CN112460638B - Coaxial grading gas fuel low-emission nozzle - Google Patents
Coaxial grading gas fuel low-emission nozzle Download PDFInfo
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- CN112460638B CN112460638B CN202011162316.2A CN202011162316A CN112460638B CN 112460638 B CN112460638 B CN 112460638B CN 202011162316 A CN202011162316 A CN 202011162316A CN 112460638 B CN112460638 B CN 112460638B
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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
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Abstract
The invention aims to provide a coaxial graded gas fuel low-emission nozzle which comprises a starting nozzle assembly, a three-level fuel air inlet system, a two-level air cyclone assembly and a two-level anti-backfire premixed gas spray pipe, wherein the starting nozzle assembly is arranged on the starting nozzle assembly; the starting nozzle can be ignited by an igniter when the combustion engine is started and the combustion chamber is accidentally extinguished; the gaseous fuel independently enters the fuel nozzle in three paths, the first-stage fuel and the second-stage fuel enter premixed air through small holes of blades of the two-stage cyclone, and the two-stage cyclone is provided with blades with different structural parameters, so that combustion areas with different backflow strengths can be formed; the two-stage anti-backfire spray pipe is matched with the two-stage swirler, so that backfire is avoided, the safety of the spray nozzle is protected, and the position of a combustion zone is stable; the third-stage fuel path is dispersedly fed into the downstream of the first two-stage combustion area through the multi-nozzle spray pipe, so that the high-working-condition fuel is uniformly fed in the axial space of the combustion chamber, the temperature uniformity in the combustion chamber is improved, the generation of nitrogen oxides is reduced, and the output power of the combustion chamber is ensured to meet the overall requirement of the gas turbine.
Description
Technical Field
The invention relates to a gas turbine, in particular to a fuel nozzle of the gas turbine.
Background
Due to the increased awareness of the global environment and the increased demand for energy flexibility, industrial low emission gas turbines are increasingly used. Gas turbines generally reduce the production of nitrogen oxide-like pollutants by increasing the air flow rate in the combustion zone of the combustor and reducing the combustion temperature. However, the problems that the combustion chamber is easy to extinguish under low working conditions, has poor variable working condition combustion stability, is easy to generate oscillatory combustion and has insufficient combustion are caused, the working condition range of safe, efficient and environment-friendly operation of the gas turbine is reduced, and the operation reliability, economy and emission performance of the gas turbine are seriously influenced.
The technical key of the low-emission wide-working-condition stable combustion is to reasonably organize the flow of fuel and air in a combustion area, so that the state of the combustion area is suitable for different working condition requirements of a gas turbine, and a fuel nozzle of a combustion chamber is a core part for organizing and adjusting the flow of working media in the combustion area. The invention carries out grading treatment on the air and fuel inlet air of the fuel nozzle, and is characterized in that the fuel can be intensively supplied to the air strong backflow area under the lower working condition, thereby improving the combustion stability; under the high working condition with better stability, the fuel is dispersedly supplied to the low reflux area and the no reflux area, thereby avoiding a local high temperature area and reducing the generation of nitrogen oxide pollutants. The invention realizes the low-emission stable combustion of the fuel nozzle in a wide working condition range, ensures that other properties of the combustion chamber meet the overall performance requirements of the gas turbine, and has important application value.
Disclosure of Invention
The invention aims to provide a coaxial graded gas fuel low-emission nozzle which can realize low-emission stable combustion of a gas turbine in a wide working condition range and solve the problems of unstable combustion of the gas turbine in a low working condition, high nitrogen oxide emission in a high working condition and the like.
The purpose of the invention is realized as follows:
the invention relates to a coaxial grading gas fuel low-emission nozzle, which is characterized in that: the burner comprises a starting igniter assembly, a first-stage burner assembly, a second-stage burner assembly, a third-stage burner assembly and a flange, wherein the first-stage burner assembly comprises a first-stage swirler, a cup-shaped piece, a first sealing piece and a second sealing piece;
the first-stage swirler comprises a cylinder section, the cylinder section is inserted into a central hole of a flange and is fastened and fixed with the outer wall surface of a shell of the starting igniter assembly through the inner wall surface of the central hole of the flange, a circular platform is arranged at an outlet of the cylinder section, two circles of bosses concentric with the cylinder section are arranged on the circular platform, three clamping grooves are arranged at the tail ends of the bosses and the circular platform, the three clamping grooves are matched and respectively used for fixing a first sealing element, a second sealing element and the flange to form three coaxial annular independent fuel division cavities, and the three fuel division cavities are respectively connected with three pipe joints on the flange, a first cover plate, a second cover plate and a third cover plate to form three independent fuel passages; each blade of the first-stage swirler is internally provided with three parallel holes which are respectively communicated with three fuel partition cavities, wherein the parallel holes communicated with the first-stage fuel partition cavity are blind holes, the parallel holes communicated with the second fuel partition cavity and the third-stage fuel partition cavity are through holes, the blade root of each blade is provided with a bayonet slot, and the throat part of the cup-shaped piece is fixed at the outlet of the first-stage swirler through the bayonet slot;
the second stage swirler is positioned through a bayonet groove of the first stage swirler, a fourth sealing element is positioned through the bayonet groove between the first stage swirler and the second stage swirler, a second stage fuel coaxial annular independent partition cavity and a third stage fuel coaxial annular independent partition cavity are formed in the second stage swirler, two stages of gas fuel flowing out of a through hole of a blade of the first stage swirler are respectively guided into a blade inner hole channel of the second stage swirler, the second stage fuel coaxial annular independent partition cavity is communicated with a blind hole in the blade of the second stage swirler, the third stage fuel coaxial annular independent partition cavity is communicated with a through hole in the blade of the second stage swirler, the blades of the second stage swirler are respectively and uniformly distributed around the circumferential direction of a central shaft of a nozzle, the root part of the blade of the second stage swirler is provided with the bayonet groove, and a second cover plate is positioned and connected with the second stage swirler through the bayonet groove;
the partition board and the cylinder are positioned through bayonet grooves at the root parts of the blades of the second-stage swirler and are fixed with the second-stage swirler, a cavity formed between the partition board and the cylinder is connected with through holes on the blades of the second-stage swirler to guide third-stage gas fuel into a third-stage burner assembly from the second-stage burner assembly, a hole with a bayonet groove is formed in the cylinder, and the nozzle is inserted into the bayonet groove hole.
The present invention may further comprise:
1. the first-stage gas fuel enters the first fuel passage through the first-stage pipe joint, enters the first-stage swirler through the hole channel on the flange, flows into the blind hole of the first-stage swirler blade through the first-stage fuel partition cavity, is sprayed out through the small hole on the blade, and simultaneously enters the first-stage swirler through the channel formed by the first-stage swirler blade, and enters the cup-shaped piece after being mixed with premixed gas formed by the gas fuel, and is ignited by the starting torch to form a first-stage combustion area.
2. Part of fuel enters a second-stage fuel passage through a second-stage pipe joint, enters a second-stage swirler through a flange and a first-stage swirler vane upper hole channel, flows into a second-stage swirler vane through a third sealing element and a fourth sealing element inner ring cavity, and is sprayed out through a vane upper hole; meanwhile, air enters the second-stage combustor assembly through a channel formed by the second-stage swirler vanes, premixed gas formed by mixing with fuel enters the pressing piece, and flame in the first-stage combustion area is ignited to form a second-stage combustion area.
3. Part of the fuel enters a third-stage fuel passage through a third-stage pipe joint, enters an annular cavity formed by the partition plate and the cylinder through the flange, the first-stage burner assembly and the second-stage burner assembly, is finally sprayed out through small holes in the nozzle and enters the downstream of a second combustion area to form axial grading of the fuel.
The invention has the advantages that: compared with other gas turbine gas fuel nozzles, the gas turbine gas fuel nozzle has the advantages that the sealing piece is additionally arranged inside the nozzle, and the sleeve structure is additionally arranged on the outer wall of the nozzle, so that the grading number of the gas fuel is increased in a limited space. The fine control of the nozzle on the gas fuel feeding position is realized, and the uniform mixing of the fuel and air during combustion is ensured. Under a lower working condition, the fuel can be intensively supplied into the air strong backflow area, so that the combustion stability is improved; under the high working condition with better stability, the fuel is dispersedly supplied to the low reflux area and the no reflux area, thereby avoiding a local high temperature area and reducing the generation of nitrogen oxide pollutants.
Drawings
FIG. 1 is a front view of the present invention;
FIG. 2 is a schematic cross-sectional view A-A of the present invention;
FIG. 3 is an exploded view of the present invention;
FIG. 4 is a schematic view of the flange plate interface with the primary burner assembly;
FIG. 5 is a schematic view of a seal and first stage swirler connection interface in the first stage combustor assembly;
FIG. 6 is a schematic view of a seal and second stage swirler connection interface in a secondary combustor assembly.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
with reference to fig. 1-6, the present invention generally comprises a starter igniter assembly 1, a first stage burner assembly 2, a second stage burner assembly 3, a third stage burner assembly 4, a flange 5, and a pipe fitting 6 as shown in fig. 2.
The starting igniter assembly 1 is inserted in a central circular hole of the flange 5 and connected to the flange 5 through six bolts 1-1 and locking gaskets 1-2, and an outlet of the starting igniter assembly 1 extends into a throat part of a cup-shaped part 2-4 of the first-stage combustor assembly 2. When the gas turbine is operated to the ignition condition, the igniter assembly 1 is started to form an ignition torch at the throat part of the cup-shaped piece 2-4, and the fuel-air premixed gas flowing in through the primary combustor is ignited.
The first stage burner assembly 2 is mainly composed of a first stage swirler 2-1, a cup-shaped member 2-4, a first sealing member 2-2 and a second sealing member 2-3. The primary swirler 2-1 is composed of a cylinder section, a fuel dividing cavity and swirl vanes, and the positions of all the parts are shown in figure 5. The cylinder section is inserted into the central hole of the flange 5 and is fastened and fixed by the inner wall surface of the central circular hole of the flange 5 and the outer wall surface of the shell of the starting igniter assembly 1. The outlet of the circular through section is provided with a circular platform, the platform is provided with two circles of circular bosses concentric with the circular cylinder section, the tail ends of the bosses and the circular platform are provided with clamping grooves for positioning, the three clamping grooves are matched and welded with a first sealing element 2-2, a second sealing element 2-3 and a flange 5 to form three coaxial annular independent fuel division cavities, and the three division cavities are respectively connected with three pipe joints 6 on the flange 5, a first cover plate 2-5, a second cover plate 3-5 and a third cover plate 4-4 to form three independent fuel passages. Each blade of the first stage swirl blade is provided with three parallel holes which are respectively communicated with the three fuel partition cavities. Wherein, the hole communicated with the first stage fuel partition cavity is a blind hole and is communicated with a plurality of small holes at the belly of the blade; and the holes of the second stage fuel partition cavity and the third stage fuel partition cavity are through holes, and the fuel can be conveyed into the lower stage combustor. The blade root of the rotational flow blade is provided with a bayonet slot, and the throat part of the cup-shaped part 2-4 is positioned and welded at the outlet of the first-stage cyclone 2-1 through the bayonet slot.
The first-stage gas fuel enters the first-stage fuel path through the first-stage pipe joint 6, enters the first-stage swirler 2-1 through the upper hole channel of the flange 5, flows into the blind hole of the swirl vane of the first-stage swirler 2-1 through the first-stage fuel partition cavity, and is sprayed out through the small hole on the swirl vane. Meanwhile, air enters the swirler through a channel formed by the first-stage swirl vanes, is mixed with gas fuel to form uniform premixed gas, then enters the cup-shaped piece 2-4, and is ignited by a starting torch. The first-stage combustion area has high backflow strength and stable combustion, and the combustion area serving as stable flame keeps burning after ignition is successful, and continues to ignite the lower-stage combustion area.
Second stage burner assembly 3 generally includes a second stage swirler 3-1, a third seal 3-2, a fourth seal 3-3, and a hold-down member 3-4. The second-stage swirler 3-1 is welded in a locating mode through a bayonet groove of the first-stage swirler 2-1, a fourth sealing piece 3-3 shown in figure 6 is arranged between the first-stage swirler 2-1 and the second-stage swirler 3-1 and welded in a locating mode through the bayonet groove, a second-stage fuel coaxial annular independent partition cavity and a third-stage fuel coaxial annular independent partition cavity are formed in the second-stage swirler 3-1, and two-stage gas fuels flowing out of through holes of blades of the first-stage swirler 2-1 are respectively guided into inner hole channels of swirl blades of the second-stage swirler 3-1. The second-stage annular independent partition cavity is communicated with a blind hole in the second-stage cyclone blade, and the blind hole is communicated with a plurality of small holes in the belly of each blade. The third-stage annular independent partition cavity is communicated with the through holes in the second-stage swirl blades. The second-stage swirl vanes are uniformly distributed around the central shaft of the nozzle in the circumferential direction. The root of the second-stage swirl vane is provided with a bayonet slot, and the compressing piece 3-4 is connected with the second-stage swirler 3-1 through the bayonet slot in a positioning welding manner.
Along with the increase of the working condition of the gas turbine, the total amount of required fuel is increased, in order to avoid overhigh temperature of a first-stage combustion area and cause overhigh emission of nitrogen oxides, partial fuel enters a second-stage fuel path through a second-stage pipe joint, enters a second-stage swirler 3-1 through a flange 5 and an upper hole channel of a blade of the first-stage swirler 2-1, flows into a swirl vane of the second-stage swirler 3-1 through an inner ring cavity of a third sealing element 3-2 and a fourth sealing element 3-3, and is ejected through a small hole on the swirl vane; meanwhile, air enters the second-stage combustor assembly 2 through a channel formed by the second-stage swirl blades, is mixed with fuel to form uniform premixed gas, then enters the pressing pieces 3-4, and is ignited by flame in the first-stage combustion area to form a second-stage combustion area.
A tertiary burner assembly 4. Mainly comprises a fuel nozzle 4-3, a clapboard 4-1 and a cylinder 4-2. The partition plate 4-1 and the cylinder 4-2 are positioned through a bayonet groove at the root part of the second-stage rotational flow blade and are connected with the second-stage cyclone 3-1 in a welding way. The cavity formed between the baffle 4-1 and the barrel 4-2 is connected to the swirler vanes of the second stage swirler 3-1 through holes to direct the third stage fuel gas from the second stage burner assembly 3 to the third stage burner assembly 4. The cylinder 4-2 is provided with a plurality of holes with clamping grooves, and the nozzle 4-3 is inserted in the clamping groove holes by welding.
Along with the further increase of the working condition, the total amount of the required fuel is increased, in order to avoid overhigh temperature of the first-stage combustion area and the second-stage combustion area and cause overhigh emission of nitrogen oxides, the fuel enters a third-stage fuel path through a third-stage pipe joint, enters an annular cavity formed by the partition plate 4-1 and the cylinder 4-2 through a channel of the flange 5, the first-stage combustor assembly 2 and the second-stage combustor assembly 3, is finally sprayed out through small holes on the nozzle 4-3 and enters the downstream of the second combustion area to form axial grading of the fuel, and the uniformity of the fuel distribution in the combustion chamber under high working condition is ensured.
Claims (4)
1. A coaxial staged low gas fuel discharge nozzle, characterized by: the burner comprises a starting igniter assembly, a first-stage burner assembly, a second-stage burner assembly, a third-stage burner assembly and a flange, wherein the first-stage burner assembly comprises a first-stage swirler, a cup-shaped piece, a first sealing piece and a second sealing piece;
the first-stage swirler comprises a cylinder section, the cylinder section is inserted into a central hole of a flange and is fastened and fixed with the outer wall surface of a shell of the starting igniter assembly through the inner wall surface of the central hole of the flange, a circular platform is arranged at an outlet of the cylinder section, two circles of bosses concentric with the cylinder section are arranged on the circular platform, three clamping grooves are arranged at the tail ends of the bosses and the circular platform, the three clamping grooves are matched and respectively used for fixing a first sealing element, a second sealing element and the flange to form three coaxial annular independent fuel division cavities, and the three fuel division cavities are respectively connected with three pipe joints on the flange, a first cover plate, a second cover plate and a third cover plate to form three independent fuel passages; each blade of the first-stage swirler is internally provided with three parallel holes which are respectively communicated with three fuel partition cavities, wherein the parallel holes communicated with the first-stage fuel partition cavity are blind holes, the parallel holes communicated with the second fuel partition cavity and the third-stage fuel partition cavity are through holes, the blade root of each blade is provided with a bayonet slot, and the throat part of the cup-shaped piece is fixed at the outlet of the first-stage swirler through the bayonet slot;
the second stage swirler is positioned through a bayonet groove of the first stage swirler, a fourth sealing element is positioned through the bayonet groove between the first stage swirler and the second stage swirler, a second stage fuel coaxial annular independent partition cavity and a third stage fuel coaxial annular independent partition cavity are formed in the second stage swirler, two stages of gas fuel flowing out of a through hole of a blade of the first stage swirler are respectively guided into a blade inner hole channel of the second stage swirler, the second stage fuel coaxial annular independent partition cavity is communicated with a blind hole in the blade of the second stage swirler, the third stage fuel coaxial annular independent partition cavity is communicated with a through hole in the blade of the second stage swirler, the blades of the second stage swirler are respectively and uniformly distributed around the circumferential direction of a central shaft of a nozzle, the root part of the blade of the second stage swirler is provided with the bayonet groove, and a second cover plate is positioned and connected with the second stage swirler through the bayonet groove;
the partition board and the cylinder are positioned through bayonet grooves at the root parts of the blades of the second-stage swirler and are fixed with the second-stage swirler, a cavity formed between the partition board and the cylinder is connected with through holes on the blades of the second-stage swirler to guide third-stage gas fuel into a third-stage burner assembly from the second-stage burner assembly, a hole with a bayonet groove is formed in the cylinder, and the nozzle is inserted into the bayonet groove hole.
2. A coaxial staged gaseous fuel low emission nozzle as defined in claim 1, wherein: the first-stage gas fuel enters the first fuel passage through the first-stage pipe joint, enters the first-stage swirler through the hole channel on the flange, flows into the blind hole of the first-stage swirler blade through the first-stage fuel partition cavity, is sprayed out through the small hole on the blade, and simultaneously enters the first-stage swirler through the channel formed by the first-stage swirler blade, and enters the cup-shaped piece after being mixed with premixed gas formed by the gas fuel, and is ignited by the starting torch to form a first-stage combustion area.
3. A coaxial staged gaseous fuel low emission nozzle as defined in claim 2, wherein: part of fuel enters a second-stage fuel passage through a second-stage pipe joint, enters a second-stage swirler through a flange and a first-stage swirler vane upper hole channel, flows into a second-stage swirler vane through a third sealing element and a fourth sealing element inner ring cavity, and is sprayed out through a vane upper hole; meanwhile, air enters the second-stage combustor assembly through a channel formed by the second-stage swirler vanes, premixed gas formed by mixing with fuel enters the pressing piece, and flame in the first-stage combustion area is ignited to form a second-stage combustion area.
4. A coaxial staged gaseous fuel low emission nozzle as defined in claim 3, wherein: part of the fuel enters a third-stage fuel passage through a third-stage pipe joint, enters an annular cavity formed by the partition plate and the cylinder through the flange, the first-stage burner assembly and the second-stage burner assembly, is finally sprayed out through small holes in the nozzle and enters the downstream of a second combustion area to form axial grading of the fuel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011162316.2A CN112460638B (en) | 2020-10-27 | 2020-10-27 | Coaxial grading gas fuel low-emission nozzle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011162316.2A CN112460638B (en) | 2020-10-27 | 2020-10-27 | Coaxial grading gas fuel low-emission nozzle |
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| CN112460638A CN112460638A (en) | 2021-03-09 |
| CN112460638B true CN112460638B (en) | 2022-04-08 |
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| CN113310071B (en) * | 2021-06-16 | 2022-11-15 | 哈尔滨工程大学 | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine |
| CN116202105B (en) * | 2023-02-27 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | Swirl combustion chamber head structure for optimizing combustion performance |
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| CN111207413A (en) * | 2020-02-29 | 2020-05-29 | 哈尔滨工业大学 | Multistage swirl miniature gas turbine combustor |
| CN111649354A (en) * | 2020-06-15 | 2020-09-11 | 江苏科技大学 | Three-cyclone classification cyclone and combustion chamber thereof |
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| DE1147803B (en) * | 1959-05-22 | 1963-04-25 | Bmw Triebwerkbau Ges M B H | Fuel delivery within the runner shaft of rotary atomizers for combustion chambers, especially for gas turbines |
| US5829369A (en) * | 1996-11-12 | 1998-11-03 | The Babcock & Wilcox Company | Pulverized coal burner |
| CN103256633B (en) * | 2012-02-16 | 2015-03-25 | 中国科学院工程热物理研究所 | Low-pollution combustion chamber adopting fuel-grading and three-stage cyclone air inlet |
| CN104566459B (en) * | 2014-12-08 | 2017-12-12 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber is classified nozzle of air supply |
| CN105042638B (en) * | 2015-06-25 | 2017-04-19 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN105157062A (en) * | 2015-10-19 | 2015-12-16 | 北京航空航天大学 | Low-emission combustion chamber with double-layer axial hydrocyclone adopted at precombustion stage |
| CN107559881B (en) * | 2017-09-18 | 2019-09-20 | 北京航空航天大学 | A kind of main combustion stage uses the low pollution combustor head construction of angular injection nozzle |
| CN110878948B (en) * | 2018-09-05 | 2023-05-23 | 中国科学院工程热物理研究所 | Gas turbine axial staged combustor and control method thereof |
| CN109737452B (en) * | 2019-01-23 | 2021-07-30 | 南方科技大学 | Center grading low-pollution combustion chamber suitable for gaseous fuel |
| CN110925796A (en) * | 2019-11-06 | 2020-03-27 | 西北工业大学 | Stepped low-pollution combustion chamber structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207413A (en) * | 2020-02-29 | 2020-05-29 | 哈尔滨工业大学 | Multistage swirl miniature gas turbine combustor |
| CN111649354A (en) * | 2020-06-15 | 2020-09-11 | 江苏科技大学 | Three-cyclone classification cyclone and combustion chamber thereof |
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