CN108019749A - A kind of swirl-flow premixed nozzle of radial grading - Google Patents
A kind of swirl-flow premixed nozzle of radial grading Download PDFInfo
- Publication number
- CN108019749A CN108019749A CN201711341715.3A CN201711341715A CN108019749A CN 108019749 A CN108019749 A CN 108019749A CN 201711341715 A CN201711341715 A CN 201711341715A CN 108019749 A CN108019749 A CN 108019749A
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- Prior art keywords
- air flow
- main body
- stage fuel
- radial
- combustion
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 72
- 239000000446 fuel Substances 0.000 claims abstract description 67
- 238000002347 injection Methods 0.000 claims abstract description 18
- 239000007924 injection Substances 0.000 claims abstract description 18
- 230000009977 dual effect Effects 0.000 claims 1
- 241000734468 Listera Species 0.000 abstract 1
- 239000003344 environmental pollutant Substances 0.000 description 7
- 231100000719 pollutant Toxicity 0.000 description 7
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 6
- 239000000243 solution Substances 0.000 description 6
- 238000009792 diffusion process Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 230000008602 contraction Effects 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
Classifications
-
- 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
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
-
- 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
- F23D14/48—Nozzles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a kind of swirl-flow premixed nozzle of radial grading.The swirl-flow premixed nozzle of radial grading includes pre-combustion grade fuel channel main body, main combustion stage fuel channel main body, main air flow path bodies, flow-disturbing sleeve；Wherein, it is provided with pre-combustion grade fuel channel in the pre-combustion grade fuel channel main body；Main combustion stage fuel channel is provided with the main combustion stage fuel channel main body；Main air runner is formed between main air flow path bodies and pre-combustion grade fuel channel main body；Secondary air runner is formed between flow-disturbing sleeve and main air flow path bodies；Twayblade swirl-flow devices are provided with pre-combustion grade fuel channel main body；Level-one spray-hole and two-stage injection hole are provided with pre-combustion grade fuel channel main body；Radial vortex device is provided with secondary air runner.The application is simple in structure, and the mixing efficiency of fuel and air is high, and the pressure loss is small, meets engine request.
Description
Technical Field
The invention relates to the technical field of gas turbine combustors, in particular to a radial grading rotational flow premixing nozzle.
Background
With the environmental protection issues being emphasized, the requirements of various countries in the world for the emission standards of gas turbine combustors are becoming more and more strict, and the gas turbine is generally required to maintain the emission of the combustors at a low level in the load range of 50% and above, while maintaining high combustion efficiency. The pollutants discharged from the combustion chamber mainly include nitrogen oxides, carbon monoxide and hydrocarbon compounds, wherein nitrogen oxides NOx are an important index of pollutant emission, and a premixed combustion technology is widely adopted for achieving the purpose of low NOx emission. Most of the premixed combustion technologies adopt a rotational flow mixing technology to realize good mixing of fuel and oxidant, and lean premixed combustion is carried out, but when a combustion chamber works in the state, the problems of unstable combustion, thermoacoustic oscillation and the like are easily generated. To solve the problem, the engineering usually adopts a mode of organizing certain diffusion flames to stabilize the premixed flames, and for the diffusion flames, the more fuel participating in diffusion combustion, the better the combustion stability, but the poorer the pollutant NOx emission performance. Therefore, in order to solve the contradiction between pollutant emission and combustion flame stability, designing a nozzle capable of reasonably organizing premixed combustion and diffusion combustion becomes the core technology of a low-emission combustor.
In the prior art, the design forms of the nozzles of the combustion chamber are various, particularly the structure of the nozzles for injecting gaseous fuel is complex and various, but most of the nozzles are complex in structure form, the change of the fuel mixing condition and the speed type is not ideal enough, and the problem of contradiction between stable combustion and low emission cannot be solved in engineering.
The existing gaseous fuel nozzle has complicated and various structural forms, but the structure of a premixing nozzle which comprehensively considers low-emission combustion and stable flame is less, and the nozzles cannot solve the contradiction problem of low-emission and stable combustion in engineering.
1) For the premixing nozzle, in order to realize the uniform mixing of fuel and air and meet the requirements of different working conditions, the structural design of the nozzle is complex, the processing and adjusting difficulty is increased, and risks such as tempering are caused.
2) The mixing nozzle adopting the traditional structure has a simple structure, but cannot realize uniform mixing of fuel and air, and causes the problems of overhigh pollutant discharge and the like.
3) For the premixing nozzle, although the uniform mixing of fuel and air can be realized and the pollutant discharge is reduced, the problems of unstable combustion, thermoacoustic oscillation, flameout and the like are easy to occur.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a radially staged swozzle premix nozzle that overcomes or at least alleviates at least one of the above-mentioned deficiencies of the prior art.
In order to achieve the purpose, the invention provides a radial grading rotational flow premixing nozzle which comprises a pre-combustion stage fuel channel main body, a main combustion stage fuel channel main body, a primary air flow channel main body and a turbulence sleeve; a pre-combustion stage fuel passage is arranged in the pre-combustion stage fuel passage main body; a main combustion stage fuel channel is arranged in the main combustion stage fuel channel main body;
a primary air flow channel is formed between the inner wall of the primary air flow channel main body and the outer wall of the pre-combustion stage fuel channel main body;
a secondary air flow channel is formed between the inner wall of the turbulence sleeve and the outer wall of the primary air flow channel main body;
the pre-combustion stage fuel passage main body is provided with a double-blade rotational flow device, and the double-blade rotational flow device is positioned in the primary air flow passage;
the precombustion stage fuel passage main body is provided with a primary jet hole and a secondary jet hole which are communicated with the precombustion stage fuel passage and the primary air flow passage; the primary jet hole is opposite to the turbulent flow sleeve; the secondary jet hole is arranged at the position where the double-blade swirling device is arranged on the pre-combustion stage fuel passage main body;
a radial rotational flow device is arranged in the secondary air flow channel, a radial rotational flow blade is arranged in the radial rotational flow device, and an inner flow channel communicated with the outer part of the radial rotational flow blade is arranged in the radial rotational flow blade; wherein,
the primary injection hole is used for injecting the pre-combustion fuel into the primary air flow channel; the secondary injection holes are used for injecting pre-combustion stage fuel into the primary air flow passage.
Preferably, the double-blade cyclone device comprises a plurality of groups of blade groups, each group of blade group is provided with two blades, and a cyclone air flow channel is formed between each two blades; the rotational flow air flow channel is communicated with the primary air flow channel; the primary jet hole is communicated with the rotational flow air flow channel.
Preferably, the swirl air flow passage is at an angle offset from the axial direction of the pre-stage fuel passage body.
Preferably, an outlet of the swirling air flow channel formed between the two blades, which is communicated with the primary air flow channel, is a contraction outlet or an expansion outlet.
Preferably, the outlet of the radial swirl vane, which is communicated with the inner flow passage outside the radial swirl vane, is in the form of an open or arrayed injection port.
Preferably, the number of the primary injection holes is plural; the number of the secondary injection holes is plural.
Preferably, the flow disturbing sleeve comprises a flow disturbing device and a secondary venturi structure, the flow disturbing device intersecting the secondary venturi structure.
Preferably, the highest point of the flow perturbation means in the flow passage is no higher than the highest point of the throat of the venturi structure.
Preferably, the number of the flow disturbing devices is plural.
The radial grading rotational flow premixing nozzle completes the proper mixing proportion of fuel and air at the nozzle outlet, achieves reasonable speed distribution, enters a combustion chamber to be organized into a stable flow field and a combustion field, and can achieve the purposes of low-emission combustion and flame stabilization. Meanwhile, the nozzle is simple in structure, high in mixing efficiency of fuel and air, small in pressure loss and capable of meeting engineering requirements.
Drawings
FIG. 1 is a schematic view of a radially staged swozzle premix nozzle according to a first embodiment of the present application.
FIG. 2 is a schematic view of a two-bladed swirler assembly of the radially staged swirl premix nozzle shown in FIG. 1.
FIG. 3 is a schematic view of the radial swirler assembly of the radially staged swirl premix nozzle shown in FIG. 1.
FIG. 4 is a schematic view of a turbulator sleeve configuration in the radially staged swozzle shown in FIG. 1.
Reference numerals:
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
FIG. 1 is a schematic view of a radially staged swozzle premix nozzle according to a first embodiment of the present application. FIG. 2 is a schematic view of a two-bladed swirler assembly of the radially staged swirl premix nozzle shown in FIG. 1. FIG. 3 is a schematic view of the radial swirler assembly of the radially staged swirl premix nozzle shown in FIG. 1. FIG. 4 is a schematic view of a turbulator sleeve configuration in the radially staged swozzle shown in FIG. 1.
The radial staged swirl premix nozzle shown in fig. 1 to 4 comprises a pre-combustion stage fuel passage main body, a main combustion stage fuel passage main body, a primary air flow passage main body and a turbulence sleeve; wherein,
a pre-combustion stage fuel channel 1 is arranged in the pre-combustion stage fuel channel main body;
a main combustion stage fuel channel 2 is arranged in the main combustion stage fuel channel main body;
a primary air flow channel 3 is formed between the inner wall of the primary air flow channel main body and the outer wall of the pre-combustion fuel channel main body;
a secondary air flow channel 4 is formed between the inner wall of the turbulence sleeve and the outer wall of the primary air flow channel main body;
a double-blade rotational flow device 11 is arranged on the main body of the pre-combustion stage fuel passage, and the double-blade rotational flow device 11 is positioned in the primary air flow passage 3;
the precombustion stage fuel passage main body is provided with a primary jet hole 9 and a secondary jet hole 10 which are communicated with the precombustion stage fuel passage 1 and the primary air flow passage 3; the primary jet hole 9 is opposite to the turbulent flow sleeve 5; the position of the secondary injection hole 10 is the position of a double-blade swirling device 11 arranged on the main body of the pre-combustion stage fuel channel;
a radial rotational flow device 13 is arranged in the secondary air flow channel 4, a radial rotational flow blade is arranged in the radial rotational flow device 13, and an inner flow channel communicated with the outer part of the radial rotational flow blade is arranged in the radial rotational flow blade; wherein,
the primary injection hole 9 is used for injecting the pre-combustion fuel into the primary air flow passage 3; the secondary injection hole 10 is used to inject the pre-combustion stage fuel into the primary air flow passage 3.
When the gas fuel is used, semi-premixed diffusion combustion can be formed in the central area of the head of the combustion chamber, and the working mode of full-premixed combustion is realized on the outer layer of the central area. In the primary air channel, a part of fuel of the pre-combustion stage is firstly mixed with a small amount of air in a narrow channel between the axial swirl blades of each group, the fuel is contracted through the outlet channel and then is jetted to be partially premixed with the air, the other part of the fuel is mixed with incoming flow at the throat of the contraction section of the venturi tube in a jetting mode, meanwhile, in the secondary air channel, the fuel of the main combustion stage and the air are completely premixed, and the graded swirl premixing nozzle can organize a stable combustion flow field at the head of the combustion chamber, so that the emission of pollutants in the combustion chamber is effectively reduced.
Referring to fig. 2, in the present embodiment, the dual-blade cyclone device 11 includes a plurality of blade sets, each blade set has two blades, and a cyclone air flow passage is formed between each two blades; the rotational flow air flow passage is communicated with the primary air flow passage; the first-stage jet hole is communicated with the rotational flow air flow channel.
Referring to fig. 2, in the present embodiment, the swirl air flow passage is at an angle offset from the axial direction of the pre-combustion stage fuel passage body.
Referring to fig. 2, in the present embodiment, an outlet of the swirling air flow channel formed between the two blades, which communicates with the primary air flow channel, is a constricted outlet or an expanded outlet.
Referring to fig. 3, in the present embodiment, the outlet of the radial swirl vane communicating with the inner flow passage outside the radial swirl vane is in the form of an open or array of nozzle openings.
Referring to fig. 2, in the present embodiment, the number of the primary injection holes is plural; the number of the secondary injection holes is plural.
Referring to fig. 4, in this embodiment, the flow perturbation sleeve comprises a flow perturbation device 6 and a secondary venturi structure 7, the flow perturbation device 6 intersecting the secondary venturi structure 7.
Referring to fig. 4, in this embodiment, the highest point of the flow perturbation means 6 in the flow passage is no higher than the highest point of the throat of the venturi structure 7.
Referring to fig. 4, in the present embodiment, the number of the spoiler 6 is plural.
In the present embodiment, the swirling direction of the double-blade swirling device and/or the radial swirling device 13 can be clockwise or counterclockwise as viewed from the downstream.
The shape of the secondary injection hole can be set according to the requirement. Such as circular, oval, triangular, etc.
Referring to fig. 1, in the present embodiment, a primary venturi structure 8 is provided on the primary air flow passage body.
The first-stage injection holes 9 are distributed in an inclined radial direction and can correspond to the throat of the first-stage venturi 8 and also can correspond to the front section or the rear section.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (9)
1. A radial grading rotational flow premixing nozzle is characterized by comprising a pre-combustion stage fuel channel main body, a main combustion stage fuel channel main body, a primary air flow channel main body and a turbulence sleeve; wherein,
a pre-combustion stage fuel passage (1) is arranged in the pre-combustion stage fuel passage main body;
a main combustion stage fuel channel (2) is arranged in the main combustion stage fuel channel main body;
a primary air flow channel (3) is formed between the inner wall of the primary air flow channel main body and the outer wall of the pre-combustion stage fuel channel main body;
a secondary air flow channel (4) is formed between the inner wall of the turbulence sleeve and the outer wall of the primary air flow channel main body;
the main body of the pre-combustion stage fuel passage is provided with a double-blade rotational flow device (11), and the double-blade rotational flow device (11) is positioned in the primary air flow passage (3);
the precombustion stage fuel passage main body is provided with a primary jet hole (9) and a secondary jet hole (10) which are communicated with the precombustion stage fuel passage (1) and the primary air flow passage (3); the primary jet hole (9) is opposite to the turbulent flow sleeve (5); the secondary injection hole (10) is arranged at the position where a double-blade swirling device (11) is arranged on the pre-combustion stage fuel passage main body;
a radial rotational flow device (13) is arranged in the secondary air flow channel (4), a radial rotational flow blade is arranged inside the radial rotational flow device (13), and an inner flow channel communicated with the outer part of the radial rotational flow blade is arranged in the radial rotational flow blade; wherein,
the primary injection hole (9) is used for injecting the pre-combustion fuel into the primary air flow passage (3); the secondary injection hole (10) is used for injecting pre-combustion stage fuel into the primary air flow passage (3).
2. The radially staged swozzle premix nozzle of claim 1, wherein said dual vane swirler assembly (11) comprises a plurality of sets of two vanes forming a swirl air flow path therebetween; the rotational flow air flow channel is communicated with the primary air flow channel; the primary jet hole is communicated with the rotational flow air flow channel.
3. The radially staged swozzle premix nozzle of claim 2, wherein said swirl air flow passage is angled away from an axial direction of said pre-combustion stage fuel passage body.
4. The radially staged swozzle premix nozzle of claim 3, wherein the exit of the swirling air flow path formed between two of said vanes communicating with said primary air flow path is a converging exit or a diverging exit.
5. The radially staged swozzle premix nozzle of claim 1, wherein the outlets of the inner flow passages of the radial swirl vanes communicating with the outside of the radial swirl vanes are in the form of open or arrayed nozzle orifices.
6. The radially staged swozzle premix nozzle of claim 1, wherein said primary injection orifices are plural in number; the number of the secondary injection holes is plural.
7. The radially staged swozzle as defined in claim 1, wherein said turbulator sleeve comprises a turbulator (6) and a secondary venturi structure (7), said turbulator (6) intersecting said secondary venturi structure (7).
8. The radial grading rotational flow premixing nozzle as required in claim 7 is characterized in that the highest point of the flow disturbing device (6) in the flow channel is not higher than the highest point of the throat of the venturi structure (7).
9. The radially staged swozzle premix nozzle of claim 8, wherein said turbulators (6) are plural in number.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711341715.3A CN108019749A (en) | 2017-12-14 | 2017-12-14 | A kind of swirl-flow premixed nozzle of radial grading |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711341715.3A CN108019749A (en) | 2017-12-14 | 2017-12-14 | A kind of swirl-flow premixed nozzle of radial grading |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108019749A true CN108019749A (en) | 2018-05-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711341715.3A Pending CN108019749A (en) | 2017-12-14 | 2017-12-14 | A kind of swirl-flow premixed nozzle of radial grading |
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| Country | Link |
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| CN (1) | CN108019749A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113983496A (en) * | 2021-09-23 | 2022-01-28 | 中国联合重型燃气轮机技术有限公司 | Nozzle, combustion chamber and gas turbine |
| CN114087607A (en) * | 2020-07-27 | 2022-02-25 | 芜湖美的厨卫电器制造有限公司 | Premixing device and gas water heater |
| CN115254476A (en) * | 2022-09-27 | 2022-11-01 | 成都中科翼能科技有限公司 | Nozzle structure for gas turbine |
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| CN115254476A (en) * | 2022-09-27 | 2022-11-01 | 成都中科翼能科技有限公司 | Nozzle structure for gas turbine |
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Application publication date: 20180511 |
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