CN109404966B - Combustion chamber head device and gas turbine - Google Patents
Combustion chamber head device and gas turbine Download PDFInfo
- Publication number
- CN109404966B CN109404966B CN201811475257.7A CN201811475257A CN109404966B CN 109404966 B CN109404966 B CN 109404966B CN 201811475257 A CN201811475257 A CN 201811475257A CN 109404966 B CN109404966 B CN 109404966B
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- Prior art keywords
- pipe
- radial
- fuel
- main
- duty
- Prior art date
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 38
- 239000000446 fuel Substances 0.000 claims abstract description 120
- 239000007921 spray Substances 0.000 claims abstract description 40
- 210000002445 nipple Anatomy 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000004891 communication Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 abstract description 28
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 abstract description 15
- 239000003344 environmental pollutant Substances 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 238000005461 lubrication Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The embodiment of the invention provides a combustion chamber head device and a gas turbine, relates to the technical field of gas turbines, and mainly solves the technical problem of uneven gas premixing; a combustion chamber head assembly comprising: a main stage fuel pipe, a duty stage fuel pipe and a radial cyclone; one end of the duty-level fuel pipe is provided with a duty-level fuel spray hole, wherein an annular main-level fuel channel is arranged in the pipe wall of the main-level fuel pipe, and the main-level fuel pipe is sleeved on the periphery of the duty-level fuel pipe; the combustion chamber head device provided by the embodiment of the invention can greatly improve the premixing uniformity of fuel and air, can effectively avoid the existence of local high-concentration fuel points, further can eliminate the occurrence of local high-temperature phenomenon during combustion, and greatly reduces the emission of nitrogen oxides.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustion chamber head device and a gas turbine.
Background
Low pollutant emissions are an important indicator of gas turbine combustor design, and today, with the strong initiative of low pollution, low emissions in the whole society, low pollutant emissions indicators of gas turbines are becoming more stringent; the fuel premix combustion technology is widely applied to the design of low-pollution gas turbine combustors, wherein the premixing uniformity of air and fuel plays a decisive role in the emission of pollutants; however, the existing fuel premixing technology still has great defects, the premixing is not uniform enough, local high temperature phenomenon is caused during combustion, and the emission of nitrogen oxides is high.
Disclosure of Invention
The invention provides a combustion chamber head device and a gas turbine, which can effectively prevent local high temperature phenomenon and greatly reduce the emission of nitrogen oxides.
A combustion chamber head assembly comprising: a main stage fuel pipe, a duty stage fuel pipe and a radial cyclone; one end of the duty fuel pipe is provided with a duty fuel spray hole, wherein,
an annular main-stage fuel channel is arranged in the pipe wall of the main-stage fuel pipe, and the main-stage fuel pipe is sleeved on the periphery of the duty-stage fuel pipe and is arranged close to the duty-stage fuel spray hole;
the combustion chamber head device further comprises a radial diverter and a spray pipe;
the inside of the radial flow divider is provided with a flow dividing channel, the main-stage fuel pipe is arranged in the center of the radial flow divider, and the main-stage fuel channel is communicated with the flow dividing channel; the radial swirler is arranged on the radial diverter, the radial swirler is coaxially arranged with the radial diverter, and a plurality of spray pipes are arranged on the radial diverter and are communicated with the diversion channels; wherein the nozzles are disposed proximate to the blades of the radial swirler and each of the nozzles is equidistant from a center of the radial swirler.
As an example, the radial shunt is configured as a disk-like structure with a central aperture;
the spray pipe and the radial swirler are arranged on the first side surface of the radial flow divider, and the radial swirler and the first side surface enclose a gas mixing cavity;
the main fuel pipe is arranged on the second side face of the radial flow divider, the duty fuel pipe penetrates through the center hole, and the duty fuel spray hole is positioned in the gas mixing cavity.
As an example, the pipe wall of the primary fuel pipe is constructed in a hollow structure, and the hollow portion forms the primary fuel passage.
As an example, the outer tube wall of one end of the primary fuel tube has a bulge with a nipple thereon that communicates with the primary fuel passage.
As an example, the radial flow divider is constructed in a hollow structure, the hollow portion forming the flow dividing passage;
and a plurality of spray pipes are communicated with the diversion channel.
As an example, the radial diverter is provided with a plurality of diversion channels which are arranged in a radial direction, and the spray pipes are respectively communicated with the diversion channels in a one-to-one correspondence manner.
As an example, the included angles between two adjacent diversion channels are the same.
As an example, the pipe wall of the spray pipe is provided with a plurality of main-stage fuel spray holes, and the opening directions of the plurality of main-stage fuel spray holes are the same.
As an example, the nozzles are located at the periphery of the radial swirler.
A gas turbine comprising a combustion chamber, a turbine and an auxiliary system, wherein a flame tube is arranged in the combustion chamber, the gas turbine further comprises the combustion chamber head device, and a gas mixing cavity of the combustion chamber head device is in butt joint with the flame tube.
The combustion chamber head device and the gas turbine provided by the embodiment of the invention have the beneficial effects that:
the combustion chamber head device provided by the embodiment of the invention can greatly improve the premixing uniformity of fuel and air, can effectively avoid the existence of local high-concentration fuel points, further can eliminate the occurrence of local high-temperature phenomenon during combustion, and greatly reduces the emission of nitrogen oxides.
Drawings
FIG. 1 is a schematic cross-sectional view of a combustion chamber head apparatus according to a first embodiment of the present invention;
FIG. 2 is a schematic view of the structure of the bottom plate of the combustion chamber head apparatus of the first embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of a combustion chamber head apparatus according to a second embodiment of the present invention;
FIG. 4 is a schematic view of the structure of a bottom plate of a combustion chamber head apparatus according to a second embodiment of the present invention;
FIG. 5 is a schematic cross-sectional view of a main stage fuel nozzle of a combustor head assembly according to an embodiment of the present invention.
Reference numerals:
1-a primary fuel pipe; 11-primary fuel passage; 12-outer tube wall; 121-bump; 1211-a mouthpiece; 13-inner tube wall; 2-duty grade fuel pipe; 21-duty grade fuel spray holes; 3-radial cyclones; 31-a housing; 32-a gas mixing chamber; 4-radial diverter; 41-split flow channel; 42-a bottom plate; 421-separator; 422-flange; 43-cover plate; 5-spraying pipes; 51—main stage fuel injection holes.
Detailed Description
In order to enable those skilled in the art to better understand the technical scheme of the present invention, the following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings.
As shown in fig. 1 to 4, a combustion chamber head apparatus according to an embodiment of the present invention includes: a main stage fuel pipe 1, an on-duty stage fuel pipe 2 and a radial cyclone 3; one end of the class fuel pipe 2 is provided with a class fuel spray hole 21; the main-stage fuel pipe 1 is sleeved on the periphery of the duty-stage fuel pipe 2 and is arranged close to the duty-stage fuel spray hole 21; the combustion chamber head device also comprises a radial diverter 4 and a spray pipe 5; the inside of the radial flow splitter 4 has a split passage 41, the primary fuel pipe 1 is disposed in the center of the radial flow splitter 4, and the primary fuel passage 11 communicates with the split passage 41; the radial swirler 3 is arranged on the radial diverter 4, the radial swirler 3 and the radial diverter 4 are coaxially arranged, and a plurality of spray pipes 5 are arranged on the radial diverter 4 and are communicated with the diversion channel 41; wherein the nozzles 5 are arranged close to the blades of the radial swirler 3 and each nozzle 5 is at the same distance from the centre of the radial splitter 4.
In the embodiment provided by the invention, fuel is injected into the main-stage fuel channel 11 of the main-stage fuel pipe 1, then flows through the diversion channel 41 of the radial diverter 4 to the spray pipes 5, and finally the fuel is uniformly sprayed out of each spray pipe 5 to be mixed with air flowing through the radial swirler 3 sufficiently uniformly. The annular main fuel channel 11 ensures that fuel in the channel is uniformly distributed in the radial direction, and further, under the action of the radial flow divider 4, the fuel can be uniformly distributed in each spray pipe 5 in the radial direction, so that the quantity of the fuel sprayed out by each spray pipe 5 can be ensured to be consistent, the premixing uniformity of the fuel and air is greatly improved, the existence of local high-concentration fuel is avoided, the occurrence of local high-temperature phenomenon during fuel combustion is eliminated, and the emission quantity of nitrogen oxides is reduced.
Further, as shown in fig. 1 and 2, in the first embodiment of the present invention for providing a combustion chamber head apparatus, the radial splitter 4 is constructed in a disk-like structure having a center hole; the spray pipe 5 and the radial swirler 3 are arranged on the first side surface of the radial flow divider 4, and the radial swirler 3 and the first side surface enclose a gas mixing cavity 32; the main fuel pipe 1 is arranged on the second side surface of the radial flow divider 4, the duty fuel pipe 2 is provided with a central hole in a penetrating way, and the duty fuel spray hole 21 is positioned in the gas mixing cavity 32. The pipe wall of the primary fuel pipe 1 is constructed in a hollow structure, and the hollow portion forms a primary fuel passage 11.
Specifically, as shown in fig. 1, the primary fuel pipe 1 includes an inner pipe wall 13 and an outer pipe wall 12, a certain gap is provided between the inner pipe wall 13 and the outer pipe wall 12, and the primary fuel channel 11 is formed, and the duty fuel pipe 2 is disposed in the pipe of the inner pipe wall 13. The radial flow splitter 4 comprises a disc-shaped bottom plate 42 and a disc-shaped cover plate 43, wherein a flange 422 is arranged on one side surface of the bottom plate 42, through holes (not shown in the figure) are formed in the middle parts of the bottom plate 42 and the cover plate 43, the diameter of the through holes of the cover plate 43 is larger than that of the through holes of the bottom plate 42, and the cover plate 43 is buckled on one side surface of the cover plate 43 with the flange 422; the main fuel pipe 1 is arranged in the through hole of the cover plate 43 and the through hole of the bottom plate 42 in a penetrating way; wherein the outer tube wall 12 of the primary fuel tube 1 is arranged in the wall of the through hole of the cover plate 43 and is connected with the cover plate 43; the inner wall of the primary fuel pipe 1 is disposed in the wall of the through hole of the bottom plate 42 and is connected to the bottom plate 42 so that the primary fuel passage 11 communicates with the branch passage 41. The bottom plate 42 is provided with a plurality of holes, and the spray pipes 5 are inserted in the holes of the bottom plate 42 in a one-to-one correspondence manner, so that the connection between the spray pipes 5 and the flow divider (the bottom plate 42) is realized, and the communication between the flow dividing channel 41 and the spray pipes 5 is also realized. Further, in the embodiment provided by the invention, the radial swirler 3 comprises blades and a housing 31, a plurality of blades are arranged on the housing 31, and a gas mixing cavity 32 is defined among the blades, the housing 31 and a bottom plate 42; the plurality of further spray pipes 5 are arranged on the periphery of the radial swirler 3, and fuel sprayed by the spray pipes 5 is brought into the gas mixing cavity 32 through the radial swirler 3 before air enters the gas mixing cavity 32, so that the mixing of the fuel and the gas is realized; in addition, in other implementations, the plurality of nozzles 5 may also be disposed inside the radial swirler 3, which is not particularly limited herein; the arrangement of the structure of the embodiment not only can ensure that the fuel in the main-stage fuel channel 11 and the fuel in the shunt channel 41 are uniformly distributed in the radial direction, but also ensures that the structure layout is more compact, and the occupation of space is reduced; in addition, the primary fuel pipe 1 and the radial flow divider 4 may be fixed by a welded connection manner, and the radial flow divider 4 and the radial flow divider 3 may also be fixed by a welded connection manner, which may be adopted by those skilled in the art according to actual situations, or by other connection members.
Further, as shown in fig. 5, the wall of the nozzle 5 has a plurality of main fuel nozzles 51, and the opening directions of the plurality of main fuel nozzles 51 are the same; the number and the aperture of the main fuel nozzles 51 can be adjusted according to the actual requirements.
Further, the outer tube wall 12 at one end of the primary fuel tube 1 has a bulge 121, and the bulge 121 has a nipple 1211 communicating with the primary fuel channel 11; wherein the nipple 1211 is adapted to effectively and conveniently interface with an external fuel supply line. In consideration of the fact that the fuel has a certain speed and pressure when entering the primary fuel pipe 1, the bulge portion 121 can play a certain role in buffering the fuel, and uniformity of the fuel in the inner radial direction of the primary fuel pipe 1 can be further guaranteed.
In addition, the present invention provides a second embodiment of the combustion chamber head apparatus, as shown in fig. 3 and 4, unlike the first embodiment, the radial splitter 4 has a plurality of radially disposed splitting passages 41 therein; specifically, the bottom plate 42 is provided with a plurality of radially arranged partition plates 421, a diversion channel 41 is formed between two (specific) adjacent partition plates 421, and the plurality of diversion channels 41 are communicated with the plurality of spray pipes 5 in a one-to-one correspondence manner; as can be seen from the figure, in the present embodiment, the radial flow divider 4 has four flow dividing channels 41 and four nozzles 5 corresponding to each other, and the included angle between two adjacent flow dividing channels 41 is 90 degrees. This structural arrangement effectively reduces the accumulation and storage of fuel in the radial flow divider 4, thereby enabling an increase in the corresponding velocity of the fuel.
On the other hand, the embodiment of the invention also provides a gas turbine, which comprises a combustion chamber, a turbine and an auxiliary system, wherein a flame tube is arranged in the combustion chamber, the gas turbine further comprises the combustion chamber head device, and a gas mixing cavity 32 (a shell 31 of the radial swirler 3) of the combustion chamber head device is in butt joint with the flame tube. Wherein the auxiliary system may for example comprise: the lubrication system is used for providing reliable lubrication for the moving parts of the gas turbine so as to ensure the normal operation of the moving parts; a fuel supply system provides motive fuel for the normal operation of the gas turbine. Of course, the auxiliary systems are not limited to the above two types of systems, and are not described herein in detail.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (8)
1. A combustion chamber head assembly comprising: a main stage fuel pipe, a duty stage fuel pipe and a radial cyclone; one end of the duty fuel pipe is provided with a duty fuel spray hole, which is characterized in that,
an annular main-stage fuel channel is arranged in the pipe wall of the main-stage fuel pipe, and the main-stage fuel pipe is sleeved on the periphery of the duty-stage fuel pipe and is arranged close to the duty-stage fuel spray hole;
the combustion chamber head device further comprises a radial diverter and a spray pipe;
the inside of the radial flow divider is provided with a plurality of flow dividing channels, an included angle between two adjacent flow dividing channels is 90 degrees, the main fuel pipe is arranged at the center of the radial flow divider, and the main fuel channel is communicated with the flow dividing channels; the radial swirler is arranged on the radial diverter, the radial swirler is coaxially arranged with the radial diverter, and a plurality of spray pipes are arranged on the radial diverter and are communicated with the diversion channels; the radial swirler comprises a plurality of blades and a shell, wherein the blades are arranged on the shell, the spray pipes are arranged close to the blades of the radial swirler, and the distance between each spray pipe and the center of the radial swirler is the same; the radial splitter is configured as a disk-like structure having a central aperture;
the spray pipe and the radial swirler are arranged on the first side surface of the radial flow divider, and the radial swirler and the first side surface enclose a gas mixing cavity;
the main fuel pipe is arranged on the second side surface of the radial flow divider, the duty fuel pipe penetrates through the center hole, and the duty fuel spray hole is positioned in the gas mixing cavity;
the spray pipe is positioned at the periphery of the radial cyclone;
the main-stage fuel pipe comprises an inner pipe wall and an outer pipe wall, a certain gap is formed between the inner pipe wall and the outer pipe wall, the main-stage fuel channel is formed, and the duty-stage fuel pipe is arranged in the pipe of the inner pipe wall;
the radial flow divider comprises a disc-shaped bottom plate and a disc-shaped cover plate, a flange is arranged on one side surface of the bottom plate, the cover plate is buckled on one side surface of the bottom plate with the flange, and through holes are formed in the middle parts of the bottom plate and the cover plate; the main fuel pipe is arranged in the through hole of the cover plate and the through hole of the bottom plate in a penetrating way; the outer pipe wall of the main fuel pipe is arranged in the hole wall of the through hole of the cover plate and is connected with the cover plate; the inner wall of the main fuel pipe is arranged in the hole wall of the through hole of the bottom plate and is connected with the bottom plate.
2. The combustor head assembly of claim 1, wherein a tube wall of the primary fuel tube is configured as a hollow structure, the hollow forming the primary fuel passage.
3. The combustor head assembly of claim 2, wherein an outer tube wall at one end of the primary fuel tube has a boss with a nipple thereon in communication with the primary fuel passage.
4. The combustion chamber head apparatus of claim 1 wherein,
the radial flow divider is constructed in a hollow structure, and the hollow part forms the flow dividing channel;
and a plurality of spray pipes are communicated with the diversion channel.
5. The combustion chamber head apparatus of claim 1 wherein,
the radial flow divider is internally provided with a plurality of flow dividing channels which are radially arranged, and the spray pipes are respectively communicated with the flow dividing channels in a one-to-one correspondence manner.
6. The combustion chamber head apparatus of claim 5 wherein the included angle between adjacent ones of said flow dividing passages is the same.
7. The combustion chamber head apparatus of claim 1, wherein a wall of the nozzle pipe has a plurality of the main stage fuel injection holes, and the plurality of the main stage fuel injection holes are opened in the same direction.
8. A gas turbine comprising a combustor, a turbine and an auxiliary system, the combustor having a liner therein, the gas turbine further comprising a combustor head assembly as claimed in any one of claims 1 to 7, a gas mixing chamber of the combustor head assembly interfacing with the liner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811475257.7A CN109404966B (en) | 2018-12-04 | 2018-12-04 | Combustion chamber head device and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811475257.7A CN109404966B (en) | 2018-12-04 | 2018-12-04 | Combustion chamber head device and gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109404966A CN109404966A (en) | 2019-03-01 |
| CN109404966B true CN109404966B (en) | 2024-03-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811475257.7A Active CN109404966B (en) | 2018-12-04 | 2018-12-04 | Combustion chamber head device and gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN109404966B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111043625B (en) * | 2019-12-31 | 2024-06-04 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of miniature gas turbine and miniature gas turbine |
| CN114738799B (en) * | 2022-04-20 | 2024-03-26 | 新奥能源动力科技（上海）有限公司 | Head assembly of dual-fuel combustion chamber, combustion chamber and gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2342685A1 (en) * | 2000-04-07 | 2001-10-07 | Shigemi Mandai | Cooling system for gas turbine combustor |
| CN101709884A (en) * | 2009-11-25 | 2010-05-19 | 北京航空航天大学 | Premixing and pre-evaporating combustion chamber |
| CN102200291A (en) * | 2011-03-29 | 2011-09-28 | 北京航空航天大学 | Pneumatic primary level graded low-pollution combustion chamber |
| CN102889616A (en) * | 2012-09-29 | 2013-01-23 | 中国科学院工程热物理研究所 | Multi-point direct spray combustion chamber based on venturi premixing double spiral nozzle |
| CN209399412U (en) * | 2018-12-04 | 2019-09-17 | 新奥能源动力科技（上海）有限公司 | Chamber head part device and gas turbine |
-
2018
- 2018-12-04 CN CN201811475257.7A patent/CN109404966B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2342685A1 (en) * | 2000-04-07 | 2001-10-07 | Shigemi Mandai | Cooling system for gas turbine combustor |
| CN101709884A (en) * | 2009-11-25 | 2010-05-19 | 北京航空航天大学 | Premixing and pre-evaporating combustion chamber |
| CN102200291A (en) * | 2011-03-29 | 2011-09-28 | 北京航空航天大学 | Pneumatic primary level graded low-pollution combustion chamber |
| CN102889616A (en) * | 2012-09-29 | 2013-01-23 | 中国科学院工程热物理研究所 | Multi-point direct spray combustion chamber based on venturi premixing double spiral nozzle |
| CN209399412U (en) * | 2018-12-04 | 2019-09-17 | 新奥能源动力科技（上海）有限公司 | Chamber head part device and gas turbine |
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| Publication number | Publication date |
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| CN109404966A (en) | 2019-03-01 |
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