CN109539314A - A kind of novel radial swirler with wave blade - Google Patents
A kind of novel radial swirler with wave blade Download PDFInfo
- Publication number
- CN109539314A CN109539314A CN201811349348.6A CN201811349348A CN109539314A CN 109539314 A CN109539314 A CN 109539314A CN 201811349348 A CN201811349348 A CN 201811349348A CN 109539314 A CN109539314 A CN 109539314A
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- Prior art keywords
- blade
- cyclone
- radial swirler
- air
- wave
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
-
- 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)
Abstract
The technical problem to be solved by the present invention is to propose a kind of novel radial swirler with wave blade, the combustion chamber cyclone includes multiple blades, the center cone of cyclone front and rear baffle and bullet-shaped, the radial swirler structure is simple, it is easily manufactured, it is suitable for being matched with the flowing of the air-flow of combustor head, blade surface is corrugated gully, blade interior is axially disposed mutually separated cavity, for transporting fuel oil, tail portion is sinusoidal waveform, it is effectively improved eddy flow effect, it is more uniform to make fuel gas and air mix, with forming better quality gaseous mixture.
Description
Technical field
The present invention relates to a kind of components of gas turbine, and in particular to a kind of novel radial rotation with wave blade
Flow device.
Background technique
In gas-turbine unit, air is compressed by compressor, and is mixed and burned with fuel generates stream in the combustion chamber
Heat combustion flow downstream, and the turbines at different levels by extracting energy, high-pressure turbine drive compressor, and low-pressure turbine then passes through band
Dynamic fan, for example, upstream fan in a typical aviation turbofan gas-turbine unit and do useful work.Combustion
Burn room performance be for the overall performance of gas-turbine unit it is highly important, compressed air is mixed in combustion chamber and fuel oil
It closes, becomes the mixture of fuel oil and air, then ignition generates combustion gas.Vortex motion in gas-turbine combustion chamber is used for
Stablize flame, and promotes the mixing of fuel and air, thus, vortex motion is gas turbine combustors aerodynamics
Essential component part, vortex motion generally realize that common cyclone mainly has by various forms of cyclones
Two kinds of forms: axial-flow type cyclone and radial cyclone；The selection of cyclone type depends primarily on the indoor air of burning
Flow direction, the head cyclone of straight-flow combustor are mostly advisable with axial-flow type cyclone, and reverse-flow can type combustor is then mostly with radial vortex
Device is advisable.
Judge the swirl strength of cyclone, generally defined with swirling number, swirling number is bigger, and swirl strength is higher, meaning
Fluid whirl it is stronger.In lean fuel premixed combustion room, swirling number is particularly important, because swirling number is too small to will cause burning reflux
Area can not be formed, flame instability, incomplete combustion；However when swirling number is excessive (Re > 18000), meeting be swum out of under cyclone
Existing vortex core can generate very strong Vortex Shedding phenomenon into hole phenomenon, and with the pressure oscillation of low frequency, suitable amplitude, this is
Lean-gas premixed combustion combustion chamber is relatively also easy to produce the basic reason of oscillatory occurences.
Under normal circumstances, gas turbine includes the combustion chamber with cyclone, together with fuel nozzle therein (or eddy flow fire
Expect nozzle).Each cyclone in nozzle includes one or more channels, with for by fuel air mixture (or only
By air) it is transmitted to combustion chamber.The eddy flow fuel nozzle improves fuel and sky for stablizing to flame before ignition
The mixing of gas, the cyclone include the blade of multiple extensions from nozzle, and have aerodynamic profile, and swirler blades are usually wrapped
Channel is included, for providing fuel to the teasehole on the surface of the swirler blades.When fuel is discharged from teasehole, combustion
Expect with the fluid for flowing through the swirler blades to be usually that air is mixed.In general, swirler blades are in the swirler blades
At trailing edges have bending, can in the cyclone or the downstream of the cyclone generate stream separation, which increase backfires
A possibility that occurring with flame stabilization.To solve these flow field problems, a kind of common method is modified to blade profile.
Change requires new casting process and Mechanical processing of casting every time.
Summary of the invention
The technical problem to be solved by the present invention is to propose a kind of novel radial swirler with wave blade.It is described
Combustion chamber cyclone includes the center cone of multiple blades and cyclone front and rear baffle and bullet-shaped, the radial swirler structure
Simply, easily manufactured, it is suitable for being matched with the air-flow flowing side of combustor head, blade surface is corrugated a gully, in blade
Portion is axially disposed mutually separated cavity, and for transporting fuel oil, tail portion is sinusoidal waveform, is effectively improved eddy flow effect.
Technical solution
The purpose of the present invention is to provide a kind of novel radial swirlers with wave blade, allow good fuel
(the especially mixing of liquid fuel and air) is mixed with air device, and the uniform air flow of maximum possible, makes combustion chamber cyclone
The air-flow vortex of generation is relatively reliable effectively.
Technical solution of the present invention is as follows:
To solve its technical problem, a kind of novel radial swirler with wave blade of the present invention includes front-and-back stop
Plate, waveform blade, the center cone of bullet-shaped.
The waveform blade, it is characterised in that: two planes are connected with cyclone front and rear baffle blade respectively up and down, and blade is whole
The streamlined structure of body, side wall are corrugated surface there are gully, and blade inlet edge has protrusion, and trailing edge is sinusoidal waveform, and blade is hollow
Structure is provided with two cavitys (ante-chamber and back cavity) being mutually mutually separated, and is used for fuel oil transportation, and row spray is respectively provided with inside and outside leading edge
The shape in hole, spray orifice can also use long slit, rectangle, polygon in addition to basic circle, and blade incline along disc radius axis
Oblique 30 ° of angle, while blade opposing axial is distributed uniformly and circumferentially, totally 10 blades, 36 ° of central angle of interval are preceding
Edge and trailing edge are slightly less than baffle outer diameter and internal diameter about 2mm~4mm.
The center cone of the bullet-shaped, it is characterised in that: center cone column diameter is about the one third of air stream outlet,
Spout uses direct projection multiple exit formula thereon, and main injection jet diameter about 0.1mm at center, side is distributed uniformly and circumferentially two numbers of rows
Amount is 10 subjet, diameter about 0.05~0.08mm.
The invention has the following advantages:
The present invention is a kind of novel radial swirler with wave blade, and Wave blade passes through whole streamlined
Design structure, surface gully shape, when so that air-flow flowing through channel, air-flow pass through it is smaller by resistance when blade inlet edge, distribution
More uniformly, improve flow conditions, trailing edge sinusoidal waveform has circumferential deflection in air current flow direction, makes air-flow by one
Fixed active force, and in vortex is flowed to, local dip is strengthened, upstream fuel gas and air can be made to mix more equal
It is even, form better quality ground gaseous mixture；Blade interior is provided with the cavity being spaced apart from each other, respectively ante-chamber and back cavity, cavity fortune
Defeated mixed fuel gas enables fuel gas to sufficiently achieve channel depths, and front and back cavity has channel to be connected, and fuel gas will be from edge
Spout spray, lengthen the distance of air-fuel mixture, keep air-fuel mixture more abundant.
Detailed description of the invention
Fig. 1: radial swirler structural schematic diagram of the invention
Fig. 2: radial swirler Leaf positional distribution figure of the invention
Fig. 3: radial swirler blade construction schematic diagram of the invention
In figure: 1, cyclone front apron, 2, wave blade, 3, center cone, 4, cyclone rear baffle, 5, blade ante-chamber,
6, blade back cavity, 7, blade inlet edge spout, 8, blade inlet edge, 9, trailing edge, 10, center nozzle.
Specific embodiment
Now in conjunction with attached drawing, the invention will be further described:
In conjunction with Fig. 1, Fig. 2, Fig. 3, the present invention provides: the present invention proposes a kind of novel radial vortex with wave blade
Device can be effectively improved air-flow flow distribution and air-fuel mixture situation, generate stable high-quality amount and mix gas and eddy flow whirlpool.Fig. 1 is this
Invention radial swirler structural schematic diagram, radial swirler front apron (1), wave blade (2), center nozzle (3), rear baffle
(4)；Fig. 2 is radial swirler Leaf positional distribution figure, Fig. 3 is radial swirler blade construction schematic diagram, and wave can be clearly seen
The structure of blade, blade ante-chamber (5), blade back cavity (6), blade inlet edge spout (7).
Radial swirler front apron (1) and rear baffle (4) are in order to allow the flow to radially flow into and by cyclone
After blade air-flow can return to flow along central axis direction, generated at cyclone rear portion and stablize eddy flow；Swirler blades use
Wave blade (2), blade generally airflow design, leading edge have protrusion in direction of flow, it is contemplated that can generate mutually opposing rotation
Vortex, to maintain the flowing of air or air fuel mixture, and then improve flame holding, and reduce on cyclone
Pressure drop；There is inclined hole to spray spray orifice inside and outside leading edge, the shape of spray orifice except it is basic it is round in addition to can also using long slit, rectangle,
Polygon is all made of inclined hole, and fuel oil is sprayed to rear ramp, in the mixing of cyclone beginning just preliminary progress fuel oil and air,
The case where small part fuel oil can also impinge upon with air and generate second-time breakage on center cone wall surface, improve air-fuel mixture；Trailing edge is just
String waveform, and has circumferential deflection in air current flow direction so that air-flow in flow direction by certain active force, and locate
In flowing to vortex, local dip is strengthened, upstream fuel gas and air can be made to mix more uniformly, with forming better quality
Gaseous mixture；Blade interior is provided with the cavity being spaced apart from each other, respectively ante-chamber and back cavity, and cavity transports mixed fuel gas, makes
Fuel gas can sufficiently achieve channel depths, and front and back cavity has channel to be connected, and fuel gas will be sprayed from the spout of edge, lengthen oil
The distance of gas mixing, keeps air-fuel mixture more abundant.
Claims (4)
1. a kind of novel radial swirler with wave blade, including cyclone front apron, wave blade, bullet-shaped
Center cone and cyclone rear baffle, characteristic be: wave blade up and down two planes respectively with cyclone front and rear baffle phase
Even, integrally streamlined structure, side wall are corrugated surface there are gully to blade, and blade inlet edge has protrusion, and trailing edge is sinusoidal waveform, leaf
Piece is hollow structure, is provided with two cavitys (ante-chamber and back cavity) being mutually mutually separated, is respectively provided with row's spray orifice inside and outside leading edge.
2. a kind of novel radial swirler with wave blade according to claim 1, it is characterised in that: baffle is
Circular configuration for specification air-flow flow path and provides blade support.
3. a kind of novel radial swirler with wave blade according to claim 1, it is characterised in that: on blade
Lower two planes are connected with cyclone front and rear baffle respectively, and integrally streamlined structure, side wall are that there are gully, leaves for corrugated surface to blade
Piece leading edge has protrusion, and trailing edge is sinusoidal waveform, and blade is hollow structure, be provided with mutually be mutually separated two cavitys (ante-chamber and after
Chamber), it is used for fuel oil transportation, row's spray orifice is respectively provided with inside and outside leading edge, the shape of spray orifice can also be using length in addition to basic circle
Slit, rectangle, polygon, blade is along 30 ° of slanted angle of disc radius axis, while blade opposing axial is along the circumferential direction
It is uniformly distributed, totally 10 blades, is spaced 36 ° of central angle, leading edge and trailing edge are slightly less than baffle outer diameter and internal diameter about 2mm~4mm.
4. a kind of novel radial swirler with wave blade according to claim 1, it is characterised in that: center cone
Approximate bullet shape, cylinder maximum gauge are about the one third of air stream outlet, and spout uses direct projection multiple exit formula thereon, in
Main injection jet diameter about 0.1mm at the heart, side are distributed uniformly and circumferentially the subjet that two rows of quantity are 10, and diameter is about
0.05~0.08mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811349348.6A CN109539314A (en) | 2018-11-14 | 2018-11-14 | A kind of novel radial swirler with wave blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811349348.6A CN109539314A (en) | 2018-11-14 | 2018-11-14 | A kind of novel radial swirler with wave blade |
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| Publication Number | Publication Date |
|---|---|
| CN109539314A true CN109539314A (en) | 2019-03-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811349348.6A Pending CN109539314A (en) | 2018-11-14 | 2018-11-14 | A kind of novel radial swirler with wave blade |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520755A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Low-pollution combustor head swirler structure |
| CN112728584A (en) * | 2020-11-24 | 2021-04-30 | 南京航空航天大学 | Flame stabilizer, radial flame stabilizer and combustion chamber |
| CN113864821A (en) * | 2020-06-30 | 2021-12-31 | 通用电气公司 | Improved fuel circuit for fuel injector |
| CN114674011A (en) * | 2022-03-14 | 2022-06-28 | 中国航空发动机研究院 | Swirler and driving system |
| CN115200048A (en) * | 2022-05-31 | 2022-10-18 | 北京航空航天大学 | Combustion chamber with two-stage blade enhanced mixing |
| CN115682030A (en) * | 2021-07-29 | 2023-02-03 | 通用电气公司 | Mixer blade |
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| CN1789817A (en) * | 2004-12-17 | 2006-06-21 | 通用电气公司 | Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers |
| CN102378878A (en) * | 2009-04-06 | 2012-03-14 | 西门子公司 | Swirler, combustion chamber, and gas turbine with improved swirl |
| CN205825112U (en) * | 2016-07-13 | 2016-12-21 | 哈尔滨汽轮机厂有限责任公司 | A kind of two points of swirl-flow premixed burner noz(zle)s of gas turbine dry low pollution combustor unit |
| CN205825113U (en) * | 2016-06-16 | 2016-12-21 | 上海和兰动力科技有限公司 | The radial swirler of gas-turbine combustion chamber |
| CN206905031U (en) * | 2017-06-14 | 2018-01-19 | 华电电力科学研究院 | A kind of cyclone with lobe swirl vane |
| CN208058907U (en) * | 2018-04-12 | 2018-11-06 | 中国船舶重工集团公司第七0三研究所 | A kind of variable-flow cyclone |
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Patent Citations (6)
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| CN1789817A (en) * | 2004-12-17 | 2006-06-21 | 通用电气公司 | Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers |
| CN102378878A (en) * | 2009-04-06 | 2012-03-14 | 西门子公司 | Swirler, combustion chamber, and gas turbine with improved swirl |
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| CN206905031U (en) * | 2017-06-14 | 2018-01-19 | 华电电力科学研究院 | A kind of cyclone with lobe swirl vane |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520755A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Low-pollution combustor head swirler structure |
| CN113864821A (en) * | 2020-06-30 | 2021-12-31 | 通用电气公司 | Improved fuel circuit for fuel injector |
| CN112728584A (en) * | 2020-11-24 | 2021-04-30 | 南京航空航天大学 | Flame stabilizer, radial flame stabilizer and combustion chamber |
| CN112728584B (en) * | 2020-11-24 | 2021-12-07 | 南京航空航天大学 | Flame stabilizer, radial flame stabilizer and combustion chamber |
| CN115682030A (en) * | 2021-07-29 | 2023-02-03 | 通用电气公司 | Mixer blade |
| CN114674011A (en) * | 2022-03-14 | 2022-06-28 | 中国航空发动机研究院 | Swirler and driving system |
| CN114674011B (en) * | 2022-03-14 | 2023-04-25 | 中国航空发动机研究院 | Cyclone and power system |
| CN115200048A (en) * | 2022-05-31 | 2022-10-18 | 北京航空航天大学 | Combustion chamber with two-stage blade enhanced mixing |
| CN115200048B (en) * | 2022-05-31 | 2023-09-19 | 北京航空航天大学 | Two-stage blade intensified mixing combustion chamber |
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Application publication date: 20190329 |
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| WD01 | Invention patent application deemed withdrawn after publication |