CN110542120B - Fuel injection device and gas turbine - Google Patents
Fuel injection device and gas turbine Download PDFInfo
- Publication number
- CN110542120B CN110542120B CN201910432050.XA CN201910432050A CN110542120B CN 110542120 B CN110542120 B CN 110542120B CN 201910432050 A CN201910432050 A CN 201910432050A CN 110542120 B CN110542120 B CN 110542120B
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- Prior art keywords
- fuel
- hole
- tube
- guide portion
- circumferential direction
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/62—Mixing devices; Mixing tubes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Abstract
The present invention relates to a fuel injection device and a gas turbine. The fuel injection device is provided with a premixing tube (2), a fuel introduction portion, and a downstream side plate. The premixer tube (2) is provided with a tube main body (21) and a guide portion (22). A through hole (23) for communicating the internal space with the external space (S2) is formed in the upstream end (2A) of the tube main body (21) on the side close to the introduction port (2A). The guide portion (22) extends from an end (23a) of the through hole (23) in the circumferential direction around an axis (A2) of the premixer tube (2) so as to intersect both the circumferential direction and an axial direction (Da) in which the axis (A2) extends.
Description
Technical Field
The present invention relates to a fuel injection device and a gas turbine.
Background
In many cases, a fuel injection device such as a gas turbine or a boiler supplies a mixed gas in which compressed air and a fuel gas are mixed in advance to a combustor.
Patent document 1 discloses a fuel injection device that injects a mixture of compressed air and a fuel gas from a plurality of injection holes regularly formed in a circular substrate.
Prior art documents
Patent document
Patent document 1: japanese patent laid-open publication No. 2016-080214
In the fuel injection device described in patent document 1, it is desirable to uniformly mix the compressed air and the fuel gas in order to reduce NOx (nitrogen oxide). Specifically, the compressed air and the fuel gas are preferably uniformly mixed before reaching the plurality of discharge holes of the fuel injection device.
However, when the fuel gas is injected into the air using the premixer tube to mix the air and the fuel gas, the length of the premixer tube needs to be increased in order to sufficiently mix the air and the fuel gas. When the premixer tube becomes long, the component cost increases, or the combustion stability decreases, and combustion vibration may occur.
Disclosure of Invention
An object of the present invention is to provide a fuel injection device and a gas turbine that can sufficiently mix air and fuel gas while suppressing an increase in the length of a premixer tube.
Means for solving the problems
According to a first embodiment of the present invention, a fuel injection device includes a premixer tube, a fuel introduction portion, and a downstream side plate. The premixer tube introduces air from the inlet port into the internal space. The premixer tube ejects the mixture gas in which the air and the fuel are mixed from the ejection port. The fuel introducing portion introduces fuel into the internal space. The end of the premixer tube on the outlet side passes through the downstream side plate. A downstream side plate supports a downstream end of the premixer tube. The premixer tube includes a tube main body and a guide portion. A through hole for communicating the internal space with the external space is formed in the upstream end of the tube main body on the side close to the introduction port. The guide portion extends from an end portion of the through hole in the circumferential direction around the axis of the premixer tube so as to intersect both the circumferential direction and the axial direction in which the axis extends.
With this configuration, a part of the air introduced into the inner space of the premixer tube is introduced into the inner space of the premixer tube through the through hole formed at the upstream end portion. At this time, the air is guided by the guide portion extending from the end of the through hole in the circumferential direction so as to intersect both the circumferential direction and the axial direction in which the axis extends. The flow of air guided by the guide portion includes a flow toward the circumferential direction. Therefore, the flow of air introduced into the inner space of the premixer tube includes a swirling flow centered on the axis of the premixer tube. Thus, the mixing of the air and the fuel is promoted by the swirling flow.
Therefore, the air and the fuel gas can be sufficiently mixed while suppressing the length of the premixer tube from becoming long.
According to the second aspect of the present invention, the guide portion of the first embodiment may include an inner guide portion. The inner guide portion extends from a first end of the through hole in the circumferential direction toward an inner side of the introduction port and a side close to a second end of the through hole.
By using the inner guide portion configured as described above, the air introduced into the internal space through the through hole can be swirled from the first end portion of the through hole in the circumferential direction toward the second end portion.
According to a third aspect of the present invention, the guide portion according to the first or second aspect may be provided with an outer guide portion. The outer guide portion extends from a second end of the through hole in the circumferential direction toward an outer side of the introduction port and a side close to the first end of the through hole.
By guiding the air by the outer guide portion configured as described above, the air introduced into the internal space through the through hole can be swirled in a direction from the first end portion of the through hole in the circumferential direction toward the second end portion.
According to a fourth aspect of the present invention, the guide portion and the through-hole of any one of the first to third aspects may be provided in plurality at intervals in a circumferential direction of the introduction port.
With this configuration, air can be simultaneously introduced into the internal space from the plurality of through holes. The air introduced into the internal space from the plurality of through holes is guided by the guide portion extending from the plurality of through holes, and therefore the swirling flow of the air introduced into the internal space can be further strengthened.
According to a fifth aspect of the present invention, the fuel introducing portion according to any one of the first to fourth aspects may be provided with a nozzle. The nozzle is inserted into the internal space from the introduction port and injects fuel from a distal end portion.
With this configuration, when the fuel is injected into the inner space of the premixer tube by the nozzle inserted from the inlet, a swirling flow can be generated in the flow of the air flowing around the nozzle and flowing toward the downstream side. Therefore, the air and the fuel can be sufficiently mixed by the swirling flow at the downstream side of the nozzle and can be ejected from the ejection port.
According to a sixth aspect of the present invention, the fuel introducing portion according to any one of the first to fourth aspects may include the downstream side plate, the upstream side plate, the fuel supply pipe, and the fuel through-hole forming portion. The upstream side plate forms a cavity with the outer wall of the premixer tube and the downstream side plate. The upstream side plate is disposed closer to the introduction port than the downstream side plate, and has an upstream side through hole through which the premixer tube passes. A fuel supply tube supplies fuel to the cavity. The fuel through-hole forming portion forms a part of an outer wall of the premixer tube, and forms a fuel through-hole penetrating the outer wall of the premixer tube.
With this configuration, when fuel is supplied from the fuel supply pipe to the cavity and fuel is supplied from the cavity to the internal space, a swirling flow can be formed in the internal space of the premixer tube. Therefore, the fuel and the air supplied from the cavity can be sufficiently mixed in the internal space of the premixer tube and can be ejected from the ejection port.
According to a seventh aspect of the present invention, a gas turbine includes the fuel injection device according to any one of the first to seventh aspects.
With this configuration, air and fuel can be sufficiently mixed, and therefore, nitrogen oxides can be reduced. Further, since the entire length of the premixer tube can be shortened, combustion vibration can be suppressed.
Effects of the invention
According to the fuel injection device and the gas turbine described above, the compressed air and the fuel gas can be sufficiently mixed while suppressing an increase in the length of the premixer tube.
Drawings
Fig. 1 is a schematic configuration diagram of a gas turbine according to a first embodiment of the present invention.
Fig. 2 is a sectional view showing a schematic configuration of a fuel injection device according to a first embodiment of the present invention.
Fig. 3 is an enlarged perspective view of an upstream end of a tube main body of a premixer tube according to a first embodiment of the present invention.
Fig. 4 is a view of the tube main body of the premixer tube in the first embodiment of the present invention, as viewed from the axial direction.
Fig. 5 corresponds to fig. 4, and shows a second embodiment of the present invention.
Fig. 6 is a diagram showing an example of arrangement of the premixer tubes in the second embodiment of the present invention.
Fig. 7 corresponds to fig. 4 in the third embodiment of the present invention.
Fig. 8 is a view corresponding to fig. 2 of another modification of the embodiment of the present invention.
Description of reference numerals:
1. 101 fuel injection device
2. 202, 302 premixer tube
2a end (upstream end)
2A introducing port
2at end face
2b end part
2B spout
2bt end face
2d outer wall
2f outer peripheral surface
2i inner peripheral surface
3 upstream side plate
3a first through hole
3b second through hole (upstream side through hole)
3c side
4 downstream side plate
4a face
4b side
5 outer side wall
5a inner peripheral surface
8 fuel supply pipe
8a end part
12 fuel through hole forming part
12h fuel through hole
21 tube body
22 guide part
22I inner guide part
22O outer guide part
22Ot end
23 through hole
23a first side part (first end part)
23b second side part (second end part)
23c bottom edge
30 fuel nozzle
30f outer peripheral surface
31 front end part
51 compressor
52 burner
53 turbine
56 compressor rotor
57 compressor chamber
58 compressor stationary blade cascade
59 compressor rotor shaft
60 compressor rotor blade cascade
61 turbine rotor
62 turbine chamber
63 turbine stationary blade cascade
64 turbine rotor shaft
65 turbine rotor blade cascade
67 intermediate machine room
68 gas turbine rotor
69 burning cylinder
100 gas turbine
Detailed Description
(first embodiment)
Next, a fuel injection device and a gas turbine according to a first embodiment of the present invention will be described with reference to the drawings.
Fig. 1 is a schematic configuration diagram of a gas turbine according to an embodiment of the present invention.
As shown in fig. 1, the gas turbine 100 of the present embodiment includes a compressor 51, a plurality of combustors 52, and a turbine 53.
The compressor 51 compresses the outside gas Ao to generate compressed air a. The compressor 51 has a compressor rotor 56, a compressor casing 57, and a plurality of compressor vane cascades 58.
The compressor rotor 56 rotates about the gas turbine axis Ar. Compressor rotor 56 has a compressor rotor shaft 59 and a plurality of compressor blade cascades 60. The compressor rotor shaft 59 extends along the gas turbine axis Ar. A plurality of compressor rotor blade cascades 60 are mounted to compressor rotor shaft 59.
The compressor chamber 57 covers the compressor rotor 56.
The plurality of compressor rotor blade cascades 60 are aligned in the axial direction of the gas turbine axis Ar. Each of the compressor rotor blade cascade 60 is composed of a plurality of rotor blades (not shown) arranged in the circumferential direction of the gas turbine axis Ar. A compressor stationary blade cascade 58 is disposed downstream of each of the plurality of compressor rotor blade cascades 60.
The plurality of compressor stationary blade cascades 58 are each fixed to the inside of the compressor casing 57. Each of the plurality of compressor stationary blade cascades 58 is constituted by a plurality of stationary blades (not shown) arranged in the circumferential direction of the gas turbine axis Ar.
The plurality of burners 52 generate high-temperature and high-pressure combustion gas G. The plurality of burners 52 are fixed to the intermediate housing 67. The plurality of combustors 52 are arranged at intervals in the circumferential direction of the gas turbine axis Ar.
Each of the plurality of burners 52 includes the fuel injection device 1 and a combustion liner 69.
The fuel injection device 1 generates a mixture of compressed air a compressed by the compressor 51 and fuel gas F and supplies the mixture to the combustion liner 69. The fuel injection device 1 is disposed inside an outer cylinder (not shown) of the combustor 52.
The combustor liner 69 combusts the air-fuel mixture supplied from the fuel injection device 1, and guides the combusted combustion gas G to the turbine 53.
The turbine 53 converts thermal energy of the combustion gas G into rotational energy. The turbine 53 includes a turbine rotor 61, a turbine casing 62, and a plurality of turbine stator vanes 63. The turbine rotor 61 rotates about the gas turbine axis Ar. The turbine rotor 61 has a turbine rotor shaft 64 and a plurality of turbine bucket cascades 65. The turbine rotor shaft 64 extends along a gas turbine axis Ar. The turbine rotor 61 is connected to the compressor rotor 56 described above, and constitutes a gas turbine rotor 68 together with the compressor rotor 56. The gas turbine rotor 68 of this embodiment is exemplified in the case where a generator G as a load is connected.
A plurality of turbine bucket cascades 65 are mounted to turbine rotor shaft 64. These turbine blade cascades 65 are aligned in the axial direction of the gas turbine axis Ar. Each of the plurality of turbine rotor blade cascades 65 is constituted by a plurality of rotor blades (not shown) arranged in the circumferential direction of the gas turbine axis Ar.
The plurality of turbine stationary blade cascades 63 are disposed on the upstream side of the plurality of turbine rotor blade cascades 65. The turbine stationary blade cascades 63 are fixed to the inside of the turbine casing 62. Each of the plurality of turbine stationary blade cascades 63 is constituted by a plurality of stationary blades (not shown) arranged in the circumferential direction of the gas turbine axis Ar.
The turbine chamber 62 covers the turbine rotor 61. An intermediate casing 67 is disposed between the turbine casing 62 and the compressor casing 57. The intermediate casing 67 is formed in a cylindrical shape centered on the gas turbine axis Ar.
According to the gas turbine 100, the outside air Ao introduced into the compressor 51 is compressed by the plurality of compressor stator blade cascades 58 and the compressor rotor blade cascades 60, and becomes high-temperature and high-pressure compressed air a. The compressed air a is mixed with fuel gas F in the combustor 52. The mixed gas mixture is burned to become high-temperature and high-pressure combustion gas G. The combustion gas G passes through the turbine stationary blade cascade 63 and the turbine rotor blade cascade 65 of the turbine 53. At this time, the turbine rotor shaft 64 is rotationally driven, and rotational energy is transmitted to the generator G coupled to the gas turbine rotor 68. The rotational energy is converted into electric energy by the generator G and output.
Fig. 2 is a sectional view showing a schematic configuration of a fuel injection device according to a first embodiment of the present invention.
As shown in fig. 2, the fuel injection device 1 includes a fuel supply pipe 8, a plurality of premixer tubes 2, an upstream side plate 3, a downstream side plate 4, and an outer side wall 5.
In the following description, the direction in which the axis At of the fuel supply pipe 8 extends is referred to as the axial direction Da. A direction orthogonal to the axis At is a radial direction Dr, a side distant from the axis At in the radial direction Dr is a radial direction outer side Dr1, and a side close to the axis At in the radial direction Dr is a radial direction inner side Dr 2. The side of the axial line Da where the fuel gas F is introduced (left side in fig. 2) is referred to as an upstream side Da1, and the side of the axial line Da where the fuel gas F is injected (right side in fig. 2) is referred to as a downstream side Da 2. The circumferential direction around the axis At is simply referred to as the circumferential direction Dc.
The fuel supply pipe 8 forms a flow path for guiding the fuel gas F supplied from the outside to the cavity PF (described later in detail). The fuel supply pipe 8 is tubular extending in the axial direction Da. The fuel gas F in the fuel supply pipe 8 flows from the upstream side Da1 to the downstream side Da 2. The end 8a of the downstream side Da2 of the fuel supply pipe 8 is supported by the upstream side plate 3 and opens into the cavity PF.
The upstream side plate 3 supports an end portion (upstream side end portion) 2a of the upstream side Da1 of the plurality of premixer tubes 2 and an end portion 8a of the downstream side Da2 of the fuel supply pipe 8, respectively. The upstream side plate 3 also closes the opening of the upstream side Da1 of the outer side wall 5. The upstream side plate 3 has a circular plate shape centered on the axis At. The upstream side plate 3 includes: a first through hole 3a formed in the center of the disk; and a plurality of second through-holes (upstream side through-holes) 3b formed around the first through-hole 3 a.
The end 8a of the downstream side Da2 of the fuel supply pipe 8 passes through the first through hole 3 a. More specifically, the end portions 8a of the downstream side Da2 of the fuel supply pipe 8 are arranged so as to protrude toward the downstream side Da2 of the upstream side plate 3 through the first through holes 3a, respectively. The end 2a of the upstream side Da1 of the premixer tube 2 passes through the second through hole 3 b. More specifically, the end portions 2a of the upstream side Da1 of the premixer tubes 2 are arranged to protrude toward the upstream side Da1 of the upstream side plate 3 through the second through holes 3 b.
The downstream side plate 4 supports the end portions 2b of the downstream sides Da2 of the plurality of premixer tubes 2. The downstream side plate 4 also closes the opening of the downstream side Da2 of the outer side wall 5. The downstream side plate 4 is formed in a circular plate shape centered on the axis At and has substantially the same outer diameter as the upstream side plate 3.
The outer wall 5 is formed in a cylindrical shape with a cavity PF formed therein. More specifically, the outer wall 5 is cylindrical and extends in the axial direction Da about the axis At. The upstream side Da1 of the outer side wall 5 has its opening closed by the upstream side plate 3, and the downstream side Da2 has its opening closed by the downstream side plate 4. That is, the downstream side plate 4 and the upstream side plate 3 are connected via the outer wall 5. Thus, a cavity PF for storing the fuel gas G is defined between the surface 4a of the upstream side Da1 of the downstream side plate 4, the surface 3c of the downstream side Da2 of the upstream side plate 3, the inner circumferential surface 5a of the outer wall 5, and the outer circumferential surface 2f of the outer wall 2d of the premixer tube 2.
The premixer tubes 2 are formed in a cylindrical shape extending in the axial direction Da. The premixer tube 2 introduces the compressed air a from the inlet port 2A on the upstream side Da1, and discharges the air-fuel mixture MG obtained by mixing the compressed air a and the fuel gas F from the outlet port 2B on the downstream side Da 2. As described above, the end 2a of the upstream side Da1 of the premixer tube 2 of this embodiment is supported by the upstream side plate 3, and the end 2b of the downstream side Da2 is supported by the downstream side plate 4.
The end portion 2b of the downstream side Da2 of the premixer tube 2 illustrated in the first embodiment is not projected from the downstream side plate 4 to the downstream side Da2, but is arranged at the same position as the surface 4b of the downstream side Da2 of the downstream side plate 4 in the axial direction Da. In other words, the end surface 2bt of the downstream side Da2 of the premixer tube 2 is flush with the surface 4b of the downstream side Da2 of the downstream side plate 4. An end 2a of the upstream side Da1 of the premixer tube 2 is formed to protrude from the upstream side plate 3 toward the upstream side Da 1.
The outer wall 2d of the premixer tube 2 includes a fuel through-hole forming portion 12 that forms a fuel through-hole 12h that penetrates in the radial direction. In the first embodiment, the downstream side plate 4, the upstream side plate 3, the fuel supply pipe 8, and the fuel through-hole forming portion 12 constitute a fuel supply portion of the present invention.
The fuel through hole 12h communicates the internal space S1 of the premixer tube 2 with the cavity PF. The fuel gas F accommodated in the cavity PF flows into the internal space S1 of the premixer tube 2 through the fuel through holes 12 h. The fuel through-hole 12h has, for example, a circular cross-sectional shape and extends in the radial direction of the premixer tube 2. The fuel through-holes 12h of this embodiment are provided in plurality at intervals in the circumferential direction of the premixer tube 2. The fuel through holes 12h of the plurality of premixer tubes 2 are located at the same position in the axial direction Da. The fuel through-hole 12h exemplified in this embodiment is located closer to the introduction port 2A than the center of the premixer tube 2 in the axial direction Da. The extending direction of the fuel through holes 12h is not limited to the radial direction. The positions of the fuel through holes 12h in the plurality of premixer tubes 2 may be different from each other in the axial direction Da.
Fig. 3 is an enlarged perspective view of an upstream end of a tube main body of a premixer tube according to a first embodiment of the present invention. Fig. 4 is a view of the tube main body of the premixer tube in the first embodiment of the present invention, as viewed from the axial direction.
As shown in fig. 3 and 4, the premixer tube 2 includes a tube main body 21 and a guide portion 22.
The tube main body 21 includes a through hole 23 communicating the internal space S1 and the external space S2 at an end 2A of the upstream side Da1 close to the introduction port 2A. The through hole 23 is formed in the end 2a of the upstream side Da1 at a position closer to the upstream side Da1 than the upstream side plate 3. The through-hole 23 of this embodiment is formed so as to be recessed from the end surface 2at of the upstream side Da1 of the tube main body 21 toward the downstream side Da 2. More specifically, the through-hole 23 includes: a first side portion (first end portion) 23a and a second side portion (second end portion) 23b extending in the axial direction Da from the end surface 2at of the upstream side Da 1; and a bottom side portion 23c extending in a circumferential direction (hereinafter, simply referred to as circumferential direction Dc2) about the axis a2 of the pipe main body 21 so as to connect end portions of the first side portion 23a and the second side portion 23b on the downstream side Da2 to each other.
The plurality of through holes 23 are formed at intervals in the circumferential direction Dc2 of the tube main body 21. Four through holes 23 of this embodiment are formed at equal intervals in the circumferential direction Dc2 of the tube main body 21. The example is a case where the length Lc1 of the circumferential direction Dc2 of these through holes 23 is longer than the distance Lc2 between the through holes 23 adjacent in the circumferential direction Dc 2. In this embodiment, the first side portion 23a is disposed on the first side in the circumferential direction Dc2 of the pipe main body 21, and the second side portion 23b is disposed on the second side in the circumferential direction Dc2 of the pipe main body 21. The through-hole 23 of this embodiment is formed such that the bottom side portion 23c is longer than the first side portion 23a and the second side portion 23 b. Therefore, the through hole 23 is rectangular in shape that is long in the circumferential direction Dc2 as viewed in the radial direction of the tube main body 21.
The guide portion 22 guides the air a introduced into the internal space S1 of the tube main body 21 through the through hole 23 in a turning direction around the axis a2 of the tube main body 21. The guide portion 22 of this embodiment includes an inner guide portion 22I. The inner guide portion 22I extends from a first edge portion (first end portion) 23a, which is an end portion of the through hole 23 in the circumferential direction Dc2 centered on the axis a2 of the tube main body 21, so as to intersect both the circumferential direction Dc2 and the axial direction Da (or the extending direction of the axis a 2). The inner guide portion 22I is disposed in the range where the through hole 23 is formed in the circumferential direction Dc 2.
As shown in fig. 4, the inner guide portion 221 extends obliquely with respect to a virtual straight line VL extending in the radial direction around the axis a2 of the tube main body 21. The inner guide portion 22I is inclined so as to approach the center of the tube main body 21 (in other words, the axis a2) from the first side portion 23a toward the second side portion 23 b. The inner guide portion 22I in fig. 4 extends linearly from the first side portion 23a, but may be formed to be slightly curved.
The angle θ 1 formed by the tangent TL1 at the radially inner end edge of the first side portion 23a and the inner guide portion 22I may be between 90 degrees and 45 degrees. The angle θ 1 may be about 60 degrees. By setting the angle θ 1 to about 60 degrees, when the position of the fuel through hole 12h in the axial direction Da is fixed, the position where the air a and the fuel gas G are sufficiently mixed in the axial direction Da can be set closer to the introduction port 2A.
The length L1 of the inner guide 22I may be shorter than the length Lc1 of the through hole 23 in the circumferential direction Dc 2. The length L1 of the inner guide 22I may be about half the length Lc1 of the through hole 23. The inner guide 22I may be formed by cutting the tube main body 21 of the introduction port 2A and bending a part of the tube main body 21. This enables the inner guide 22I to be easily formed.
In the first embodiment described above, a part of the air a introduced into the internal space S1 of the premixer tube 2 is introduced into the internal space S1 of the premixer tube 2 through the through-hole 23 formed at the end 2a of the upstream side Da 1. At this time, the air a is guided by the inner guide portion 22I, and the inner guide portion 22I extends from the first edge portion 23a, which is the end of the through hole 23 in the circumferential direction Dc2, in a direction intersecting both the circumferential direction Dc2 and the axial direction Da. The flow of the air a guided by the inner guide portion 22I includes a flow toward the circumferential direction Dc 2. Therefore, the flow of the air a introduced into the internal space S1 of the premixer tube 2 includes a swirling flow centered on the axis a2 of the premixer tube 2. Therefore, the swirling flow promotes mixing of the air a and the fuel F.
As a result, the air a and the fuel F can be sufficiently mixed while suppressing the length of the premixer tube 2 from increasing.
The inner guide portion 22I in the first embodiment described above extends from the first side portion 23a of the through hole 23 in the circumferential direction Dc2 toward the inside of the introduction port 2A and toward the side close to the second side portion 23b of the through hole 23. Therefore, by guiding the air a by the inner guide portion 22I configured as described above, the air a introduced into the internal space S1 through the through-hole 23 can be swirled in the direction from the first side portion 23a toward the second side portion 23b of the through-hole 23 in the circumferential direction Dc 2.
The inner guide portion 22I and the through-holes 23 of the first embodiment are provided in plurality at intervals in the circumferential direction Dc2 of the introduction port 2A. Therefore, the air a can be simultaneously introduced into the internal space S1 from the plurality of through holes 23. Since the air a introduced into the internal space S1 from the plurality of through holes 23 is guided by the inner guide portions 22I extending from the plurality of through holes 23, the swirling flow of the air a introduced into the internal space S1 can be further strengthened.
The upstream side plate 3 of the first embodiment forms a cavity PF between the outer wall 2d of the premixer tube 2 and the downstream side plate 4. The upstream side plate 3 is disposed closer to the introduction port 2A than the downstream side plate 4, and has a second through hole 3b through which the premixer tube 2 passes. The fuel supply pipe 8 supplies fuel F to the cavity PF. The fuel through-hole forming portion 12 forms a part of the outer wall 2d of the premixer tube, and forms a fuel through-hole 12h that penetrates the outer wall 2d of the premixer tube 2. Therefore, the fuel F is supplied from the fuel supply pipe 8 to the cavity PF, and the fuel F is supplied from the cavity PF to the internal space S1.
Thus, when the fuel F is supplied from the cavity PF through the fuel through-hole 12h, the swirling flow can be formed in the inner space S1 of the premixer tube 2 by the inner guide portion 22I disposed on the upstream side Da1 of the fuel through-hole 12 h. Therefore, in the internal space S1 of the premixer tube 2, the fuel F and the air a supplied from the cavity PF can be sufficiently mixed and ejected from the ejection port 2B.
The gas turbine 100 according to the first embodiment includes the fuel injection device 1 having the above-described configuration, and thus air a and fuel F can be sufficiently mixed, and nitrogen oxides can be reduced. Further, even if the entire length of the premixer tube 2 is not formed long, the air a and the fuel F can be sufficiently mixed. Therefore, the total length of the premixer tube 2 can be shortened to suppress combustion vibration while reducing nitrogen oxides.
Further, since the guide portions 22 (inner guide portions 22I) are not disposed outside the premixer tubes 2, the guide portions 22 are prevented from interfering with each other and the interval between adjacent premixer tubes 2 can be prevented from increasing.
(second embodiment)
Next, a second embodiment of the present invention will be described with reference to the drawings. The fuel injection device of the second embodiment differs from the fuel injection device 1 of the first embodiment only in the configuration of the guide portion. Therefore, the same portions as those of the first embodiment described above will be described with the same reference numerals with reference to fig. 2, and redundant description will be omitted.
The fuel injection device of the second embodiment includes the fuel supply pipe 8, the plurality of premixer tubes 202, the upstream side plate 3, the downstream side plate 4, and the outer wall 5, as in the first embodiment.
Fig. 5 corresponds to fig. 4, and shows a second embodiment of the present invention.
As shown in fig. 5, the premixer tube 202 is formed in a cylindrical shape extending in the axial direction Da (see fig. 2). The premixer tube 202 includes a tube main body 21 and a guide portion 22. The tube main body 21 includes a through hole 23 in the same manner as the tube main body 21 of the first embodiment, and the through hole 23 communicates the internal space S1 and the external space S2 at an end 2A of the upstream side Da1 (see fig. 2) which is a side close to the introduction port 2A. The through-hole 23 of the second embodiment is formed so as to be recessed from the end surface 2at of the upstream side Da1 of the tube main body 21 toward the downstream side Da2 (see fig. 2). The through-hole 23 includes, as in the first embodiment: a first side 23a and a second side 23b extending in the axial direction Da from the end surface 2at of the upstream side Da 1; and a bottom side portion 23c extending in the circumferential direction Dc2 so as to connect end portions of the first side portion 23a and the second side portion 23b on the downstream side Da2 to each other.
The plurality of through holes 23 are formed at intervals in the circumferential direction Dc2 of the tube main body 21. The through-holes 23 exemplified in the second embodiment are also formed in four at equal intervals in the circumferential direction Dc2 of the tube main body 21, similarly to the through-holes 23 of the first embodiment. In the second embodiment, the length Lc1 of the through-holes 23 in the circumferential direction Dc2 and the distance Lc2 between the through-holes 23 adjacent in the circumferential direction Dc2 are in the same relationship as in the first embodiment.
As in the first embodiment, the guide portion 22 guides the air a introduced into the internal space S1 of the tube main body 21 through the through hole 23 in a revolving direction around the axis a2 of the tube main body 21. The guide portion 22 of the second embodiment includes an outer guide portion 22O. The outer guide portion 22O extends from the second side portion 23b so as to intersect both the circumferential direction Dc2 and the axial direction Da. In other words, the outer guide 22O extends obliquely to the virtual straight line VL extending in the radial direction DrA centered on the axis a2 of the tube main body 21.
The outer guide portion 22O extends from the second side portion 23b toward the outer side DrA1 in the radial direction DrA and toward the side close to the first side portion 23a in the circumferential direction Dc2 of the tube main body 21. Thus, the end portion 22Ot of the outer guide portion 22O on the side close to the first side portion 23a is disposed outward of the first side portion 23a and the second side portion 23b in the radial direction Dr2 of the tube main body 21. The end 22Ot of the outer guide portion 22O of the second embodiment on the side close to the first side portion 23a is disposed radially outward DrA1 with respect to a tangent TL2 passing through the end edge of the radially outward side DrA1 of the second side portion 23 b. The outer guide portion 22O may extend from the second side portion 23b in the direction of the tangent TL 2.
The outer guide portion 22O is illustrated as extending linearly from the second side portion 23b when viewed from the axial direction Da, but the outer guide portion 22O may be formed in a curved shape slightly curved when viewed from the axial direction Da. The outer guide 22O of the second embodiment may be formed by forming a notch in the tube main body 21 of the introduction port 2A by cutting or the like and bending a part of the tube main body 21, similarly to the inner guide 22I of the first embodiment. This enables the outer guide 22O to be easily formed.
The length L2 of the outer guide portion 22O is shorter than the length Lc1 of the through hole 23 in the circumferential direction Dr 2. The length L2 of the outer guide 22O may be about half the length Lc1 of the through hole 23.
Fig. 6 is a diagram showing an example of arrangement of the premixer tubes in the second embodiment of the present invention.
The plurality of premixer tubes 202 of the second embodiment may be arranged as shown in fig. 6. Of the four outer guide portions 22O of the premixer tube 202, two predetermined outer guide portions 22O disposed to face each other with the axis a2 of the premixer tube 202 interposed therebetween are disposed to extend in the first direction D1 orthogonal to the axis a 2. The remaining two of the outer guide portions 22O shown in fig. 6 extend in the direction (second direction D2) orthogonal to the axis a2 and the first direction D1. By disposing as shown in fig. 6, the intervals between the plurality of premixer tubes 202 can be reduced, and interference between the outer guide portions 22O of the adjacent premixer tubes 202 can be suppressed.
The outer guide portion 22O of the second embodiment described above extends from the second side portion 23b of the through hole 23 in the circumferential direction Dc2 toward the radially outer side DrA1 and toward the side close to the first side portion 23a of the through hole 23. Therefore, by guiding the air a by the outer guide portion 22O, the air a introduced into the internal space S1 through the through-hole 23 can be swirled in the direction from the first side portion 23a toward the second side portion 23b of the through-hole 23 in the circumferential direction Dc2, as in the first embodiment.
The outer guide portion 22O and the through-hole 23 of the second embodiment are provided in plurality at intervals in the circumferential direction Dc 2. Therefore, the air a can be simultaneously introduced into the internal space S1 from the plurality of through holes 23. Since the air a introduced into the internal space S1 from the plurality of through holes 23 is guided by the outer guide portions 22O extending from the plurality of through holes 23, the swirling flow of the air a introduced into the internal space S1 can be further strengthened.
The guide portion 22 (outer guide portion 22O) is not disposed in the inner space S1 of the premixer tube 202 of the second embodiment. Therefore, for example, an increase in the pressure loss of the air a flowing into the internal space S1 of the premixer tube 202 can be suppressed.
(third embodiment)
Next, a third embodiment of the present invention will be described with reference to the drawings. The fuel injection device according to the third embodiment differs from the first and second embodiments only in the configuration of the guide portion. Therefore, the same portions as those of the second embodiment are described with reference to fig. 2 with the same reference numerals, and overlapping description is omitted.
Fig. 7 corresponds to fig. 4 in the third embodiment of the present invention.
As shown in fig. 7, the premixer tube 302 of the fuel injection apparatus according to the third embodiment includes a tube main body 21 and a guide portion 22.
The tube main body 21 includes a through hole 23 that communicates the internal space S1 with the external space S2 at an end 2a (see fig. 2) of the upstream side Da 1.
The guide portion 22 guides the air a introduced into the internal space S1 of the tube main body 21 through the through hole 23 in a turning direction around the axis a2 of the tube main body 21. The guide portion 22 of the third embodiment includes an inner guide portion 22I and an outer guide portion 22O.
The inner guide portion 22I has the same configuration as the inner guide portion 22I of the first embodiment described above, and extends from the first edge portion 23a, which is the end of the through hole 23, in a direction intersecting both the circumferential direction Dc2 and the axial direction Da. That is, the inner guide portion 22I extends obliquely with respect to a virtual straight line VL extending in the radial direction around the axis a2 of the tube main body 21. The inner guide portion 22I extends linearly from the first side portion 23a as in the first embodiment, but may be formed to be slightly curved.
The outer guide portion 22O has the same configuration as the outer guide portion 22O of the second embodiment described above, and extends from the second side portion 23b, which is an end portion of the through hole 23, in a direction intersecting both the circumferential direction Dc2 and the axial direction Da. That is, the outer guide portion 22O extends obliquely to a virtual straight line extending in a radial direction around the axis a2 of the tube main body 21. The inclination angle θ 2 of the outer guide portion 22O with respect to the tangent TL2 passing through the outer end edge of the second side portion 23b is smaller than the inclination angle θ 1 of the inner guide portion 22I with respect to the tangent TL passing through the inner end edge of the first side portion 23 a.
The inner guide 22I and the outer guide 22O may be formed by forming a notch in the tube main body 21 of the introduction port 2A by, for example, cutting and bending a part of the tube main body 21, as in the first and second embodiments. In this case, in the third embodiment, a notch may be formed in the axial direction Da in the vicinity of the center of the through hole 23 in the circumferential direction Dc2, and a portion closer to the first side portion 23a than the notch may be used as the inner guide portion 22I, and a portion closer to the second side portion 23b may be used as the outer guide portion 22O. This makes it possible to easily form the inner guide 22I and the outer guide 22O.
In the third embodiment described above, the guide portion 22 includes the inner guide portion 22I and the outer guide portion 22O. Therefore, the air a passing through the through-holes 23 can be guided by both the inner guide portion 22I and the outer guide portion 22O. Therefore, the swirling flow can be generated more stably than in the case where the air a is guided by only one of the inner guide portion 22I and the outer guide portion 22O.
In the third embodiment described above, the inclination angle θ 1 of the inner guide portion 22I with respect to the tangent line TL is larger than the inclination angle θ 2 of the outer guide portion 22O with respect to the tangent line TL 2. With this configuration, the air a guided to the inside of the through-hole 23 by the outer guide portion 22O collides with the inner guide portion 22I in the internal space S1 of the tube main body 21 and is guided by the inner guide portion 22I. As a result, the flow direction of the air a passing through the through-holes 23 can be directed toward the radially inner side DrA2 in a stepwise manner by the outer guide portion 22O and the inner guide portion 22I. As a result, the swirling flow can be generated more smoothly in the internal space S1 of the premixer tube 2.
(other modification example)
Fig. 8 is a view corresponding to fig. 2 of another modification of the embodiment of the present invention.
In the above embodiments, the case where the fuel introducing portion supplies the fuel F from the fuel supply pipe 8 to the cavity PF, and then supplies the fuel F from the cavity PF to the internal space S1 has been described as an example. However, the structure of the fuel introducing portion is not limited to the structure of each of the above embodiments.
For example, as in the fuel injection device 101 of another modification shown in fig. 8, when the fuel introduction portion FI is provided with the fuel nozzle 30 that injects the fuel F from the tip end portion 31, the guide portion 22 (not shown in fig. 8) of the first to third embodiments described above can be applied. The plurality of fuel nozzles 30 are provided, and each extend in the axial direction Da like the premixer tubes 2. The fuel nozzles 30 have an outer diameter smaller than an inner diameter of the premixer tubes 2, and the fuel nozzles 30 are respectively inserted into the premixer tubes 2. An inner space S1 through which air a flows is formed between the fuel nozzle 30 and the inner circumferential surface 2i of the premixer tube 2. In the modification shown in fig. 8, the tip end portion 31 of the fuel nozzle 30 is disposed closer to the introduction port 2A than the center of the premixer tube 2 in the axial direction Da.
With the configuration as the fuel injection device 101 of this modification, similarly to the first to third embodiments described above, the air a flowing into the internal space S1 from the through hole 23 formed in the upstream end portion 2a can be guided by the guide portion 22 to generate the swirling flow. The internal space S1 formed between the inner circumferential surface 2i and the outer circumferential surface 30f of the fuel nozzle 30, which contains the swirling flow, flows toward the discharge port 2B. The fuel F injected from the tip end 31 of the fuel nozzle 30 is mixed with the air a containing the swirling flow. Then, the air a and the fuel F are mixed as they approach the discharge port 2B by the swirling flow, and the well-mixed air-fuel mixture MG is discharged from the discharge port 2B.
The present invention is not limited to the configurations of the above-described embodiments, and design changes can be made without departing from the scope of the invention.
For example, in the above-described embodiments, the case where the fuel injection devices 1 and 101 are used in the gas turbine 100 is described. However, the present invention is not limited to the gas turbine 100. For example, the fuel injection devices 1 and 101 may be applied to boilers, combustors, and the like other than the gas turbine 100.
In the above-described embodiments, the case where the linear inner guide portion 22I and the linear outer guide portion 22O are provided as the guide portion 22 when viewed from the axial direction Da is described. However, the guide portion 22 is not limited to the shape of each of the above embodiments, as long as it extends so as to intersect both the circumferential direction Dc2 and the axial direction Da. The inner guide 22I and the outer guide 22O may have other shapes such as a combination of straight lines and curved lines.
In the above-described embodiments, the case where the through-hole 23 is formed in a rectangular shape that is long in the circumferential direction Dc2 as viewed from the radially outer side DrA2 has been described. However, the shape of the through-hole 23 is not limited to the above shape, and any shape may be used as long as the air a can be introduced from the radial outside DrA 2.
Claims (7)
1. A fuel injection device is provided with:
a premixer tube that introduces air into the internal space from the inlet port and discharges a mixture gas obtained by mixing the air and the fuel from the outlet port;
a fuel introduction portion that introduces fuel into the internal space; and
a downstream side plate through which an end of the premixer tube on the outlet side passes and which supports an end of the premixer tube on the downstream side,
the premixer tube includes:
a tube main body having a through hole formed in an upstream end portion on a side close to the introduction port to communicate an internal space with an external space, the through hole including a first end portion and a second end portion extending from an upstream end surface of the tube main body in an axial direction in which an axis of the premixer tube extends, and a bottom wall portion extending in a circumferential direction around the axis so as to connect downstream end portions of the first end portion and the second end portion to each other; and
and a guide portion extending from an end portion of at least one of the first end portion and the second end portion of the through hole in the circumferential direction so as to intersect both the circumferential direction and the axial direction.
2. The fuel injection device according to claim 1,
the guide portion includes an inner guide portion extending from the first end portion of the through hole in the circumferential direction toward an inner side of the introduction port and a side close to the second end portion of the through hole.
3. The fuel injection device according to claim 1 or 2,
the guide portion includes an outer guide portion extending from the second end of the through hole in the circumferential direction toward an outer side of the introduction port and a side close to the first end of the through hole.
4. The fuel injection device according to claim 1 or 2,
the guide portion and the through hole are provided in plurality at intervals in a circumferential direction of the introduction port.
5. The fuel injection device according to claim 1 or 2,
the fuel introducing portion includes a nozzle that is inserted into the internal space from the introducing port and injects fuel from a distal end portion.
6. The fuel injection device according to claim 1 or 2,
the fuel introducing part includes:
the downstream side plate;
an upstream side plate which is disposed on a side closer to the introduction port than the downstream side plate, has an upstream side through hole through which the premixer tube passes, and has a cavity formed between the upstream side plate and an outer wall of the premixer tube and the downstream side plate;
a fuel supply pipe that supplies fuel to the cavity; and
and a fuel through-hole forming portion that forms a part of an outer wall of the premixer tube and forms a fuel through-hole that penetrates the outer wall of the premixer tube.
7. A gas turbine, wherein,
a fuel injection device according to any one of claims 1 to 6 is provided.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2018101761A JP6995696B2 (en) | 2018-05-28 | 2018-05-28 | Fuel injection system and gas turbine |
| JP2018-101761 | 2018-05-28 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110542120A CN110542120A (en) | 2019-12-06 |
| CN110542120B true CN110542120B (en) | 2021-03-05 |
Family
ID=68499490
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910432050.XA Active CN110542120B (en) | 2018-05-28 | 2019-05-22 | Fuel injection device and gas turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20190360697A1 (en) |
| JP (1) | JP6995696B2 (en) |
| CN (1) | CN110542120B (en) |
| DE (1) | DE102019003480A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6979343B2 (en) * | 2017-11-30 | 2021-12-15 | 三菱パワー株式会社 | Fuel injectors, combustors, and gas turbines |
| JP6956035B2 (en) * | 2018-03-20 | 2021-10-27 | 三菱重工業株式会社 | Combustor |
| KR102474179B1 (en) * | 2021-01-15 | 2022-12-06 | 두산에너빌리티 주식회사 | Combustor with multi-tube and gas turbine including same |
| KR102437977B1 (en) * | 2021-01-18 | 2022-08-30 | 두산에너빌리티 주식회사 | Nozzle assembly, Combustor and Gas turbine comprising the same |
| KR102460001B1 (en) * | 2021-02-17 | 2022-10-26 | 두산에너빌리티 주식회사 | Micromixer module and combustor having the same |
| US20230408096A1 (en) * | 2021-11-03 | 2023-12-21 | Power Systems Mfg., Llc | Multitube pilot injection into trapped vortices in a gas turbine engine |
| KR102583222B1 (en) * | 2022-01-06 | 2023-09-25 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
| KR20230111530A (en) * | 2022-01-18 | 2023-07-25 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
| KR102607177B1 (en) * | 2022-01-28 | 2023-11-29 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
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- 2018-05-28 JP JP2018101761A patent/JP6995696B2/en active Active
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2019
- 2019-05-10 US US16/409,061 patent/US20190360697A1/en not_active Abandoned
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Also Published As
| Publication number | Publication date |
|---|---|
| DE102019003480A1 (en) | 2019-11-28 |
| JP2019207049A (en) | 2019-12-05 |
| CN110542120A (en) | 2019-12-06 |
| US20190360697A1 (en) | 2019-11-28 |
| JP6995696B2 (en) | 2022-01-17 |
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