CN206905031U - A kind of cyclone with lobe swirl vane - Google Patents
A kind of cyclone with lobe swirl vane Download PDFInfo
- Publication number
- CN206905031U CN206905031U CN201720688832.6U CN201720688832U CN206905031U CN 206905031 U CN206905031 U CN 206905031U CN 201720688832 U CN201720688832 U CN 201720688832U CN 206905031 U CN206905031 U CN 206905031U
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- lobe
- swirl vane
- cyclone
- feed track
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Abstract
The utility model discloses a kind of 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 connects with outer feed track, back cavity connects with interior feed track.
Description
Technical field
The utility model belongs to the equipment part field of gas turbine or gas fired-boiler, and particularly one kind has lobe eddy flow
The cyclone of blade.
Background technology
In order to further reduce the discharged nitrous oxides index of the gas turbine of operating on gaseous fuel and boiler, it is necessary to this
A little equipment are operated under premixed combustion mode.Premixed combustion mode refires after needing fuel and the uniform mixing of air, fires
Material mixes more uniform 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
Gas is expected 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.
Utility model content
The trailing edge structures of cyclone are designed to lobe structure by the purpose of this utility model, and increase fuel in blade trailing edge
Gas blowout mouth, the wavy blade trailing edge of whole piece is set all to be used as fuel gas spout.
In order to solve the above problems, the utility model proposes with a kind of cyclone of lobe swirl vane.
Technical scheme is used by the utility model：
A kind of cyclone with lobe swirl vane, including lobe swirl vane, cyclone, the cyclone are cylinder
Body, cyclone are axially inside provided with interior feed track and outer feed track, and interior feed track is cyclone hollow central interior, outer defeated
It is interior feed track outer annular shape cavity to send, and lobe swirl vane is connected with cyclone side, and lobe swirl vane is streamline
Type structure, the tail edge of lobe swirl vane is wavy lobe structure, and lobe swirl vane has in the flowing direction
Circumferential deflection, the wavelength direction of lobe are the radial direction of cyclone, lobe swirl vane for inner hollow shell structure simultaneously
And be provided with two cavitys mutually separated, two cavitys are respectively ante-chamber and back cavity, and ante-chamber connects with outer feed track, back cavity with
Interior feed track connection.Interior feed track and outer feed track are used to convey fuel gas to be mixed, and will by the rotation of cyclone
Fuel gas imports lobe swirl vane, and lobe swirl vane is used for fuel gas to be discharged into perpendicular to airflow direction in air duct
Homogeneous mixed gas is mixed to form with air, the design of ante-chamber and back cavity ensures that fuel gas can sufficiently reach passage depths, and
And ante-chamber connects with outer feed track, back cavity is connected with interior feed track, and because central cavity volume is larger, passage is in using back cavity
The position at rear, substantial amounts of fuel gas is set to go deep into passage depths, and the outer feed track that a small amount of combustion gas passes through small volume
It is larger into pressure during ante-chamber, it 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, avoids air-flow from reducing gas pressure after separating.
Further, spray-hole is provided with the ante-chamber of the lobe swirl vane, spray-hole connects 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 enters ante-chamber and can still be discharged into passage
It is interior.
Further, the lobe of the lobe swirl vane is provided with spout, spout using split among lobe seam perforate or
Person's lobe laterally splits seam perforate mode, and spout connects with back cavity.The fuel gas that spout sprays is in stream parallel to airflow direction
To whirlpool region, good mixed effect can reach.
Preferably, the nozzle configuration is long slit, rectangle, circle.Whirlpool is flowed to caused by special geometric profile to strengthen
Local dip, the fuel gas and air for making 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.Whirlpool is flowed to caused by special geometric profile and strengthens local dip, and the fuel gas and air for making upstream mix more
Uniformly.
Preferably, 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
Whirlpool is flowed to caused by geometric shape and strengthens local dip, the fuel gas and air for making upstream mix evenly
Preferably, 0.4~0.9 times arc length of the lobe original position in lobe swirl vane leading edge towards trailing edge direction
Place.Whirlpool is flowed to caused by special geometric profile and strengthens local dip, and the fuel gas and air for making upstream mix evenly
The utility model compared with the existing technology has advantages below and effect：
1st, fuel gas can be sprayed, is not required in the case where fuel atmospheric pressure is low by the utility model by trailing edge spout
The penetration depth for reaching enough more can uniformly dispense fuel gas in atmosphere.
2nd, the utility model is in by blade trailing edge lobe parallelism structural in airflow direction and flows to whirlpool region, strengthen
Local dip, produces powerful fuel gas-air mixing effect, so as to form the higher homogeneous gaseous mixture of quality.
3rd, the utility model realizes fuel gas-air mixing effect by blade trailing edge lobe structure, effectively reduces eddy flow
Device rear portion is used for the space for forming homogeneous gaseous mixture, avoids needing to reserve for the aerial diffusion of fuel gas in cyclone downstream
Larger space.
4th, the wavy blade trailing edge of the utility model whole piece can all be used as fuel gas spout, be sprayed compared to by leading edge spray orifice
Gas, jet amount is bigger, and jet effect is more preferable.
Brief description of the drawings
The accompanying drawing for forming the part of the application is used for providing further understanding to of the present utility model, of the present utility model
Schematic description and description is used to explain the utility model, does not form to improper restriction of the present utility model.
Fig. 1 is the axial cross-sectional view of grade of the present utility model；
Fig. 2 is orthographic projection cross-sectional view of the present utility model；
Fig. 3 is lobe swirl vane structural representation of the present utility model；
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 structural representation of the present utility model.
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 tube 6；Gas channel 7；
Leading edge spout 8；Ante-chamber 9；Center cone 10；Lobe original position 11.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only explaining this
Utility model, it is not used to limit the utility model.
Embodiment 1：As shown in Fig. 1,2,3,5, there is the swirler assembly of lobe swirl vane, fired for gaseous fuel
Burn, including radome fairing 1, lobe swirl vane 4, cyclone, cyclone are cylinders, are 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 uses centre to split seam perforate, and trailing edge lobe spout 2 is shaped as long slit.
In use, air required for burning is by the gas channel 7 among 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.Whirlpool, which is flowed to, caused by the geometric shape of trailing edge lobe spout 2 strengthens office
Portion disturbs, and the fuel gas and air for making upstream mix 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
Flow blade lobe for semicircle, lobe original position at 0.5 times arc length of the lobe swirl vane leading edge towards 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 of stream blade is triangle, lobe original position at 0.5 times arc length of the lobe swirl vane leading edge towards 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
The lobe for flowing blade is square, and lobe original position is at 0.9 times arc length of the lobe swirl vane leading edge towards 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.
Preferred embodiment of the present utility model is the foregoing is only, it is all in this practicality not to limit the utility model
Within new spirit and principle, any modification, equivalent substitution and improvements made etc., guarantor of the present utility model should be included in
Within the scope of shield.
Claims (8)
- A kind of 1. cyclone with lobe swirl vane, it is characterised in that including lobe swirl vane, cyclone, the rotation Stream device is cylinder, and cyclone is axially inside provided with interior feed track and outer feed track, and interior feed track is in cyclone inside Cavity is entreated, outer feed track is interior feed track outer annular shape cavity, and lobe swirl vane is connected with cyclone side, lobe eddy flow Blade is streamlined structure, and lobe swirl vane is provided with circumferential deflection, the afterbody side of lobe swirl vane in the flowing direction Edge is wavy lobe structure, and the wavelength direction of lobe is the radial direction of cyclone, and lobe swirl vane is inner hollow Shell structure and be provided with two cavitys mutually separated, two cavitys are respectively ante-chamber and back cavity, ante-chamber and outer conveying Road connects, and back cavity connects 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 connects 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 among 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 At 0.4~0.9 times arc length of the lobe swirl vane leading edge towards trailing edge direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720688832.6U CN206905031U (en) | 2017-06-14 | 2017-06-14 | A kind of cyclone with lobe swirl vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720688832.6U CN206905031U (en) | 2017-06-14 | 2017-06-14 | A kind of cyclone with lobe swirl vane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206905031U true CN206905031U (en) | 2018-01-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720688832.6U Active CN206905031U (en) | 2017-06-14 | 2017-06-14 | A kind of cyclone with lobe swirl vane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109539314A (en) * | 2018-11-14 | 2019-03-29 | 西北工业大学 | A kind of novel radial swirler with wave blade |
| CN115264531A (en) * | 2022-06-30 | 2022-11-01 | 哈尔滨工程大学 | Split type lobe swirl vane and swirler suitable for gaseous fuel |
| CN115682029A (en) * | 2021-07-29 | 2023-02-03 | 通用电气公司 | Mixer blade |
-
2017
- 2017-06-14 CN CN201720688832.6U patent/CN206905031U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109539314A (en) * | 2018-11-14 | 2019-03-29 | 西北工业大学 | A kind of novel radial swirler with wave blade |
| CN115682029A (en) * | 2021-07-29 | 2023-02-03 | 通用电气公司 | Mixer blade |
| CN115264531A (en) * | 2022-06-30 | 2022-11-01 | 哈尔滨工程大学 | Split type lobe swirl vane and swirler suitable for gaseous fuel |
| CN115264531B (en) * | 2022-06-30 | 2023-04-07 | 哈尔滨工程大学 | Split type lobe swirl vane and swirler suitable for gaseous fuel |
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