CN111023156A - Swirl nozzle of combustion chamber of gas turbine - Google Patents
Swirl nozzle of combustion chamber of gas turbine Download PDFInfo
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- CN111023156A CN111023156A CN201911357611.0A CN201911357611A CN111023156A CN 111023156 A CN111023156 A CN 111023156A CN 201911357611 A CN201911357611 A CN 201911357611A CN 111023156 A CN111023156 A CN 111023156A
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- swirl
- fuel
- nozzle
- cavity
- wall
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention provides a swirl nozzle of a combustion chamber of a gas turbine, which consists of an inner swirl groove, an outer swirl groove, an inner swirl cavity, an outer swirl cavity and an outermost air passage. The two fuel oil flows into the nozzle from the inner passage of the inner cyclone cavity wall and the outer cyclone cavity wall respectively, and the fuel oil performs centrifugal wall-attached rotary motion through the flow guide of the cyclone groove. After the fuel reaches the contraction section, part of the fuel in the inner vortex cavity penetrates through the wall surface processed by the porous medium material of the contraction section under the action of centrifugal force, the fuel is well broken and atomized in the permeation process due to extremely small pores, the fuel in the inner vortex cavity collides with the fuel in the outer vortex cavity to be broken and atomized when permeating into the outer vortex cavity, then permeates into an air passage with part of the fuel in the outer vortex cavity through the porous medium material of the contraction section of the wall of the outer vortex cavity, is further broken and blown out from the air through the nozzle, and the other part of the fuel is not permeated through the porous medium and is directly sprayed out after being sheared by the air through the central nozzle of the inner vortex cavity and the central nozzle of the outer vortex. The good atomization effect of the nozzle is beneficial to the organization and combustion of the combustion chamber of the gas turbine, the working range of the nozzle is enlarged, and the combustion efficiency is improved.
Description
Technical Field
The invention belongs to the field of gas turbine combustors, and particularly relates to a swirl nozzle of a gas turbine combustor.
Background
For nearly half a century, gas turbines have always been the leading position in the fields of military, aviation, power generation and the like as power devices for energy conversion. People have carried out diligent effort for improving gas turbine's working property for modern gas turbine has possessed advantages such as the thermal efficiency is high, power density is big, operational reliability is good and with low costs, and gas turbine technique is still constantly improving and promotion.
The wide application of the gas turbine brings great test to energy supply and environmental pollution, the energy utilization rate of the gas turbine is improved, and the reduction of pollutant emission is a key problem which needs to be solved urgently in the research and development work of the gas turbine at the present stage. For a long time, as one of the factors having important influence on the energy utilization efficiency and pollutant emission of gas turbines, the processes of fuel injection and atomization have been concerned by researchers at home and abroad. The high-quality fuel injection and atomization process can realize more efficient and clean combustion of the gas turbine, and the purposes of energy conservation and emission reduction are achieved.
The fuel crushing and atomizing process is one of the important links of the working process of the gas turbine and has direct and important influence on the combustion process and the emission performance of the gas turbine. The flow characteristics of the fuel in the nozzle, as well as the initial atomisation of the fuel by the nozzle, are important as the upstream boundary of the broken up atomisation of the fuel.
Therefore, the nozzle is reasonably designed by utilizing the flow characteristics in the nozzle and the influence of air on fuel crushing and atomization, and a more effective control means can be provided for the spraying process and the tissue calcination of the modern gas turbine. According to different working conditions of the combustion chamber, fuel is induced to be broken, the fuel atomization effect is improved, the mixing level of fuel and air in the combustion chamber is improved, and the efficient clean utilization of energy is greatly influenced.
Disclosure of Invention
The invention aims to solve the technical problem of providing a swirl nozzle of a combustion chamber of a gas turbine, which realizes multiple times and multiple types of crushing and atomizing of fuel oil in the nozzle by reasonably applying an integral structure formed by combining a double swirl cavity and an air passage and a porous medium material, greatly improves the atomizing effect of the pneumatic nozzle of the existing gas turbine, is beneficial to the organization and combustion of the combustion chamber of the gas turbine, enlarges the working range of the combustion chamber and improves the combustion efficiency.
Technical scheme
The invention aims to provide a swirl nozzle of a combustion chamber of a gas turbine.
The technical scheme of the invention is as follows:
a swirl nozzle of a combustion chamber of a gas turbine comprises an inner swirl chamber wall straight-through section, an inner swirl chamber wall contraction section, an outer swirl chamber wall straight-through section, an outer swirl chamber wall contraction section, an external air passage wall surface, an inner swirl groove, an outer swirl groove, an inner swirl chamber and an outer swirl chamber. The swirl nozzle is designed by adding an external air channel into two layers of swirl cavities, and fuel oil permeates through small holes on the wall surface of the porous medium of the contraction section by virtue of centrifugal force to achieve the effect of crushing. In addition, the fuel particles penetrating through the inner rotational flow cavity wall contraction section collide with fuel in the outer rotational flow cavity for crushing, and part of the mixture of the inner rotational flow cavity wall contraction section and the outer rotational flow cavity wall contraction section continuously permeates into an external air passage, is sheared and crushed under the action of air flow and is blown out from the nozzle. Porous media used in the inner cyclone cavity wall contraction section and the outer cyclone cavity wall contraction section have no specific requirements, and porous media materials with different pores are selected according to specific atomization requirements; the inner and outer swirl grooves can be designed according to actual equipment in the same direction and the opposite direction, the size of the swirl groove is not particularly limited, the swirl number can achieve the strong swirl effect, and the processing and installation can be completed in the actual equipment; the height of the inner and outer cyclone cavities, the thickness of the straight-through section and the contraction section of the inner and outer cyclone walls and the specific contraction angle are determined according to the actual conditions of processing, the material strength requirement and the nozzle performance requirement.
The invention has the following beneficial effects:
the invention provides a swirl nozzle of a combustion chamber of a gas turbine, which consists of an inner swirl groove, an outer swirl groove, an inner swirl cavity, an outer swirl cavity and an outermost air passage. The two fuel oil flows into the nozzle from the inner passage of the inner cyclone cavity wall and the outer cyclone cavity wall respectively, and the fuel oil performs centrifugal wall-attached rotary motion through the flow guide of the cyclone groove. After the fuel reaches the contraction section, part of the fuel in the inner vortex cavity penetrates through the wall surface processed by the porous medium material of the contraction section under the action of centrifugal force, the fuel is well broken and atomized in the permeation process due to extremely small pores, the fuel in the inner vortex cavity collides with the fuel in the outer vortex cavity to be broken and atomized when permeating into the outer vortex cavity, then permeates into an air passage with part of the fuel in the outer vortex cavity through the porous medium material of the contraction section of the wall of the outer vortex cavity, is further broken and blown out from the air through the nozzle, and the other part of the fuel is not permeated through the porous medium and is directly sprayed out after being sheared by the air through the central nozzle of the inner vortex cavity and the central nozzle of the outer vortex. Through the reasonable application of the overall structure and the porous medium material which are combined with the double-swirl cavity and the air passage, multiple times and multiple types of crushing atomization of fuel in the nozzle are realized, the atomization effect of the pneumatic nozzle of the existing gas turbine is greatly improved, the combustion of a combustion chamber of the gas turbine is facilitated, the working range of the combustion chamber is enlarged, and the combustion efficiency is improved.
Drawings
FIG. 1: gas turbine combustion chamber swirl nozzle overall schematic diagram
FIG. 2: gas turbine combustion chamber swirl nozzle profile
FIG. 3: gas turbine combustion chamber swirl nozzle rear view
In the figure: 1. inner cyclone cavity wall straight section, 2 outer cyclone cavity wall straight section, 3 external air channel wall, 4 outer cyclone cavity wall contraction section, 5 inner cyclone cavity wall contraction section, 6 outer cyclone cavity, 7 inner cyclone cavity, 8 inner cyclone groove, 9 outer cyclone groove
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
with reference to fig. 1, 2 and 3, the present invention provides a gas turbine combustor swozzle. FIG. 1 is an overall schematic view of a gas turbine combustor swirler, FIG. 2 is a cross-sectional view of a gas turbine combustor swirler, and FIG. 3 is a rear view of a gas turbine combustor swirler.
The two fuel oil flows into the nozzle from the inner passage of the inner cyclone cavity wall straight-through section 1 and the passage between the inner cyclone cavity wall straight-through section 1 and the outer cyclone cavity wall straight-through section 2, and the fuel oil is guided by the inner cyclone groove 8 and the outer cyclone groove 9 to perform centrifugal wall-adhering rotation movement. After reaching the contraction section, part of the fuel oil in the inner vortex cavity permeates through the wall surface processed by the porous medium material of the contraction section 5 of the wall of the inner vortex cavity due to the action of centrifugal force, the fuel oil is well crushed and atomized due to extremely small pores in the permeation process, the fuel oil in the inner vortex cavity 7 collides with the fuel oil in the outer vortex cavity to be crushed and atomized when permeating into the outer vortex cavity 6, then permeates into an external air passage with part of the fuel oil in the outer vortex cavity through the porous medium material of the contraction section 4 of the wall of the outer vortex cavity, is further crushed and is blown out through a nozzle by air, and the other part of the fuel oil does not permeate through the porous medium and is directly sprayed out after being sheared by the air through the central nozzle of the inner vortex. Through the reasonable application of the overall structure and the porous medium material which are combined with the double-swirl cavity and the air passage, multiple times and multiple types of crushing atomization of fuel in the nozzle are realized, the atomization effect of the pneumatic nozzle of the existing gas turbine is greatly improved, the combustion of a combustion chamber of the gas turbine is facilitated, the working range of the combustion chamber is enlarged, and the combustion efficiency is improved.
Claims (2)
1. The utility model provides a gas turbine combustion chamber swirl nozzle, includes the straight section of interior whirl chamber wall, interior whirl chamber wall shrink section, the straight section of outer whirl chamber wall, outer whirl chamber wall shrink section, outside air passage wall, interior whirl groove and outer whirl groove, interior whirl chamber and outer whirl chamber, its characterized in that:
the swirl nozzle is designed by adding an external air passage to two layers of swirl cavities, and fuel oil permeates through small holes on the wall surface of the porous medium of the contraction section by virtue of centrifugal force to achieve the effect of crushing. In addition, the fuel particles penetrating through the inner rotational flow cavity wall contraction section collide with fuel in the outer rotational flow cavity for crushing, and part of the mixture of the inner rotational flow cavity wall contraction section and the outer rotational flow cavity wall contraction section continuously permeates into an external air passage, is sheared and crushed under the action of air flow and is blown out from the nozzle.
2. The gas turbine combustor swozzle of claim 1, wherein:
porous media used in the inner cyclone cavity wall contraction section and the outer cyclone cavity wall contraction section have no specific requirements, and porous media materials with different pores are selected according to specific atomization requirements;
the inner and outer swirl grooves can be designed according to actual equipment in the same direction and the opposite direction, the size of the swirl groove is not particularly limited, the swirl number can achieve the strong swirl effect, and the processing and installation can be completed in the actual equipment;
the height of the inner and outer cyclone cavities, the thickness of the straight-through section and the contraction section of the inner and outer cyclone walls and the specific contraction angle are determined according to the actual conditions of processing, the material strength requirement and the nozzle performance requirement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911357611.0A CN111023156A (en) | 2019-12-25 | 2019-12-25 | Swirl nozzle of combustion chamber of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911357611.0A CN111023156A (en) | 2019-12-25 | 2019-12-25 | Swirl nozzle of combustion chamber of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111023156A true CN111023156A (en) | 2020-04-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911357611.0A Pending CN111023156A (en) | 2019-12-25 | 2019-12-25 | Swirl nozzle of combustion chamber of gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112902231A (en) * | 2021-03-02 | 2021-06-04 | 西北工业大学 | Novel heat transfer type air atomizing nozzle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3932988A (en) * | 1972-10-25 | 1976-01-20 | Beaufrere Albert H | Fuel slinger combustor |
| CN101206029A (en) * | 2006-12-21 | 2008-06-25 | 中国科学院工程热物理研究所 | Nozzle for minisize gas-turbine combustor |
| CN103175221A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Gas-assisted dual-fuel nozzle used for chemical regenerative cycle |
| CN103225824A (en) * | 2012-01-31 | 2013-07-31 | 通用电气公司 | Fuel nozzle for a gas turbine engine and method of operating the same |
| CN103939946A (en) * | 2014-04-10 | 2014-07-23 | 北京航空航天大学 | Low-emission low-rotational-flow combustion chamber head structure for aircraft engine |
| CN107702146A (en) * | 2017-10-12 | 2018-02-16 | 四川达宇特种车辆制造厂 | For the porous evaporator medium pipe in micro gas turbine engine combustion chamber |
-
2019
- 2019-12-25 CN CN201911357611.0A patent/CN111023156A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3932988A (en) * | 1972-10-25 | 1976-01-20 | Beaufrere Albert H | Fuel slinger combustor |
| CN101206029A (en) * | 2006-12-21 | 2008-06-25 | 中国科学院工程热物理研究所 | Nozzle for minisize gas-turbine combustor |
| CN103225824A (en) * | 2012-01-31 | 2013-07-31 | 通用电气公司 | Fuel nozzle for a gas turbine engine and method of operating the same |
| CN103175221A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Gas-assisted dual-fuel nozzle used for chemical regenerative cycle |
| CN103939946A (en) * | 2014-04-10 | 2014-07-23 | 北京航空航天大学 | Low-emission low-rotational-flow combustion chamber head structure for aircraft engine |
| CN107702146A (en) * | 2017-10-12 | 2018-02-16 | 四川达宇特种车辆制造厂 | For the porous evaporator medium pipe in micro gas turbine engine combustion chamber |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112902231A (en) * | 2021-03-02 | 2021-06-04 | 西北工业大学 | Novel heat transfer type air atomizing nozzle |
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Application publication date: 20200417 |
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| RJ01 | Rejection of invention patent application after publication |