CN107246629A - Cyclone with lobe swirl vane - Google Patents
Cyclone with lobe swirl vane Download PDFInfo
- Publication number
- CN107246629A CN107246629A CN201710446949.8A CN201710446949A CN107246629A CN 107246629 A CN107246629 A CN 107246629A CN 201710446949 A CN201710446949 A CN 201710446949A CN 107246629 A CN107246629 A CN 107246629A
- Authority
- CN
- China
- Prior art keywords
- lobe
- swirl vane
- cyclone
- feed track
- chamber
- 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
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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
- F23R3/04—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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/70—Baffles or like flow-disturbing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cyclones (AREA)
Abstract
The invention discloses the cyclone with lobe swirl vane, including lobe swirl vane, cyclone, the cyclone is cylinder, cyclone is axially inside provided with interior feed track and outer feed track, interior feed track is cyclone hollow central interior, outer feed track is interior feed track outer annular shape cavity, lobe swirl vane is connected with cyclone side, lobe swirl vane is streamlined structure, the tail edge of lobe swirl vane is wavy lobe structure, lobe swirl vane has circumferential deflection in the flowing direction, the wavelength direction of lobe is the radial direction of cyclone gas channel, lobe swirl vane is the shell structure of inner hollow and is provided with two cavitys mutually separated, two cavitys are respectively ante-chamber and back cavity, ante-chamber is connected with outer feed track, back cavity is connected with interior feed track.
Description
Technical field
The invention belongs to the equipment part field of gas turbine or gas fired-boiler, the particularly rotation with lobe swirl vane
Flow device.
Background technology
In order to further reduce the gas turbine of operating on gaseous fuel and the discharged nitrous oxides index of boiler, it is necessary to this
A little equipment are operated under premixed combustion mode.Premixed combustion mode needs fuel and air to be refired after uniformly mixing, and fires
It is more uniform that material is mixed in atmosphere, and its combustion stability and discharge index are better.
At present, the hybrid mode of fuel gas and air is：The perforate near cyclone upstream or swirler blades leading edge, combustion
Expect gas by this some holes to be mixed to form homogeneous mixed gas with air in airflow direction air inlet passage.Work as fuel
Gas pressure deficiency often cannot get quality homogeneous mixed gas, and in eddy flow well when not reaching enough penetration depths
Device downstream is needed for the reserved larger space of the aerial diffusion of fuel gas.
The content of the invention
The trailing edge structures of cyclone are designed to lobe structure by the purpose of the present invention, and increase fuel gas blowout in blade trailing edge
Mouthful, make the wavy blade trailing edge of whole piece all can be as fuel gas spout.
In order to solve the above problems, the present invention proposes the cyclone with lobe swirl vane.
The technical solution adopted in the present invention is：
Cyclone with lobe swirl vane, including lobe swirl vane, cyclone, the cyclone are cylinder,
Cyclone is axially inside provided with interior feed track and outer feed track, and interior feed track is cyclone hollow central interior, outer conveying
Road is interior feed track outer annular shape cavity, and lobe swirl vane is connected with cyclone side, and lobe swirl vane is streamlined
Structure, the tail edge of lobe swirl vane is wavy lobe structure, and lobe swirl vane has week in the flowing direction
To deflection, the wavelength direction of lobe is the radial direction of cyclone, lobe swirl vane for inner hollow shell structure and
Be provided with two cavitys mutually separated, two cavitys are respectively ante-chamber and back cavity, and ante-chamber is connected with outer feed track, back cavity with it is interior
Feed track is connected.Interior feed track and outer feed track are used to convey fuel gas to be mixed, and will be fired by the rotation of cyclone
Material conductance enters lobe swirl vane, lobe swirl vane be used for by fuel gas with perpendicular to airflow direction be discharged into air duct with
Air is mixed to form homogeneous mixed gas, and the design of ante-chamber and back cavity ensures that fuel gas can sufficiently reach passage depths, and
Ante-chamber is connected with outer feed track, and back cavity is connected with interior feed track, because central cavity volume is larger, is in using back cavity after passage
The position of side, enables substantial amounts of fuel gas to go deep into passage depths, and a small amount of combustion gas is entered by the outer feed track of small volume
Pressure is larger when entering ante-chamber, will not also lead to not enter passage depths due to local pressure deficiency.
Further, the cyclone afterbody is provided with the center cone of bullet-shaped, and center cone is located at lobe swirl vane
Rear.The effect of center cone is to prevent air-flow from producing separation after cyclone, it is to avoid reduce gas pressure after air-flow separation.
Further, spray-hole is provided with the ante-chamber of the lobe swirl vane, spray-hole is connected with ante-chamber.Spray-hole
Fuel gas can be made to be sprayed from lobe swirl vane side, even if only a small amount of fuel gas can still be discharged into passage into ante-chamber
It is interior.
Further, the lobe of the lobe swirl vane is provided with spout, spout using split in the middle of lobe seam perforate or
Person's lobe laterally splits seam perforate mode, and spout is connected with back cavity.The fuel gas that spout sprays is in stream parallel to airflow direction
To whirlpool region, good mixed effect can reach.
It is preferred that, the nozzle configuration is long slit, rectangle, circle.The whirlpool that flows to that special geometric profile is produced is strengthened
Local dip, makes the fuel gas and air of upstream mix evenly.
Further, the lobe of the lobe swirl vane has Wave crest and wave trough, can be semicircle, triangle, it is square,
Sinusoidal waveform.The whirlpool that flows to that special geometric profile is produced strengthens local dip, the fuel gas and air of upstream is mixed more
Uniformly.
It is preferred that, the ratio between the lobe wave height and wavelength are 0.2 to 1, and the ratio between wavelength and channel height are 0.1 to 1.It is special
The whirlpool that flows to that geometric shape is produced strengthens local dip, the fuel gas and air of upstream is mixed evenly
It is preferred that, the lobe original position lobe swirl vane leading edge towards trailing edge direction 0.4~0.9 times of arc length
Place.The whirlpool that flows to that special geometric profile is produced strengthens local dip, the fuel gas and air of upstream is mixed evenly
The present invention compared with the existing technology has advantages below and effect：
1st, fuel gas can be sprayed in the case where fuel atmospheric pressure is low, be not required to reach by the present invention by trailing edge spout
Enough penetration depths more can uniformly dispense fuel gas in atmosphere.
2nd, the present invention is in by blade trailing edge lobe parallelism structural in airflow direction and flows to whirlpool region, strengthen office
Portion is disturbed, and powerful fuel gas-air mixing effect is produced, so as to form the higher homogeneous gaseous mixture of quality.
3rd, the present invention realizes fuel gas-air mixing effect by blade trailing edge lobe structure, effectively reduces after cyclone
Portion is used to form the space of homogeneous gaseous mixture, it is to avoid needed in cyclone downstream for the aerial diffusion of fuel gas it is reserved larger
Space.
4th, the wavy blade trailing edge of whole piece of the present invention all can as fuel gas spout, compared to by leading edge spray orifice jet,
Jet amount is bigger, and jet effect is more preferable.
Brief description of the drawings
The accompanying drawing for constituting the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not constitute inappropriate limitation of the present invention.
Fig. 1 is the axial cross-sectional view of grade of the present invention；
Fig. 2 is the orthographic projection cross-sectional view of the present invention；
Fig. 3 is the lobe swirl vane structural representation of the present invention；
Fig. 4 is the lobe nozzle exit sectional view of embodiment 4；
Fig. 5 is the lobe nozzle exit sectional view of embodiment 1；
Fig. 6 is the lobe nozzle exit sectional view of embodiment 2,3；
Fig. 7 is the structural representation of the present invention.
Label declaration：
Radome fairing 1；Trailing edge lobe spout 2；Back cavity 3；Lobe swirl vane 4；Outer shroud fuel tube 5；Inner ring fuel
Conveyance conduit 6；Gas channel 7；Leading edge spout 8；Ante-chamber 9；Center cone 10；Lobe original position 11.
Embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, it is right below in conjunction with drawings and Examples
The present invention is further elaborated.It should be appreciated that specific embodiment described herein is only to explain the present invention, not
For limiting the present invention.
Embodiment 1：As shown in Fig. 1,2,3,5, the swirler assembly with lobe swirl vane, for gaseous fuel combustion
Burn, including radome fairing 1, lobe swirl vane 4, cyclone, cyclone is cylinder, is internally provided with cylindrical cavity-inner ring
Fuel tube 6 and annular cavity-outer shroud fuel tube 5, it is defeated that inner ring fuel tube 6 is located at outer shroud fuel
Send the inner side of pipeline 5；Center cone 10 is located at fuel tube rear portion；Cyclone is radially connected with lobe swirl vane 4；Lobe
Swirl vane 4 is hollow, and the lobe of lobe swirl vane is sinusoidal waveform, and lobe original position is in lobe swirl vane leading edge direction
At 0.4 times of arc length in trailing edge direction, the ratio between lobe wave height (h) and wavelength (l) are 0.2, the ratio between wavelength (l) and channel height (bl)
It is front and rear to be divided into two chambers for 0.1, ante-chamber 9 and back cavity 3 respectively with outer shroud fuel tube 5 and the phase of inner ring fuel tube 6
Even；Leading edge spout 8 is connected with ante-chamber, and trailing edge lobe spout 2 is connected with back cavity；The radial outside of lobe swirl vane 4 connects rectification
Cover 1.Trailing edge lobe spout 2 splits seam perforate using centre, and trailing edge lobe spout 2 is shaped as long slit.
In use, the air required for burning is by the gas channel 7 in the middle of outer shroud fuel tube 5 and radome fairing 1,
Flow through lobe swirl vane 4；Fuel gas is delivered to ante-chamber 9 via outer shroud fuel tube 5, is sprayed from leading edge spout 8, another
Road fuel gas is delivered to back cavity 3 via inner ring fuel tube 6, is sprayed from trailing edge lobe spout 2.The effect of center cone 10 is
Prevent air-flow from producing separation after cyclone.The fuel gas that gas fuel orifice 8 sprays is perpendicular to airflow direction, by gas
Pressure produces enough penetration depths and mixed with air.The whirlpool that flows to that the geometric shape of trailing edge lobe spout 2 is produced strengthens office
Portion is disturbed, and the fuel gas and air of upstream is mixed evenly.The fuel gas that trailing edge lobe spout 2 sprays is parallel to air-flow side
To being in and flow to whirlpool region, can reach good mixed effect.
Embodiment 2：
The present embodiment is substantially the same manner as Example 1, and distinctive points are：As shown in Fig. 1,2,3,6, lobe is revolved in embodiment 2
It is semicircle to flow the lobe of blade, lobe original position in lobe swirl vane leading edge towards at 0.5 times of arc length in trailing edge direction,
Trailing edge lobe spout 2 splits seam perforate mode using leeward side, and trailing edge lobe spout 2 is shaped as long slit.
Embodiment 3：
The present embodiment is substantially the same manner as Example 1, and distinctive points are：As shown in Fig. 1,2,3,6, lobe is revolved in embodiment 3
The lobe for flowing blade is triangle, lobe original position in lobe swirl vane leading edge towards at 0.5 times of arc length in trailing edge direction,
The ratio between lobe wave height (h) and wavelength (l) are 0.5, and the ratio between wavelength (l) and channel height (bl) are 0.5, and trailing edge lobe spout 2 is adopted
Seam perforate mode is split with leeward side, trailing edge lobe spout 2 is shaped as rectangle.
Embodiment 4：
The present embodiment is substantially the same manner as Example 1, and distinctive points are：As shown in Figure 1,2,3, 4, lobe is revolved in embodiment 4
Flow the lobe of blade to be square, lobe original position in lobe swirl vane leading edge towards at 0.9 times of arc length in trailing edge direction, ripple
The ratio between valve wave height (h) and wavelength (l) are 1, and the ratio between wavelength (l) and channel height (bl) are 1, and trailing edge lobe spout 2 is using windward
Seam perforate mode is split in side, and trailing edge lobe spout 2 is shaped as circle.
The foregoing is only presently preferred embodiments of the present invention, be not intended to limit the invention, it is all the present invention spirit and
Within principle, any modification, equivalent substitution and improvements made etc. should be included in the scope of the protection.
Claims (8)
1. the cyclone with lobe swirl vane, it is characterised in that including lobe swirl vane, cyclone, the cyclone
For cylinder, cyclone is axially inside provided with interior feed track and outer feed track, and interior feed track is that cyclone center of inside is empty
Chamber, outer feed track is interior feed track outer annular shape cavity, and lobe swirl vane is connected with cyclone side, lobe swirl vane
For streamlined structure, lobe swirl vane is provided with circumferential deflection in the flowing direction, and the tail edge of lobe swirl vane is
Wavy lobe structure, the wavelength direction of lobe is the radial direction of cyclone, and lobe swirl vane is the shell of inner hollow
Body structure and two cavitys mutually separated are provided with, two cavitys are respectively ante-chamber and back cavity, ante-chamber connects with outer feed track
Logical, back cavity is connected with interior feed track.
2. the cyclone according to claim 1 with lobe swirl vane, it is characterised in that the cyclone afterbody is set
The center cone of bullet-shaped is equipped with, center cone is located at lobe swirl vane rear.
3. the cyclone according to claim 1 with lobe swirl vane, it is characterised in that the lobe swirl vane
Ante-chamber at be provided with spray-hole, spray-hole is connected with ante-chamber.
4. the cyclone according to claim 3 with lobe swirl vane, it is characterised in that the lobe swirl vane
Lobe be provided with spout, spout is using splitting seam perforate or lobe laterally splits seam perforate mode, spout and back cavity in the middle of lobe
Connection.
5. the cyclone according to claim 4 with lobe swirl vane, it is characterised in that the nozzle configuration is length
Slit, rectangle, circle.
6. the cyclone according to claim 3 with lobe swirl vane, it is characterised in that the lobe swirl vane
Lobe there is Wave crest and wave trough, can be semicircle, triangle, square, sinusoidal waveform.
7. the cyclone according to claim 6 with lobe swirl vane, it is characterised in that the lobe wave height and ripple
The ratio between long is 0.2 to 1, and the ratio between wavelength and channel height are 0.1 to 1.
8. the cyclone according to claim 7 with lobe swirl vane, it is characterised in that the lobe original position
In lobe swirl vane leading edge towards at 0.4~0.9 times of arc length in trailing edge direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710446949.8A CN107246629A (en) | 2017-06-14 | 2017-06-14 | Cyclone with lobe swirl vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710446949.8A CN107246629A (en) | 2017-06-14 | 2017-06-14 | Cyclone with lobe swirl vane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107246629A true CN107246629A (en) | 2017-10-13 |
Family
ID=60018940
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710446949.8A Pending CN107246629A (en) | 2017-06-14 | 2017-06-14 | Cyclone with lobe swirl vane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107246629A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111536555A (en) * | 2020-05-08 | 2020-08-14 | 中国航发湖南动力机械研究所 | Engine and engine combustion chamber thereof |
| CN113551259A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | Wave-shaped middle-slit type V-shaped flame stabilizer with lobe partition plate |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101625131A (en) * | 2008-01-22 | 2010-01-13 | 通用电气公司 | Lobe nozzles for fuel and air injection |
| JP2012237548A (en) * | 2011-05-11 | 2012-12-06 | Alstom Technology Ltd | Lobed swirler |
| CN102859281A (en) * | 2010-02-23 | 2013-01-02 | 西门子公司 | Fuel injector and swirler assembly with lobed mixer |
| CN106051826A (en) * | 2016-06-12 | 2016-10-26 | 哈尔滨工程大学 | Pyrolysis fuel gas and air rapid mixing device |
| CN106123031A (en) * | 2015-05-08 | 2016-11-16 | 安萨尔多能源瑞士股份公司 | Hybrid system |
-
2017
- 2017-06-14 CN CN201710446949.8A patent/CN107246629A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101625131A (en) * | 2008-01-22 | 2010-01-13 | 通用电气公司 | Lobe nozzles for fuel and air injection |
| CN102859281A (en) * | 2010-02-23 | 2013-01-02 | 西门子公司 | Fuel injector and swirler assembly with lobed mixer |
| JP2012237548A (en) * | 2011-05-11 | 2012-12-06 | Alstom Technology Ltd | Lobed swirler |
| CN106123031A (en) * | 2015-05-08 | 2016-11-16 | 安萨尔多能源瑞士股份公司 | Hybrid system |
| CN106051826A (en) * | 2016-06-12 | 2016-10-26 | 哈尔滨工程大学 | Pyrolysis fuel gas and air rapid mixing device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111536555A (en) * | 2020-05-08 | 2020-08-14 | 中国航发湖南动力机械研究所 | Engine and engine combustion chamber thereof |
| CN113551259A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | Wave-shaped middle-slit type V-shaped flame stabilizer with lobe partition plate |
| CN113551259B (en) * | 2021-07-19 | 2022-09-30 | 南昌航空大学 | Wavy middle-slit type V-shaped flame stabilizer with lobe partition plate |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20171013 |