WO2016093429A1 - Swirler assembly - Google Patents

Abstract

A swirler assembly comprises: a base plate; and a plurality of vanes which are arranged apart from each other along the circumferential direction of the base plate, wherein each of the vanes is provided with a gas fuel accommodating portion for storing gas fuel, a gas fuel spray port for spraying the gas fuel to the outside, a liquid fuel accommodating portion for storing liquid fuel, and a liquid fuel spray port for spraying the liquid fuel to the outside, wherein an end portion of the vane that is adjacent to the circumference of the base plate has a curved shape.

Description

Swirler assembly

Embodiments of the present invention relate to a swirler assembly, and more particularly to a swirler assembly of a gas turbine combustor for premixing fuel and air.

A gas turbine is a heat engine that operates a turbine with high-temperature and high-pressure combustion gases, and generally consists of a compressor, a combustor, and a turbine. The air is first compressed by a compressor, which is then premixed with the compressed high-pressure air and the fuel supplied from the fuel system in a pre-chamber to lower the flame temperature and inject the fuel inside the main chamber. Burn the air mixture. The turbine is rotated by expanding the high-temperature and high-pressure gas while blowing out the turbine. At this time, a swirler is used to evenly distribute the uniform fuel-air mixture in the combustion chamber in order to burn fuel efficiently and quickly.

In other words, the swirler facilitates the combustion reaction of the fuel-air mixture by allowing the compressed air and fuel to be mixed quickly and uniformly, and when the mixing degree of the fuel-air mixture supplied to the flame becomes uneven, The part with high flame temperature is generated and the emission of NOx is high. Since nitrogen oxide is one of the main causes of air pollution, strict emission standards are being applied worldwide.

Embodiments of the present invention provide a swirler assembly with improved mixing performance between air and fuel.

Embodiment according to an aspect of the present invention, the base plate; And a plurality of vanes disposed on one surface of the base plate extending in a direction transverse to the center of the base plate, and spaced apart from each other along the circumferential direction of the base plate. And a gas fuel receiving portion for storing the gas fuel introduced from the gas fuel inlet formed on the one surface, and a gas fuel injection hole extending radially from the gas fuel receiving portion toward the wall surface of the vane so that the gas fuel is injected to the outside. And a liquid fuel container for storing the liquid fuel introduced from the liquid fuel inlet formed on the one surface of the base plate, and radially from the liquid fuel container to the wall surface of the vane so that the liquid fuel is injected to the outside. Has an extended liquid fuel nozzle, Group end of the vane adjacent the outer periphery of the base plate provides a swirler assembly having a curved shape.

In the present embodiment, the vanes may be disposed spirally on the one surface of the base plate.

In this embodiment, air may be introduced into the space between the vanes adjacent to the outer circumference of the base plate.

In the present embodiment, the vane may have a front end portion having the curved shape and a rear end portion connected to the front end portion and having a width that decreases in the longitudinal direction of the vane.

In the present embodiment, the gaseous fuel is injected from the gaseous fuel injection port into the space between the adjacent vanes, and the liquid fuel may be injected from the liquid fuel injection port into the space between the adjacent vanes. have.

In the present embodiment, the gas fuel receiving portion may be formed in the front end portion, the liquid fuel receiving portion may be formed in the rear end portion.

In the present embodiment, the gas fuel receiving portion and the liquid fuel receiving portion may be formed to a height lower than the overall height of the vane.

In the present embodiment, the volume of the gas fuel containing portion may be larger than the volume of the liquid fuel containing portion.

In the present embodiment, the angle of the gas fuel injection port formed radially around the gas fuel receiving portion may be 270 degrees or less.

In the present embodiment, at least one gas fuel injection hole may be disposed at the front end portion to extend along the center line in the longitudinal direction of the vane.

In the present embodiment, a plurality of gas fuel injection holes are formed on the wall surface of the front end portion to be connected to the gas fuel receiving portion, a plurality of the liquid fuel injection holes are formed on the wall surface of the rear end portion to be connected to the liquid fuel receiving portion Can be.

In the present embodiment, the gas fuel injection port may be arranged to form a plurality of layers on the wall surface of the front end portion along the height of the vane.

In the present embodiment, the angle of the liquid fuel injection port formed radially around the liquid fuel receiving portion may be 90 degrees or less.

In the present embodiment, a groove portion may be formed at an end portion of the rear end portion facing the center of the base plate.

In the present embodiment, the groove portion may be formed in the height direction of the vane at the end of the rear end portion.

In the present embodiment, the liquid fuel injection port may be disposed at least one groove.

In the present embodiment, the gas fuel injection port and the liquid fuel injection port may be arranged to be symmetrical with respect to the center line in the longitudinal direction of the vane.

In the present exemplary embodiment, a cover plate disposed to cover the vanes may face the base plate.

In the present embodiment, a penetrating portion penetrating the cover plate in the thickness direction of the cover plate may be formed in the center of the cover plate.

In the present embodiment, the mixture of the gaseous fuel, the liquid fuel and air may pass through the through portion of the cover plate.

Embodiments of the present invention can supply fuel uniformly on the air flow path.

In addition, embodiments of the present invention can secure a sufficient time required for mixing between air and fuel by advancing the fuel supply time.

In addition, embodiments of the present invention can improve the mixing performance between air and fuel by increasing the residence time of the fuel-air mixture in the preburner.

1 is a perspective view schematically showing a swirler assembly according to an embodiment of the present invention.

FIG. 2 is an exploded view schematically showing a portion of a gas turbine having the swirler assembly of FIG. 1.

3 is a cross-sectional view of air and fuel supplied to the swirler assembly of FIG. 1 viewed from a direction crossing the Z-axis direction.

4 is a perspective view schematically illustrating the vanes of the swirler assembly of FIG. 1.

5 is a cross-sectional view of the vane of the swirler assembly of FIG. 1 viewed in a direction crossing the Z-axis direction.

6 is a cross-sectional view of the fuel flow of the swirler assembly according to the comparative example viewed in a direction crossing the Z-axis direction.

The invention will become apparent with reference to the embodiments described below in detail in conjunction with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but may be implemented in various forms. It is provided to fully convey the scope of the invention to those skilled in the art, the invention being defined only by the scope of the claims. Meanwhile, the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. In the present specification, the singular also includes the plural unless specifically stated otherwise. As used herein, “comprises” and / or “comprising” refers to the presence of one or more other components, steps, operations, and / or elements. Or does not exclude additions. 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 only used to distinguish one component from another.

1 is a perspective view schematically showing a swirler assembly according to an embodiment of the present invention.

FIG. 2 is an exploded view schematically showing a portion of a gas turbine having the swirler assembly of FIG. 1.

Referring to FIG. 1, the swirler assembly 200 includes a base plate 210 and a plurality of vanes 230 spaced apart from one surface of the base plate 210.

Referring to FIG. 2, the swirler assembly 200 may be disposed between the burner 204 and the combustors 205 and 206.

The base plate 210 may be coupled to the burner 204. In this case, fuel may be supplied to the plurality of vanes 230 to be described later through the base plate 210 from the burner 204. The base plate 210 may have a shape of a disc, but is not necessarily limited thereto. The material of the base plate 210 is not limited to a specific material, but a material resistant to heat and pressure may be used.

The base plate 210 supports the plurality of vanes 230.

The plurality of vanes 230 may be disposed on one surface of the base plate 210 extending in the direction transverse to the center O of the base plate 210. As shown in FIG. 2, the vanes 230 may be disposed. The burner 204 may be coupled to the opposite side of the disposed surface.

The plurality of vanes 230 may be spaced apart along the circumferential direction of the base plate 210. In this case, each of the plurality of vanes 230 may be disposed in a spiral shape on one surface of the base plate 210. For example, when the base plate 210 has a shape of a disc, the direction in which the space between the adjacent vanes 231 and 232 is formed may be formed to have a predetermined angle with respect to the radial direction of the base plate 210. Can be. Since the plurality of vanes 230 are disposed in a spiral manner, the strength of turning the mixture of air and fuel to be described later into the center O of the base plate 210 is increased, thereby allowing the mixture to be preburner 205. The residence time at is also longer, so that the mixing performance of the mixture can be improved.

In the drawing, each of the plurality of vanes 230 is illustrated to be disposed in a spiral toward the center O of the base plate 210, but is not necessarily limited thereto. That is, each of the plurality of vanes 230 may be disposed radially toward the center O of the base plate 210.

Meanwhile, compressed air may be introduced from a compressor (not shown) into a space between adjacent vanes 231 and 232 from an outer circumference of the base plate 210. The air here is mixed with the fuel supplied from the burner 204 and this mixture produces a high temperature, high pressure gas to be sent to a turbine (not shown) while continuously passing through the preburner 205 and the main combustor 206. . Hereinafter, the manner in which the compressed air and fuel are supplied to the swirler assembly 200 will be described in more detail.

3 is a cross-sectional view of air and fuel supplied to the swirler assembly of FIG. 1 viewed from a direction crossing the Z-axis direction.

The portion X shown in FIG. 3 represents a space between adjacent vanes 231 and 232 and adjacent vanes 231 and 232. Referring to part X of FIG. 3, air is introduced into a space between adjacent vanes 231 and 232, and gas fuel G and liquid fuel L are supplied to the space.

In particular, the liquid fuel L is supplied from a hole formed in the wall surface of the vane 231 like the gas fuel G. Furthermore, each of the vanes 230 has a shape in which a portion of the vanes 230 is curved. Hereinafter, the shape of the vane 231 and the arrangement of the fuel supply unit formed in the vane 231 will be described.

4 is a perspective view schematically illustrating the vanes of the swirler assembly of FIG. 1.

5 is a cross-sectional view of the vane of the swirler assembly of FIG. 1 viewed in a direction crossing the Z-axis direction.

4 and 5, one of the ends 231a and 231b of the vane 231, the end 231a adjacent to the outer circumference of the base plate 210 may have a curved shape. That is, the vane 231 may have a front end portion 231a having a curved shape and a rear end portion 231b connected to the front end portion 231a and decreasing in width in the longitudinal direction of the vane 231. . The shape of each of the front end portion 231a and the rear end portion 231b may be symmetrical with respect to the longitudinal center line of the vane 231.

3 to 5, each of the vanes 230 may include a gas fuel container 240, a gas fuel injection port 260, a liquid fuel container 250, and a liquid fuel injection port 270. have.

Referring to FIG. 3, the gas fuel G and the liquid fuel L each have a space between the vanes 231 and 232 adjacent from the gas fuel injection port 260 and the liquid fuel injection port 270, that is, air passes. It can be injected into the passage. At this time, the liquid fuel (L) is sprayed on the downstream side of the air flow path than the gas fuel (G), so that the flow of air flowing upstream of the air flow path is not hindered by the liquid fuel (L).

The gaseous fuel receiver 240 may be formed at the front end 231a of the vane 231, and the liquid fuel receiver 250 may be formed at the rear end 231b of the vane. At this time, the gas fuel receiving portion 240 and the liquid fuel receiving portion 250 is formed to a height lower than the overall height of the vanes 231. As a result, the fuel temporarily stored in each of the fuel receivers 240 and 250 may be prevented from leaking to the outside.

In addition, the volume of the gaseous fuel accommodating part 240 may be larger than the volume of the liquid fuel accommodating part 250. If the inflow of the liquid fuel (L) is increased, the flow rate of air and gaseous fuel (G) is caused, so that the volume of the liquid fuel receiving portion 250 smaller than the volume of the gas fuel receiving portion 240 to accommodate the liquid fuel It is necessary to adjust the supply amount of the unit 240. In this case, the gas fuel receiving unit 240 and the liquid fuel receiving unit 250 may be formed in parallel to each other inside the vane 231, but is not necessarily limited thereto.

On the other hand, the gas fuel receiving unit 240 may store the gas fuel (G) introduced from the gas fuel inlet 241 formed on one surface of the base plate 210. That is, the gaseous fuel G may be temporarily stored in the gaseous fuel receiving unit 240 before being injected into the space between the adjacent vanes 231 and 232. In this case, the gas fuel inlet 241 is connected to the burner 204 shown in FIG. 2 to supply the gas fuel G from the burner 204 to the gas fuel receiving unit 240.

A plurality of gas fuel injection holes 260 may be formed on the wall surface of the front end portion 231a of the vane 231 to be connected to the gas fuel receiving portion 240.

The gas fuel injection hole 260 may be formed to extend radially from the gas fuel receiving portion 240 toward both side walls of the vanes 231. As a result, the gas fuel G temporarily stored in the gas fuel receiving unit 240 may be injected to the outside of the vane 231 through the gas fuel injection hole 260.

Referring to FIG. 5, an angle θ of the gas fuel injection hole 260 radially formed around the gas fuel receiving part 240 may be 270 degrees or less. That is, the gaseous fuel (G) can be injected in a relatively wide range.

In particular, at least one gaseous fuel injection hole 260 may be disposed at the front end portion 231a to extend along the longitudinal center line of the vane 231. Here, the gas fuel injection hole 260 is disposed so as to correspond to the center line, which means that the gas fuel injection hole 260 is disposed at the most curved portion of the front end portion 231a of the vane 231. In this way, by arranging the gas fuel injection port 260 in the most curved portion of the front end portion 231a, the gas fuel (G) can be supplied from the time when air is introduced from the outside. Thus, the mixing time between air and fuel is further increased.

The gas fuel injection hole 260 may be arranged to form a plurality of layers on the wall surface of the front end portion 231a along the height of the vane 231. As the number of gas fuel injection holes 260 increases, the uniformity of the fuel supply may be further improved. In addition, as the number of the gas fuel injection holes 260 increases, the mixing time between the air and the fuel may be sufficiently secured by actively inducing the generation of the recirculation zone to be described later.

Meanwhile, a plurality of liquid fuel injection holes 270 may be formed on the wall surface of the rear end portion 231b of the vane 231 so as to be connected to the liquid fuel container 250.

The liquid fuel receiver 250 may store the liquid fuel L introduced from the liquid fuel inlet 251 formed on one surface of the base plate 210. That is, the liquid fuel L may be temporarily stored in the liquid fuel accommodating part 250 before being injected into the space between the adjacent vanes 231 and 232. In this case, the liquid fuel inlet 251 may be connected to the burner 204 shown in FIG. 2 similarly to the gas fuel inlet 241.

The liquid fuel injection hole 270 may be formed to extend radially from the liquid fuel receiving portion 250 toward both wall surfaces of the vanes 231. As a result, the liquid fuel L may be temporarily stored in the liquid fuel accommodating part 250 and then injected to the outside of the vane 231 through the liquid fuel injection hole 270.

Referring to FIG. 5, an angle α of the liquid fuel injection hole 270 formed radially around the liquid fuel receiving part 250 may be about 90 degrees or less. That is, the liquid fuel (L) may be injected in a relatively narrow range compared to the gas fuel (G).

In particular, as shown in FIG. 4, the groove 280 may be formed at the end of the rear end 231b of the vane 231. That is, the groove 280 may be formed at an end portion of the base plate 210 toward the center O. As shown in FIG.

The groove 280 may be formed at the end of the rear end 231b in the height direction of the vane 231, and may be formed at some of the sharp edges of the end of the rear end 231b.

At least one of the liquid fuel injection holes 270 may be disposed in the groove 280. That is, the groove portion 280 is a flat portion formed at the sharp edge of the rear end portion 231 b so as to easily arrange the liquid fuel injection hole 270 at the rear end portion 231 b, and the liquid fuel injection hole 270 disposed at the groove portion 280. ) May be disposed at the rear end 231b to extend along the longitudinal centerline of the vane 231. Accordingly, by forming the groove 280 in the rear end 231b and arranging the at least one liquid fuel injection hole 270 in the groove 280, the liquid fuel L can be stably supplied without disturbing the air flow. Can be.

On the other hand, the gas fuel injection port 260 and the liquid fuel injection port 270 formed on the wall surface of the vane 231 may be arranged to be symmetrical with respect to the longitudinal center line of the vane 231. Therefore, the fuel supply to the air flow through the space between the adjacent vanes 231 and 232 can be made uniform by the angle and the position at which the fuel is injected from the respective fuel inlets 260 and 270.

Hereinafter, the aspect of the flow of the air and fuel mixture will be described in more detail.

Gas fuel (G), liquid fuel (L) and air are mixed in the space between the adjacent vanes 231, 232 to produce a fuel-air mixture near the center O of the base plate 210. do. As a result, the fuel can be supplied from the upstream of the air flowing into the swirler assembly 200, thereby sufficiently securing the time required for mixing the air and the fuel.

Referring back to FIG. 1, the swirler assembly 200 may further include a cover plate 290. The cover plate 290 may be disposed to cover the vanes 230 to face the base plate 210. The shape and material of the cover plate 290 may be the same as the shape and material of the base plate 210 described above, but is not limited thereto.

A through part 291 penetrating the cover plate 290 may be formed at the center of the cover plate 290. The penetrating portion 291 penetrates the cover plate 290 in the thickness direction of the cover plate 290. In this case, the penetrating portion 291 may have various shapes such as a circle, a polygon, and the like.

Meanwhile, the above-described gas fuel G, liquid fuel L, and a mixture of air may pass through the penetrating portion 291 of the cover plate 290. That is, the fuel-air mixture generated while passing through the space between adjacent vanes 231 and 232 passes through the through portion 291 to exit the swirler assembly 200.

In particular, as described above, the space between the adjacent vanes 231 and 232 is formed in a spiral shape on one surface of the base plate 210 so that the gas fuel (G), the liquid fuel (L) introduced from the space, and The mixture of air may produce a swirl flow F that rotates about the Z-axis direction shown in FIG. 1. As such, the linearly introduced air in the swirler assembly 200 forms the swirl flow F, thereby slowing the flow rate of the air and increasing the reaction surface area between the air and the fuel. This may facilitate the combustion reaction in the combustor.

Hereinafter, the relationship between the aforementioned recirculation region and the shape of the vane 231 will be described in detail.

6 is a cross-sectional view of the fuel flow of the swirler assembly according to the comparative example viewed in a direction crossing the Z-axis direction.

Referring to FIG. 6, gaseous fuel flow I is injected from the outer end of the vane 131, that is, the end adjacent to the outer circumference of the base plate 110.

A substantial portion of the gaseous fuel flow I injected from the vanes 131 is directed to the space between adjacent vanes 131, 132. However, some of the gaseous fuel flow I changes to the vortex R near the outer end of the vane 131 to form a recirculation zone. This recirculation zone not only increases the mixing time between air and fuel, but also helps to form a continuous and stable ignition.

Here, for convenience of description, suppose that the swirler assembly 100 according to the comparative example has a vane 131 having a simple triangular prism shape.

If a flash back occurs while driving the swirler assembly 100, the flame is attached to the flat wall surface of the outer end of the vane 131 to melt the swirler vane 131. Melting of the swirler vane 131 remains a serious defect that significantly reduces the efficiency and performance of the gas turbine.

Therefore, it is important to increase the recirculation area to improve the mixing performance between air and fuel, while minimizing the possibility of flame attachment at the end of vane 131, which may be a problem when backfire occurs.

In the present invention, as shown in FIG. 3, the front end portion 231a of the vane 231 in which the recycle region is formed has a curved shape. As described above, as the front end portion 231a of the vane 231 has a curved shape, the contact area between the vortex R in the recirculation region and the wall surface of the front end portion 231a is reduced, so that the flame is placed on the wall surface of the vane 231. The risk of attachment can be significantly reduced.

As described above, embodiments of the present invention can supply fuel uniformly to the air flow path.

In addition, embodiments of the present invention can secure a sufficient time required for mixing between air and fuel by advancing the fuel supply time.

In addition, embodiments of the present invention can improve the mixing performance between air and fuel by increasing the residence time of the fuel-air mixture in the preburner.

Although the present invention has been described in connection with the above-mentioned preferred embodiments, it is possible to make various modifications or variations without departing from the spirit and scope of the invention. Therefore, the scope of the appended claims will be provided with such modifications and variations as long as they fall within the spirit of the invention.

The present invention relates to a swirler assembly and may be applied to a swirler assembly of a gas turbine combustor that premixes fuel and air.

Claims (20)

Base plate; And And a plurality of vanes disposed on one surface of the base plate extending in a direction transverse to the center of the base plate and spaced apart along the circumferential direction of the base plate. Each of the vanes, A gas fuel receiving portion storing gas fuel introduced from a gas fuel inlet formed on the one surface of the base plate, and a gas extending radially from the gas fuel receiving portion toward the wall surface of the vane so that the gas fuel is injected to the outside; With a fuel inlet, A liquid fuel container for storing the liquid fuel introduced from the liquid fuel inlet formed on the one surface of the base plate, and extending radially from the liquid fuel container to the wall surface of the vane so that the liquid fuel is injected to the outside; With liquid fuel injection port, And an end of the vane adjacent to the outer circumference of the base plate has a curved shape. The method of claim 1, And the vanes are spirally disposed on the one surface of the base plate. The method of claim 1, And a swirler assembly through which air is introduced into a space between the vanes adjacent to each other from the outer circumference of the base plate. The method of claim 1, The vane is a swirler assembly having a front end having the curved shape, the rear end is connected to the front end and the width decreases toward the longitudinal direction of the vane. The method of claim 1, The gas fuel is injected into the space between the adjacent vanes from the gas fuel injection port, And a swirler assembly in which the liquid fuel is injected into the space between the adjacent vanes from the liquid fuel injection port. The method of claim 4, wherein The gas fuel receiving portion is formed in the front end portion, the liquid fuel receiving portion is a swirler assembly formed in the rear end. The method of claim 1, And the gaseous fuel container and the liquid fuel container are formed at a height lower than the overall height of the vane. The method of claim 1, A swirler assembly having a volume of said gaseous fuel receptacle greater than a volume of said liquid fuel receptacle. The method of claim 1, The gas fuel injection port is a swirler assembly of which the angle formed radially around the gas fuel receiving portion is less than 270 degrees. The method of claim 6, And at least one gaseous fuel injection hole is disposed at the front end portion to extend along the longitudinal center line of the vane. The method of claim 6, And a plurality of gas fuel injection holes are formed on a wall surface of the front end portion to be connected to the gas fuel receiving portion, and a plurality of liquid fuel injection holes are formed on a wall surface of the rear end portion to be connected to the liquid fuel receiving portion. The method of claim 11, The gas fuel injection hole is arranged to form a plurality of layers on the wall surface of the front end portion along the height of the vane. The method of claim 1, The angle of the liquid fuel injection port formed radially around the liquid fuel receiving portion is less than 90 degrees swirler assembly. The method of claim 6, A swirler assembly having a groove formed at an end of the rear end facing the center of the base plate; The method of claim 14, The groove portion is a swirler assembly formed in the height direction of the vane at the end of the rear end. The method of claim 15, And at least one liquid fuel injection hole is disposed in the groove portion. The method of claim 1, And the gas fuel injection hole and the liquid fuel injection hole are arranged to be symmetrical with respect to the longitudinal center line of the vane. The method of claim 1, And a cover plate disposed to cover the vanes to face the base plate. The method of claim 18, A swirler assembly formed at a central portion of the cover plate to penetrate the cover plate in a thickness direction of the cover plate; The method of claim 19, A swirler assembly through which the mixture of the gaseous fuel, the liquid fuel, and air passes through the through portion of the cover plate.

Images