KR102138016B1 - Combustor with axial fuel staging and gas turbine including the same - Google Patents

Abstract

The present invention provides a combustor and a gas turbine including the same, wherein the combustor has an axial fuel staging system in which a fuel/air mixture is injected at stages spaced apart in two axial directions, increases a degree of mixing of fuel and air in an injector into which a secondary fuel/air mixture is injected, and can prevent flashback.

Description

Combustor with an axial fuel staging system and a gas turbine comprising the same {COMBUSTOR WITH AXIAL FUEL STAGING AND GAS TURBINE INCLUDING THE SAME}

The present invention relates to a combustor and a gas turbine including the same, and more particularly, to have an axial fuel staging system in which a fuel/air mixture is injected in two axially spaced stages, and a secondary fuel / It relates to a combustor and a gas turbine including the same that improves the mixing degree of fuel and air in an injector in which an air mixture is injected and prevents flashback.

In general, a turbine is a machine that converts the energy of a fluid such as water, gas, steam, etc. into mechanical work. Usually, several feathers or wings are planted on the circumference of a rotating body, and steam or gas is blown therein to impulse or reaction force. A turbo type machine that rotates is called a turbine.

The types of turbines include hydro turbines using energy of high water, steam turbines using energy of steam, air turbines using energy of high pressure compressed air, and gases using energy of high temperature and high pressure gas. And turbines.

In general, a gas turbine is a type of internal combustion engine that converts thermal energy into mechanical energy by injecting and rotating a high-temperature, high-pressure combustion gas generated by combustion after mixing fuel with compressed air at high pressure in a compressor.

Since these gas turbines do not have a reciprocating mechanism such as a piston of a four-stroke engine, there is no mutual friction part such as a piston-cylinder, so the consumption of lubricant is extremely small, the amplitude characteristic of reciprocating machines is greatly reduced, and high-speed motion is possible. There are advantages.

A gas turbine is a basic element, a compressor that compresses air, a compressor that generates compressed gas by burning compressed air and fuel supplied from the compressor, and a turbine that generates power by rotating the blades through high-temperature and high-pressure gas emitted from the combustor It includes.

The combustion state generated in the combustor is an isothermal heating process, which raises the combustion gas temperature to a temperature that the turbine metal can withstand. The combustor reacts with high temperature and high pressure air from the compressor with fuel to have high energy, and this turbine Corresponds to the part that serves to drive the turbine by passing on it.

In some combustors, the production of combustion gases takes place in stages spaced in two axial directions. Such combustors are said to include a "axial fuel staging (AFS)" system that delivers fuel and oxidant to one or more fuel injectors downstream of the combustor's head end. In a combustor with an AFS system, a primary fuel nozzle at the upstream end of the combustor injects fuel and air (or fuel/air mixture) axially into the primary combustion zone. Then, the AFS fuel injector located downstream of the primary fuel nozzle injects fuel and air (or secondary fuel/air mixture) into the secondary combustion zone downstream of the primary combustion zone as cross-flow. Cross-flow generally traverses the flow of combustion products from the primary combustion zone. Axial staged injection increases the likelihood of complete combustion of available fuel, which in turn reduces air pollution emissions.

In some cases, it is desirable to introduce fuel and air as a mixture into the secondary combustion zone. Accordingly, the mixing ability of the AFS injector affects the overall operating efficiency and/or exhaust gas of the gas turbine.

Also, when injecting the secondary fuel/air mixture through the AFS injector, a problem may occur in which the secondary fuel/air mixture flashback is caused by the flow of combustion products from the primary combustion zone.

U.S. Patent Publication No. 2018-0135531 (published May 17, 2018)

The present invention has an axial fuel staging system in which a fuel/air mixture is injected in two axially spaced stages, and the degree of mixing of fuel and air in an injector in which a secondary fuel/air mixture is injected The object is to provide a gas turbine including a combustor and a gas burner capable of improving and preventing flashback.

The technical problem to be achieved by the present invention is not limited to the technical problems mentioned above, and other technical problems not mentioned can be clearly understood by those skilled in the art from the following description. There will be.

An embodiment of the present invention for solving the above problems, a liner defining a combustion chamber, a transition piece coupled to the rear end of the liner, and a flow sleeve and the liner spaced apart to surround the liner and the transition piece Or is disposed along the circumferential direction of the transition piece, and includes at least one injector for injecting a mixture of fuel and air, the injector being radially through the liner and the flow sleeve or through the transition piece and the flow sleeve simultaneously. It provides a combustor comprising an injection pipe that is extended and a plurality of vanes disposed along a circumferential direction on an inner surface of the injection pipe so that an empty space is formed in the center of the injection pipe.

According to an embodiment of the present invention, further comprising a fuel plenum disposed to surround the injection pipe, the injector is provided inside each vane, a plurality of fuel communication passages in fluid communication with the fuel plenum And a plurality of first fuel ports formed in each vane to inject fuel from the fuel communication passage to the outside of the vane.

According to an embodiment of the present invention, a fuel supply flow path extending along an axial direction of the flow sleeve may be further included to supply fuel to the fuel plenum.

According to an embodiment of the present invention, each vane is provided with a plurality of first fuel ports, and the plurality of first fuel ports can be provided with at least one of each of the vanes facing each other.

According to an embodiment of the present invention, the injector may further include a plurality of second fuel ports formed in the injection pipe to inject fuel from the fuel plenum into the interior of the injection pipe.

According to an embodiment of the present invention, the plurality of second fuel ports may be arranged to be provided with at least one between the plurality of vanes.

According to an embodiment of the present invention, the injection tube may be formed of a cylindrical tube.

According to an embodiment of the present invention, the injector may further include a center body provided at the center of the injection pipe to guide a mixture of fuel and air passing through the plurality of vanes to the center of the injection pipe. have.

According to an embodiment of the present invention, an end portion of the center body to which a mixture of fuel and air that has passed through the plurality of vanes is guided may have a cone shape.

According to an embodiment of the present invention, the center body may contact the inner end of the plurality of vanes.

According to an embodiment of the present invention, at least a portion of the injection pipe may be formed to be narrower in width toward the liner or transition piece from the flow sleeve side.

According to an embodiment of the present invention, the end portion of the injection pipe may be formed with the same slope corresponding to the end shape of the center body.

According to an embodiment of the present invention, the injector is provided with at least one communication hole communicating the outside and the inside, forming a constant volume (volume) inside the damper coupled to cover the upper portion of the injection pipe It may further include.

According to an embodiment of the present invention, the injector is slidably coupled to the communication hole, and may further include a cylinder having a through passage through the inside.

According to an embodiment of the present invention, a plurality of injectors are disposed along the circumferential direction of the liner or transition piece, and at least some of the angles each injector forms with the tangent line of the liner or transition piece may be different from each other. Can.

In addition, an embodiment of the present invention for solving the above problems, a compressor for inhaling air and compressing it at high pressure, and mixing and burning compressed air and fuel in the compressor to produce high-temperature, high-pressure combustion gas A gas turbine comprising a combustor and a turbine that generates power by obtaining rotational force by the combustion gas delivered from the combustor. The combustor may include the embodiments described above.

According to the present invention, premixed combustion of fuel and air is achieved in the primary combustion zone of the combustor, and fuel and air mixtures are directly injected through the injector into the secondary combustion zone of the combustor located downstream of the primary combustion zone. As a result, the nitrogen oxide (NOx) emission level of the gas turbine may be reduced.

At this time, the injector for injecting the fuel and air mixture into the secondary combustion zone includes a plurality of vanes arranged along the circumferential direction to improve the mixing ability of the fuel and air and at the same time to generate a strong flow in the center of the injector. have. Accordingly, it is possible to prevent flashback from being caused by the flow of combustion products from the primary combustion zone.

In addition, according to the embodiment, the injector is formed to be narrower as it gets closer to the secondary combustion zone, so that the central flow of the fuel and air mixture injected into the secondary combustion zone can be strengthened and the speed can be increased, so that backfire is more It can be effectively prevented.

It should be understood that the effects of the present invention are not limited to the above-described effects, and include all effects that can be deduced from the configuration of the invention described in the detailed description or claims of the present invention.

1 is a view showing a gas turbine according to an embodiment of the present invention.
2 is a view showing a combustor included in the gas turbine of FIG. 1.
Figure 3 is a view showing a state viewed from section AA of Figure 2;
FIG. 4 is an enlarged view of a portion of the injector according to the first embodiment of FIG. 2.
5 is a view showing the injector of FIG. 4 as viewed from above.
6 is a view showing an injector portion according to a second embodiment of the present invention.
FIG. 7 is a view of the injector of FIG. 6 as viewed from above.
8 is a view showing an injector part according to a third embodiment of the present invention.
9 is a view showing an injector portion according to a fourth embodiment of the present invention.

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

In addition, terms to be described later are terms defined in consideration of functions in the present invention, which may vary according to a user's or operator's intention or practice, and the following embodiments do not limit the scope of the present invention, but rather the scope of the present invention. It is only exemplary of the components presented in the claims.

In order to clearly describe the present invention, parts irrelevant to the description are omitted, and the same reference numerals are assigned to the same or similar elements throughout the specification. Throughout the specification, when a part “includes” a certain component, this means that other components may be further provided, not excluding other components, unless specifically stated to the contrary.

First, a configuration of a gas turbine according to an embodiment of the present invention will be described with reference to FIGS. 1 and 2.

Gas turbine (1) according to an embodiment of the present invention, the casing 10, the compressor 20 for compressing high pressure by sucking air, and the air compressed by the compressor 20 and the fuel It may include a combustor 30 for mixing and combustion, and a turbine 40 that generates electric power by obtaining rotational force by the combustion gas transmitted from the combustor 30.

The casing 10 includes a compressor casing 12 in which the compressor 20 is accommodated, a combustor casing 13 in which the combustor 30 is accommodated, and a turbine casing 14 in which the turbine 40 is accommodated. can do. Here, the compressor casing 12, the combustor casing 13 and the turbine casing 14 may be sequentially arranged from the upstream side to the downstream side in the fluid flow direction.

A rotor (center axis; 50) is rotatably provided inside the casing 10, a generator (not shown) is interlocked with the rotor 50 for power generation, and the turbine is located on the downstream side of the casing 10. A diffuser for discharging the combustion gas passing through the 40 may be provided.

The rotor 50 is accommodated in the compressor rotor disk 52 accommodated in the compressor casing 12, the turbine rotor disk 54 accommodated in the turbine casing 14, and the combustor casing 13, and the compressor Tie rod (53) connecting the rotor disc (52) and the turbine rotor disc (54), the compressor rotor disc (52), the torque tube (53) and the tie rod for fastening the turbine rotor disc (54) 55) and a fixing nut (56).

The compressor rotor disk 52 is formed in a plurality (for example, 14 sheets), and the plurality of compressor rotor disks 52 may be arranged along the axial direction of the rotor 50. That is, the compressor rotor disk 52 may be formed in multiple stages. Further, each of the compressor rotor disks 52 is formed in a substantially disc shape, and a compressor blade coupling slot coupled with a compressor blade 22 to be described later may be formed on the outer circumference.

The turbine rotor disk 54 may be formed similarly to the compressor rotor disk 52. That is, the turbine rotor disk 54 may be formed in plural, and the plurality of turbine rotor disks 54 may be arranged along the axial direction of the rotor 50. That is, the turbine rotor disk 54 may be formed in multiple stages. In addition, each of the turbine rotor disk 54 is formed in a substantially disk shape, the outer peripheral portion may be formed with a turbine blade coupling slot coupled to the turbine blade 42 to be described later.

The torque tube 53 is a torque transmission member for transmitting the rotational force of the turbine rotor disk 54 to the compressor rotor disk 52, one end of which is the highest in the flow direction of air among the plurality of compressor rotor disks 52. Compressed with the compressor rotor disk located at the downstream end, the other end of the plurality of turbine rotor disk 54 may be engaged with the turbine rotor disk located at the uppermost end in the flow direction of the combustion gas. Here, protrusions are formed at one end and the other end of the torque tube 53, and grooves engaged with the protrusions are formed at each of the compressor rotor disk 52 and the turbine rotor disk 54, so that the torque tube Relative rotation of the 53 with respect to the compressor rotor disk 52 and the turbine rotor disk 54 can be prevented.

Further, the torque tube 53 may be formed in a hollow cylinder shape so that air supplied from the compressor 20 can flow through the torque tube 53 and flow to the turbine 40. At this time, the torque tube 53 is strongly formed, such as deformation and warping, due to the characteristics of the gas turbine that is continuously operated for a long period of time, and can be easily assembled and disassembled for easy maintenance.

The tie rod 55 is formed to penetrate a plurality of the compressor rotor disk 52, the torque tube 53 and the plurality of turbine rotor disk 54, one end of which is a plurality of the compressor rotor disk 52 Based on the turbine rotor disc which is fastened in the compressor rotor disc positioned at the uppermost stage in the flow direction of the heavy air, and the other end of the plurality of turbine rotor discs 54 located at the downstream stage in the flow direction of the combustion gas. It protrudes to the opposite side of the compressor 20 and can be engaged with the fixing nut 56.

Here, the fixing nut 56 pressurizes the turbine rotor disc 54 located at the lowermost stage toward the compressor 20, and the compressor rotor disc 52 located at the uppermost stage and the lowermost stage. As the spacing between the positioned turbine rotor disks 54 is reduced, a plurality of the compressor rotor disks 52, the torque tube 53 and the plurality of turbine rotor disks 54 are axial in the rotor 50 Can be compressed. Accordingly, axial movement and relative rotation of the plurality of compressor rotor discs 52, the torque tube 53, and the plurality of turbine rotor discs 54 can be prevented.

On the other hand, in the case of this embodiment, one of the tie rods is formed to penetrate through the center of the plurality of compressor rotor disks, the torque tube, and the plurality of turbine rotor disks, but is not limited thereto. That is, separate tie rods may be provided on the compressor side and the turbine side, and a plurality of tie rods may be radially disposed along the circumferential direction, and mixing of these is possible.

The rotor 50 according to this configuration may be rotatably supported at both ends by a bearing, and one end may be connected to the drive shaft of the generator.

The compressor 20, the compressor vane (24) installed in the compressor casing (12) to align the flow of air flowing into the compressor blade (22) and the compressor blade (22) rotated with the rotor (50) ).

The compressor blade 22 is formed in plural, the plural compressor blades 22 are formed in plural stages along the axial direction of the rotor 50, and the plural compressor blades 22 are provided for each stage. It may be formed radially along the rotation direction of the rotor 50.

That is, the root portion 22a of the compressor blade 22 is coupled to the compressor blade coupling slot of the compressor rotor disc 52, and the root portion 22a has the compressor blade 22 coupled to the compressor blade coupling slot. It can be formed in the form of a fir (tree), so as to prevent the rotor 50 from being separated in the radial direction of rotation. At this time, the compressor blade coupling slot may likewise be formed in a fir shape to correspond to the root portion 22a of the compressor blade.

In the present embodiment, the compressor blade root portion 22a and the compressor blade coupling slot are formed in a fir shape, but are not limited thereto, and may be formed in a dove tail shape or the like. Alternatively, the compressor blade may be fastened to the compressor rotor disk by using a fastener such as a key or bolt other than the above-mentioned type.

Here, the compressor rotor disk 52 and the compressor blade 22 are typically combined in a tangential type or an axial type. In the present embodiment, the compressor blade root portion 22a ) Is formed in a so-called axial type that is inserted along the axial direction of the rotor 50 into the compressor blade coupling slot as described above. Accordingly, the compressor blade coupling slots according to the present embodiment may be formed in plural, and the plurality of compressor blade coupling slots may be radially arranged along the circumferential direction of the compressor rotor disk 52.

The compressor vanes 24 may be formed in plural, and the plural compressor vanes 24 may be formed in plural stages along the axial direction of the rotor 50. Here, the compressor vane 24 and the compressor blade 22 may be alternately arranged along the air flow direction. In addition, the plurality of compressor vanes 24 may be formed radially along the rotational direction of the rotor 50 for each stage.

The combustor 30 mixes and combusts the air flowing from the compressor 20 with fuel to produce high-temperature, high-temperature, high-pressure combustion gas, and burns to a heat-resistant limit that the combustor and the turbine can withstand through a constant pressure combustion process. It can be formed to increase the gas temperature.

Specifically, the combustor 30 is formed in a plurality, the plurality of combustors 30 may be arranged along the rotational direction of the rotor 50 in the combustor casing.

Combustor 30 of the present invention is the first fuel / air mixture is injected and ignited in the primary combustion zone of the combustor to create the main flow of high energy combustion gas, the second fuel / air mixture is from the primary combustion zone It has an axial fuel staging system that is injected and ignited in a secondary combustion zone located downstream. This is also called a multi-stage injection system or a late-lean injection system. The second fuel/air mixture of the subsequent stage in the axial direction is injected into the main flow of high energy combustion gas and mixed with the main flow, which will be discussed in detail below.

Each combustor 30 has a liner 100 through which compressed air flows from the compressor 20, and a transition piece 200 located at the rear of the liner 100 to guide combustion gas to the turbine 40. ). The liner 100 forms a combustion chamber 120 therein, and a flow sleeve 300 is disposed to surround the liner 100 and the transition piece 200 to form an annular flow space therebetween.

In addition, each combustor 30 is provided with a plurality of nozzle assemblies 400 for mixing the compressed air and fuel supplied from the compressor 20, the nozzle assembly 400 is the liner 100 of the Combined in the front. An end plate 420 is coupled to the front of the combustor casing 13 or the flow sleeve 300, the nozzle assembly 400 is supported by the end plate 420, and the combustor can be sealed.

Accordingly, it is limited by the combustor casing 13 through a plurality of flow holes 320 formed in the flow sleeve 300 from the receiving space 302 receiving compressed air discharged from the compressor 20 Compressed air (combustion air) may be introduced into the annular flow path 140 between the liner 100 and the flow sleeve 300. As described above, compressed air flowing into the annular flow path 140 between the liner 100 and the sleeve 300 flows to the front of the combustor to reach the end plate 420 and then switches in the opposite direction to switch the nozzle assembly 400. That is, compressed air flowing from the compressor 20 is injected into the combustion chamber 120 while being mixed with fuel through the nozzle assembly 400, and in the combustion chamber 120, by an ignition plug (not shown) It ignites and burns.

At this time, the liner 100 may at least partially define a primary combustion zone 102 for burning the first fuel/air mixture injected by the nozzle assembly 400, in the axial direction of the combustor. It would be possible to define a secondary combustion zone 104 that is formed downstream from the primary combustion zone 102.

The combustor 30 further includes an injector 500 for injecting a second fuel/air mixture into the secondary combustion zone 104, corresponding to a subsequent step in the axial direction.

The injector 500 is disposed downstream of the nozzle assembly 400 in the axial direction of the combustor, and upstream of the turbine 40, and a plurality of injectors 500 can be used in a single combustor 30. In this embodiment, the injector 500 is disposed on the rear end of the liner 100, but is not limited thereto, and may be disposed on the front end or the rear end of the transition piece 200. .

The plurality of injectors 500 are spaced apart along the circumferential direction of the liner 100, and in this embodiment, the plurality of injectors 500 are provided in a single plane, but are not limited thereto, and have two or more axes It may be formed in a plurality of planes spaced in the direction. The injector 500 extends radially through the liner 100 and the flow sleeve 300 to provide fluid communication between the receiving space 302 and the combustion chamber 120. That is, the injector 500 is formed to extend in a direction transverse to the flow of compressed air in the annular flow path 140.

Part of the compressed air discharged from the compressor 20 and received in the receiving space 302 is introduced into the injector 500 and mixed with fuel, and then into the combustion chamber 120, that is, the secondary combustion zone 104 ). The second fuel/air mixture injected by the injector 500 is mixed with the hot combustion gas burned in the primary combustion zone 102. The injector 500 will be described in detail below.

At this time, cooling the liner 100 and the transition piece 200 exposed to high temperature and high pressure combustion gas is an important part for increasing the durability of the combustor. To this end, compressed air flows through the flow hole 320 formed in the flow sleeve 300 to cool the liner and transition piece as they collide vertically with the outer wall portion of the liner 100 and the transition piece 200. I can do it.

Next, the turbine 40 may be formed similarly to the compressor 20. The turbine 40, a turbine vane (42) rotating with the rotor 50 and a turbine vane fixedly installed in the turbine casing 14 to align the flow of air flowing into the turbine blade 42 ( 44).

The turbine blades 42 are formed in a plurality, the plurality of turbine blades 42 are formed in a plurality of stages along the axial direction of the rotor 50, and the plurality of turbine blades 42 are for each stage. It may be formed radially along the rotation direction of the rotor 50.

That is, the root portion 42a of the turbine blade 42 is coupled to the turbine blade coupling slot of the turbine rotor disk 54, and the root portion 42a has the turbine blade 42 having the turbine blade coupling slot. It can be formed in the form of a fir (tree), so as to prevent the rotor 50 from being separated in the radial direction of rotation. At this time, the turbine blade coupling slot may likewise be formed in a fir shape to correspond to the root portion 42a of the turbine blade.

The turbine vanes 44 may be formed in plural, and the plurality of turbine vanes 44 may be formed in plural stages along the axial direction of the rotor 50. Here, the turbine vane 44 and the turbine blade 42 may be alternately arranged along the air flow direction. In addition, the plurality of turbine vanes 44 may be formed radially along the rotational direction of the rotor 50 for each stage.

Here, unlike the compressor 20, the turbine 40 is in contact with a high-temperature and high-pressure combustion gas, and thus requires a cooling means to prevent damage such as deterioration. To this end, it may include a cooling flow path for extracting compressed air at a part of the compressor 20 and supplying the compressed air to the turbine 40.

According to an embodiment, the cooling passage may extend from the outside of the casing 10 (outside passage), or may extend through the interior of the rotor 50 (inside passage), and both the outside passage and the inside passage You can also use

At this time, the cooling flow path communicates with the turbine blade cooling flow path formed inside the turbine blade 42, so that the turbine blade 42 may be cooled by cooling air. In addition, the turbine blade cooling flow path is in communication with the turbine blade film cooling hole formed on the surface of the turbine blade 42, so that the cooling air is supplied to the surface of the turbine blade 42, so that the turbine blade 42 is The so-called membrane can be cooled by cooling air. The turbine vane 44 may also be formed to be cooled by receiving cooling air from the cooling passage similar to the turbine blade 42.

Here, the gas turbine is only an embodiment of the present invention, and the combustor of the present invention, which will be described in detail below, can be widely applied to a jet engine in which air and fuel are combusted, as well as a general gas turbine.

Hereinafter, the injector 500 according to the first embodiment of the present invention will be described in detail with reference to the attached FIGS. 3 to 5.

As described above, the injector 500 is disposed along the circumferential direction of the liner 100 to inject a mixture of fuel and air into the secondary combustion zone 104. A plurality of injectors 500 may be disposed along a circumferential direction of the liner 100 at regular intervals, and in this embodiment, four injectors 500 are disposed.

As shown in FIG. 3, the plurality of injectors 500 are installed to form a constant angle with respect to the tangent line of the liner 100 at a position where each injector is installed. At this time, at least some of the angles formed by the injectors 500 with respect to the tangent lines of the liner 100 may be different from each other. In FIG. 3, angles formed by each injector 500 with respect to the tangent line of the liner 100 are shown as α1, α2, α3, and α4, and in this embodiment, α1, α2, α3, and α4 are not the same. The different cases are shown. However, the present invention is not limited thereto, and of course, some of α1, α2, α3, and α4 are different, and some may be the same. Accordingly, the angle at which the secondary fuel/air mixture is injected from each of the injectors 500 to the secondary combustion zone 104 is different from each other, and the shape of the flame in the secondary combustion zone 104 can be adjusted. The effect of reducing the combustion vibration of can be obtained.

Looking at the structure of each injector 500 in detail with reference to Figures 4 and 5, each injector 500 is formed to extend in the radial direction to penetrate the liner 100 and the flow sleeve 300 at the same time It includes a spray tube 520 and a plurality of vanes 540 disposed along the circumferential direction on the inner surface of the spray tube 520 so that an empty space is formed in the center of the spray tube 520.

The injection tube 520 may be configured as a cylindrical tube, and defines an injection passage 522 therein. The injection pipe 520 communicates with the receiving space 302 and the combustion chamber 120 inside the liner 100, and the annulus is used to inject a secondary fuel/air mixture into the secondary combustion zone 104. It extends through the flow path 140 to the liner 100. According to an embodiment, the injection pipe 520 may be extended to protrude into the liner 100.

The plurality of vanes 540 are disposed along the circumferential direction on the inner surface of the injection tube 520, and in this embodiment, the plurality of vanes 540 are at the uppermost end of the injection tube 520, that is, the flow It is coupled to the sleeve 300 side. The plurality of vanes 540 is preferably disposed in a spaced apart state, and protrudes in a predetermined length toward the center from the inner surface of the injection pipe 520 so that a cylindrical empty space is formed in the center of the injection pipe. do. At this time, the length of the vane 540, that is, the length protruding from the inner surface of the injection pipe 520 toward the center is formed to have a length corresponding to 1/3 to 1/4 of the diameter D of the injection pipe. It is preferred. FIG. 5 shows a case in which the length of the vane 540 corresponds to 1/3 of the diameter D of the injection pipe, and accordingly, the diameter D of the injection pipe at the center of the injection pipe 520 A cylindrical empty space having a diameter corresponding to 1/3 of is formed.

The structure in which fuel and air are mixed in the injector 500 will be described. A fuel plenum 620 may be provided on the flow sleeve 300 so as to surround the injection pipe 520, and as shown in FIG. 5, the fuel plenum 620 has a cylindrical injection pipe 520. Correspondingly, it is formed as a cylindrical space. Since the fuel plenum 620 needs to be in fluid communication with each vane 540, the fuel plenum 620 is provided to correspond to a position where the plurality of vanes 540 are provided.

In order to inject the fuel of the fuel plenum 620 into the injection passage 522, each vane 540 is provided with a fuel communication passage 542 and a first fuel port 544. Specifically, the fuel communication flow path 542 is formed inside each vane and is in fluid communication with the fuel plenum 620. The first fuel port 544 is for injecting fuel from the fuel communication passage 542 to the outside of the vane 540, that is, the injection passage 522, and the vane from the fuel communication passage 542 inside the vane. It may be formed through the outer wall surface. As shown in FIG. 5, in the present exemplary embodiment, three first fuel ports 544 are provided in the respective vanes 540, and the radially inner ends of the vanes 540 face each other on the side facing each other. It is provided one by one. Accordingly, the fuel can be injected toward the empty space in the center of the injection pipe 520, and at the same time, the fuel can be injected into the injection passages on both sides divided by the vanes, and the fuels face each other in adjacent vanes. Since is injected, the fuel may collide with each other, and the mixing degree may be further improved. However, the present invention is not limited thereto, and one fuel port may be provided only on one surface of each vane, and a plurality of fuel ports may be provided on the side surfaces facing each other.

In addition, to supply fuel to the fuel plenum 620 may further include a fuel supply flow path 640 is formed extending along the axial direction of the flow sleeve (300). The fuel supply passage 640 is connected to an external fuel supply (not shown) to serve to supply fuel to the fuel plenum 620. In this embodiment, the fuel supply passage 640 is the flow sleeve It is accommodated in 300, but is not limited thereto, and may be formed between the liner and the flow sleeve.

As described above, since one end of the injection passage 522 communicates with the accommodation space 302, compressed air flows into the injection passage 522, and through the first fuel port 544 to the injection passage 522. As the fuel is injected, the fuel and air are mixed to pass through the injection passage 522. In particular, swirl flow is generated by the vane 540 to effectively mix fuel and air, and the central flow in the empty space at the center of the injection pipe is stronger and faster than the surrounding flow through the vane. Therefore, after the secondary fuel/air mixture is injected into the secondary combustion zone 104, flashback is caused by the flow of combustion products generated by combustion in the primary combustion zone 102, that is, hot gas. Can be prevented.

In addition, a plurality of second fuel ports 524 for injecting fuel from the fuel plenum 620 into the inside of the injection pipe, that is, the injection passage 522 is further formed in the injection pipe 520 according to an embodiment. Can be. As shown in FIG. 5, the plurality of second fuel ports 524 may be arranged to be provided at least one between the plurality of vanes 540, and thus fuel for each injection passage partitioned by the plurality of vanes. Can be injected radially inward. Due to this, sufficient fuel can be supplied to the injection passage 522, and the mixing degree of fuel and air can be further improved.

Further, according to an embodiment, at least a portion of the injection pipe 520 may be formed to be narrower in width from the flow sleeve 300 toward the liner 100. As shown in FIG. 4, the injection pipe 520 may be formed to be narrower from the lower end of the vane 540 to the end extending toward the liner 100, and the inclination (β of the narrowed portion) ) Is preferably 30 ~ 60 °. Accordingly, since the central flow of the secondary fuel/air mixture passing through the injection passage 522 may become stronger and faster, the secondary fuel/air mixture may be injected into the secondary combustion zone 104 and then 1 Flashback can be prevented from occurring by the flow of combustion products from the vehicle combustion zone 102.

Next, the injector 2500 according to the second embodiment of the present invention will be described with reference to FIGS. 6 and 7.

The injector 2500 according to the second embodiment includes the same configuration as the injector 500 according to the first embodiment described above, but is provided in the center of the injection pipe 520 to provide the plurality of vanes 540 It further includes a center body 2700 for guiding the mixture of fuel and air passing through the center of the injection pipe.

The center body 2700 may be coupled to the injection pipe 520 or the vane 540 according to an embodiment, and is disposed in an empty space in the center of the injection pipe, but spaced apart from the inner end of the plurality of vanes 540 It may be arranged in a closed state or may be arranged in contact. In this embodiment, as the center body 2700 is coupled to abut against the inner ends of the plurality of vanes 540, a portion 2700a of the center body is at 1/3 of the diameter D of the injection pipe. It is formed in a cylindrical shape with a corresponding diameter. In addition, it is preferable that the end 2700b of the center body to which the mixture of fuel and air that has passed through the plurality of vanes 540 is guided has a cone shape. At this time, the inclination γ of the center body end 2700b may be 30 to 60°, and in particular, it may be formed in the same manner as the inclination β of the portion in which the width is narrowed in the injection pipe 520. That is, the end portion of the injection pipe 520 may correspond to the shape of the end portion 2700b of the center body.

As such, as the second fuel/air mixture passing through the vane 540 is guided to the center of the injection pipe 520 by the center body 2700, the central flow may be strong, and the injection pipe 520 ) Can speed up the second fuel/air mixture more effectively.

At this time, as shown in Figure 7, the center body 2700 is disposed at the center of the injection pipe, so that each vane 540 has two first fuel ports 544, one on each side facing each other. Can be. In addition, it is needless to say that the fuel may be injected radially inside the injection passage 522 by the plurality of second fuel ports 524.

Next, an injector 3500 according to a third embodiment of the present invention will be described with reference to the accompanying FIG. 8.

The injector 3500 according to the third embodiment includes the same configuration as the injector 500 according to the first embodiment described above, but is provided with at least one communication hole 3820 communicating between the outside and the inside, It further includes a damper 3800 that is formed to form a constant volume inside and covers the upper portion of the injection pipe 520.

The damper 3800 may be formed to have the same size as the injection pipe 520, and may be combined to entirely cover the upper portion of the injection pipe 520. That is, the damper 3800 may be formed in a cylindrical shape having the same diameter as the diameter D of the injection pipe. In addition, the damper 3800 has a constant height to form a constant volume therein. The inner volume of the damper 3800 and the outside, that is, at least one communication hole 3820 communicating with the receiving space 302 may be formed on any of the side and top surfaces of the damper 3800, but in this embodiment A plurality of communication holes 3820 are provided on the upper surface of the damper 3800.

Accordingly, as the compressed air of the accommodation space 302 flows through the internal volume of the damper 3800 through the plurality of communication holes 3820, the combustion vibration decreases as it enters the injection passage 522 of the injection pipe. Can be. At this time, the internal volumes of the dampers 3800 installed in each of the plurality of injectors 3500 installed along the circumferential direction of the liner 100 may be formed differently from each other.

However, the present invention is not limited thereto, and the configuration of the damper 3800 may be added to the injector 2500 according to the second embodiment.

Finally, the injector 4500 according to the fourth embodiment of the present invention will be described with reference to the accompanying FIG. 9.

The injector 4500 according to the fourth embodiment includes the same configuration as the injector 500 according to the first embodiment described above, but is provided with at least one communication hole 4820 communicating with the outside and the inside, It forms a constant volume (volume) therein and is slidably coupled to the damper (4800) and the communication hole (4820) coupled to cover the upper portion of the injection pipe (520), the through passage (4842) penetrating the inside It further includes a cylinder (4840).

The damper 4800 may be formed to have the same size as the injection pipe 520, and may be combined to cover the upper portion of the injection pipe 520 as a whole. That is, the damper 4800 may be formed in a cylindrical shape having the same diameter as the diameter D of the injection pipe. In addition, the damper 4800 has a constant height to form a constant volume therein. The inner volume and the outside of the damper 4800, that is, at least one communication hole 4820 communicating with the receiving space 302 may be formed on any of the side and top surfaces of the damper 4800, but in this embodiment A plurality of communication holes 4820 are provided on the upper surface of the damper 4800.

At this time, the cylinder 4840 is slidably coupled to each of the communication holes 4820, and may be slidably coupled along the axial direction of the cylinder with, for example, a bearing. In this embodiment, a cylinder is coupled to each communication hole, but a cylinder may be coupled to only a part of the plurality of communication holes. As such, as the cylinder 4840 slides inside the communication hole 4820, the length protruding into the damper 4800 may vary, and as a result, the internal volume of the damper 4800 may change. have.

In addition, for the internal volume of the damper 4800 to communicate with the outside, each cylinder 4840 is provided with a through passage 4482 passing through the center. Accordingly, the compressed air of the accommodation space 302 is burned as it enters the injection passage 522 of the injection pipe through the internal volume of the damper 4800 through the through passage 4484 of the cylinder 4840. Vibration can be reduced.

However, the present invention is not limited thereto, and configurations of the damper 4800 and the cylinder 4840 may also be added to the injector 2500 according to the second embodiment.

According to the present invention, premixed combustion of fuel and air is achieved in the primary combustion zone of the combustor, and fuel and air mixtures are directly injected through the injector into the secondary combustion zone of the combustor located downstream of the primary combustion zone. As a result, the nitrogen oxide (NOx) emission level of the gas turbine may be reduced.

At this time, the injector for injecting the fuel and air mixture into the secondary combustion zone includes a plurality of vanes arranged along the circumferential direction to improve the mixing ability of the fuel and air and at the same time to generate a strong flow in the center of the injector. have. Accordingly, it is possible to prevent flashback from being caused by the flow of combustion products from the primary combustion zone.

In addition, according to the embodiment, the injector is formed to be narrower as it gets closer to the secondary combustion zone, so that the central flow of the fuel and air mixture injected into the secondary combustion zone can be strengthened and the speed can be increased, so that backfire is more It can be effectively prevented.

The present invention is not limited to the specific embodiments and descriptions described above, and various modifications can be carried out by anyone having ordinary knowledge in the technical field to which the present invention pertains without departing from the gist of the present invention as claimed in the claims. And such modifications are within the protection scope of the present invention.

10: casing 12: compressor casing
13: Combustor casing 14: Turbine casing
20: compressor 22: compressor blade
22a: Compressor blade root part 24: Compressor vane
30: combustor 40: turbine
42: turbine blade 42a: turbine blade root
44: turbine vane 50: rotor
52: compressor rotor disc 53: torque tube
54: turbine rotor disc 55: tie rod
56: fixing nut
100: liner 102: primary combustion zone
104: secondary combustion zone 120: combustion chamber
140: annular flow path 200: transition piece
300: floating sleeve 302: receiving space
320: flow hole 400: nozzle assembly
420: end plate 500: injector
520: spray pipe 522: spray passage
524: Second fuel port 540: Bain
542: fuel communication flow path 544: first fuel port
620: fuel plenum 640: fuel supply flow path
2500: Injector 2700: Center body
3500: Injector 3800: Damper
3820: Communication Hall
4500: Injector 4800: Damper
4820: communication hole 4840: cylinder
4842: through passage

Claims (16)

A liner defining a combustion chamber;
A transition piece coupled to the rear end of the liner;
A flow sleeve spaced apart to surround the liner and the transition piece; And
It includes at least one injector disposed along the circumferential direction of the liner or transition piece, and injecting a mixture of fuel and air;
The injector,
An injection tube extending radially to penetrate the liner and the flow sleeve or the transition piece and the flow sleeve simultaneously; And
It includes; a plurality of vanes disposed in the circumferential direction on the inner surface of the injection tube so that an empty space is formed in the center of the injection tube;
It further includes a fuel plenum disposed to surround the injection pipe;
The injector,
A plurality of fuel communication passages provided inside each vane and in fluid communication with the fuel plenum; And
It further includes a plurality of first fuel ports formed in each vane to inject fuel from the fuel communication passage to the outside of the vane.
Each vane is provided with a plurality of first fuel ports,
The plurality of first fuel ports are characterized in that each of the vanes are provided with at least one at each side of the vanes facing each other and radially inner ends of the vanes.
A liner defining a combustion chamber;
A transition piece coupled to the rear end of the liner;
A flow sleeve spaced apart to surround the liner and the transition piece; And
It includes at least one injector disposed along the circumferential direction of the liner or transition piece, and injecting a mixture of fuel and air;
The injector,
An injection tube extending radially to penetrate the liner and the flow sleeve or the transition piece and the flow sleeve simultaneously;
A plurality of vanes arranged along the circumferential direction on the inner surface of the spray tube to form an empty space at the center of the spray tube;
A damper having at least one communication hole communicating with the outside and the inside, and forming a constant volume therein to be coupled to cover the upper portion of the injection pipe; And
A cylinder that is slidably coupled to the communication hole and has a through passage through the inside.
According to claim 1,
And a fuel supply flow path extending along an axial direction of the flow sleeve to supply fuel to the fuel plenum.
delete According to claim 1,
The injector,
And a plurality of second fuel ports formed in the injection pipe to inject fuel from the fuel plenum into the interior of the injection pipe.
The method of claim 5,
The plurality of second fuel ports are arranged so that at least one is provided for each of the plurality of vanes, the combustor.
According to claim 1,
The injection tube is characterized in that it is formed of a cylindrical tube, a combustor.
delete delete delete According to claim 1,
At least a part of the injection pipe is characterized in that the combustor is formed so that the width becomes narrower toward the liner or transition piece side from the flow sleeve side.
delete According to claim 1,
The injector,
At least one communication hole communicating with the outside and the inside is provided, the damper is formed to form a constant volume (volume) and coupled to cover the upper portion of the injection pipe; further comprising, a combustor.
The method of claim 13,
The injector,
A cylinder which is slidably coupled to the communication hole and has a through passage through the inside.
According to claim 1,
A plurality of the injectors are arranged along the circumferential direction of the liner or transition piece, and at least some of the angles each injector makes with the tangent line of the liner or transition piece are different from each other.
A compressor that sucks air and compresses it at a high pressure;
Claims 1 to 3, 5 to 7, 11 and 13 to 15 to generate a high-temperature, high-pressure combustion gas by mixing and burning compressed air and fuel in the compressor. Combustor according to any one of the preceding; And
A turbine comprising: a turbine that generates power by obtaining rotational force by the combustion gas transmitted from the combustor.

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