KR102126810B1 - Mounting structure of gas turbine combustion nozzle for improving a vibration characteristics - Google Patents

Abstract

The disclosed invention relates to a mounting structure of a combustor nozzle, a combustor nozzle having at least two flanges along a circumferential direction; and a combustor burner body having at least one mounting hole into which the combustor nozzle is inserted; and, One end is fixed to the burner burner body, the other end is a bolt protruding outward through a through hole formed in the flange of the burner nozzle; and, inserted to surround the bolt, both ends of the burner burner body and the flange A spring that contacts and exerts an elastic force; And a nut screwed to the other end of the bolt protruding through the through hole of the flange.

Description

Mounting structure of gas turbine combustion nozzle for improving a vibration characteristics}

The present invention relates to a mounting structure of a combustor nozzle for a gas turbine, the durability and life of the combustor nozzle by appropriately damping this vibration in the middle of a path through which the combustion vibration or drive vibration of the gas turbine is transmitted through the combustor burner. It relates to a mounting structure of the combustor nozzle for the gas turbine that can increase.

The thermodynamic cycle of the gas turbine engine ideally follows the Brayton cycle. The Brighton cycle consists of four processes: isothermal entropy compression (thermal compression), constant pressure rapid expansion, isentropic expansion (insulation expansion), and constant pressure heat dissipation. That is, after inhaling atmospheric air and compressing it at a high pressure, the fuel is burned in a constant pressure environment to release thermal energy, and this high-temperature combustion gas is expanded and converted into kinetic energy, and then exhaust gas containing residual energy is released into the atmosphere. . That is, the cycle is performed in four processes: compression, heating, expansion, and heat dissipation.

To realize the above Brayton cycle, the gas turbine engine includes a compressor, a combustor, and a turbine. The compressor sucks and compresses external air and supplies it to the combustor, and the combustor produces a high-temperature combustion gas by statically combusting fuel with the supplied air. The high temperature combustion gas produced by the combustor is supplied to the turbine and used as power generation through adiabatic expansion.

The combustor is arranged downstream of the compressor, and a plurality of burners are arranged along the annular combustor casing. Each burner is provided with several combustor nozzles, and the fuel injected from the combustor nozzles is mixed with air in an appropriate ratio to achieve a state suitable for combustion.

Gas and liquid fuels or a combination of these may be used for gas turbine engines. It is important to create a combustion environment for lowering the amount of exhaust gas such as carbon monoxide and nitrogen oxide. Although combustion control is relatively difficult, it has the advantage of reducing the combustion temperature and reducing the exhaust gas by producing uniform combustion. premixed combustion) is applied a lot. In the case of premixed combustion, compressed air is mixed with fuel injected from the combustor nozzle and then into the combustion chamber. The initial ignition of the premixed gas is performed using an igniter, and then combustion is maintained by supplying fuel and air when the combustion is stable.

As such, the combustor has the highest temperature environment in the gas turbine engine, and measures against vibration and high temperature are important because the driving vibration of the gas turbine engine is transmitted as well as the combustion vibration. As a countermeasure against cooling in a high-temperature environment, various technologies using high-pressure air produced by a compressor have been introduced, while a countermeasure against vibration is relatively inadequate. This is also because the development of combustors has been mainly focused on cooling design and combustion control. In particular, when designing the vibration of a combustor, vibration measures against the combustor nozzle have been lacking until now. The combustor nozzle is a kind of tubular structure, which is made of material due to vibration and high temperature applied to the combustor nozzle when used for a long time due to the complicated passage structure through which air and fuel pass. Deterioration and the like are often combined to cause problems in the performance and durability of the combustor nozzle. Therefore, it is necessary to take measures against vibration of the combustor nozzle.

Korean Patent Publication No. 2017-0002124 (January 2017.06 published)

It is an object of the present invention to provide a vibration countermeasure capable of reducing problems that occur in the performance and durability of a combustor nozzle even in an environment where vibration is applied for a long period of time.

The mounting structure of the combustor nozzle according to the present invention includes: a combustor nozzle having at least two flanges along a circumferential direction; and a combustor burner body having at least one mounting hole into which the combustor nozzle is inserted; and the combustor One end is fixed to the burner body, and the other end is a bolt protruding outward through a through hole formed in the flange of the combustor nozzle; and, inserted to surround the bolt, and both ends are in contact with the burner body and the flange Spring to apply an elastic force; And a nut screwed to the other end of the bolt protruding through the through hole of the flange.

Accordingly, the combustor nozzle can move elastically with respect to the combustor burner body by the elasticity of the spring.

Then, the vibration characteristics of the combustor nozzle can be adjusted by adjusting the tightening degree of the nut.

Depending on the embodiment, a plate in the form of a plate may be interposed on a surface where both ends of the spring contact the burner body and the flange.

In addition, at least the bolt and spring among the bolts, springs, and nuts may be accommodated in a mounting space formed in the burner body.

At this time, it may be preferable that the mounting space is isolated from the mounting hole.

In addition, an incision for accommodating the flange of the combustor nozzle may be formed in the inlet region of the mounting space.

In one embodiment of the present invention, the spring is a compression coil spring, and furthermore, the coil spring may be a nonlinear coil spring in which the vibration width of the combustor nozzle relative to the intensity of external vibration changes nonlinearly.

The nonlinear coil spring may be a conical coil spring or a barrel coil spring.

On the other hand, the present invention is a gas turbine comprising a turbine that generates power by receiving the combustion gas produced by the combustor, and a high-temperature combustion gas that expands when the compressed air is mixed with fuel and burns in the compressor. , A combustor nozzle having at least two or more flanges along a circumferential direction; and a combustor burner body having at least one mounting hole into which the combustor nozzle is inserted; and one end fixed to the combustor burner body, the other end A bolt protruding outwardly through a through hole formed in the flange of the combustor nozzle; and a spring inserted to surround the bolt and contacting both ends of the combustor burner body and the flange to apply elastic force; And a nut screwed to the other end of the bolt protruding through the through hole of the flange.

Combustor nozzle mounting structure of the present invention having the above configuration is a combustor nozzle is mounted in a floating state with respect to the combustor burner body, the elasticity of the spring interposed in the middle attenuates vibration and shock transmitted to the combustor nozzle, thereby combustor This will improve the performance and durability of the nozzle.

In addition, the combustor nozzle mounting structure of the present invention can properly design the behavior of the combustor nozzle according to the vibration frequency by combining the tightening of the nut and the characteristics of the spring.

1 is a view showing the overall configuration of a gas turbine to which a mounting structure of a combustor nozzle according to the present invention can be applied.
Figure 2 is an enlarged view of a part of the combustor in the gas turbine of Figure 1;
3 is a view showing the mounting structure of the combustor nozzle according to the present invention.
Figure 4 is a cross-sectional view of the combustor nozzle mounting structure of Figure 3;
5 and 6 illustrate various embodiments of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

In describing the embodiments of the present invention, descriptions of well-known structures that will be apparent to those skilled in the art will be omitted so as not to obscure the subject matter of the present invention. In addition, in adding the reference numerals to the components of each drawing, the same reference numerals will be assigned to the same components, even if they are displayed on different drawings, and when referring to the drawings, the thickness or configuration of the lines shown in the drawings It should be considered that the size of the elements may be exaggerated for clarity and convenience of explanation.

In addition, in describing the components of the embodiments of the present invention, terms such as first, second, A, B, (a), and (b) may be used. These terms are only for distinguishing the component from other components, and the nature, order, or order of the component is not limited by the term. When a component is described as being "connected", "coupled" or "connected" to another component, the component may be directly connected to or connected to the other component, but another component between each component It should also be understood that intervening may be indirectly "connected", "coupled" or "connected".

1 shows a general configuration of a gas turbine 100 to which a mounting structure of a combustor nozzle according to the present invention can be applied. Hereinafter, starting from the general configuration of the gas turbine 100, the structure for mounting the combustor nozzle of the present invention will be described in detail.

The gas turbine 100 includes a housing 102, and a diffuser 106 through which the combustion gas passing through the turbine is discharged is provided at the rear side of the housing 102. In addition, a combustor 104 that receives and compresses compressed air toward the front of the diffuser 106 is disposed.

When referring to the air flow direction, the compressor section 110 is located on the upstream side of the housing 102 and the turbine section 120 is arranged on the downstream side. In addition, between the compressor section 110 and the turbine section 120, a torque tube 130 as a torque transmission member for transmitting rotational torque generated in the turbine section 120 to the compressor section 110 is disposed. .

Compressor section 110 is provided with a plurality of (eg, 14) compressor rotor discs 140, and each compressor rotor disc 140 is fastened so as not to be spaced apart in the axial direction by tie rods 150 It is done.

Specifically, each of the compressor rotor disks 140 is aligned with each other along the axial direction as the tie rod 150 passes through the center. Here, each of the adjacent compressor loader disks 140 are arranged such that their opposing surfaces are compressed by the tie rods 150, thereby making relative rotation impossible.

A plurality of blades 144 are radially coupled to the outer circumferential surface of the compressor rotor disk 140. Each blade 144 is provided with a root portion 146 is fastened to the compressor rotor disk 140.

Between each rotor disk 140, a vane (not shown) which is fixedly arranged in the housing 102 is positioned. Unlike the rotor disc, the vane is fixed not to rotate, and serves to guide air to the blades of the rotor disc located downstream by aligning the flow of compressed air passing through the blades of the compressor rotor disc.

The fastening method of the root portion 146 is tangential type (tangential type) and axial type, which is classified based on the direction in which the root portion 146 is formed on the rotor disk. The fastening method of the root portion 146 may be selected according to a required structure of a commercial gas turbine, and may have a commonly known dovetail or fir-tree shape. In some cases, the blade may be fastened to the rotor disk using a fastening device other than the above-mentioned type, for example, a key or a bolt.

The tie rod 150 is arranged to penetrate the center of the plurality of compressor rotor disks 140, one end of which is fastened in the compressor rotor disk located at the upstream side, and the other end is fixed within the torque tube 130. .

Since the shape of the tie rod 150 may be formed in various structures according to the gas turbine, it is not necessarily limited to the shape shown in FIG. 1. That is, as shown, one tie rod may have a form passing through the central portion of the rotor disk, or a plurality of tie rods may have a form arranged in a circumferential shape, and mixing of these is possible.

In the combustor 104, the compressed air that is introduced is mixed and burned with fuel to produce high-temperature, high-pressure combustion gas with high energy, and the combustion gas temperature is increased to a heat-resistant limit that the combustor and turbine parts can withstand through an isostatic combustion process.

Combustors constituting the combustion system of the gas turbine may be arranged in a plurality of casings formed in a cell form, a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a combustor It comprises a transition piece (Transition Piece) that becomes the connection portion of the turbine.

Specifically, the combustor liner (hereinafter simply referred to as "liner") provides a combustion space in which fuel injected by the fuel nozzle is mixed with compressed air of the compressor and combusted. The liner may include a flame cylinder providing a combustion space in which fuel mixed with air is burned, and a flow sleeve surrounding the flame cylinder to form an annular space. In addition, a fuel nozzle is coupled to the front end of the liner, and an ignition plug is coupled to the side wall.

On the other hand, a transition piece is connected to the rear end of the liner so as to send the combustion gas burned by the spark plug to the turbine side. The transition piece is cooled by compressed air supplied from the compressor by the outer wall so that damage due to high temperature of the combustion gas is prevented.

To this end, the transition piece is provided with holes for cooling so as to spray air therein, and compressed air flows to the liner side after cooling the main body therein through the holes.

In addition, the cooling air that cools the above-described transition piece flows in the annular space of the liner, and compressed air is provided from the outside of the flow sleeve to the cooling wall through cooling holes provided in the flow sleeve to collide. have.

The gas turbine illustrated in FIG. 1 is provided with a plurality of burners constituting the combustor 104 and is disposed in an annular shape along the periphery of the housing 102. The liner and the transition piece are connected to each burner in a pair, and the downstream end of the transition piece is fixed to the turbine section 120 to be described later to deliver high-temperature and high-pressure combustion gas.

Meanwhile, the high temperature and high pressure combustion gas from the combustor is supplied to the turbine section 120. As the supplied high-temperature and high-pressure combustion gas expands, a rotational torque is generated by impinging and reacting to a rotor blade of the turbine, and the rotational torque thus obtained is transmitted to the compressor section through the aforementioned torque tube and exceeds the power required to drive the compressor The effective power to be used is used to drive a generator or the like.

The turbine section is basically similar to the structure of the compressor section. That is, the turbine section 120 is also provided with a plurality of turbine rotor disks 180 similar to the compressor rotor disk of the compressor section. Accordingly, the turbine rotor disk 180 also includes a plurality of turbine blades 184 arranged radially. The turbine blade 184 may also be coupled to the turbine rotor disk 180 in a dovetail or other manner. In addition, a vane (not shown) fixed to the housing is provided between the blades 184 of the turbine rotor disk 180, and the vanes guide the flow direction of the combustion gas passing through the blades.

And, Figures 2 to 4 show the overall configuration of the mounting structure of the combustor nozzle 300 according to the present invention. However, FIGS. 3 and 4 only briefly show alternative configurations of the combustor nozzle 300 and the combustor burner, which relates to the “mounting structure” of the combustor nozzle 300 for the combustor burner. Therefore, in the description of the present invention, it is considered that a detailed illustration and description of unnecessary surroundings may interfere with the understanding of the present invention, and on the other hand, an analysis of the technical features of the present invention is shown. It is also to avoid the possibility of being limited to being applied only to the configuration of the nozzle 300 and the burner burner.

2 to 4, the present invention is a structure in which the combustor nozzle 300 is mounted on the body 400 of the combustor burner. Unlike the conventional art, the combustor nozzle 300 is provided on the combustor burner body 400. It is characterized by being mounted in a kind of floating state. That is, in the prior art, the combustor nozzle 300 has been mounted in a structure that is firmly fixed like a body without shaking to the body 400 of the combustor burner, whereas the present invention provides the combustor nozzle 300 to the combustor burner body 400. There is a difference in that it has a structure that is mounted to enable elastic relative motion.

Hereinafter, the present invention having the above characteristics will be described in detail.

At least one mounting hole 410 into which the combustor nozzle 300 is inserted is provided in the body 400 of the burner. In a large gas turbine combustor, each burner may be provided with 4 to 10 combustor nozzles 300. The diameter of the mounting hole 410 approximately corresponds to the outer diameter of the combustor nozzle 300, and various sealing means, such as an O-ring 460, are arranged on the interface with the combustor nozzle 300 to prevent backflow of combustion gas from the combustion chamber. It is also prevented.

In addition, the combustor nozzle 300 inserted and mounted in the mounting hole 410 is provided with at least two or more flanges 310 along its circumferential direction. The flange 310 is a part corresponding to a kind of bracket for fixing the combustor nozzle 300 to the body 400 of the burner nozzle, and protrudes in the radial direction of the combustor nozzle 300. Since the flange 310 is a place where the force for fixing the combustor nozzle 300 acts, it is preferable that a plurality of flanges 310 are disposed at an isometric angle along the circumferential direction in consideration of balance of power and airtightness therethrough. .

Here, the connection or coupling between the combustor nozzle 300 and the body 400 of the sequential burner is made through a combination of a bolt 430, a nut 450, and a spring 440.

The bolt 430 has one end fixed to the burner body 400 of the combustor, while the other end protrudes to the outside through the through hole 312 formed in the flange 310 of the combustor nozzle 300. Depending on the embodiment, the bolt 430 is composed of a stud bolt, and one end may be embedded in the burner burner body 400. When the combustor nozzle 300 is mounted, the through hole 312 of the flange 310 may be inserted into the mounting hole 410 of the combustor burner body 400 according to the other end of the bolt 430.

Here, the spring 440 is applied to the combustor burner body 400 and the flange 310 to apply elastic force by contacting both ends thereof. As shown in FIGS. 3 and 4, the spring 440 uses a bolt 430. It is arranged to wrap. Looking at this structure, it is understood that the bolt 430 serves as a guide for inducing movement or vibration of the combustor nozzle 300 and at the same time serves as a support for preventing buckling of the spring 440. Can.

Then, the nut 450 is screwed to the other end of the bolt 430 protruding through the through hole 312 of the flange 310. As the nut 450 is tightened, the force of the flange 310 pressing the spring 440 becomes stronger, so that the preload (preload) applied to the spring 440 can be adjusted according to the tightening degree of the nut 450. . 3 and 4, since the combustor nozzle 300 is mounted on the combustor burner body 400 in a floating structure supported by the elasticity of the spring 440, the combustor nozzle 300 The silver combustor can move elastically with respect to the burner body 400. In other words, since various vibrations transmitted to the combustor nozzle 300 through the combustor burner body 400 are attenuated by the spring 440, the combustor nozzle 300 can be protected from vibration. In addition, since the preload of the spring 440 can be changed according to the tightening degree of the nut 450, it is also possible to adjust the vibration characteristics of the combustor nozzle 300 by adjusting the tightening degree of the nut 450.

Depending on the embodiment, as shown in Figure 4, the spring 440 by interposing a plate-shaped plate 442 on the surface of both ends of the spring 440 contacting the combustor burner body 400 and the flange 310 It can also be configured to operate stably.

And, the elastic support structure such as the bolt 430 and the spring 440 may be completely exposed outside the combustor burner body 400, but a part of the elastic support structure, for example, the bolt 430, as shown in the drawing ), it is also possible to configure at least the bolt 430 and the spring 440 of the spring 440 and the nut 450 to be accommodated in the mounting space 420 formed in the combustor burner body 400. The mounting space 420 is formed by concave the space into which the elastic support structure can enter the combustor burner body 400. When the elastic support structure is buried in the combustor burner body 400, various foreign matters such as dust or oil are embedded. There is an advantage that it is possible to reduce the contamination problem caused by, and also does not need to increase the length of the combustor nozzle (300).

In addition, when forming the mounting space 420, the mounting space 420 and the mounting hole 410 are structurally isolated from each other, that is, the wall surface between the mounting space 420 and the mounting hole 410 as shown in FIG. 4. It may be nice to have this. This is advantageous in that the isolation of the mounting space 420 with respect to the mounting hole 410 connected to the combustion chamber is airtight, and the wall surface blocking between the mounting space 420 and the mounting hole 410, such as the O-ring 460, is also advantageous. This is because it can also be used as a structure for installing sealing means.

The nut 450 does not have a large force even when exposed to the outside, and may be desirable to be embedded in the burner burner body 400 if it is not inconvenient to adjust the tightening of the nut 450. In addition, in order to prevent the bolt 430 and the spring 440 from being almost exposed, it may be necessary to make the flange 310 of the combustor nozzle 300 enter the inside of the combustor burner body 400 to act as a kind of cover. In this case, as shown in FIG. 4, an incision 422 is formed in the inlet region of the mounting space 420 to accommodate the flange 310 of the combustor nozzle 300. The incision 422 is generally formed to have an appropriate depth so that the interference does not occur when the flange 310 moves according to the vibration of the combustor nozzle 300. Conversely, if the depth of the incision 422 is properly selected, It is also possible to make it act as a stopper.

On the other hand, in the illustrated structure, the spring 440 is a compression spring is suitable, in particular, a compression coil spring disposed to surround the bolt 430 may be applied. Here, as the coil spring, a non-linear coil spring in which the vibration width of the combustor nozzle 300 is changed non-linearly with respect to the intensity of external vibration may be applied. In a typical coil spring, the displacement of the spring with respect to the strength of the external force is proportional, and in a nonlinear coil spring, this relationship is not proportional. For example, the non-linear coil spring may move smoothly and largely with respect to low-frequency vibrations, but may have a slight movement characteristic when the frequency is high. Therefore, when the nonlinear coil spring is applied, the behavior of the combustor nozzle 300 according to the vibration frequency can be appropriately designed.

5 and 6 show an embodiment in which a non-linear coil spring is applied to the present invention, FIG. 5 is an example in which a conical coil spring 440-1 formed in a conical shape is applied, and FIG. 6 is a barrel-shaped coil formed in a barrel shape Spring 440-2 is an example applied. Since there are various other types of nonlinear coil springs, FIGS. 5 and 6 should be understood as some practical examples.

The above description is merely illustrative of the technical idea of the present invention, and those skilled in the art to which the present invention pertains may make various modifications and variations without departing from the essential characteristics of the present invention. Therefore, the embodiments disclosed in the present invention are not intended to limit the technical spirit of the present invention, but to explain, and the scope of the technical spirit of the present invention is not limited by these embodiments. The scope of protection of the present invention should be interpreted by the following claims, and all technical spirits within the equivalent range should be interpreted as being included in the scope of the present invention.

300: combustor nozzle 310: flange
312: through hole 400: burner burner body
410: mounting hole 420: mounting space
422: incision 430: bolt
440: spring
440-1: conical coil spring
440-2: Barrel coil spring
442: plate-shaped plate 450: nut

Claims (20)

A combustor nozzle having at least two flanges along the circumferential direction;
A combustor burner body having at least one mounting hole into which the combustor nozzle is inserted;
A bolt having one end fixed to the burner burner body and the other end projecting to the outside through a through hole formed in a flange of the burner nozzle;
A spring which is inserted so as to surround the bolt, and that both ends are in contact with the combustor burner body and the flange to apply elastic force; And
Includes a nut that is screwed to the other end of the bolt protruding through the through hole of the flange;
The combustor nozzle is elastically movable relative to the combustor burner body by the elasticity of the spring,
At least the bolts and springs of the bolts, springs, and nuts are accommodated in a mounting space formed in the combustor burner body, the mounting space is isolated from the mounting hole, and a flange of the combustor nozzle is provided at an inlet area of the mounting space. Mounting structure of the combustor nozzle, characterized in that the incision is formed to accommodate the. delete According to claim 1,
Mounting structure of the combustor nozzle, characterized in that the vibration characteristics of the combustor nozzle can be adjusted by adjusting the tightening degree of the nut. According to claim 1,
Combustor nozzle mounting structure, characterized in that a plate-shaped plate is interposed on both ends of the spring in contact with the combustor burner body and the flange. delete delete delete According to claim 1,
The spring is a compression coil spring, characterized in that the mounting structure of the combustor nozzle. The method of claim 8,
The coil spring is a non-linear coil spring mounting structure, characterized in that the vibration width of the combustor nozzle relative to the intensity of external vibration is changed nonlinearly. The method of claim 9,
The nonlinear coil spring is a conical coil spring, or a barrel coil spring. In the gas turbine comprising a combustor for generating a high-temperature combustion gas that expands by mixing and combusting compressed air with fuel in a compressor, and a turbine that generates power by receiving the combustion gas produced by the combustor,
The combustor,
A combustor nozzle having at least two flanges along the circumferential direction;
A combustor burner body having at least one mounting hole into which the combustor nozzle is inserted;
A bolt having one end fixed to the burner burner body and the other end projecting to the outside through a through hole formed in a flange of the burner nozzle;
A spring which is inserted so as to surround the bolt, and that both ends are in contact with the combustor burner body and the flange to apply elastic force; And
Includes a nut that is screwed to the other end of the bolt protruding through the through hole of the flange;
The combustor nozzle is elastically movable relative to the combustor burner body by the elasticity of the spring,
At least the bolts and springs of the bolts, springs, and nuts are accommodated in a mounting space formed in the combustor burner body, the mounting space is isolated from the mounting hole, and a flange of the combustor nozzle is provided at an inlet area of the mounting space. Gas turbine characterized in that the incision is formed to accommodate the. delete The method of claim 11,
Gas turbine, characterized in that by adjusting the tightening degree of the nut to adjust the vibration characteristics of the combustor nozzle. The method of claim 11,
Gas turbine, characterized in that a plate-shaped plate is interposed on both ends of the spring contacting the combustor burner body and the flange. delete delete delete The method of claim 11,
The spring is a gas turbine, characterized in that the compression coil spring. The method of claim 18,
The coil spring is a gas turbine, characterized in that the non-linear coil spring in which the vibration width of the combustor nozzle with respect to the intensity of external vibration changes nonlinearly. The method of claim 19,
The non-linear coil spring is a conical coil spring, or a gas turbine, characterized in that the barrel coil spring.

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