CN216114147U - Cyclone burner and gas turbine - Google Patents
Cyclone burner and gas turbine Download PDFInfo
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- CN216114147U CN216114147U CN202122799406.9U CN202122799406U CN216114147U CN 216114147 U CN216114147 U CN 216114147U CN 202122799406 U CN202122799406 U CN 202122799406U CN 216114147 U CN216114147 U CN 216114147U
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- fuel
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- wall
- cyclone burner
- sleeve
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- 239000000446 fuel Substances 0.000 claims abstract description 95
- 239000007921 spray Substances 0.000 claims abstract description 31
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 8
- 238000005452 bending Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 abstract description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 15
- 239000007789 gas Substances 0.000 description 14
- 238000002485 combustion reaction Methods 0.000 description 10
- 238000005299 abrasion Methods 0.000 description 3
- 230000008602 contraction Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 239000000383 hazardous chemical Substances 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000008260 defense mechanism Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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Abstract
The utility model relates to the technical field of engines, and discloses a cyclone burner and a gas turbine, wherein the cyclone burner comprises: a fuel delivery assembly and a swirler, wherein the fuel delivery assembly comprises a first passage and a second passage for dual passage supply of fuel; the swirler is internally provided with a first fuel channel, a plurality of first jet holes, a second fuel channel and a plurality of second jet holes; the inlet of the first fuel channel is communicated with the outlet of the first channel, and the outlet of the first fuel channel is communicated with the plurality of first jet holes so as to jet the fuel from the first channel through the first jet holes; the inlet of the second fuel channel is communicated with the outlet of the second channel, and the outlet of the second fuel channel is communicated with the plurality of second spray holes so as to spray the spray holes from the second channel through the second spray holes; the plurality of second spray holes are positioned at the upstream of the plurality of first spray holes, so that the fuel sprayed from the second spray holes can be premixed with air, and the uniformity of the fuel in the air is improved; wherein, the inner wall surfaces of the first fuel channel and the second fuel channel are both smooth curved surfaces.
Description
Technical Field
The utility model relates to the technical field of engines, in particular to a cyclone burner and a gas turbine.
Background
There is a great deal of concern over the increasing health and environmental hazards posed by combustion pollution emissions to humans, and the laws and regulations and related policies regarding the control of pollution emissions are becoming more stringent. And certain requirements are also put forward for the problem of NOx and CO pollution emission of the micro gas turbine.
The micro gas turbine combustion products contain NOx (nitrogen oxides) which mainly comprises NO and NO 2. Technical measures are taken to reduce the NOx emission of the micro gas turbine as much as possible. In a gas turbine, NOx is mainly thermal NOx generated by high combustion temperature, and the key point is to control the temperature in the combustion chamber to a low level (typically 1700K-1900K, which affects the combustion efficiency) and make the temperature distribution in the combustion chamber uniform. At present, the low NOx emission combustor of the ground combustion engine mainly comprises fuel classification, lean premixing, steam humidification and the like.
However, the total pressure loss generated by the fuel passage in the swirl burner in the prior art is large, and the abrasion is large after long-time operation.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a cyclone combustor and a gas turbine, which are used for reducing total pressure loss and abrasion of a fuel channel.
In order to achieve the purpose, the utility model provides the following technical scheme:
in a first aspect, there is provided a cyclone burner comprising: a fuel delivery assembly and a swirler, wherein the fuel delivery assembly comprises a first passage and a second passage for dual passage supply of fuel; the swirler is internally provided with a first fuel channel, a plurality of first jet holes, a second fuel channel and a plurality of second jet holes; the inlet of the first fuel channel is communicated with the outlet of the first channel, and the outlet of the first fuel channel is communicated with the plurality of first jet holes so as to jet the fuel from the first channel through the first jet holes; the inlet of the second fuel channel is communicated with the outlet of the second channel, and the outlet of the second fuel channel is communicated with the plurality of second jet holes so as to jet out the jet holes from the second channel through the second jet holes; the second spray holes are positioned at the upstream of the first spray holes, so that the fuel sprayed out from the second spray holes can be premixed with air, and the uniformity of the fuel in the air is improved; the inner wall surfaces of the first fuel channel and the second fuel channel are smooth curved surfaces, so that sudden expansion or sudden contraction of the first fuel channel and the second fuel channel is avoided, total pressure loss is reduced, the abrasion of the fuel channels is small, the flow capacity cannot change greatly, and the condition of uneven cooling and heating is improved.
Optionally, the second fuel passage has at least one bend, each bend being a rounded structure.
Optionally, the swirler comprises a push rod and a plurality of vanes distributed at intervals on the circumference of the push rod, the push rod has a first end and a second end along the axial direction, and the second end is located at the upstream of the first end; the second fuel passage includes a first segment that is an annular cavity with an inlet at an end face of the second end, and a plurality of second segments, each of which is located in a corresponding one of the vanes and extends in a direction away from the central axis of the ram and is connected to the first segment; wherein an inner wall surface of a junction of each of the second segments and the first segment forms a rounded corner.
Optionally, the entrance of the first section forms a flare structure, the inner wall surface of which forms a fillet.
Optionally, the first fuel channel is located in the ejector rod and extends in the axial direction of the ejector rod, the inlet of the first channel is located on the end face of the second end, and the plurality of second nozzle holes are located on the end face of the first end; at least one second spray hole is distributed on the wall surface of each blade, which is far away from the first end in the axial direction of the ejector rod, and each second spray hole is communicated with the second section in the corresponding blade.
Optionally, each of the second nozzle holes faces in an opposite direction to any of the first nozzle holes.
Optionally, the first segment surrounds the first fuel passage; the fuel delivery assembly comprises a first sleeve and a second sleeve, the first sleeve is positioned in the second sleeve and is coaxial with the first sleeve, a space enclosed by the first sleeve forms the first channel, and a space enclosed by the first sleeve and the second sleeve forms the second channel; the inner wall of the first channel is matched with the inner wall of the first fuel channel, and the inner wall of the second channel is matched with the inner wall of the second fuel channel.
Optionally, in the axial direction of the top bar, each blade comprises a straight section and a bent section which are connected with each other, wherein the straight section is located on one side of the bent section away from the first end and extends in a direction parallel to the axis of the top bar; each said blade having opposite pressure and suction sides in a direction about the axis of said ram, each said cranked section being cranked against said pressure side; the wall surface of each blade, which is close to the first end, is close to the wall surface of the second end, the extension length of the straight section is 30-40% of the extension length of the blade, the installation angle of the bending section relative to the straight section is 30-60 degrees, and the torsion angle is 20-40 degrees; the number of the blades is between 6 and 12.
Optionally, a wall surface of each vane near the first end forms a convex first cylindrical surface, a wall surface near the second end forms a concave second cylindrical surface, an axis of the first cylindrical surface is perpendicular to a thickness direction of the vane, and an axis of the second cylindrical surface is parallel to the thickness direction of the vane.
In a second aspect, a gas turbine is provided, the gas turbine comprising a cyclone burner according to any of the above aspects.
The advantages of the gas turbine and the swirl burner described above with respect to the prior art are the same and will not be described further here.
Drawings
FIG. 1 is a first perspective view of a cyclone burner provided in an embodiment of the present application;
FIG. 2 is a perspective view of a second cyclonic burner provided in accordance with an embodiment of the present disclosure;
FIG. 3 is a longitudinal cross-sectional view of a swirler in a swirl burner provided in an embodiment of the present application;
FIG. 4 is a longitudinal cross-sectional view of a cyclonic burner provided in an embodiment of the present application;
FIG. 5 is a side view of a cyclonic burner provided in an embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 5, a cyclone burner provided in an embodiment of the present application includes: a fuel delivery assembly and swirler 3, wherein the fuel delivery assembly comprises a first passage T1 and a second passage T2 for dual passage supply of fuel; the swirler 3 is internally provided with a first fuel channel U1, a plurality of first spray holes 5, a second fuel channel U2 and a plurality of second spray holes 7; the inlet of the first fuel channel U1 is communicated with the outlet of the first channel T1, and the outlet is communicated with a plurality of first jet holes 5 so as to spray the fuel from the first channel T1 to the main combustion area through the first jet holes 5; the inlet of the second fuel channel U2 is communicated with the outlet of the second channel T2, and the outlet is communicated with a plurality of second spray holes 7 so as to spray the spray holes from the second channel T2 through the second spray holes 7; the second spray holes 7 are positioned at the upstream of the first spray holes 5, so that the fuel sprayed from the second spray holes 7 can be premixed with air, and the uniformity of the fuel in the air is improved; wherein the inner wall surfaces of the first fuel channel U1 and the second fuel channel U2 are both smooth curved surfaces; when the multi-head combustor is used for a long time, fuel can wash the inner walls of the first fuel channel U1 and the second fuel channel U2, so that the positions of right angles and the like are abraded, the shapes of the wall surfaces of the first fuel channel U1 and the second fuel channel U2 are changed, and the flow pressure loss of the first fuel channel U1 and the flow pressure loss of the second fuel channel U2 are reduced after the multi-head combustor runs for a period of time, so that the problem of cold and hot spots of a combustion area can be caused due to different fuel flow rates when the multi-head combustor is adopted. The first fuel channel U1 and the second fuel channel U2 do not have any geometric characteristics such as right-angled bends, sudden expansions and contractions and the like, and are completely composed of smooth round corners and cylindrical wall surfaces, so that the pressure loss of fuel in the channels is reduced to the maximum extent. Smooth curved surfaces may be manufactured using 3D metal additive.
In one particular embodiment, the second fuel passage U2 has at least one bend, each bend being a rounded configuration that avoids bulging or collapsing of the inner wall surface.
In a specific embodiment, the swirler 3 comprises a top rod 14 and a plurality of vanes 11 distributed at intervals on the circumference of the top rod 14, the top rod 14 has a first end and a second end along the axial direction, the second end is located at the upstream of the first end, wherein the first end may be provided with a baffle 4, the baffle 4 may be a double-layer plate, each layer plate is distributed with first spray holes 5, and the first spray holes 5 on the two layer plates have no overlap in projection on the axial direction of the top rod 14 to increase the path when spraying fuel, the first spray holes 5 have throttling function and can be used as a means for controlling the fuel flow of the path, because the fuel flow velocity of the first spray holes 5 on the baffle 4 is high, the baffle can be used as a combustion flashback defense mechanism, when the operating condition of the combustor changes or the flame is not backfire into the unburnt mixed gas of the upstream channel immediately after the front end is burned out; the second fuel channel U2 includes a first segment U21 and a plurality of second segments U22, the first segment U21 being an annular cavity with an inlet at the end face of the second end, each second segment U22 being located within a corresponding one of the vanes 11 and extending in a direction away from the central axis of the stem 14 and being connected to the first segment U21; the inner wall surface of the joint of each second section U22 and the first section U21 forms a rounded corner, and the radius r2 of the rounded corner ranges from 2mm to 3 mm.
In a specific embodiment, the inlet of the first section U21 forms a flaring structure 6, the inner wall surface of the flaring structure 6 is rounded to prevent the fuel from encountering a sudden expansion and contraction when flowing, and the radius r1 is 0.5-2 mm. And the joint of the second nozzle hole 7 and the second segment U22 is also rounded, and the radius mark is r3, and r3 is 0.5-2 mm.
In a specific embodiment, the first fuel channel U1 is located in the top rod 14 and extends along the axial direction of the top rod 14, the inlet of the first channel T1 is located at the end surface of the second end, and the plurality of second nozzle holes 7 are located at the end surface of the first end; at least one second spray hole 7 is distributed on the wall surface of each blade 11 far away from the first end in the axial direction of the ejector rod 14, and each second spray hole 7 is communicated with a second section U22 in the corresponding blade 11.
In a specific embodiment, each second nozzle hole 7 is opposite to the orientation of any first nozzle hole 5, the premixed fuel is injected in a direction opposite to the direction of the incoming air, and the fuel is injected into the air in a reverse flow mode, and the premixed fuel is injected from each second nozzle hole 7, so that the uniformity of gas mixing in the air is improved to the maximum extent.
In one particular embodiment, the first segment U21 encircles the first fuel passage U1; the fuel delivery assembly comprises a first sleeve 2 and a second sleeve 1, wherein the first sleeve 2 is positioned in the second sleeve 1 and is coaxial with the first sleeve 2, a space enclosed by the first sleeve 2 forms a first passage T1, and a space enclosed by the first sleeve 2 and the second sleeve 1 forms a second passage T2; the inner wall of the first channel T1 fits into the inner wall of the first fuel channel U1, and the inner wall of the second channel T2 fits into the inner wall of the second fuel channel U2. The space reasonable arrangement of the structure is beneficial to improving the space utilization rate.
In a specific embodiment, in the axial direction of the carrier rod 14, each blade 11 comprises a straight section 12 and a twisted section 13 connected to each other, wherein the straight section 12 is located on the side of the twisted section 13 away from the first end and extends in a direction parallel to the axis of the carrier rod 14; each blade 11 has opposite pressure 10 and suction 15 surfaces in a direction around the axis of the ram 14, each turn-up section 13 being turned up towards the pressure surface 10; from the wall surface of each blade 11 close to the first end to the wall surface close to the second end, the extension length of the straight section 12 is 30-40% of the extension length of the blade 11, the installation angle of the bending section 13 relative to the straight section 12 is 30-60 degrees, and the torsion angle is 20-40 degrees; the number of the blades 11 is between 6 and 12, so that stable flow of the airflow is facilitated.
In a specific embodiment, the wall surface of each vane 11 near the first end forms a convex first cylindrical surface M1, the wall surface near the second end forms a concave second cylindrical surface 9, the axis of the first cylindrical surface M1 is perpendicular to the thickness direction of the vane 11, and the axis of the second cylindrical surface 9 is parallel to the thickness direction of the vane 11.
The guide wall 8 surrounds the swirler 3, the outlet mixture of the vanes 11 of the swirler 3 is combusted through the outlet of the guide wall 8, and the air inlet of the guide wall 8 is chamfered, so that the expansion angle of airflow flame can be changed, and peripheral flame is stabilized.
Based on the same inventive concept, the embodiment of the application provides a gas turbine, and the gas turbine comprises the cyclone burner provided by the embodiment. The effects thereof refer to the above embodiments.
It will be apparent to those skilled in the art that various changes and modifications may be made in the embodiments of the present invention without departing from the spirit and scope of the utility model. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A cyclone burner, characterized by comprising: a fuel delivery assembly and a swirler, wherein the fuel delivery assembly includes a first passage and a second passage;
the swirler is internally provided with a first fuel channel, a plurality of first jet holes, a second fuel channel and a plurality of second jet holes; the inlet of the first fuel channel is communicated with the outlet of the first channel, and the outlet of the first fuel channel is communicated with the plurality of first jet holes; the inlet of the second fuel channel is communicated with the outlet of the second channel, and the outlet of the second fuel channel is communicated with the plurality of second spray holes; the plurality of second jet holes are positioned at the upstream of the plurality of first jet holes;
wherein the inner wall surfaces of the first fuel passage and the second fuel passage are both smooth curved surfaces.
2. The cyclone burner of claim 1, wherein the second fuel passage has at least one bend, each bend being a rounded configuration.
3. The cyclone burner of claim 2, wherein the swirler includes a lifter and a plurality of vanes spaced circumferentially about the lifter, the lifter having a first end and a second end in an axial direction, the second end being upstream of the first end;
the second fuel passage includes a first segment that is an annular cavity with an inlet at an end face of the second end, and a plurality of second segments, each of which is located in a corresponding one of the vanes and extends in a direction away from the central axis of the ram and is connected to the first segment;
wherein an inner wall surface of a junction of each of the second segments and the first segment forms a rounded corner.
4. The cyclone burner of claim 3, wherein the inlet of the first section forms a flare structure, an inner wall surface of the flare structure forming a fillet.
5. The cyclone burner of claim 3, wherein the first fuel passage is located within and extends axially of the pin, the inlet of the first passage is located at an end face of the second end, and the plurality of second nozzle holes are located at an end face of the first end;
at least one second spray hole is distributed on the wall surface of each blade, which is far away from the first end in the axial direction of the ejector rod, and each second spray hole is communicated with the second section in the corresponding blade.
6. The cyclone burner of claim 5, wherein each of the second nozzle holes is oriented opposite to an orientation of any of the first nozzle holes.
7. The cyclone burner of claim 5, wherein the first segment surrounds the first fuel passage;
the fuel delivery assembly comprises a first sleeve and a second sleeve, the first sleeve is positioned in the second sleeve and is coaxial with the first sleeve, a space enclosed by the first sleeve forms the first channel, and a space enclosed by the first sleeve and the second sleeve forms the second channel;
the inner wall of the first channel is matched with the inner wall of the first fuel channel, and the inner wall of the second channel is matched with the inner wall of the second fuel channel.
8. The cyclone burner of claim 5, wherein each of the vanes includes a straight section and a twisted section connected to each other in an axial direction of the ejector pin, wherein the straight section is located on a side of the twisted section remote from the first end and extends in a direction parallel to an axis of the ejector pin;
each said blade having opposite pressure and suction sides in a direction about the axis of said ram, each said cranked section being cranked against said pressure side;
the wall surface of each blade, which is close to the first end, is close to the wall surface of the second end, the extension length of the straight section is 30-40% of the extension length of the blade, the installation angle of the bending section relative to the straight section is 30-60 degrees, and the torsion angle is 20-40 degrees;
the number of the blades is between 6 and 12.
9. The cyclone burner of claim 5, wherein the wall of each vane adjacent the first end defines a convex first cylindrical surface and the wall adjacent the second end defines a concave second cylindrical surface, the first cylindrical surface having an axis perpendicular to the thickness direction of the vane and the second cylindrical surface having an axis parallel to the thickness direction of the vane.
10. A gas turbine comprising a cyclone burner according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122799406.9U CN216114147U (en) | 2021-11-16 | 2021-11-16 | Cyclone burner and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122799406.9U CN216114147U (en) | 2021-11-16 | 2021-11-16 | Cyclone burner and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216114147U true CN216114147U (en) | 2022-03-22 |
Family
ID=80717128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122799406.9U Active CN216114147U (en) | 2021-11-16 | 2021-11-16 | Cyclone burner and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216114147U (en) |
-
2021
- 2021-11-16 CN CN202122799406.9U patent/CN216114147U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240520 Address after: Room 101, building 7, zone a, Shanghai Lingang Xinxing Industrial Park, 600 Xinyuan South Road, Pudong New Area, Shanghai, 201406 Patentee after: ENN ENERGY POWER TECHNOLOGY (SHANGHAI) Co.,Ltd. Country or region after: China Address before: 065009 science and innovation base, Hangyi road free trade zone, Daxing airport District, Langfang pilot Free Trade Zone, Langfang, Hebei 2187 Patentee before: Shengneng Industrial Technology (Langfang) Co.,Ltd. Country or region before: China |
|
| CP03 | Change of name, title or address |
Address after: No. 99 Haoge Road, Pudong New Area, Shanghai, June 2014 Patentee after: ENN ENERGY POWER TECHNOLOGY (SHANGHAI) Co.,Ltd. Country or region after: China Address before: Room 101, building 7, zone a, Shanghai Lingang Xinxing Industrial Park, 600 Xinyuan South Road, Pudong New Area, Shanghai, 201406 Patentee before: ENN ENERGY POWER TECHNOLOGY (SHANGHAI) Co.,Ltd. Country or region before: China |