CN114110662B - Low-nitrogen combustion chamber of gas turbine - Google Patents
Low-nitrogen combustion chamber of gas turbine Download PDFInfo
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- CN114110662B CN114110662B CN202111412397.1A CN202111412397A CN114110662B CN 114110662 B CN114110662 B CN 114110662B CN 202111412397 A CN202111412397 A CN 202111412397A CN 114110662 B CN114110662 B CN 114110662B
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- main combustion
- duty
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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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- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The invention relates to a low-nitrogen combustion chamber of a gas turbine, which comprises a flame tube and a combustion chamber head, wherein the combustion chamber head is connected with the flame tube and comprises a main combustion stage radial swirler, the output side of the main combustion stage radial swirler is provided with a direct-current channel, one end of the direct-current channel is connected with the main combustion stage radial swirler, and the other end of the direct-current channel is connected with the flame tube; a main combustion stage combustion-supporting air turbulence structure and a main combustion stage gas nozzle are arranged in the direct-current channel; the direct current channel comprises a turbulence section, a main combustion-supporting air turbulence structure is arranged at the input end of the turbulence section, and a main combustion-supporting gas nozzle is arranged in the turbulence section. Compared with the prior art, the invention has the advantages of more stable combustion, strong safety and the like.
Description
Technical Field
The invention relates to the technical field of combustion chambers of gas turbines, in particular to a low-nitrogen combustion chamber of a gas turbine.
Background
The combustor is one of three major core components of a gas turbine, and functions to convert chemical energy of fuel into heat energy to drive the turbine to rotate at high speed, and further to convert the heat energy into mechanical work. With the increasingly strict requirements for nitrogen oxide emission at home and abroad, the design and development of low-nitrogen combustion chambers become more and more important.
At present, the lean-burn premixed combustion technology is a combustion mode for reducing nitrogen oxide emission in the main flow of the industry, and the core idea of the technology is to increase the flow of combustion-supporting air, fully mix gas and the combustion-supporting air before the gas and the combustion-supporting air enter a combustion chamber, absorb the heat emitted by combustion through excessive combustion-supporting air so as to reduce the smoke temperature of a main combustion area of the combustion chamber, and further reduce the generation amount of thermal nitrogen oxide. However, when the premixing degree of gas and air is high, the existing low-nitrogen combustion chamber still has the possibility of backfire, so that flame is unstable, a large amount of nitrogen oxides can be generated, and potential safety hazards still exist.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a low-nitrogen combustion chamber of a gas turbine.
The purpose of the invention can be realized by the following technical scheme:
a low-nitrogen combustion chamber of a gas turbine comprises a flame tube and a combustion chamber head, wherein the combustion chamber head is connected with the flame tube and comprises a main combustion stage radial swirler, a direct-current channel is arranged on the output side of the main combustion stage radial swirler, one end of the direct-current channel is connected with the main combustion stage radial swirler, and the other end of the direct-current channel is connected with the flame tube; a main combustion stage combustion-supporting air turbulence structure and a main combustion stage gas nozzle are arranged in the direct-current channel; the direct current channel comprises a turbulence section, the main combustion-supporting air turbulence structure is arranged at the input end of the turbulence section, and the main combustion-supporting gas nozzle is arranged in the turbulence section.
Furthermore, one end of the direct current channel, which is connected with the flame tube, is of a necking structure.
Further, the cross-sectional area of the necking structure is not less than 50% of the cross-sectional area before necking.
Furthermore, the main combustion stage combustion air turbulence structure is an annular protrusion arranged on the inner wall of the direct-flow channel.
Further, the cross section of the main combustion stage combustion air turbulence structure is rectangular, semicircular or triangular.
Furthermore, the combustion chamber also comprises an on-duty flame stabilizing structure, the on-duty flame stabilizing structure comprises an on-duty gas spray pipe, an on-duty radial swirler and an air flow channel, one end of the air flow channel is connected with the on-duty radial swirler, and the other end of the air flow channel is connected with the flame tube; the duty-class gas spray pipe is arranged on one side of the air flow channel, the duty-class gas spray pipe is connected with the air flow channel through a duty-class gas nozzle, and the duty-class gas nozzle is arranged at one end, connected with the flame tube, of the air flow channel.
Furthermore, one end of the air flow channel, which is connected with the flame tube, is of a flaring structure.
Furthermore, the combustion chamber comprises a main combustion grade fuel gas spray pipe, a main combustion grade fuel gas pressure stabilizing cavity and a main combustion grade fuel gas flow equalizing cavity, one end of the main combustion grade fuel gas flow equalizing cavity is connected with the main combustion grade fuel gas spray pipe, the other end of the main combustion grade fuel gas flow equalizing cavity is connected with the main combustion grade fuel gas pressure stabilizing cavity, and the main combustion grade fuel gas nozzle is connected with the main combustion grade fuel gas pressure stabilizing cavity.
Further, the combustion chamber comprises a casing, and the flame tube is arranged inside the casing.
Further, a seam-shaped flow passage is formed between the inner wall of the casing and the outer wall of the flame tube.
Compared with the prior art, the invention has the following advantages:
1. the main combustion stage combustion-supporting air turbulence structure and the main combustion stage gas nozzle are arranged in the straight-through flow channel behind the main combustion stage radial swirler, and the main combustion stage gas nozzle is positioned in a turbulence section formed by the main combustion stage combustion-supporting air turbulence structure. The circumferential flow velocity in the turbulent flow section helps the gas and the air to be quickly mixed, so that the mixing effect of the main combustion air and the gas of the combustion chamber of the gas turbine is improved, and the reduction of the emission of nitrogen oxides in the combustion chamber is facilitated.
2. According to the invention, the necking structure is arranged at one end of the direct current channel connected with the flame tube, the flow rate of the main combustion level premixed gas is improved by reducing the flow area, tempering and dispersion combustion can be prevented, and the combustion stability is improved.
3. The invention is provided with the on-duty flame stabilizing structure, one side of the on-duty radial swirler is provided with the air flow passage, and one end of the air flow passage connected with the flame tube is of a flaring structure, so that the flow rate of on-duty combustion-supporting air can be reduced, the relative residence time of on-duty gas and combustion-supporting air is prolonged, the stable on-duty flame can be established, and the combustion stability of the system is improved.
4. The structure of the main combustion stage combustion air turbulence structure can be set to be rectangular, semicircular or triangular, the rectangular turbulence effect is good, the semicircular pressure drop is good, the triangular turbulence effect and the triangular pressure drop are between the rectangular turbulence effect and the semicircular pressure drop, and the requirements of combustion chambers under different conditions can be met through different structures.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
FIG. 2 is a schematic view of the structure of the head of the combustion chamber of the present invention.
FIG. 3 is a schematic diagram of a cross-section of a combustion air turbulence structure of a primary combustion stage of the present invention being rectangular.
FIG. 4 is a schematic view of a cross-section of a combustion air turbulence structure of a primary combustion stage of the present invention being semi-circular.
FIG. 5 is a schematic view of a cross-section of a combustion air turbulence structure of a primary combustion stage of the present invention being triangular.
Fig. 6 is a schematic view of the turbulent flow region flow of the present invention (the dotted line arrows indicate the gas flow direction, and the solid line arrows indicate the air flow direction).
Fig. 7 is a schematic view of the flow field of the combustor head of the present invention (the dashed arrows indicate the gas flow direction and the solid arrows indicate the air flow direction).
Reference numerals:
1-a casing; 2, mounting a top cover on the casing; 3-an air inlet; 4-a flame tube; 5-a main combustion stage gas spray pipe; 6-a combustion chamber head; 7-a main combustion stage fuel gas pressure stabilizing cavity; 8-duty gas spray pipe; 9-a main combustion stage radial swirler; 10-duty radial swirler; 11-a main combustion stage combustion air turbulence structure; 12-a main combustion stage premixed gas outlet; 13-duty combustion air outlet; 14-main combustion stage gas flow equalizing cavity; 15-a flame tube positioning flange; 16-cooling holes; 17-a mixing hole; 18-a direct current channel; 19-a main combustion stage gas nozzle; 20-an air flow channel; 21-duty gas nozzle.
Detailed Description
The invention is described in detail below with reference to the figures and the specific embodiments. The present embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation manner and a specific operation process are given, but the scope of the present invention is not limited to the following embodiments.
The embodiment provides a gas turbine low-nitrogen combustion chamber, and the cross-sectional view of the combustion chamber is shown in fig. 1, and the combustion chamber mainly comprises a casing 1, a casing upper top cover 2 arranged at the top of the casing 1, an air inlet 3 arranged at the bottom of the casing 1, a flame tube 4 arranged inside the casing 1, a combustion chamber head 6 arranged at the top of the flame tube 4, and a flame tube positioning flange 15. The straight wall of the flame tube 4 is provided with a cooling hole 16 and a mixing hole 17. The wall surface cooling holes 16 are oblique straight holes, and the mixing holes 17 are flat straight holes and are uniformly distributed in the circumferential direction. The upper part of the flame tube 4 is welded and fixed with the head part 6 of the combustion chamber, the middle part is welded and fixed with the flame tube positioning flange 15, and the flame tube positioning flange 15 is fixed with the casing 1 and the upper top cover 2 of the casing. The air inlet 3 is preferably a circular seam-shaped flow channel formed between the inner wall of the casing and the outer wall of the flame tube, and air enters the combustion chamber through the air inlet 3 in a countercurrent mode after being pressurized by the air compressor.
The enlarged partial view of the combustion chamber head 6 is shown in fig. 2, and includes a main combustion stage gas nozzle 5, a main combustion stage gas pressure stabilizing cavity 7, an on-duty stage gas nozzle 8, a main combustion stage radial swirler 9, an on-duty stage radial swirler 10, a main combustion stage combustion air turbulence structure 11, a main combustion stage premixed gas outlet 12 and an on-duty stage combustion air outlet 13.
Wherein, a direct current channel 18 is arranged on one side of the main combustion stage radial swirler 9, one end of the direct current channel is connected with the main combustion stage radial swirler 9, and the other end is connected with the flame tube 4. The main combustion stage combustion-supporting air turbulence structure 11 and the main combustion stage gas nozzle 19 are sequentially arranged in the direct current channel 18, the main combustion stage combustion-supporting air turbulence structure 11 is an annular bulge, and the cross section of the bulge can be rectangular, semicircular or triangular, as shown in fig. 3-5. The rectangular section is easy to process, the wake vortex area is large, the turbulent flow effect is best, but the pressure drop is large; the semi-circular section has good streamline and small pressure drop, but the tail vortex area is also small, so that the processing is not easy; the turbulent flow effect, the pressure drop and the processing difficulty of the triangular section are all between the two structures. Different cross-sectional shapes can be selected according to specific situations, and the rectangular shape is preferred in the embodiment. The main combustion stage combustion air turbulence structure 11 is located behind the blades of the main combustion stage radial swirler 9, and the height of the main combustion stage combustion air turbulence structure is not more than 50% of the width of the straight-flow channel 18, so that air can normally circulate, and preferably 45% in the embodiment. The straight flow channel 18 includes a spoiler, as shown in fig. 6, which forms a spoiler when air is introduced from the radial swirler 9 of the main combustion stage and passes through the turbulence structure 11 of the combustion air of the main combustion stage. The position of the main combustion stage gas nozzle 19 is positioned in the turbulent flow section. The main combustion grade gas spout 19 sets up on the outer wall of main combustion grade gas pressure stabilizing cavity 7, and main combustion grade gas pressure stabilizing cavity 7 is connected main combustion grade gas uniform flow cavity 14, and main combustion grade gas uniform flow cavity 14 is connected main combustion grade gas spray tube 5, and after main combustion grade gas is input from main combustion grade gas spray tube 5, through the steady voltage of flow equalizing, the section of vortex is got into through main combustion grade gas spout 19. The circumferential flow velocity brought by the radial swirler 9 and the turbulent flow area of the main combustion stage can help the main combustion stage fuel gas to be quickly mixed with air, and the emission of nitrogen oxides in the combustion chamber is favorably reduced.
In addition, the direct current channel 18 is connected to one end of the flame tube 4, that is, the main combustion stage premixed gas outlet 12, and is of a throat structure, the cross-sectional area of the throat is not less than 50% of the cross-sectional area before the throat, and in this embodiment, the cross-sectional area is preferably 55%, so that the flow rate of the main combustion stage premixed gas can be increased by reducing the flow area, backfire and diffusion combustion can be prevented, and the combustion stability and the nitrogen reduction effect can be improved.
The present embodiment further provides an on-duty flame stabilization structure, which includes an on-duty gas nozzle 8, an on-duty radial swirler 10, and an air flow passage 20. One end of the air flow channel 20 is connected with the class radial swirler 10, and the other end is connected with the flame tube 4. The duty-on gas spray pipe 8 and the casing 1 are coaxially arranged and are arranged in parallel to the air flow channel 20, a chamfer is arranged at the tail end of the duty-on gas spray pipe 8, the angle is 30-60 degrees, duty-on gas nozzles 21 which are uniformly arranged in the circumferential direction are arranged on the chamfer and are used for conveying duty-on gas, and the air injection end of the duty-on gas nozzle 21 is arranged at one end, connected with the flame tube 4, of the air flow channel 20. The air flow passage 20 is connected with one end of the flame tube 4, namely the duty-level combustion air outlet 13, and is of a flaring structure. Air is fed into the air channel through the on-duty radial swirler 10 and mixed with the on-duty fuel gas delivered by the nozzle. This structure reduces the class air of on duty near the class gas spout of on duty through increase air flow area, prolongs the mixing time of class gas and combustion air on duty, and then stabilizes the class flame, improves the combustion stability of system.
The general working flow of the present embodiment is as follows, firstly, air enters the combustion chamber head 6 through the air inlet 3, flows into the main combustion stage radial swirler 9 and the duty stage radial swirler 10 respectively, and inputs the main combustion stage gas into the main combustion stage gas nozzle 5 and inputs the duty stage gas into the duty stage gas nozzle 8. The main combustion level gas is mixed with air in the direct current channel 18 through the main combustion level gas nozzle 19, the duty level gas is mixed with air in the air flow channel 20 through the duty level gas nozzle 21, and the mixed gas is input into the flame tube to finally complete combustion. The flow field pattern of the combustion chamber head 6 is shown in fig. 7.
The foregoing detailed description of the preferred embodiments of the invention has been presented. Numerous modifications and variations will readily occur to those skilled in the art, in light of the present disclosure, without inventive faculty. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (4)
1. A gas turbine low-nitrogen combustor comprises a flame tube (4) and a combustor head (6), wherein the combustor head (6) is connected with the flame tube (4), and is characterized in that the combustor head (6) comprises a main combustion stage radial swirler (9), a direct-current channel (18) is arranged on the output side of the main combustion stage radial swirler (9), one end of the direct-current channel (18) is connected with the main combustion stage radial swirler (9), and the other end of the direct-current channel (18) is connected with the flame tube (4); a main combustion stage combustion air turbulence structure (11) and a main combustion stage gas nozzle (19) are arranged in the direct current channel (18); the direct current channel (18) comprises a turbulent flow section, the main combustion grade combustion air turbulent flow structure (11) is arranged at the input end of the turbulent flow section, and the main combustion grade fuel gas nozzle (19) is arranged in the turbulent flow section;
one end of the direct current channel (18) connected with the flame tube (4) is of a necking structure;
the cross section area of the necking structure is not less than 50% of the cross section area before necking;
the main combustion stage combustion air turbulence structure (11) is an annular bulge arranged on the inner wall of the direct-flow channel (18);
the section of the main combustion stage combustion air turbulence structure (11) is rectangular, semicircular or triangular;
the combustion chamber further comprises an on-duty flame stabilizing structure, the on-duty flame stabilizing structure comprises an on-duty gas spray pipe (8), an on-duty radial swirler (10) and an air flow channel (20), one end of the air flow channel (20) is connected with the on-duty radial swirler (10), and the other end of the air flow channel is connected with the flame tube (4); the on-duty gas spraying pipe (8) is arranged on one side of the air flow channel (20), the on-duty gas spraying pipe (8) is connected with the air flow channel (20) through an on-duty gas nozzle (21), and the on-duty gas nozzle (21) is arranged at one end, connected with the flame tube (4), of the air flow channel (20);
the combustion chamber comprises a main combustion grade fuel gas spray pipe (5), a main combustion grade fuel gas pressure stabilizing cavity (7) and a main combustion grade fuel gas uniform flow cavity (14), wherein one end of the main combustion grade fuel gas uniform flow cavity (14) is connected with the main combustion grade fuel gas spray pipe (5), the other end of the main combustion grade fuel gas uniform flow cavity is connected with the main combustion grade fuel gas pressure stabilizing cavity (7), and a main combustion grade fuel gas nozzle (19) is connected with the main combustion grade fuel gas pressure stabilizing cavity (7).
2. The gas turbine low-nitrogen combustor according to claim 1, wherein one end of the air flow passage (20) connected with the flame tube (4) is of a flaring structure.
3. A gas turbine low-nitrogen combustor according to claim 1, characterized in that the combustor comprises a casing (1), and the flame tube (4) is arranged inside the casing (1).
4. The gas turbine low-nitrogen combustor of claim 3, characterized in that a slit-shaped flow passage is formed between the inner wall of the casing (1) and the outer wall of the flame tube (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111412397.1A CN114110662B (en) | 2021-11-25 | 2021-11-25 | Low-nitrogen combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111412397.1A CN114110662B (en) | 2021-11-25 | 2021-11-25 | Low-nitrogen combustion chamber of gas turbine |
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| CN114110662A CN114110662A (en) | 2022-03-01 |
| CN114110662B true CN114110662B (en) | 2023-02-10 |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102597631A (en) * | 2009-08-26 | 2012-07-18 | 西门子公司 | Burner, in particular for gas turbines |
| CN102906500A (en) * | 2009-08-26 | 2013-01-30 | 西门子公司 | Swirl blade, burner and gas turbine |
| CN103216848A (en) * | 2012-01-18 | 2013-07-24 | 通用电气公司 | Combustor assembly with impingement sleeve holes and turbulators |
| CN203586283U (en) * | 2013-07-10 | 2014-05-07 | 辽宁省燃烧工程技术中心（有限公司） | Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel |
| CN203687097U (en) * | 2013-12-24 | 2014-07-02 | 中航商用航空发动机有限责任公司 | Impact divergence turbulent flow cooling flame tube and combustion chamber |
| CN104110699A (en) * | 2014-07-09 | 2014-10-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Premixing nozzle of gas turbine combustion chamber |
| CN106969380A (en) * | 2017-03-22 | 2017-07-21 | 同济大学 | A kind of low-nitrogen discharged combustion chamber and the gas turbine containing the combustion chamber |
| CN109579053A (en) * | 2018-11-30 | 2019-04-05 | 山东交通学院 | A kind of gas engine gas mixing chamber |
| CN109611889A (en) * | 2018-12-07 | 2019-04-12 | 中国航发沈阳发动机研究所 | A kind of gas fuel nozzle component |
| US10371000B1 (en) * | 2018-03-23 | 2019-08-06 | Rosemount Aerospace Inc. | Flush-mount combined static pressure and temperature probe |
| CN112393273A (en) * | 2020-12-04 | 2021-02-23 | 重庆超力高科技股份有限公司 | Premixing type burner |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130333389A1 (en) * | 2012-06-15 | 2013-12-19 | General Electric Company | Cross fire tube retention system for a gas turbine engine |
| CN206361713U (en) * | 2016-12-14 | 2017-07-28 | 中国燃气涡轮研究院 | Improve the rotarytype injector of fuel feeding scope |
| CN209782713U (en) * | 2018-12-04 | 2019-12-13 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of gas turbine and gas turbine |
| CN110285447B (en) * | 2019-06-06 | 2020-07-28 | 同济大学 | Low-emission combustion chamber of gas turbine and variable-load air distribution and adjustment method |
| CN112539192B (en) * | 2019-09-20 | 2023-01-24 | 中国航发商用航空发动机有限责任公司 | Gas turbine, combustor, compressor stall monitoring device, monitoring method and computer readable storage medium |
-
2021
- 2021-11-25 CN CN202111412397.1A patent/CN114110662B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102597631A (en) * | 2009-08-26 | 2012-07-18 | 西门子公司 | Burner, in particular for gas turbines |
| CN102906500A (en) * | 2009-08-26 | 2013-01-30 | 西门子公司 | Swirl blade, burner and gas turbine |
| CN103216848A (en) * | 2012-01-18 | 2013-07-24 | 通用电气公司 | Combustor assembly with impingement sleeve holes and turbulators |
| CN203586283U (en) * | 2013-07-10 | 2014-05-07 | 辽宁省燃烧工程技术中心（有限公司） | Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel |
| CN203687097U (en) * | 2013-12-24 | 2014-07-02 | 中航商用航空发动机有限责任公司 | Impact divergence turbulent flow cooling flame tube and combustion chamber |
| CN104110699A (en) * | 2014-07-09 | 2014-10-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Premixing nozzle of gas turbine combustion chamber |
| CN106969380A (en) * | 2017-03-22 | 2017-07-21 | 同济大学 | A kind of low-nitrogen discharged combustion chamber and the gas turbine containing the combustion chamber |
| US10371000B1 (en) * | 2018-03-23 | 2019-08-06 | Rosemount Aerospace Inc. | Flush-mount combined static pressure and temperature probe |
| CN109579053A (en) * | 2018-11-30 | 2019-04-05 | 山东交通学院 | A kind of gas engine gas mixing chamber |
| CN109611889A (en) * | 2018-12-07 | 2019-04-12 | 中国航发沈阳发动机研究所 | A kind of gas fuel nozzle component |
| CN112393273A (en) * | 2020-12-04 | 2021-02-23 | 重庆超力高科技股份有限公司 | Premixing type burner |
Non-Patent Citations (1)
| Title |
|---|
| 《旋流器和射流孔流通面积对燃烧室流场及温度场影响的数值研究》;吕亚亚;《热能动力工程》;20190228;第2页-第9页 * |
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| CN114110662A (en) | 2022-03-01 |
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