CN105650676A - Rotational flow blade of combustion chamber of ground gas turbine - Google Patents
Rotational flow blade of combustion chamber of ground gas turbine Download PDFInfo
- Publication number
- CN105650676A CN105650676A CN201610146423.3A CN201610146423A CN105650676A CN 105650676 A CN105650676 A CN 105650676A CN 201610146423 A CN201610146423 A CN 201610146423A CN 105650676 A CN105650676 A CN 105650676A
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- China
- Prior art keywords
- combustion chamber
- swirl vane
- combustion
- boss
- ground
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Classifications
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention provides a rotational flow blade of a combustion chamber of a ground gas turbine. The rotational flow blade is mainly used in a head main-combustion-level whirlcone of the combustion chamber of the ground gas turbine. The cross section of the rotational flow blade is in a wing shape, a groove and boss structure is adopted in the blade surface on the windward face, and turbulent transition is promoted to occur in advance. A flow separation phenomenon is not likely to happen to a turbulent boundary layer, and therefore a low-pressure area on the back of the blade is reduced, and resistance is reduced. Meanwhile, the turbulence intensity is increased, the premixing evenness of fuel in the main whirlcone can be improved, the combustion evenness of a main combustion area in the combustion chamber is effectively improved, a local high temperature area is avoided, and the emission of NOx is greatly reduced.
Description
Technical field
The present invention relates to internal combustion turbine field, specifically, it relates to the swirl vane of a kind of ground combustion machine combustion chamber.
Background technology
Internal combustion turbine is the crystallization of modern industry achievement, and combustion chamber is the important parts of internal combustion turbine, and the main function of combustion chamber makes the chemical energy of fuel be converted into heat energy. Along with the development of ground gas turbine technology, modern ground gas turbine pursues ultra-low emission, and direction towards high temperature rise is developed simultaneously, and primary chamber design is proposed requirements at the higher level by the lifting of internal combustion turbine overall performance.
Fig. 1 is the structural representation of existing general dry type low-nitrogen oxide discharging combustion chamber, and combustion barrel is located in combustion chamber, and the air inlet end of combustion barrel is provided with end plate, and end plate is fixed with swirler on duty and 8 main cyclone devices around swirler on duty. Main cyclone device is made up of whirl cylinder 5 and blade 2, and level swirler on duty is made up of whirl cylinder 6 and blade 7, and blade 2,7 is arranged around the centre hole at middle part. The centre hole of main combustion stage jet pipe 1 in the middle part of main cyclone device blade 2 is worn and is become owner of whirl cylinder, the centre hole penetration value class whirl cylinder of level jet pipe 3 on duty in the middle part of swirler blades 7 on duty. Main cyclone cylinder fuel is vertical axial ejection from spray orifice 4, with the air phase blending through swirl vane 2, forms pre-mixed Fuel-air.
Outside main combustion stage adopts premixed combustion mode, and its fuel accounting is more than 90%, and the quality of its combustion position is directly connected to the combustion position of whole combustion chamber. The main combustion stage head air of ground combustion machine combustion chamber general at present after the swirl vane eddy flow of micro-angle, then be perpendicular to the methane gas phase blending flowing to ejection, form the mixture of fuel and air. The mixture homogeneity of fuel and air can not be guaranteed, and the mixture homogeneity of fuel directly affects the combustion position of downstream combustion chamber and the discharge of pollution.
Summary of the invention
The technical problem to be solved in the present invention is to provide the swirl vane of a kind of ground combustion machine combustion chamber, this swirl vane can improve the pre-mixed homogeneity of the fuel in main cyclone device, effectively improve the combustion uniformity of primary combustion zone in combustion chamber, avoid the appearance in district of localized hyperthermia, greatly reduce the quantity discharged of NOx. It is used in the head main combustion stage swirler of ground combustion machine combustion chamber,
The present invention is solved the problems of the technologies described above by following technique means: the swirl vane of a kind of ground combustion machine combustion chamber, the cross section of described swirl vane is the aerofoil profile of the big tail point of a kind of head, the blade surface in face adopts indenture structure windward, indenture impels turbulent flow to turn to twist generation, not easily there is flow separation phenomenon in turbulent boundary layer, thus the low pressure area after blade back is reduced, reduce the blending simultaneously strengthening air-flow and fuel of resistance.
The swirl vane cross section of the present invention is a kind of aerofoil profile, surface, side has one layer of tectum windward, it is circular or just hexagonal groove that this tectum has the profile specified in a large number by a large amount of dot matrix member, and position boss in the inner is also circular or positive hexagon accordingly.
As the preferred embodiment of the present invention: swirl vane windward side surface coating there is the circular groove and annular boss that specify by a large amount of dot matrix member in a large number, each circular groove has two within it grade round boss.
The installation angle of described swirl vane is 3��5 ��.
The 70% of the front end, whole surface windward that described a large amount of dot matrix member covers swirl vane, and the width between centers of groove or boss between two is 0.7mm.
The diameter of the circular groove of described dot matrix member is 0.8mm, and the outside diameter of round boss is 0.5mm, and interior diameter is 0.3mm.
The thickness of described swirl vane surface coating is between 0.1mm��0.2mm.
Adopt the present invention can obtain following useful effect:
1) the present invention is by changing the surface tissue of ground combustion machine combustion chamber main combustion stage swirl vane, utilizes surface groove and boss to the disturbance of air-flow so that turn twists and to occur in advance, reduces the low pressure area after blade, reduce resistance to flow.
2) the blade of the present invention groove on surface and the design of boss windward, strengthens the turbulivity of flow of air, enhances the mixture homogeneity of air and fuel greatly, substantially improve combustion conditions, reduce the discharge of NOx.
Accompanying drawing explanation
Fig. 1: existing general dry type low-nitrogen oxide discharging combustion chamber;
Fig. 2: the example three-dimensional appearance figure of the present invention;
Fig. 3: the blade convex surface front view of the present invention;
Fig. 4: the 3-D view of another kind of surface tissue of the present invention.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail:
As shown in Figure 2, the swirl vane of a kind of ground combustion machine combustion chamber of the present embodiment, swirl vane 2 cross section of the present invention is a kind of aerofoil profile, surface, side has one layer of tectum windward, it is circular groove 9 that this tectum has the profile specified in a large number by a large amount of dot matrix member, position boss in the inner is also circular 8 accordingly, and the thickness of described swirl vane surface coating is between 0.2��0.3mm.
As shown in Figure 3, for the blade convex surface front view of the present invention, the diameter of the circular groove 9 of dot matrix member is 0.8mm, the degree of depth is 0.1��0.2mm, the outside diameter being positioned at its inner circular boss 8 is 0.5mm, and interior diameter is 0.3mm, and the height of boss is 0.08��0.12mm, and the width between centers of groove or boss between two is 0.7mm, described a large amount of dot matrix member covers the 70% of the front end, whole surface windward of swirl vane 2. The installation angle of described main combustion stage swirl vane 2 is 3��5 ��.
As shown in Figure 4, for the structure formation of another kind of surperficial dot matrix member of the present invention, the circumscribed circle diameter of positive hexagonal indentations 10 is 0.1��0.2mm, the outside circumscribed circle diameter of position positive hexagon boss 11 in the inner is 0.5mm, the external circular diameter in interior limit is 0.3mm, the height of boss is 0.08mm��0.12mm, and the width between centers of groove or boss between two is 0.75mm.
Above-described embodiment is only the preferred embodiment of the present invention, it should not become limiting the scope of the invention, and the specific embodiment of the present invention does not limit above-described embodiment. Foregoing according to the present invention; according to ordinary technical knowledge and the customary means of this area; not departing under the above-mentioned basic fundamental thought prerequisite of the present invention, the present invention can also make the amendment of other various ways, replacement or change, all should drop within the scope of rights protection of the present invention.
Claims (6)
1. the swirl vane of a ground combustion machine combustion chamber, it is characterized in that, described swirl vane cross section is a kind of 6 race's aerofoil profiles, surface, side has one layer of tectum windward, this tectum has in the multi-facet hexagon or circle, hexagon or circle that dot matrix member specifies each has two in this Polygons or circle grade hexagon or circle.
2. the swirl vane of a kind of ground combustion machine combustion chamber according to claim 1, it is characterised in that, the installation angle of described swirl vane is 3��5 ��.
3. the swirl vane of a kind of ground combustion machine combustion chamber according to claim 1, it is characterised in that, the 70% of the front end, whole surface windward that described a large amount of dot matrix member covers swirl vane, and the width between centers of groove or boss between two is 0.7mm.
4. the swirl vane of a kind of ground combustion machine combustion chamber according to claim 1, it is characterized in that, the groove shapes of described dot matrix member is hexagon or circle, and the diameter of circular groove is 0.8mm, the outside diameter of round boss is 0.5mm, and interior diameter is 0.3mm.
5. the swirl vane of a kind of ground combustion machine combustion chamber according to claims 1 to 4, it is characterized in that, the circumscribed circle diameter of described positive hexagonal indentations is 0.1��0.2mm, the outside circumscribed circle diameter of position positive hexagon boss in the inner is 0.5mm, the external circular diameter in interior limit is 0.3mm, the height of boss is 0.08mm��0.12mm, and the width between centers of groove or boss between two is 0.75mm.
6. the swirl vane of a kind of ground combustion machine combustion chamber according to claims 1 to 5, it is characterised in that, the thickness of described swirl vane surface coating is between 0.1mm��0.2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610146423.3A CN105650676A (en) | 2016-03-15 | 2016-03-15 | Rotational flow blade of combustion chamber of ground gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610146423.3A CN105650676A (en) | 2016-03-15 | 2016-03-15 | Rotational flow blade of combustion chamber of ground gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105650676A true CN105650676A (en) | 2016-06-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610146423.3A Pending CN105650676A (en) | 2016-03-15 | 2016-03-15 | Rotational flow blade of combustion chamber of ground gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN105650676A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106838598A (en) * | 2017-04-06 | 2017-06-13 | 吉林大学 | A kind of bionical Anti-erosion surface texture |
| CN109539307A (en) * | 2018-11-08 | 2019-03-29 | 西北工业大学 | Do the swirler blades of pit processing in a kind of surface |
| CN114636168A (en) * | 2022-03-15 | 2022-06-17 | 西北工业大学 | Novel air swirler who contains torrent emergence structure |
Citations (11)
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| US5167485A (en) * | 1990-01-08 | 1992-12-01 | General Electric Company | Self-cooling joint connection for abutting segments in a gas turbine engine |
| CN1776200A (en) * | 2004-11-16 | 2006-05-24 | 通用电气公司 | Method for making a repaired turbine engine stationary vane assembly and repaired assembly |
| JP2006283606A (en) * | 2005-03-31 | 2006-10-19 | Mitsubishi Heavy Ind Ltd | High temperature member for gas turbine |
| CN101131095A (en) * | 2006-08-21 | 2008-02-27 | 通用电气公司 | Conformal tip baffle airfoil |
| CN101148994A (en) * | 2006-07-27 | 2008-03-26 | 通用电气公司 | Dust hole dome blade |
| CN101839150A (en) * | 2009-03-18 | 2010-09-22 | 通用电气公司 | Use and transform the method for the film-cooling augmentation device that is used for turbine airfoil |
| EP2275645A2 (en) * | 2009-07-17 | 2011-01-19 | Rolls-Royce Corporation | Gas turbine component comprising stress mitigating features |
| CN102102961A (en) * | 2009-12-16 | 2011-06-22 | 北京化工大学 | Self rotation type rotor connection structure in heat exchange tube |
| CN103291371A (en) * | 2012-02-29 | 2013-09-11 | 通用电气公司 | Scalloped surface turbine stage with purge trough |
| US20140311150A1 (en) * | 2013-04-17 | 2014-10-23 | General Electric Company | Fuel nozzle for a pre-mix combustor of a gas turbine engine |
| CN104791019A (en) * | 2014-01-17 | 2015-07-22 | 通用电气公司 | Turbine blade and method for enhancing life of turbine blade |
-
2016
- 2016-03-15 CN CN201610146423.3A patent/CN105650676A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5167485A (en) * | 1990-01-08 | 1992-12-01 | General Electric Company | Self-cooling joint connection for abutting segments in a gas turbine engine |
| CN1776200A (en) * | 2004-11-16 | 2006-05-24 | 通用电气公司 | Method for making a repaired turbine engine stationary vane assembly and repaired assembly |
| JP2006283606A (en) * | 2005-03-31 | 2006-10-19 | Mitsubishi Heavy Ind Ltd | High temperature member for gas turbine |
| CN101148994A (en) * | 2006-07-27 | 2008-03-26 | 通用电气公司 | Dust hole dome blade |
| CN101131095A (en) * | 2006-08-21 | 2008-02-27 | 通用电气公司 | Conformal tip baffle airfoil |
| CN101839150A (en) * | 2009-03-18 | 2010-09-22 | 通用电气公司 | Use and transform the method for the film-cooling augmentation device that is used for turbine airfoil |
| EP2275645A2 (en) * | 2009-07-17 | 2011-01-19 | Rolls-Royce Corporation | Gas turbine component comprising stress mitigating features |
| CN102102961A (en) * | 2009-12-16 | 2011-06-22 | 北京化工大学 | Self rotation type rotor connection structure in heat exchange tube |
| CN103291371A (en) * | 2012-02-29 | 2013-09-11 | 通用电气公司 | Scalloped surface turbine stage with purge trough |
| US20140311150A1 (en) * | 2013-04-17 | 2014-10-23 | General Electric Company | Fuel nozzle for a pre-mix combustor of a gas turbine engine |
| CN104791019A (en) * | 2014-01-17 | 2015-07-22 | 通用电气公司 | Turbine blade and method for enhancing life of turbine blade |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106838598A (en) * | 2017-04-06 | 2017-06-13 | 吉林大学 | A kind of bionical Anti-erosion surface texture |
| CN109539307A (en) * | 2018-11-08 | 2019-03-29 | 西北工业大学 | Do the swirler blades of pit processing in a kind of surface |
| CN114636168A (en) * | 2022-03-15 | 2022-06-17 | 西北工业大学 | Novel air swirler who contains torrent emergence structure |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160608 |
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| WD01 | Invention patent application deemed withdrawn after publication |