CN110440290A - Microring array nozzle for gas turbines - Google Patents
Microring array nozzle for gas turbines Download PDFInfo
- Publication number
- CN110440290A CN110440290A CN201810409372.8A CN201810409372A CN110440290A CN 110440290 A CN110440290 A CN 110440290A CN 201810409372 A CN201810409372 A CN 201810409372A CN 110440290 A CN110440290 A CN 110440290A
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- China
- Prior art keywords
- microring array
- fuel
- hole
- component
- pipe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000446 fuel Substances 0.000 claims abstract description 126
- 238000002485 combustion reaction Methods 0.000 claims abstract description 13
- 238000005192 partition Methods 0.000 claims description 20
- 239000011148 porous material Substances 0.000 claims description 8
- 239000007921 spray Substances 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 239000011799 hole material Substances 0.000 claims 15
- 230000010355 oscillation Effects 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 22
- 239000000203 mixture Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 239000003344 environmental pollutant Substances 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000005764 inhibitory process Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention discloses a kind of microring array nozzles for gas turbines, the microring array nozzle includes fuel chambers, it prewhirls component and microring array pipe, the component of prewhirling is arranged through the fuel chambers, the component of prewhirling includes inner tube, outer tube and eddy flow part, circular passage is formed between the outer tube and said inner tube, said inner tube is equipped with the first hole, the outer tube is equipped with the second hole, the microring array pipe is located in the fuel chambers, the microring array pipe is equipped with third hole, wherein, a part of fuel in the circular passage, which enters to prewhirl with the air in inner tube in inner tube through the first hole, to be mixed, another part fuel being discharged from the second hole enters in microring array pipe through third hole to be mixed with the air in microring array pipe.Microring array nozzle for gas turbines of the invention, by fuel and air prewhirl mixing and microring array combine can stable point fire source, prevent flame from putting out or being lifted excessively high, enhance flame holding, inhibit combustion oscillation.
Description
Technical field
The present invention relates to technical field of gas turbine, more particularly to a kind of microring array nozzle for gas turbines.
Background technique
The mixture of compressed air and fuel burns in the burner of gas turbine, generates high-temperature flue gas and turbine is pushed to do
Function, wherein fuel and air are mixed and are sprayed to combustion zone by its nozzle (also commonly referred to as fuel nozzle) by burner.
Fuel and air mixture homogeneity is to improve fuel and air an important factor for influencing gas turbine pollutant emission and be uniformly mixed
Degree can reduce pollutant emission.
In the related technology, the nozzle of gas turbine uses microring array structure, and fuel and air are mixed in multiple microring array pipes
Enter combustion chamber after closing, the mixture of fuel and air burns under small scale, can dispersed flame face, reduce temperature ladder
Degree disperses heat release, to reduce pollutant emission.However, the nozzle of such mode is easy to happen lifting in exit flame, i.e.,
Flame root is located at the certain position of nozzle downstream, and lifting flame is not complete stability, it is easy to be gone out by external disturbance
Existing oscillation on small scale generates noise, and as the raising of nozzle exit velocity, the distance of flame lifting increase, is easy to induce combustion
Burn oscillation.
Summary of the invention
The present invention is directed to solve at least some of the technical problems in related technologies.
For this purpose, the present invention proposes a kind of microring array nozzle for gas turbines, which being capable of stable ignition
Source prevents flame from putting out or being lifted excessively high, enhancing flame holding, inhibition combustion oscillation.
The microring array nozzle for gas turbines of embodiment according to the present invention includes: fuel chambers；It prewhirls component, it is described
Component of prewhirling is arranged through the fuel chambers, and the component of prewhirling includes inner tube, the outer tube being set in said inner tube and is located at
Eddy flow part in said inner tube forms circular passage between the outer tube and said inner tube, said inner tube is equipped with the first hole, described
Outer tube is equipped with the second hole, wherein air enters said inner tube through the first end of said inner tube, fuel through the circular passage the
One end enters the circular passage, and a part of fuel in the circular passage enters in said inner tube through first hole
It is mixed with prewhirling with the air in said inner tube, mixed fuel and air of prewhirling are sprayed through the second end of said inner tube, institute
It states fuel described in another part in circular passage and the outer tube is discharged through second hole；Microring array pipe, the microring array pipe
It is located in the fuel chambers, the microring array pipe is equipped with third hole, wherein air enters institute through the first end of the microring array pipe
State microring array pipe, from second hole be discharged another part fuel of the outer tube enter through the third hole it is described micro- mixed
It closes in pipe to be mixed with the air in the microring array pipe, mixed fuel and air are sprayed through the second end of the microring array pipe
Out.
Microring array nozzle for gas turbines according to an embodiment of the present invention, the microring array nozzle by prewhirl mixing and
The mode that microring array combines realizes the mixing of fuel and air, can stable point fire source, prevent flame put out or be lifted it is excessively high,
Enhance flame holding, inhibits combustion oscillation.
In some embodiments, the flow direction along the fuel in the circular passage, first hole are located at institute
The upstream for stating the second hole, from second hole be discharged another part fuel of the outer tube along with the fuel in the ring
It flows into the third hole in the opposite direction in flow direction in shape channel.
In some embodiments, the microring array nozzle further includes adjustable plate, and the adjustable plate separates the fuel chambers
At the first fuel chambers and the second fuel chambers, the adjustable plate is equipped with multiple intercommunicating pores, component and the microring array of prewhirling
Pipe extends through first fuel chambers and second fuel chambers, and the third hole is connected to first fuel chambers, described
Second hole is connected to second fuel chambers.
In some embodiments, the microring array pipe is equipped with multiple, and multiple microring array pipes are parallel to each other.
In some embodiments, it is described prewhirl component and the microring array pipe it is parallel to each other.
In some embodiments, the component of prewhirling includes that component is prewhirled and multiple peripheries are prewhirled component in center, it is described in
Heart component of prewhirling is located at the centers of the fuel chambers, multiple peripheries prewhirl component around the center prewhirl component it is uniform between
Every arrangement.
In some embodiments, the microring array nozzle further include: central support tube, prewhirl component and one at the center
The microring array pipe is divided to be located in the central support tube；Multiple partitions, the inner end of the partition and the central support tube
Periphery wall is connected, outer end the extending radially outwardly along the central support tube of the partition, and multiple partitions are around described
Central support tube uniform intervals arrangement.
In some embodiments, the eddy flow part includes central axis and multiple swirl vanes for being located on the central axis,
There is swirl channel between the adjacent swirl vane, the swirl vane is equipped with the teasehole being connected to first hole,
A part of fuel in the circular passage enters the teasehole through first hole and sprays through the teasehole, ejection
The fuel is prewhirled in the swirl channel with the air in said inner tube and is mixed.
In some embodiments, the microring array nozzle further includes first end plate, the second end plate and shroud, the first end
Plate is located at the first end of the shroud and second end plate is located at the second end of the shroud to cross the fuel chambers.
In some embodiments, the flush with outer surface of the second end of the component of prewhirling and second end plate, it is described pre-
The first end for revolving component stretches out the first end plate, and the first end of the microring array pipe and the outer surface of the first end plate are flat
Together, the flush with outer surface of the second end of the microring array pipe and second end plate.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the microring array nozzle for gas turbines of embodiment according to the present invention；
Fig. 2 is the schematic diagram of internal structure of the microring array nozzle for gas turbines of embodiment according to the present invention；
Fig. 3 is the axis side structure schematic diagram of the microring array nozzle for gas turbines of embodiment according to the present invention；
Fig. 4 is the partial enlargement diagram of the microring array nozzle for gas turbines of embodiment according to the present invention；
Fig. 5 is the partial top view of the microring array nozzle for gas turbines of embodiment according to the present invention；
Fig. 6 is the D-D sectional view in Fig. 5 for gas turbines of embodiment according to the present invention.
Appended drawing reference:
Fuel chambers 1, the first fuel chambers 11, the second fuel chambers 12, component 2 of prewhirling, center are prewhirled component 201, and periphery is prewhirled
Component 202, inner tube 21, outer tube 22, eddy flow part 23, central axis 231, swirl vane 232, teasehole 233, swirl channel 234, the
One hole 24, circular passage 25, the second hole 26, microring array pipe 3, third hole 31, first end plate 4, the second end plate 5, shroud 6 are adjusted
Plate 7, intercommunicating pore 8, central support tube 9, partition 10.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings.Below with reference to
The embodiment of attached drawing description is exemplary, it is intended to is used to explain the present invention, and is not considered as limiting the invention.At this
In the description of invention, it is to be understood that term " center ", "upper", "lower", "front", "rear", "left", "right", "inner", "outside",
The orientation or positional relationship of the instructions such as " axial direction ", " radial direction ", " circumferential direction " is to be based on the orientation or positional relationship shown in the drawings, and is only
For the convenience of describing the present invention and simplifying the description, rather than the device or element of indication or suggestion meaning must have specific side
Position is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.
As shown in figures 1 to 6, microring array nozzle for gas turbines according to an embodiment of the present invention include fuel chambers 1, it is pre-
Revolve component 2 and microring array pipe 3.Wherein, the injection direction of mixture in as shown in Figure 1, 2 is defined for direction from top to bottom, such as
Shown in Fig. 1 arrow.Specifically, microring array nozzle further includes that first end plate 4, the second end plate 5 and shroud 6, first end plate 4 are located at set
The first end (Fig. 1,2 shown in lower end) of cover 6, the second end plate 5 are located at the second end (Fig. 1,2 shown in upper end) of shroud 6, thus
Fuel chambers 1 are crossed by first end plate 4, the second end plate 5 and shroud 6.Wherein, term " first ", " second " are only used for description mesh
, it is not understood to indicate or imply relative importance or implicitly indicates the quantity of indicated technical characteristic.It limits as a result,
Surely having the feature of " first ", " second " can explicitly or implicitly include at least one of the features.
Component 2 of prewhirling is arranged through fuel chambers 1, and specifically, the first end of component 2 of prewhirling (Fig. 1,2 shown in lower end) is stretched
First end plate 4 out, the second end (Fig. 1,2 shown in upper end) for component 2 of prewhirling protrude into the appearance in combustion chamber 1 with the second end plate 5
Face (upper surface of Fig. 1, the second end plate 5 shown in 2) is concordant.In other words, as shown in Figure 1, 2, the prewhirl lower end of component 2 is located at the
The lower section of end plate 4, the upper end for component 2 of prewhirling are protruded into combustion chamber 1 and concordant with the upper surface of the second end plate 5.
As shown in fig. 6, component 2 of prewhirling includes inner tube 21, outer tube 22 and eddy flow part 23, inner tube 21 is equipped with the first hole 24,
External air can be entered in inner tube 21 by the first end of inner tube 21 (Fig. 1,2 shown in lower end).
Outer tube 22 is set in inner tube 21, circular passage 25 is formed between outer tube 22 and inner tube 21, as shown in figure 4, outer tube
22 are equipped with the second hole 26.Specifically, outer tube 22 and inner tube 21 are coaxially disposed.External fuel can pass through circular passage 25
First end (Fig. 1,2 shown in lower end) enters in circular passage 25, and a part of fuel in circular passage 25 is through in inner tube 21
First hole 24 enters in inner tube 21；Outer tube is discharged through the second hole 26 on outer tube 22 in another part fuel in circular passage 25
22。
Eddy flow part 23 is located in inner tube 21, into inner tube 21 air and a part of fuel under the action of eddy flow part 23
Can prewhirl mixing, the mixtures of mixed fuel and air of prewhirling by the second end of inner tube 21 (Fig. 1, shown in 2 on
End) it sprays.
Specifically, as shown in figure 5, eddy flow part 23 includes central axis 231 and the multiple swirl vanes being located on central axis 231
232, multiple swirl vanes 232 are arranged around 231 uniform intervals of central axis, have swirl channel between adjacent swirl vane 232
234, swirl vane 232 is interior to have the fuel channel being connected to the first hole 24 in inner tube 21, and the end face of swirl vane 232 is equipped with
With multiple teaseholes 233 of fuel passage, the air in inner tube 21 enters swirl channel through the first end of swirl channel 234
In 234, a part of fuel in circular passage 25 enters the fuel channel in swirl vane 232 through the first hole 24, and through multiple
Teasehole 233 sprays, and the fuel of ejection is prewhirled in swirl channel 234 with air, mixed, mixed fuel and air of prewhirling
Mixture through swirl channel 234 second end be discharged.In the description of the present invention, the meaning of " plurality " is at least two, example
Such as two, three etc., unless otherwise specifically defined.
Microring array pipe 3 is located in fuel chambers 1, specifically, the first end of microring array pipe 3 (Fig. 1,2 shown in lower end) and the
The outer surface (lower surface of Fig. 1, first end plate 4 shown in 2) of end plate 4 concordantly, the second end of microring array pipe 3 (Fig. 1, shown in 2
Upper end) with the flush with outer surface of the second end plate 5.
Microring array pipe 3 is equipped with third hole 31, wherein and outside air enters microring array pipe 3 through the first end of microring array pipe 3,
Enter microring array through the third hole 31 on microring array pipe 3 from another part fuel of the second hole 26 discharge outer tube 22 on outer tube 22
In pipe 3, to carry out microring array with the air in microring array pipe 3, second end of the fuel and air through microring array pipe 3 after microring array
It sprays.
Microring array nozzle for gas turbines according to an embodiment of the present invention, the microring array nozzle setting prewhirl component and
Microring array pipe realizes prewhirl mixing and the microring array of fuel and air respectively, by combining two kinds of hybrid modes being capable of stable point
Fire source prevents flame from putting out or being lifted excessively high, enhancing flame holding, inhibition combustion oscillation.
In the present invention unless specifically defined or limited otherwise, fisrt feature in the second feature " on " or " down " can be with
It is that the first and second features directly contact or the first and second features pass through intermediary mediate contact.
In some embodiments, the flow direction along fuel in circular passage 25, such as the side in Fig. 1,2 from top to bottom
To the first hole 24 is located at the upstream in the second hole 26, and another part fuel edge being discharged from the second hole 26 of outer tube 22 and fuel exist
It flows into third hole 31 in the opposite direction in flow direction in circular passage 25.In other words, as shown in Figure 1, 2, fuel is in annular
Flow direction in channel 25 is from top to bottom that the first hole 24 is located at the lower section in the second hole 26, from 26 row of the second hole of outer tube 22
Another part fuel out flows into the third hole 31 on microring array pipe 3 along direction from top to bottom.Fisrt feature is
Two features " top " can be fisrt feature and be directly above or diagonally above the second feature, or be merely representative of first feature horizontal height height
In second feature.Fisrt feature can be fisrt feature in second feature " lower section " and be directly under or diagonally below the second feature, or
First feature horizontal height is merely representative of less than second feature.
In some embodiments, microring array nozzle for gas turbines further includes adjustable plate 7, and adjustable plate 7 is by fuel chambers 1
The first fuel chambers 11 and the second fuel chambers 12 are separated into, i.e. adjustable plate 7 is located between first end plate 4 and the second end plate 5, specifically
Ground, first end plate 4, adjustable plate 7 and the second end plate 5 are parallel to each other, and adjustable plate 7 is arranged adjacent to the second end plate 5.
Specifically, the second fuel chambers 12 are located at the top of the first fuel chambers 11, i.e., are between first end plate 4 and adjustable plate 7
First fuel chambers 11 are the second fuel chambers 12 between second end plate 5 and adjustable plate 7.
Adjustable plate 7 is equipped with multiple intercommunicating pores 8, prewhirls component 2 and microring array pipe 3 extends through the first fuel chambers 11 and the
Two fuel chambers 12, the third hole 31 on microring array pipe 3 are connected to the first fuel chambers 11, the second hole 26 and the second combustion on outer tube 22
Expect that room 12 is connected to.Second fuel chambers 12 are entered by another part fuel of the second hole 26 discharge outer tube 22, then through on adjustable plate 7
Intercommunicating pore 8 enters the first fuel chambers 11, to be entered in microring array pipe 3 by third hole 31.
Specifically, as shown in Figure 1, 2, prewhirl component 2 lower end stretch out first end plate 4 lower surface, the upper of component 2 of prewhirling
It holds concordant with the upper surface of the second end plate 5 across adjustable plate 7；The lower end of microring array pipe 3 is concordant with the lower surface of first end plate 4,
The upper end of microring array pipe 3 is concordant with the upper surface of the second end plate 5.
In some embodiments, microring array pipe 3 is equipped with multiple, and multiple microring array pipes 3 are parallel to each other.Further, in advance
It revolves component 2 and microring array pipe 3 is parallel to each other.
In some embodiments, component 2 of prewhirling includes that component 201 is prewhirled and multiple peripheries are prewhirled component 202, center in center
It prewhirls component 201 and periphery component 202 of prewhirling includes inner tube 21, outer tube 22 and eddy flow part 23, wherein center is prewhirled component
201 be located at fuel chambers 1 center, multiple peripheries prewhirl component 202 around center prewhirl 201 uniform intervals of component arrangement.Specifically
Ground, as shown in Figure 2,3, microring array nozzle for gas turbines is equipped with that component 201 is prewhirled at a center and six peripheries are prewhirled
Component 202, center component 201 of prewhirling are located at the centers of fuel chambers 1, and component 202 is prewhirled around fuel chambers 1 in six peripheries
Center uniform intervals arrangement.
In some embodiments, microring array nozzle for gas turbines further includes central support tube 9 and multiple partitions 10,
Center is equipped in central support tube 9 to prewhirl component 201 and a part of microring array pipe 3；The inner end of partition 10 and central support tube 9
Periphery wall is connected, outer end the extending radially outwardly along central support tube 9 of partition 10, and multiple partitions 10 surround central support tube 9
Uniform intervals arrangement.Specifically, as shown in Figure 2,3,9 periphery of central support tube is set there are six partition 10, and a center is pre-
Rotation component 201 is located at the center of central support tube 9, and multiple partitions 10 are arranged around 9 uniform intervals of central support tube, and per adjacent
A periphery is equipped between partition 10 to prewhirl component 202.In the present invention unless specifically defined or limited otherwise, term " phase
Even ", the terms such as " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；
It can be directly connected, it can also indirectly connected through an intermediary, unless otherwise restricted clearly.For the common of this field
For technical staff, the specific meanings of the above terms in the present invention can be understood according to specific conditions.
Below with reference to the accompanying drawings 1-6 describes the microring array nozzle for gas turbines of specific embodiment according to the present invention.
As shown in figures 1 to 6, microring array nozzle for gas turbines according to an embodiment of the present invention include prewhirl component 2,
Microring array pipe 3, first end plate 4, the second end plate 5, shroud 6, adjustable plate 7, central support tube 9 and six partitions 10, first end plate 4
It is located at the lower end of shroud 6, the second end plate 5 is located at the upper end of shroud 6, so that first end plate 4, the second end plate 5 and shroud 6 cross combustion
Expect room 1.Central support tube 9 is located at the center of fuel chambers 1 and along the axially extending of fuel chambers 1, the inner end of partition 10 and center branch
The periphery wall of stay tube 9 is connected, outer end the extending radially outwardly along central support tube 9 of partition 10, and six partitions 10 surround center
9 uniform intervals of support tube arrangement.
Fuel chambers 1 are separated into the first fuel chambers 11 of lower end and the second fuel chambers 12 of upper end by adjustable plate 7, such as Fig. 1,2
Shown, the second end plate 5, adjustable plate 7 and first end plate 4 are set gradually and parallel to each other from top to bottom, and adjustable plate 7 is equipped with multiple
Intercommunicating pore 8, the fuel in the second fuel chambers 12 enter the first fuel chambers 11 through intercommunicating pore 8.
The prewhirl lower end of component 2 is located at the lower section of first end plate 4, and the upper end for component 2 of prewhirling passes through adjustable plate 7 and second end
The upper surface of plate 5 is concordant.Component 2 of prewhirling includes that component 201 is prewhirled and six peripheries are prewhirled component 202 in a center, and center is pre-
Rotation component 201 is located at the center of fuel chambers 1 and is located at the center of central support tube 9, and component 202 is prewhirled around center in six peripheries
201 uniform intervals of component of prewhirling arrangement, and be equipped with a periphery between each adjacent separator 10 and prewhirl component 202.
Component 201 is prewhirled at center and periphery is prewhirled, and component 202 includes inner tube 21, outer tube 22 and eddy flow part 23, inner tube 21
Be equipped with the first hole 24, the first hole 24 is arranged adjacent to the lower end of inner tube 21, external air can by the lower end of inner tube 21 into
Enter in inner tube 21.
Outer tube 22 is set in inner tube 21 and is coaxially disposed with inner tube 21, forms circular passage between outer tube 22 and inner tube 21
25, outer tube 22 is equipped with the second hole 26, and the second hole 26 is connected to the second fuel chambers 12.Eddy flow part 23, eddy flow are equipped in inner tube 21
Part 23 includes central axis 231 and the multiple swirl vanes 232 being located on central axis 231, and multiple swirl vanes 232 surround central axis
231 uniform intervals arrangement, and there is swirl channel 234 between adjacent swirl vane 232.It is logical with fuel in swirl vane 232
Road, the fuel channel are connected to the first hole 24 in inner tube 21, and the end face of swirl vane 232 is equipped with more with fuel passage
A teasehole 233.Wherein, external fuel is able to enter in circular passage 25, in a part of fuel warp in circular passage 25
The first hole 24 on pipe 21 enters the fuel channel in swirl vane 232, and the fuel in fuel channel is sprayed through teasehole 233,
The fuel of ejection is prewhirled in swirl channel 234 with the air in inner tube 21, is mixed；Another part fuel in circular passage 25
Outer tube 22 is discharged through the second hole 26 on outer tube 22.
Multiple microring array pipes 3 parallel to each other are located in fuel chambers 1, and microring array pipe 3 and component 2 of prewhirling are parallel to each other, and
The lower end of microring array pipe 3 is concordant with the lower surface of first end plate 4, and the upper surface of the upper end of microring array pipe 3 and the second end plate 5 is flat
Together.Microring array pipe 3 is equipped with third hole 31, and third hole 31 is connected to the first fuel chambers 11, wherein outside air is through microring array pipe 3
First end enter microring array pipe 3, from outer tube 22 the second hole 26 discharge outer tube 22 another part fuel enter second combustion
Expect room 12, then enter the first fuel chambers 11 through the intercommunicating pore 8 on adjustable plate 7, to enter microring array pipe 3 by third hole 31
Interior, to carry out microring array with the air in microring array pipe 3, the fuel and air after microring array are sprayed through the upper end of microring array pipe 3.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " example ", " specifically show
The description of example " or " some examples " etc. means specific features, structure, material or spy described in conjunction with this embodiment or example
Point is included at least one embodiment or example of the invention.In the present specification, schematic expression of the above terms are not
It must be directed to identical embodiment or example.Moreover, particular features, structures, materials, or characteristics described can be in office
It can be combined in any suitable manner in one or more embodiment or examples.In addition, without conflicting with each other, the skill of this field
Art personnel can tie the feature of different embodiments or examples described in this specification and different embodiments or examples
It closes and combines.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, modifies, replacement and variant.
Claims (10)
1. a kind of microring array nozzle for gas turbines characterized by comprising
Fuel chambers；
It prewhirls component, the component of prewhirling is arranged through the fuel chambers, and the component of prewhirling includes inner tube, is set in described
Outer tube on pipe and the eddy flow part being located in said inner tube, form circular passage between the outer tube and said inner tube, described interior
Pipe is equipped with the first hole, and the outer tube is equipped with the second hole, wherein air enters said inner tube, fuel through the first end of said inner tube
First end through the circular passage enters the circular passage, and a part of fuel in the circular passage is through described the
One hole enters in said inner tube to be mixed with prewhirling with the air in said inner tube, and mixed fuel and air of prewhirling are through described interior
The second end of pipe sprays, and the outer tube is discharged through second hole in fuel described in another part in the circular passage；
Microring array pipe, the microring array pipe are located in the fuel chambers, and the microring array pipe is equipped with third hole, wherein air warp
The first end of the microring array pipe enters the microring array pipe, and described another part combustion of the outer tube is discharged from second hole
Material enters in the microring array pipe through the third hole to mix with the air in the microring array pipe, mixed fuel and sky
Gas is sprayed through the second end of the microring array pipe.
2. microring array nozzle for gas turbines according to claim 1, which is characterized in that along the fuel described
Flow direction in circular passage, first hole are located at the upstream in second hole, and the outer tube is discharged from second hole
Another part fuel flow into described along the direction opposite with the flow direction of the fuel in the circular passage
Third hole.
3. microring array nozzle for gas turbines according to claim 2, which is characterized in that it further include adjustable plate, institute
It states adjustable plate and the fuel chambers is separated into the first fuel chambers and the second fuel chambers, the adjustable plate is equipped with multiple intercommunicating pores,
It is described to prewhirl component and the microring array pipe extends through first fuel chambers and second fuel chambers, the third hole with
The first fuel chambers connection, second hole is connected to second fuel chambers.
4. microring array nozzle for gas turbines according to claim 1, which is characterized in that the microring array pipe is equipped with
Multiple, multiple microring array pipes are parallel to each other.
5. microring array nozzle for gas turbines according to claim 4, which is characterized in that component and the institute of prewhirling
It is parallel to each other to state microring array pipe.
6. microring array nozzle for gas turbines according to claim 5, which is characterized in that the component of prewhirling includes
Component is prewhirled at center and multiple peripheries are prewhirled component, center component of prewhirling is located at the centers of the fuel chambers, multiple described
Periphery prewhirl component around the center prewhirl component uniform intervals arrangement.
7. microring array nozzle for gas turbines according to claim 6, which is characterized in that further include:
Central support tube, component is prewhirled at the center and a part of microring array pipe is located in the central support tube；
Multiple partitions, the inner end of the partition are connected with the periphery wall of the central support tube, and the outer end of the partition is along described
Central support tube extends radially outwardly, and multiple partitions are arranged around the central support tube uniform intervals.
8. microring array nozzle for gas turbines according to claim 1, which is characterized in that during the eddy flow part includes
Mandrel and the multiple swirl vanes being located on the central axis have swirl channel, the rotation between the adjacent swirl vane
Stream blade is equipped with the teasehole that is connected to first hole, a part of fuel in the circular passage through first hole into
Enter the teasehole and sprayed through the teasehole, the fuel of ejection and the air in said inner tube are in the swirl channel
It inside prewhirls mixing.
9. microring array nozzle for gas turbines according to claim 1 to 8, which is characterized in that further include
First end plate, the second end plate and shroud, the first end plate is located at the first end of the shroud and second end plate is located at institute
The second end of shroud is stated to cross the fuel chambers.
10. microring array nozzle for gas turbines according to claim 9, which is characterized in that the component of prewhirling
The flush with outer surface of second end and second end plate, the first end of the component of prewhirling stretches out the first end plate, described micro-
The flush with outer surface of the first end of mixing tube and the first end plate, the second end of the microring array pipe and second end plate
Flush with outer surface.
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| CN115355536A (en) * | 2022-08-17 | 2022-11-18 | 北京理工大学 | Oxyhydrogen micro-mixed combustion device suitable for gas turbine and use method thereof |
| CN115451431A (en) * | 2022-09-22 | 2022-12-09 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle premixing system for combustion chamber of gas turbine |
| CN116697405A (en) * | 2023-05-31 | 2023-09-05 | 中国航发燃气轮机有限公司 | Premixing rotational flow micro-mixing nozzle and combustion chamber |
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| CN116697405B (en) * | 2023-05-31 | 2024-01-19 | 中国航发燃气轮机有限公司 | Premixing rotational flow micro-mixing nozzle and combustion chamber |
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|---|---|
| CN110440290B (en) | 2024-03-29 |
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