KR200491497Y1 - Injection testing device of gas turbine fuel nozzle - Google Patents

Abstract

The present invention relates to a gas turbine fuel nozzle injection test apparatus.
The gas turbine fuel nozzle injection test apparatus according to the present invention checks and manages internal defects or deformations of nozzles and injection characteristics of individual nozzles through an injection test on the gas turbine fuel nozzles, thereby instability of gas turbine combustion due to fuel nozzle defects By preventing the phenomenon in advance, it is possible to improve the reliability of the entire gas turbine facility.

Description

Injection test device of gas turbine fuel nozzle

The present invention relates to a gas turbine fuel nozzle injection test apparatus.

Specifically, the present invention confirms and manages the internal defects or deformation of the nozzle and the injection characteristics of individual nozzles through an injection test on the gas turbine fuel nozzle, thereby preventing instability of gas turbine combustion due to the fuel nozzle defect in advance. , For gas turbine fuel nozzle injection test device that can improve the reliability of the entire gas turbine installation.

In general, thermal power generation refers to power generation by converting thermal energy obtained by burning fossil fuels such as coal, oil, and gas into mechanical energy, and converting it back into electrical energy. Refers to the development of a method of operating a steam turbine with steam generated from a steam generator by sending exhaust gas to an exhaust heat recovery boiler through an exhaust duct.

In the thermal power generation method, power is generated by heating water with heat generated by burning fuel, and then steam is used to drive the steam turbine connected to the generator using this steam, and power generation that uses the internal combustion engine such as a diesel engine to drive the generator. And a power generation method using a gas turbine as a prime mover.

Among these thermal power generation or combined power generation methods, a turbine facility such as a steam turbine or a gas turbine is a device that generates electricity by converting thermal energy of a working medium into mechanical energy in a thermodynamic cycle using working steam or gas, and rotating the generator. Steam turbines and gas turbines are mainly used.

A steam turbine is an engine that converts the thermal energy of high-pressure steam into mechanical energy, and the principle of operation is to accelerate the steam flow by blowing and expanding high-temperature and high-pressure steam produced in a boiler from a nozzle or a fixed blade, and hitting a rotating blade. The revolving blade rotates due to the reaction, ultimately converting the rotational force generated into electrical energy.

In comparison, a gas turbine uses combustion gas instead of steam, and is a power generation facility that generates electricity using combustion gas of fuel.

The gas turbine for a power plant is a combined facility that uses natural gas and light oil. Compressed air is used when combusting liquid fuel such as diesel oil. At this time, the compressed air is atomized into small particles as air for high-speed spraying and atomized into small particles. To help complete combustion.

On the other hand, when burning natural gas, air is supplied to the liquid fuel passage to prevent flame stabilization and backfire, and it is generated by mixing and burning natural gas or light oil and air in the combustion chamber by inhaling the air through the air inlet and compressing it with a compressor. Power is generated by driving the gas turbine with the burnt gas.

Such a gas turbine is largely composed of an air compressor, a combustor, and a turbine. When air compressed at a high pressure in a compressor started by a separate power source enters the combustion chamber, fuel is injected from the combustion chamber and ignited to generate high-pressure combustion gas generated at that time. The rotor blades collide with the blades of the turbine and are converted into electrical energy using the rotational force generated by the rotation of the rotating blades.

In the gas turbine facility of such a power plant, a fuel nozzle for injecting fuel is installed in the combustion chamber. When the gas turbine is operated for a certain period of time, the nozzle of the nozzle may be caused by combustion gas generated by the operation of the gas turbine or foreign substances in the compressed air. There was a problem that the fuel injection amount of the nozzle was reduced because the flow path was reduced or blocked.

Regarding the problem of reducing the injection amount of the fuel nozzle, in the past, the state of the fuel nozzle was only visually inspected, and such a visual confirmation method could not properly check the presence or absence of deformation or deformation inside the injection nozzle.

In addition, although a fuel nozzle injection test apparatus has been partially disclosed, there is still a need to develop a device capable of checking the injection status of a plurality of fuel nozzles under various conditions, only by performing an injection test while a single fuel nozzle is fixed. Is emerging.

Republic of Korea Registered Utility Model Publication No. 20-0448437

The present invention provides a gas turbine fuel nozzle injection test device capable of checking and managing defects or deformations inside the gas turbine fuel nozzle, and injecting characteristics of individual nozzles, and proactively inspecting them.

In particular, the present invention provides a gas turbine fuel nozzle injection test apparatus designed to individually check the injection status of a plurality of fuel nozzles under various conditions.

The present invention has been devised to solve the above problems, and relates to a gas turbine fuel nozzle injection test apparatus.

The gas turbine fuel nozzle injection test apparatus comprises a frame unit; A pair of flange units; A pair of lever fixed type disc hand wheel units; A pair of worm reducer units; And a heavy-duty caster, and each angle of a gas turbine fuel nozzle coupled to the flat-faced flange is individually controlled by a user's individual motion for each handle included in the pair of lever fixed disk hand wheel units. It is designed to be adjustable.

The frame unit includes a frame formed by the combination of pipes having a predetermined shape, and first to third flange fixing support blocks that are fixed to the frame and fix the flange via a shaft, based on a central vertical frame It is divided into a first frame area and a second frame area.

The pair of flange units includes a flat face type flange and a shaft for a flange, and are respectively located in the first frame region and the second frame region.

The flat face type flange has an inner diameter and an outer diameter, and an inner hollow area is formed and is designed to be coupled to a gas turbine fuel nozzle including at least two bolt grooves.

The shaft for the flange is coupled to the thickness face of the flat face flange.

The pair of lever fixed type disc hand wheel units include a hand wheel, a shaft for a hand wheel, a housing, and a lever, and are located in the first frame region and the second frame region, respectively. The hand wheel includes a handle designed to be gripped by a user and a disk that is integrally rotated in combination with the handle and has a hollow in the center of the opposite side of the surface on which the handle is located, and the shaft for the hand wheel comprises The hollow portion formed on the disk is coupled to one end, the worm and the other end included in the worm reducer unit are coupled and rotated axially according to the rotation of the disk via the handle, and the housing protects the shaft for the hand wheel, The lever controls the rotation of the disk by controlling the rotation fixing bar and the rotation fixing bar having a rotation axis in a direction orthogonal to the rotation axis of the hand wheel shaft.

The pair of worm reducer units have an output torque in the range of 20 Nm to 30 Nm, a reduction ratio in the range of 10 to 30, and are coupled to the blocks for fixing the first and second flanges via brackets, respectively. .

The heavy load caster includes an adjustment portion, a wheel body and a wheel, and an allowable load is within a range of 2,500 N to 4,000 N. The adjusting portion is attached with a rubber adjustment pad and is designed with a combination of bolts and nuts, and the wheel body is designed to be fixedly attached to the bottom horizontal frame located on the lower surface of the frame unit, and the wheel is coupled to the wheel body And rotates.

In one example, the frame of the frame unit includes a bottom horizontal frame positioned at the bottom, first and second side vertical frames positioned at the side ends of the first and second frame regions, and a central vertical frame positioned at the center. , And a first horizontal connection frame that connects the first and second side vertical frames and the center vertical frame and is located in a direction in which the spray nozzle rotates, and the first and second side vertical frames and the center vertical frame. It may include a second horizontal connection frame that is connected and located in the opposite direction to the direction in which the injection nozzle rotates. In this case, the first horizontal connection frame is positioned to satisfy Equation 1 below, and the second horizontal connection frame is It can be positioned to satisfy the following Equation 2.

[Equation 1]

L1 ² + L2 ² > R1 ²

In Equation 1, L1 means the width direction distance from the rotation shaft of the flange shaft to the end of the frame unit, and L2 means the height direction distance from the top of the frame unit horizontal to the rotation shaft of the flange shaft to the first horizontal connection frame. R1 is the maximum turning radius of the gas turbine fuel nozzle:

[Equation 2]

L1 ² + L3 ² > R2 ²

In Equation 2, L1 means the width direction distance from the rotation shaft of the flange shaft to the end of the frame unit, and L3 means the height direction distance from the top of the frame unit horizontal to the rotation shaft of the flange shaft and the second horizontal connection frame. R2 means the minimum turning radius of the gas turbine fuel nozzle.

In one example, the first and second flange fixing support blocks are respectively located on top of the first and second side vertical frames, and shaft support grooves and worm reducers designed to be positioned at either end of the shaft for the flanges Each of the bolt grooves that can be coupled to the bracket for fixing the unit may be included, and the third flange fixing support block may be located at the top of the central vertical frame, and the opposite end of either end of the shaft for the flange may be interpolated. It may include a through-hole to enable.

In one example, the flat-faced flange may further include a rubber gasket located on a surface in contact with the gas turbine fuel nozzle.

The gas turbine fuel nozzle injection test apparatus according to the present invention may also further include a pair of digital inclinometers attached to each of the flange shafts included in the pair of flange units.

The gas turbine fuel nozzle injection test apparatus according to the present invention can effectively check and manage the internal defects or deformation of the fuel nozzle and the injection characteristics of the individual nozzles, and check in advance.

The gas turbine fuel nozzle injection test apparatus according to the present invention is designed to individually check the injection conditions of a plurality of fuel nozzles under various conditions, so that the injection characteristics under various injection conditions can be individually checked for each fuel nozzle. There is an advantage.

Of course, the effect of the present invention is not limited to the above-mentioned range.

1 is a perspective view of a gas turbine fuel nozzle injection test apparatus according to the present invention.
2 is a view for explaining the structure of the frame unit according to the present invention in more detail.
3 is a view for explaining the structure of the flange unit according to the present invention in more detail.
4 is a view for explaining in more detail the structure of the lever fixed disk hand wheel unit according to the present invention.
5 is a view for explaining the structure of the heavy-duty caster according to the present invention in more detail.
6 is a view for explaining in more detail the position of the first and second horizontal connection frame in the frame unit according to the present invention.

Hereinafter, the present invention will be described in more detail with reference to the drawings and examples.

In this specification, a singular expression includes a plural expression unless otherwise specified.

The terms used in the present specification, while considering the functions in the present invention, selected general terms that are currently widely used as possible, but may vary according to intentions or precedents of a person skilled in the art or the appearance of new technologies. Also, in certain cases, some terms are arbitrarily selected by the applicant, and in this case, their meaning will be described in detail in the description of the corresponding design. Therefore, the term used in the present invention should be defined based on the meaning of the term and the overall contents of the present design, not just the name of the term.

Since the embodiments of the present invention can apply various transformations and have various embodiments, specific embodiments will be illustrated in the drawings and described in detail in the detailed description. However, it is not intended to limit the scope of the specific embodiments, it should be understood to include all conversions, equivalents, or substitutes included in the scope of the designed idea and technology. In describing the embodiments, when it is determined that the detailed description of the related known technology may obscure the subject matter, the detailed description is omitted.

In the present specification, terms such as first and second may be used to describe various components, but the components should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from other components.

In this specification, terms such as “comprise” or “consist of” are intended to indicate that a feature, number, step, operation, component, part, or combination thereof described in the specification exists, or one or more other. It should be understood that features or numbers, steps, operations, components, parts, or combinations thereof are not excluded in advance.

Hereinafter, a gas turbine fuel nozzle injection test apparatus according to the present invention will be described in detail with reference to the accompanying drawings.

1 is a perspective view of a gas turbine fuel nozzle injection test apparatus according to the present invention.

As shown in Figure 1, the gas turbine fuel nozzle injection test apparatus according to the present invention, the frame unit 100; A pair of flange units 200 a, b; A pair of lever fixed disk hand wheel units 300 a, b; A pair of worm reducer units 400 a, b; And a flat face type flange by a user's individual operation for each of the handles 301 a and b included in the pair of lever fixed disk hand wheel units 300 a and b, including a caster 500 for heavy loads. It is designed to individually adjust the angles of the gas turbine fuel nozzles 600 a and b coupled to 201 a and b).

The frame unit 100 performs a role of a structure in which each component in the gas turbine fuel nozzle injection test apparatus is coupled and supported. As shown in FIG. 2, the frame 101 is formed by coupling pipes having a predetermined shape. ) And a first to third flange fixing support block (102, 103, 104) fixedly coupled to the frame 101 and fixed to the flange via a shaft, the first frame area (relative to the central vertical frame 108) A) and the second frame area (B).

The frame unit 100 may be formed of, for example, a unit frame formed of a combination of round or square pipes, and may have a cuboid cube structure as a whole.

When the structure of the frame in the frame unit 100 is described in more detail, the frame of the frame unit 100 includes a bottom horizontal frame 105 positioned at a bottom portion; First and second side vertical frames 106 and 107 located at side ends; And a central vertical frame 108 located in the central portion.

Further, the frame in the frame unit 100 includes first and second connecting frames 109 and 110 connecting the first and second side vertical frames 106 and 107 and the central vertical frame 108 in the longitudinal direction. can do.

Specifically, the first connection frame 109 may be a frame positioned in a direction in which the injection nozzle rotates, and the second connection frame 110 may be a frame positioned in a direction opposite to the direction in which the injection nozzle rotates. The first and second connecting frames 109 and 110 may serve to secure structural rigidity and stability of the entire frame unit by fixing and connecting the vertical frames 106, 107, and 108 of the frame unit 100 to each other.

On the other hand, since the first connection frame 109 is a frame positioned in the direction in which the injection nozzle rotates, it is positioned lower than the second connection frame 110 so that the nozzle tip does not interfere with the frame structure when the injection nozzle rotates. can do.

Furthermore, the first connection frame 109 and the second connection frame 110 may be positioned to satisfy the relationship between the maximum and minimum rotational radii of the injection nozzle and the following equations 1 and 2, respectively.

[Equation 1]

L1 ² + L2 ² > R1 ²

In Equation 1, L1 means the width direction distance from the rotation shaft of the flange shaft to the end of the frame unit, and L2 means the height direction distance from the top of the frame unit horizontal to the rotation shaft of the flange shaft to the first horizontal connection frame. R1 is the maximum turning radius of the gas turbine fuel nozzle:

[Equation 2]

L1 ² + L3 ² > R2 ²

In Equation 2, L1 means the width direction distance from the rotation shaft of the flange shaft to the end of the frame unit, and L3 means the height direction distance from the top of the frame unit horizontal to the rotation shaft of the flange shaft and the second horizontal connection frame. R2 means the minimum turning radius of the gas turbine fuel nozzle.

More specifically, that the first connection frame 109 is positioned to satisfy Equation 1, as shown in FIG. 6A, is the square of the width direction distance L1 from the rotating shaft of the flange shaft to the end of the frame unit. The nozzle tip at the center of the fuel nozzle, which is the sum of the squares of the height direction distance (L2) from the top of the frame unit which is horizontal to the axis of rotation of the shaft for the flange and the first horizontal connecting frame 109, is the maximum turning radius of the gas turbine fuel nozzle This means that it is located in the frame 101 so that it is greater than the square of the distance to the end, and this is a gas coupled to the flat face flange by the user's individual motion for each handle included in the lever fixed disc hand wheel unit. Despite the rotation of the turbine fuel nozzle, it may mean that the tip of the nozzle tip is not interfered by the first connection frame 109.

In addition, the second connection frame 110 is positioned to satisfy the above Equation 2, as shown in FIG. 6B, the square of the width direction distance L1 from the rotational shaft of the flange shaft to the end of the frame unit and the plan From the center of the fuel nozzle, which is the minimum rotation radius (R2) of the gas turbine fuel nozzle, where the sum of the squares of the height direction distance (L3) from the top of the frame unit which is horizontal to the axis of rotation of the paper shaft to the second horizontal connection frame is from the center of the fuel nozzle to the end of the fuel supply. This means that it is located on the frame 101 so that it is greater than the square of the distance, which is a gas turbine fuel nozzle coupled to the flat face flange by the user's individual motion for each handle included in the lever fixed disk hand wheel unit. In spite of the rotation, it may mean that the fuel supply end is not interfered by the second connection frame 110.

As described above, when the first and second connecting frames 109 and 110 are positioned in the frame 101 so as to satisfy Equations 1 and 2, damage or interference of the nozzle caused by the frame can be prevented.

The frame unit 100 includes first to third flange fixing blocks 102, 103, and 104 fixedly coupled to the frame 101 and fixing the flange through the shaft.

  The first and second flange fixing support blocks 102 and 103 have the same shape or shape, and are positioned at both ends of the frame to serve to fix and support the ends of the flange shaft.

Specifically, the first and second flange fixing support blocks 102 and 103 are located on top of the first and second side vertical frames 106 and 107, respectively, as shown in FIG. Each of the may include a shaft support groove designed to be located and a bolt groove to enable coupling of the bracket for fixing the worm reducer unit. Therefore, the worm reducer unit 400 a, b may be coupled to the first and second flange fixing support blocks 102 and 103 via the bracket for fixing the worm reducer unit fixed through the bolt fastened to the bolt groove. have.

 The third flange fixing block 104 is located at the center of the frame and serves to support and fix each of the flanges included in the flange unit to the frame, and includes a through hole through which the shaft of the flange unit can be interpolated. can do.

In one example, the third flange fixing support block 104 is located at the top of the central vertical frame 108, the first and second flange fixing support block 104 of the support shaft of the flange for fixing fixed to the support groove It may include a through hole that allows either end of the opposite end to be interpolated. One end of each of the shafts for flanges in the flange units 200 a and b existing in each of the first frame region A and the second frame region B may be located in the through hole.

Bearings may be fastened to the through holes of the first and second flange fixing support blocks 102 and 103 and the third flange fixing support block 104 for smooth rotation of the flange shaft.

The frame unit 100 is divided into a first frame area A and a second frame area B based on the central vertical frame 108. The first frame area (A) and the second frame area (B) have a pair of flange units (200a, b), a pair of lever fixed disk hand wheel units (300a, b), and a pair of worm reducer units (400a). , b) and gas turbine fuel nozzles, respectively. Meanwhile, the area sizes of the first frame area A and the second frame area B may be substantially the same.

The size of the frame unit 100 may be, for example, in the range of 800 mm to 1500 mm in width, in the range of 300 mm to 800 mm in width, and in the range of 600 mm to 1,000 m in height. It is not limited thereto.

The gas turbine fuel nozzle injection test apparatus also includes a pair of flange units 200a and b. The pair of flange units 200a and b are respectively located in the first frame region A and the second frame region B.

As shown in Figure 3, the pair of flange units (200a, b) has a predetermined inner diameter and outer diameter of the inner hollow region is formed and includes at least two or more bolt grooves gas turbine fuel nozzle is coupled It includes a flat face-type flange 201 and a flange shaft 202 for coupling to the thickness of the flat face-type flange 201, respectively.

The flange units 200a and b are coupled and fixed to the frame unit 100 in a state where the gas turbine fuel nozzle is fastened, and thus serve to induce rotation and injection angle changes of the gas turbine fuel nozzle through the shaft.

The flange units 200a and b include a flat face flange 201 and a flange shaft 202, as shown in FIG.

The flat face-type flange 201 has an inner hollow region with a predetermined inner diameter and outer diameter, and is designed to be coupled to a gas turbine fuel nozzle including at least two bolt grooves.

In one example, the flat face type flange 201 may be a carbon steel flange having an inner diameter in the range of 300 mm to 350 mm, an outer diameter in the range of 360 mm to 450 mm, and formed in the inner hollow region.

The flat face type flange 201 includes at least two or more bolt grooves. Specifically, as shown in FIG. 3, the flat face type flange 201 preferably includes four bolt grooves.

A gas turbine fuel nozzle is coupled and fixed on the flat face type flange 201 via a bolt, and the top of the flat face type flange 201 may include a configuration such as a rubber gasket to minimize damage to the fuel nozzle.

In one example, the flat-faced flange 201 may further include a rubber gasket located on a surface in contact with the gas turbine fuel nozzle.

The shaft 202 for the flange of the thickness face of the flat face type flange 201 is coupled. As shown in FIG. 3, the shaft 202 for the flange has one end coupled to the worm reducer units 400a and b. The first flange shaft 202a and one end may be formed of a second flange shaft 202b coupled to a through hole of the third flange fixing support block 104. The first flange shaft 202a and the second flange shaft 202b have different configurations coupled at their ends, and their lengths may also be different from each other. Specifically, the first flange shaft 202a may have a longer length than the second flange shaft 202b.

The shaft 202 for the flange can be fixed by using a method such as welding to the flat face type flange 201 after individual production, but this is only an example, and various coupling fixing methods can be used without limitation. .

The material or material of the flange shaft 202 is not particularly limited, and may be manufactured using the same carbon steel material as the flat face type flange 201.

The gas turbine fuel nozzle injection test apparatus also includes a pair of lever fixed disk hand wheel units 300a and b. The pair of lever fixed type disc hand wheel units 300a and b are individually positioned in the first frame area A and the second frame area B, respectively.

The lever fixed type disc hand wheel unit (300a, b) includes a circular disc, a handle attached to the disc, and a shaft coupled to the disc, to advance the movement of the worm to the worm reducer and the rotational force of the worm gear engaged with the worm By providing, and providing a rotational force to the shaft 202 for the flange included in the flange unit (200a, b), it is a configuration that ultimately performs the axial rotation of the gas turbine fuel nozzle and the angle change accordingly.

As shown in Figure 4, the lever fixed disk hand wheel unit (300a, b) is combined with the handle 3011 and the handle 3011 designed to be gripped by the user, rotates integrally and the handle 3011 is located Hand wheel 301 including a disc 3012 having a hollow portion at the center of the opposite side of the surface, and a hollow portion formed at the disc 3012 of the hand wheel 301 is coupled to one end and the worm reducer units 400a, b The worm and the other end included in the housing, the shaft 302 for the hand wheel rotating axially according to the rotation of the disk 3012 via the handle 3011, the housing 303 and the hand protecting the shaft 302 for the hand wheel It includes a stopper 304 including a rotation fixing bar having a rotation axis in a direction orthogonal to the rotation axis of the wheel shaft 302 and a lever for controlling rotation of the disk 3012 by controlling the rotation fixing bar.

The lever fixed disc hand wheel unit 300a, b includes a hand wheel 301 including a handle 3011 and a disc 3012.

The size of the disk 3012 in the hand wheel 301 may be, for example, an aluminum material having a diameter in the range of 100 mm to 250 mm, but is not limited thereto.

The lever fixed type disc hand wheel unit 300a, b is a lever fixed type, and the rotation fixing bar of the hand wheel shaft 302 and the stopper 304 may be orthogonal to each other, and as the user rotates the lever When the shaft 302 for the hand wheel is fixed by the rotation fixing bar, the rotation and angle of the gas turbine fuel nozzle via the worm reducer units 400a and b may be maintained in a stopped state.

The housing 303 that protects the shaft 302 for the hand wheel may be, for example, an aluminum material that has been subjected to post-treatment such as anodizing to enhance its surface strength.

The stopper 304 is a lever-type stopper 304 including a rotation fixing bar and a lever, and may serve to induce rotation and angular stop of the gas turbine fuel nozzle.

The gas turbine fuel nozzle injection test apparatus also includes a pair of worm reducer units 400a and b. The pair of worm reducer units 400a and b have output torques in the range of 20 Nm to 30 Nm, reduction ratios in the range of 10 to 30, and blocks for fixing the first and second flanges via brackets. Respectively.

The worm reducer units 400a and b include a worm gear engaged with the worm and a housing or a gearbox protecting the worm gear, and the shaft for the hand wheel (because the worm is simultaneously engaged with the shaft 302 for the worm gear and the hand wheel) According to the rotation of 302), it is possible to provide a rotational force to the worm gear, and ultimately, it is possible to perform axial rotation of the gas turbine fuel nozzle and change of the angle accordingly.

The worm reducer unit 400 a, b used in the present invention is, in particular, the hand wheel unit 300 a, b considering the weight of the gas turbine fuel nozzle coupled to the flange unit 200 a, b and the flange unit 200 a, b. ) It should be used to have an output torque and a reduction ratio to smoothly change the angle according to the operation.

Specifically, the worm reducer units 400a and b should have an output torque in the range of 20 Nm to 30 Nm, and a reduction ratio in the range of 10 to 30, preferably an output torque of 25 Nm to 30 Nm It is preferably within the range, and the reduction ratio is in the range of 15 to 25, more preferably, the output torque is 29 Nm, and the reduction ratio is more preferably 20.

In another example, the worm reducer unit 400a, b also has an input radial load (Fr1) in the range of 150 N to 250 N, and an output radial load (Fr2) from 1,200 N to It can be in the range of 1,500 N.

In another example, the worm reducer unit 400a, b has an input power in the range of 0.40 kW to 0.60 kW, and an out put speed (n2) in the range of 100 rpm to 200 rpm. You can.

The gas turbine fuel nozzle injection test apparatus also includes a heavy duty caster 500. The heavy-duty caster 500 is a wheel designed to be fixedly attached to a bottom adjustment frame 501, which is a rubber material adjustment pad and is designed with a combination of bolts and nuts, and a bottom horizontal frame 105 located at the bottom of the frame unit 100. It includes a body 502 and a wheel 503 coupled to the wheel body 502 and rotating. In addition, the heavy load caster 500 has an allowable load in the range of 2,500 N to 4,000 N.

The caster 500 used in the present invention is provided with an adjustment unit 501 and a wheel 503 to be movable while supporting the weight of the frame unit 100, the flange unit 200, and the gas turbine fuel nozzle. It serves to make the test device move by control.

Particularly, the caster 500 used in the present invention is for heavy loads, and the allowable load should be within the range of 2,500 N to 4,000 N. Only when the caster 500 within the allowable load range is used, supportability and mobility are supported. It can be secured at the same time.

The caster 500, as shown in FIG. 5, includes an adjustment unit 501, a wheel body 502, and a wheel 503.

The adjustment unit 501 is a rubber adjustment pad is attached and is designed by a combination of bolts and nuts. For example, a special neoprene rubber adjustment pad is attached and a vertical support formed in the longitudinal direction by a combination of bolts and nuts. And it may be made of a horizontal support that is coupled to the vertical support and located on the bottom surface.

The wheel body 502 is designed to be fixedly attached to the bottom horizontal frame 105 positioned on the lower surface of the frame unit 100, and serves to connect and support the adjustment unit 501 and the wheel 503. The wheel body 502 may be made of, for example, steel plate hot commercial (SPHC) surface-treated with trivalent chromium, but is not limited thereto.

The wheel 503 is a mixture of special reinforced plastic and nylon and is axially fixed to the wheel body 502.

The heavy load caster 500 has an allowable load in the range of 2,500 N to 4,000N, and preferably an allowable load in the range of 2,700 N to 4,000N or 2,900N to 4,000N.

The heavy load caster 500 may be located at four edges of the bottom horizontal frame 105 positioned at the bottom of the frame unit 100, but is not limited thereto, as shown in FIG. The location is not limited as long as it does not impair the purpose of securing ease.

Gas turbine fuel nozzle injection test apparatus according to the present invention is the angle of the gas turbine fuel nozzle coupled to the flat-faced flange by the user's individual motion for each handle included in the pair of lever fixed disk hand wheel unit It is designed to be individually adjustable.

In particular, the gas turbine fuel nozzle injection test apparatus according to the present invention can individually adjust the rotation angle of the gas turbine fuel nozzles located in each of the first frame region (A) and the second frame region (B), thereby injecting under various conditions There is an advantage that the test can be performed.

Specifically, the gas turbine fuel nozzle injection test apparatus according to the present invention connects each supply pipe of a fluid or compressed air, such as water or diesel, to each of the two fuel nozzles, which are fixedly coupled on a flange, via a manifold, Since the injection angle of the fuel nozzle can be adjusted by rotating the handle while adjusting the flow rate through a flow rate controller or the like, there is an advantage of performing an injection test under various flow rate and injection angle conditions.

The gas turbine fuel nozzle injection test apparatus according to the present invention may further include an inclinometer to visually confirm the angle of the gas turbine fuel nozzle.

Specifically, the gas turbine fuel nozzle injection test apparatus according to the present invention further includes a pair of digital inclinometers (not shown) attached to each of the flange shafts 202 included in the pair of flange units 200. You can.

As further comprising a digital inclinometer as described above, there is an advantage that it is possible to more easily perform the injection condition check of the gas turbine fuel nozzle according to the hydraulic condition and the inclined condition.

In the above, the gas turbine fuel nozzle injection test apparatus according to the present invention has been shown in accordance with the detailed description and drawings, but this is merely an example, and various changes and changes are within the scope of the technical idea of the present invention. It is possible.

100: frame unit
101: frame
102: block for fixing the first flange
103: second flange fixing support block
104: third flange fixed support block
105: bottom horizontal frame
106: first side vertical frame
107: second side vertical frame
108: center vertical frame
109: 1st connection frame
110: second connection frame
A: 1st frame area
B: second frame area
200a, b: flange unit
201: Flat face type flange
202: flange shaft
202a, b: Shaft for flanges 1 and 2
300a, b: lever fixed disc hand wheel unit
301: hand wheel
3011: handle
3012: disk
302: shaft for hand wheel
303: housing
304: stopper
400 a, b: Wim reducer unit
500: caster
501: Adjusting unit
502: wheel body
503; Wheel

Claims (5)

A frame formed by the coupling of a pipe having a predetermined shape, and a first to third flange fixing support block that is fixed to the frame and fixedly supports the flange through a shaft, and includes a first frame based on a central vertical frame A frame unit divided into a region and a second frame region;
An inner hollow area is formed with a predetermined inner diameter and outer diameter, and a flat face type flange designed to be coupled to a gas turbine fuel nozzle including at least two bolt grooves and a plan coupled to the thickness face of the flat face type flange A pair of flange units each including a shaft for paper, and individually positioned in the first frame region and the second frame region;
A hand wheel comprising a handle designed to be gripped by a user and a disk having a hollow portion in the center of the opposite side of the surface on which the handle is located, combined with the handle and integrally rotating, and once formed with the hollow portion formed on the disc of the hand wheel The combined worm and the other end included in the worm reducer unit, the shaft for a hand wheel that rotates according to the rotation of the disk via the handle, a housing for protecting the shaft for the hand wheel, and a shaft for rotating the shaft for the hand wheel A stopper including a rotation fixing bar having a rotation axis in an orthogonal direction and a lever for controlling rotation of the disk by controlling the rotation fixing bar, and a pair of levers respectively located in the first frame region and the second frame region Fixed disk hand wheel unit;
A pair of worm gear units having an output torque in the range of 20 Nm to 30 Nm, a reduction ratio in the range of 10 to 30, and coupled to the first and second flange fixing support blocks via brackets, respectively; And
An adjustment pad of rubber material is attached and designed by a combination of a bolt and a nut, a wheel body designed to be fixedly attached to a bottom horizontal frame located on a lower surface of the frame unit, and a wheel coupled to the wheel body and rotating, Heavy duty caster with a permissible load in the range of 2,500 N to 4,000 N; includes,
Gas turbine fuel nozzles designed to individually adjust the angles of the gas turbine fuel nozzles coupled to the flat-faced flange by the user's individual operation of each of the handles included in the pair of lever fixed disk hand wheel units. Injection test device. According to claim 1,
The frame of the frame unit,
Bottom horizontal frame located at the bottom, first and second side vertical frames at the side ends of the first and second frame regions, center vertical frame at the center, and the first and second side vertical frames respectively And a first horizontal connection frame that connects the central vertical frame and is located in a direction in which the injection nozzle rotates, and a direction opposite to a direction in which the first and second side vertical frames and the central vertical frame are connected and the injection nozzle rotates. It includes a second horizontal connection frame located on,
The first horizontal connection frame is positioned to satisfy Equation 1 below, and the second horizontal connection frame is located to satisfy Equation 2: Gas turbine fuel nozzle injection test device:
[Equation 1]
L1 ² + L2 ² > R1 ²
In Equation 1, L1 means the width direction distance from the rotation shaft of the flange shaft to the end of the frame unit, and L2 means the height direction distance from the top of the frame unit horizontal to the rotation shaft of the flange shaft to the first horizontal connection frame. R1 is the maximum turning radius of the gas turbine fuel nozzle:
[Equation 2]
L1 ² + L3 ² > R2 ²
In Equation 2, L1 means the width direction distance from the rotation shaft of the flange shaft to the end of the frame unit, and L3 means the height direction distance from the top of the frame unit horizontal to the rotation shaft of the flange shaft to the second horizontal connection frame. R2 is the minimum turning radius of the gas turbine fuel nozzle. According to claim 2,
The first and second flange fixing block,
Each of the first and second side vertical frames is located at the top, and includes a shaft support groove designed to be located at one end of the shaft for the flange and a bolt groove for coupling the bracket for fixing the worm reducer unit,
The third flange fixing support block,
Gas turbine fuel nozzle injection test apparatus which is located at the top of the central vertical frame and includes a through hole through which the opposite end of either end of the shaft for the flange can be interpolated. According to claim 3,
The flat face flange,
Gas turbine fuel nozzle injection test device further comprises a rubber gasket located on the surface of the gas turbine fuel nozzle contact. The method of claim 4,
Gas turbine fuel nozzle injection test apparatus further comprises a pair of digital inclinometer attached to each of the shaft for the flange included in the pair of flange units.

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