzle shrouds on which the fuel injection nozzles are mounted are integrally formed;
A first heat distortion compensation unit formed along a circumference of the nozzle shroud and provided to compensate for the heat deformation space of the nozzle shroud in a high temperature environment; And
A second heat deformation compensation unit formed at a boundary between the nozzle shroud and the nozzle plate and provided to compensate for a heat deformation space of the boundary in a high temperature environment;
Gas turbine comprising a.
The method of claim 11,
The first heat deformation compensation unit includes a partition unit formed along a circumference of the nozzle shroud and divides the nozzle shroud into a plurality of unit shroud blocks in a circumferential direction.
The division unit is spaced apart a predetermined interval between the unit shroud block, to compensate for the width direction heat deformation space of the unit shroud block in a high temperature environment, the combustor formed along the longitudinal direction of the unit shroud block.
The method of claim 12,
The first heat distortion compensation unit,
And at least one first slot formed along the width direction of the unit shroud block and provided to compensate for a longitudinal heat deformation space of the unit shroud block in a high temperature environment.
The method of claim 13,
And the first slot is formed to extend in the width direction of the unit shroud block in the division part.
The method of claim 12,
The first heat distortion compensation unit,
And a second slot formed at an inner end of the dividing portion and provided to compensate for a heat deformation space at a joint between the unit shroud blocks in a high temperature environment.
The method of claim 12,
The first heat distortion compensation unit,
And a rounding groove formed along the width direction of the unit shroud block and provided to compensate for a longitudinal heat deformation space of the unit shroud block in a high temperature environment.
The method of claim 11,
The second heat distortion compensation unit,
And a depression formed in a boundary portion of the nozzle shroud and the nozzle plate and provided in a form recessed in the opposite direction (-Z) of the nozzle shroud at the boundary portion.
The method of claim 17,
And the depression is curved along the periphery of the boundary in the direction opposite the protrusion (-Z) of the nozzle shroud.
The method of claim 17,
The second heat distortion compensation unit,
And an auxiliary groove formed on the depression in the opposite direction (-Z) of the nozzle shroud on the depression to compensate for the heat deformation space of the depression in a high temperature environment.
The method of claim 18,
The second heat distortion compensation unit,
And an auxiliary protrusion formed at an opposite side of the auxiliary groove in the depression so that the rigidity of the depression is improved.

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