CN114777158A - Combustion chamber mixing structure based on blunt body group - Google Patents
Combustion chamber mixing structure based on blunt body group Download PDFInfo
- Publication number
- CN114777158A CN114777158A CN202210523369.5A CN202210523369A CN114777158A CN 114777158 A CN114777158 A CN 114777158A CN 202210523369 A CN202210523369 A CN 202210523369A CN 114777158 A CN114777158 A CN 114777158A
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- China
- Prior art keywords
- wall
- bluff body
- combustion chamber
- blunt body
- body group
- 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.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 30
- 238000002156 mixing Methods 0.000 title claims abstract description 13
- 230000000694 effects Effects 0.000 abstract description 5
- 230000000087 stabilizing effect Effects 0.000 abstract description 3
- 239000000446 fuel Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Images
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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
The invention aims to provide a combustion chamber mixing structure based on a blunt body group, which comprises a combustion chamber and the blunt body group, wherein the combustion chamber comprises a front wall and a pipe wall behind the front wall, a nozzle is arranged on the front wall, the blunt body group comprises a front blunt body and a rear blunt body, the front blunt body comprises an outer wall and an inner wall, the inner wall is positioned outside the nozzle, the outer wall is positioned outside the inner wall, a flow channel is formed between the outer wall and the inner wall, the flow channel is communicated with the inner space of the pipe wall, an air inlet is arranged on the pipe wall, and the rear blunt body is arranged behind the air inlet. The invention adds a plurality of pairs of blunt body groups on the basis of the traditional combustion chamber, can replace a swirler, improves the oil-gas mixing effect and plays a role in stabilizing flame.
Description
Technical Field
The invention relates to a gas turbine, in particular to a combustion chamber structure of the gas turbine.
Background
The gas turbine has the characteristics of high power density and strong maneuverability, and the main components of the gas turbine comprise a gas compressor, a combustion chamber and a turbine, which are typical power devices. The compressor applies work to the incoming flow gas to improve the pressure, fuel is ignited in the combustion chamber and mixed with the incoming flow high-pressure gas to push the turbine to apply work, and the work generated by the turbine is used for driving the compressor to rotate to form a Brayton cycle. However, the problems of insufficient fuel combustion and unstable combustion exist in the combustion chamber, which greatly affects the working stability of the gas turbine, and for this reason, a structure needs to be designed to play a role of flame stabilization while improving the oil-gas mixing effect.
Disclosure of Invention
The invention aims to provide a combustion chamber mixing structure based on a bluff body group, which can improve the oil-gas mixing effect and the flame stabilizing effect.
The purpose of the invention is realized by the following steps:
the invention relates to a combustion chamber mixing structure based on a bluff body group, which is characterized in that: including combustion chamber, bluff body group, the combustion chamber includes the pipe wall at antetheca and rear, and preceding wall mounting nozzle, bluff body group is including preceding bluff body and back bluff body, preceding bluff body includes outer wall and inner wall, and the inner wall is located the nozzle outside, and the outer wall is located the inner wall outside, forms the runner between outer wall and the inner wall, and runner intercommunication pipe wall inner space sets up the inlet port on the pipe wall, and the bluff body after the inlet port rear sets up.
The present invention may further comprise:
1. the rear blunt body is fixed on the pipe wall through a connecting rod per se by adopting a fan-shaped section, and blocks air flow entering the pipe wall.
2. The outer wall and the inner wall of the front bluff body are both provided with trapezoidal sections, 6 outer walls and 6 inner walls are circumferentially arranged, and the trapezoidal sections enable airflow to generate a body shedding vortex; 6 rear bluff bodies are uniformly arranged in the circumferential direction; the front bluff body and the rear bluff body are arranged in a spatial crossing mode.
The invention has the advantages that: the invention adds a plurality of pairs of blunt body groups on the basis of the traditional combustion chamber, can replace a swirler, improves the oil-gas mixing effect and plays a role in stabilizing flame.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of an anterior bluff body and a posterior bluff body;
FIG. 3 is a schematic view of a cross arrangement of front and rear bluff bodies;
FIG. 4 is a schematic view showing the axial arrangement of the front bluff body, the rear bluff body and the combustion chamber tube wall air inlets;
FIG. 5 is a schematic view of the composition of the anterior bluff body;
FIG. 6 is a schematic view of a rear bluff body;
fig. 7 is a flow chart of the flow field in the combustor 1 after the addition of the bluff body group 2.
Detailed Description
The invention is described in more detail below by way of example with reference to the accompanying drawings:
with reference to fig. 1-7, the present invention comprises: a combustion chamber 1 and a bluff body group 2. Wherein, the combustion chamber comprises a front wall 1.1, a tube wall 1.2 and a nozzle 1.3; the bluff body group 2 comprises a front bluff body 2.1 and a rear bluff body 2.2.
The front bluff body 2.1 consists of an outer wall 2.1.1 and an inner wall 2.1.2, and a flow passage is formed between the outer wall 2.1.1 and the inner wall 2.1.2.
The front bluff body 2.1 adopts a trapezoidal cross section, is fixed on the front wall 1.1 of the combustion chamber 1, and is uniformly arranged in the circumferential direction by 6; the trapezoidal section can ensure that the air can be stably fed from the 1.2 side of the pipe wall while generating a body shedding vortex behind the front bluff body 2.1.
The rear bluff body 2.2 is fixed on the pipe wall 1.2 of the combustion chamber 1 through a connecting rod of the rear bluff body, 6 rear bluff bodies are evenly arranged in the circumferential direction, only the main airflow is blocked, and the excessive total pressure loss can not be caused when the vortex is generated.
The air inlet of the pipe wall 1.2 of the combustion chamber 1 is positioned between the front bluff body 2.1 and the rear bluff body 2.2, and the air inlet is arranged between the two front bluff bodies 2.1 in the circumferential direction in the form shown in figure 1.
The front bluff body 2.1 and the rear bluff body 2.2 are arranged in a cross-like manner, and the arrangement is shown in fig. 3.
As shown in fig. 7, a large vortex generated by the main airflow exists in front of the rear bluff body 2.2, a deswirler vortex exists between the front bluff body 2.1 and the large vortex, and the two vortex regions form a relatively tight large-scale vortex region.
When the gas turbine normally works, the high-pressure airflow from the compressor is divided into two flows, one main flow enters the combustion chamber 1 from an air inlet of the pipe wall 1.2 of the combustion chamber 1, and the other secondary flow enters from a flow channel of the front bluff body 2.1. The main air flow is blocked by the rear blunt body 2.2 to generate vortex after entering from the air inlet holes 1.2 on the tube wall, and the secondary air flow is blocked by the vortex group after entering from the narrow flow passage of the front blunt body 2.1 to form a compact detached vortex. On the whole, the main airflow and the secondary airflow form a large-area compact vortex region under the action of the blunt body group 2, which is beneficial to the oil-gas mixing effect and stabilizes the flame.
Claims (3)
1. The utility model provides a combustion chamber mixing structure based on bluff body group which characterized by: including combustion chamber, bluff body group, the combustion chamber includes the pipe wall at antetheca and rear, preceding wall mounting nozzle, bluff body group is including preceding bluff body and back bluff body, preceding bluff body includes outer wall and inner wall, and the inner wall is located the nozzle outside, and the outer wall is located the inner wall outside, forms the runner between outer wall and the inner wall, and runner intercommunication pipe wall inner space sets up the inlet port on the pipe wall, and the bluff body after the inlet port rear sets up.
2. The bluff body group-based combustion chamber blending structure of claim 1, wherein: the rear blunt body is fixed on the pipe wall through a connecting rod per se by adopting a fan-shaped section, and blocks air flow entering the pipe wall.
3. The bluff body group-based combustion chamber blending structure of claim 1, wherein: the outer wall and the inner wall of the front bluff body are both provided with trapezoidal sections, 6 outer walls and 6 inner walls are circumferentially arranged, and the trapezoidal sections enable airflow to generate a body shedding vortex; 6 rear bluff bodies are uniformly arranged in the circumferential direction; the front bluff body and the rear bluff body are arranged in a spatial crossing mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210523369.5A CN114777158A (en) | 2022-05-13 | 2022-05-13 | Combustion chamber mixing structure based on blunt body group |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210523369.5A CN114777158A (en) | 2022-05-13 | 2022-05-13 | Combustion chamber mixing structure based on blunt body group |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114777158A true CN114777158A (en) | 2022-07-22 |
Family
ID=82436745
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210523369.5A Pending CN114777158A (en) | 2022-05-13 | 2022-05-13 | Combustion chamber mixing structure based on blunt body group |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114777158A (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101737802A (en) * | 2009-11-27 | 2010-06-16 | 北京航空航天大学 | Central cavity stable fire tangential combustion chamber |
| CN103017203A (en) * | 2012-12-06 | 2013-04-03 | 中国科学院工程热物理研究所 | Fractional combustion chamber |
| CN203823810U (en) * | 2014-02-27 | 2014-09-10 | 南昌航空大学 | Advanced vortex combustor with flow deflectors |
| US20140260289A1 (en) * | 2013-03-14 | 2014-09-18 | Rolls-Royce Corporation | Multi-passage diffuser with reactivated boundary layer |
| CN203928005U (en) * | 2014-04-28 | 2014-11-05 | 南昌航空大学 | A kind of advanced vortex combustion cavity that installs long direction eddy generator additional |
| CN104848256A (en) * | 2015-05-20 | 2015-08-19 | 北京航空航天大学 | Thin film evaporation type flame stabilizer without gas inlet ring |
| CN105588144A (en) * | 2016-03-02 | 2016-05-18 | 上海电气燃气轮机有限公司 | Flame steady combustion device and method for combustion chamber of gas turbine |
| CN108954393A (en) * | 2018-09-30 | 2018-12-07 | 上海电力学院 | A kind of advanced standing vortex burning chamber of built-in flow spoiler |
| CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN208832506U (en) * | 2018-08-10 | 2019-05-07 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN110513721A (en) * | 2019-09-19 | 2019-11-29 | 广东省航空航天装备技术研究所 | Bluff body structure surely fires combustion chamber |
| CN110686275A (en) * | 2019-09-23 | 2020-01-14 | 中国科学院工程热物理研究所 | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation |
-
2022
- 2022-05-13 CN CN202210523369.5A patent/CN114777158A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101737802A (en) * | 2009-11-27 | 2010-06-16 | 北京航空航天大学 | Central cavity stable fire tangential combustion chamber |
| CN103017203A (en) * | 2012-12-06 | 2013-04-03 | 中国科学院工程热物理研究所 | Fractional combustion chamber |
| US20140260289A1 (en) * | 2013-03-14 | 2014-09-18 | Rolls-Royce Corporation | Multi-passage diffuser with reactivated boundary layer |
| CN203823810U (en) * | 2014-02-27 | 2014-09-10 | 南昌航空大学 | Advanced vortex combustor with flow deflectors |
| CN203928005U (en) * | 2014-04-28 | 2014-11-05 | 南昌航空大学 | A kind of advanced vortex combustion cavity that installs long direction eddy generator additional |
| CN104848256A (en) * | 2015-05-20 | 2015-08-19 | 北京航空航天大学 | Thin film evaporation type flame stabilizer without gas inlet ring |
| CN105588144A (en) * | 2016-03-02 | 2016-05-18 | 上海电气燃气轮机有限公司 | Flame steady combustion device and method for combustion chamber of gas turbine |
| CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN208832506U (en) * | 2018-08-10 | 2019-05-07 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN108954393A (en) * | 2018-09-30 | 2018-12-07 | 上海电力学院 | A kind of advanced standing vortex burning chamber of built-in flow spoiler |
| CN110513721A (en) * | 2019-09-19 | 2019-11-29 | 广东省航空航天装备技术研究所 | Bluff body structure surely fires combustion chamber |
| CN110686275A (en) * | 2019-09-23 | 2020-01-14 | 中国科学院工程热物理研究所 | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation |
Non-Patent Citations (1)
| Title |
|---|
| 许力，王忠义: "柴油发动机超速故障浅析", 城市车辆, pages 58 * |
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Application publication date: 20220722 |
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