CN112984558A - Natural gas nozzle of gas turbine - Google Patents
Natural gas nozzle of gas turbine Download PDFInfo
- Publication number
- CN112984558A CN112984558A CN202110287615.7A CN202110287615A CN112984558A CN 112984558 A CN112984558 A CN 112984558A CN 202110287615 A CN202110287615 A CN 202110287615A CN 112984558 A CN112984558 A CN 112984558A
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- China
- Prior art keywords
- nozzle
- gas turbine
- gas
- natural gas
- nozzle head
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- 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
Links
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 86
- 239000007789 gas Substances 0.000 title claims abstract description 61
- 239000003345 natural gas Substances 0.000 title claims abstract description 43
- 238000002485 combustion reaction Methods 0.000 claims abstract description 31
- 238000007789 sealing Methods 0.000 claims description 6
- 238000003466 welding Methods 0.000 claims description 3
- 239000000446 fuel Substances 0.000 description 21
- 238000002347 injection Methods 0.000 description 8
- 239000007924 injection Substances 0.000 description 8
- 238000004364 calculation method Methods 0.000 description 5
- 238000009826 distribution Methods 0.000 description 5
- 238000000889 atomisation Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000007921 spray Substances 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000000704 physical effect Effects 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
Images
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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Abstract
The invention discloses a natural gas nozzle of a gas turbine, which comprises a screw plug, a nozzle body, a nozzle head assembly and a filter element, wherein the screw plug is fixedly connected with the nozzle body; the nozzle body is fixed on a shell of a combustion chamber of the gas turbine, an air supply channel is arranged inside the nozzle body, a screw plug is arranged at one end of the air supply channel, and a nozzle head assembly is arranged at the other end of the air supply channel; the gas supply channel is communicated with a gas supply main pipe through a branch pipeline, and a filter element is arranged on the branch pipeline; the nozzle tip assembly includes a nozzle nut body and a nozzle tip; the nozzle head is fixed on the nozzle nut body, the nozzle nut body is connected to the end part of the nozzle body, and the diameters of the nozzle nut body and the nozzle head are larger than that of the air supply channel; the end face of the nozzle head is circumferentially provided with a plurality of inclined nozzles, the central axes of the nozzles all point to the central axis of the nozzle head, and the central part of the end face of the nozzle head is provided with the nozzles, so that the combustible range of natural gas is improved, the stable working range of a combustion chamber is enlarged, and the combustion efficiency is improved.
Description
Technical Field
The invention belongs to the field of combustion of gas turbines, and particularly belongs to a natural gas nozzle of a gas turbine.
Background
The first gas turbine is modified into an industrial gas turbine burning natural gas, the function of introducing technology is played, the scientific and technological level and the production capacity of China are effectively improved, and the market competitiveness of companies is enhanced. The modified industrial gas turbine takes natural gas as fuel, the fuel is changed into gas from liquid, and the nozzle needs to be modified, so that the natural gas nozzle designed in the prior art can not meet the requirement, and the problems of poor operation stability and narrow natural gas combustible range of the gas turbine in the operation process exist.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides the natural gas nozzle of the gas turbine, which has a simple structure, improves the combustible range of natural gas, enlarges the stable working range of a combustion chamber and improves the combustion efficiency.
In order to achieve the purpose, the invention provides the following technical scheme:
a natural gas nozzle of a gas turbine comprises a screw plug, a nozzle body, a nozzle head assembly and a filter element;
the nozzle body is fixed on a shell of a combustion chamber of the gas turbine, an air supply channel is arranged inside the nozzle body, a screw plug is arranged at one end of the air supply channel, and a nozzle head assembly is arranged at the other end of the air supply channel; the gas supply channel is communicated with a gas supply main pipe through a branch pipeline, and a filter element is arranged on the branch pipeline;
the nozzle tip assembly includes a nozzle nut body and a nozzle tip; the nozzle head is fixed on the nozzle nut body, the nozzle nut body is connected to the end part of the nozzle body, and the diameters of the nozzle nut body and the nozzle head are larger than that of the air supply channel;
the end face of the nozzle head is circumferentially provided with a plurality of inclined nozzles, the central axes of the nozzles all point to the central axis of the nozzle head, and the central part of the end face of the nozzle head is provided with the nozzles.
Preferably, the plurality of nozzles on the nozzle head are all conical.
Preferably, 12 inclined nozzles are circumferentially arranged on the end surface of the nozzle head.
Preferably, the included angle between the central axis of the inclined nozzle and the central axis of the nozzle head is 38-42 degrees.
Preferably, a gasket is arranged at the connecting part of the air supply channel of the nozzle nut body and the nozzle body, and a clamping ring is arranged on the outer side wall of the nozzle nut body and the outer side wall of the nozzle body for fixed connection.
Preferably, the diameter of the gas supply channel is the same as the diameter of the branch duct.
Preferably, a sealing ring is arranged at the connecting part of the screw plug and the nozzle body.
Preferably, a stop ring is arranged at the connecting part of the branch pipeline and the filter element.
Preferably, the nozzle nut body and the nozzle head are fixedly connected by welding.
Preferably, the outer side wall of the nozzle body is provided with a mounting hole, and the nozzle body is fixed on the shell of the combustion chamber of the gas turbine through the mounting hole by a screw.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a natural gas nozzle of a gas turbine, which is characterized in that a nozzle head component is arranged, natural gas is atomized in the nozzle head component, and a nozzle is arranged at the central axis part of a nozzle head, so that the defect of narrow combustible range of the natural gas can be overcome, the stable working range of a combustion chamber is expanded, and the combustion efficiency is improved. The natural gas is filtered by the filter element, so that sundries are prevented from entering the combustion chamber; the plurality of inclined nozzles are circumferentially arranged, so that the uniformity of gas injection is ensured, and the combustion efficiency is ensured. The natural gas nozzle has a simple structure and can meet the overall requirements of the gas turbine.
Furthermore, the conical nozzle arranged on the nozzle head ensures the injection speed of the natural gas and avoids the reduction of atomization quality and combustion efficiency caused by the reduction of the injection speed.
Furthermore, the sealing ring is arranged at the connecting part of the screw plug and the nozzle body, so that an air supply channel inside the nozzle body is protected, sundries are prevented from being leaked, and gas leakage is avoided.
Drawings
FIG. 1 is a schematic illustration of a gas turbine natural gas nozzle according to the present invention;
FIG. 2 is a schematic view of the nozzle head assembly of the present invention;
FIG. 3 is a schematic view of a stop ring and cartridge arrangement of the present invention;
in the drawings: 1 is a screw plug; 2 is a sealing ring; 3 is a nozzle body; 4 is a clamping ring; 5 is a gasket; 6 is a nozzle head assembly; 7 is a nozzle nut body; 8 is a nozzle head; 9 is a stop ring; and 10 is a filter element.
Detailed Description
The present invention will now be described in further detail with reference to specific examples, which are intended to be illustrative, but not limiting, of the invention.
As shown in fig. 1 to 3, the natural gas nozzle of a gas turbine according to the present invention includes a plug screw 1, a seal ring 2, a nozzle body 3, a collar 4, a gasket 5, a nozzle head assembly 6, a check ring 9, and a filter element 10.
The nozzle body 3 is fixed on a shell of a combustion chamber of a gas turbine, an air supply channel is arranged in the nozzle body 3, a screw plug 1 is arranged at one end of the air supply channel, and a nozzle head assembly 6 is arranged at the other end of the air supply channel; the gas supply channel is communicated with a gas supply main pipe through a branch pipeline, and a filter element 10 is arranged on the branch pipeline; the nozzle tip assembly 6 comprises a nozzle nut body 7 and a nozzle tip 8; the nozzle head 8 is fixed on the nozzle nut body 7, the nozzle nut body 7 is connected to the end part of the nozzle body 3, and the diameters of the nozzle nut body 7 and the nozzle head 8 are larger than that of the air supply channel; a plurality of inclined nozzles are circumferentially arranged on the end surface of the nozzle head 8, the central axes of the nozzles all point to the central axis of the nozzle head 8, and the nozzle is arranged in the center of the end surface of the nozzle head 8.
The nozzle head assembly 6 is arranged, natural gas is atomized in the nozzle head assembly, and the nozzles are arranged at the central axis part of the nozzle head 8, so that the defect that the combustible range of the natural gas is narrow can be overcome, the stable working range of the combustion chamber is expanded, and the combustion efficiency is improved. The natural gas is filtered by the filter element 10, so that sundries are prevented from entering the combustion chamber; the plurality of inclined nozzles are circumferentially arranged, so that the uniformity of gas injection is ensured, and the combustion efficiency is ensured. The natural gas nozzle has a simple structure and can meet the overall requirements of the gas turbine.
Examples
The natural gas nozzle of the gas turbine is suitable for an industrial gas turbine, the modified industrial gas turbine takes natural gas as fuel, the fuel is changed from liquid to gas, and the natural gas nozzle mainly considers how to properly spray the fuel into a combustion area to well organize combustion so as to achieve the combustion efficiency and power of a prototype.
The natural gas nozzle should consider the structure parameter of the prototype gas turbine in the design, and ensure the accuracy of the design. For example
Characteristics of prototype gas turbine: power under ISO conditions, efficiency, air flow, etc.
Characteristics of the prototype gas turbine combustor: structural features, combustor inlet air pressure, air flow, fuel flow, combustion efficiency, outlet temperature, etc.
Formal characteristics of prototype gas turbine nozzle: such as the cone angle of atomization of the centrifugal nozzle, the fuel injection velocity, etc.
Physical properties of the prototype combustion fuel and the modified combustion fuel of the gas turbine: the composition of the fuel, density, lower heating value, theoretical equivalent air, etc., and the combustion of the fuel.
Modifying and designing the performance indexes to be achieved: complete machine power, combustion efficiency, exhaust pollution indexes and the like.
The method comprises the steps of performing inverse check calculation on a prototype nozzle by the Abelmervich theory about a centrifugal nozzle, determining the pressure of the prototype nozzle and the fuel injection speed of the nozzle, and calculating the size and the structure of a natural gas nozzle, wherein the natural gas nozzle simulates the injection mode of a liquid fuel nozzle in the air supply mode, so that the concentration distribution of natural gas in a combustion space is basically similar to the concentration distribution rule of liquid fuel, the assembly position and the form of the natural gas nozzle are the same as those of the prototype nozzle, the nozzle is matched at two positions in the assembly, namely the nozzle head is matched with a swirler sleeve, and a nozzle shell is fixed in a combustion chamber shell. The shell form of the original nozzle is adopted, double oil ways are changed into a single air supply channel, the assembly size is unchanged, and the influence of the injection speed on the characteristics of the nozzle is considered.
The calculation of the pressure loss distribution in the flow path is to calculate the pressure loss of each series element in the same flow path by the flow rate continuation principle based on the total pressure drop and the total flow rate. The calculation of the fuel flow of the nozzle and the spray cone angle is based on a maximum flow theoretical method and a momentum equation method, and factors such as fuel physical properties, nozzle structural characteristics and the like are considered for calculation, and the fuel atomization quality is calculated according to an empirical relational expression. Under the condition of considering factors such as fuel viscosity, nozzle structural form and the like, the nozzle performance is accurately calculated by adopting a special nozzle design program, and the program calculates parameters such as fuel flow, spray cone angle, atomization quality and fuel pressure distribution under given pressure on the basis of the known nozzle geometric dimension and fuel temperature, namely the design dimensions of the tangential groove and the nozzle are obtained by solving.
Through calculation and analysis, the natural gas nozzle of the gas turbine comprises a screw plug 1, a sealing ring 2, a nozzle body 3, a clamping ring 4, a gasket 5, a nozzle head assembly 6, a stop ring 9 and a filter element 10.
The nozzle body 3 is fixed on a shell of a combustion chamber of a gas turbine, an air supply channel is arranged in the nozzle body 3, a plug screw 1 is arranged at one end of the air supply channel, and a sealing ring 2 is arranged at the connecting part of the plug screw 1 and the nozzle body 3. The other end of the gas supply channel is provided with a nozzle head assembly 6; the air supply channel is communicated with an air supply main pipe through a branch pipeline, and the branch pipeline is provided with a filter element 10. The diameter of the gas supply channel is the same as the diameter of the branch pipe.
The nozzle tip assembly 6 comprises a nozzle nut body 7 and a nozzle tip 8; the nozzle head 8 is fixed on the nozzle nut body 7 through welding, the nozzle nut body 7 is connected to the end part of the nozzle body 3, and the diameters of the nozzle nut body 7 and the nozzle head 8 are larger than that of the air supply channel; the connecting part of the air supply channel of the nozzle nut body 7 and the nozzle body 3 is provided with a gasket 5, and the outer side wall of the nozzle nut body 7 and the outer side wall of the nozzle body 3 are provided with a clamping ring 4 for fixed connection.
A plurality of inclined nozzles are circumferentially arranged on the end surface of the nozzle head 8, the central axes of the nozzles all point to the central axis of the nozzle head 8, and the nozzle is arranged in the central part of the end surface of the nozzle head 8. The nozzles of the nozzle head 8 are all conical. The connection part of the branch pipeline and the filter element 10 is provided with a stop ring 9. The outer side wall of the nozzle body 3 is provided with a mounting hole, and the nozzle body 3 passes through the mounting hole through a screw to be fixed on a shell of a combustion chamber of the gas turbine.
And finally, calculating to obtain that 13 nozzles are arranged on the nozzle head 8, 12 conical nozzles are uniformly distributed on the pitch circle of the nozzle head 8, and the center of the nozzle head 8 is also provided with the conical nozzles. The diameter of each single nozzle is 2.65mm, the included angle between the central axis of each inclined nozzle and the central axis of the nozzle head 8 is 38-42 degrees, and 40 degrees is preferred in the embodiment; the 12 nozzles 2 are evenly distributed on the end surface of the nozzle head 8 along the circumference, and the diameter of the circumferential distribution is phi 25.
Claims (10)
1. A gas turbine natural gas nozzle, comprising a plug screw (1), a nozzle body (3), a nozzle head assembly (6) and a filter element (10);
the nozzle body (3) is fixed on a shell of a combustion chamber of a gas turbine, an air supply channel is arranged in the nozzle body (3), a screw plug (1) is arranged at one end of the air supply channel, and a nozzle head assembly (6) is arranged at the other end of the air supply channel; the gas supply channel is communicated with a gas supply main pipe through a branch pipeline, and a filter element (10) is arranged on the branch pipeline;
the nozzle head assembly (6) comprises a nozzle nut body (7) and a nozzle head (8); the nozzle head (8) is fixed on the nozzle nut body (7), the nozzle nut body (7) is connected to the end part of the nozzle body (3), and the diameters of the nozzle nut body (7) and the nozzle head (8) are larger than that of the air supply channel;
the end face of the nozzle head (8) is circumferentially provided with a plurality of inclined nozzles, the central axes of the nozzles all point to the central axis of the nozzle head (8), and the central part of the end face of the nozzle head (8) is provided with the nozzles.
2. A gas turbine natural gas nozzle according to claim 1, characterized in that the nozzles in the nozzle head (8) are conical.
3. A gas turbine natural gas nozzle according to claim 1, characterized in that 12 inclined nozzles are circumferentially arranged on the end surface of the nozzle head (8).
4. A gas turbine natural gas nozzle according to claim 1, characterized in that the angle between the central axis of the inclined nozzle opening and the central axis of the nozzle head (8) is 38 ° to 42 °.
5. The natural gas nozzle of the gas turbine as claimed in claim 1, wherein the connection part of the gas supply channel of the nozzle nut body (7) and the nozzle body (3) is provided with a gasket (5), and the nozzle nut body (7) and the outer side wall of the nozzle body (3) are fixedly connected by a clamping ring (4).
6. A gas turbine natural gas nozzle as claimed in claim 1, wherein the diameter of said gas supply passage is the same as the diameter of the branch conduit.
7. A gas turbine natural gas nozzle according to claim 1, characterized in that the connection of the plug screw (1) and the nozzle body (3) is provided with a sealing ring (2).
8. A gas turbine natural gas nozzle according to claim 1, characterized in that the connection of the branch conduit to the filter element (10) is provided with a stop ring (9).
9. A gas turbine natural gas nozzle according to claim 1, characterised in that the nozzle nut body (7) and the nozzle tip (8) are fixedly connected by welding.
10. A gas turbine natural gas nozzle according to claim 1, characterized in that the outer side wall of the nozzle body (3) is provided with mounting holes, and the nozzle body (3) is fixed to the casing of the gas turbine combustor by screws passing through the mounting holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110287615.7A CN112984558A (en) | 2021-03-17 | 2021-03-17 | Natural gas nozzle of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110287615.7A CN112984558A (en) | 2021-03-17 | 2021-03-17 | Natural gas nozzle of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112984558A true CN112984558A (en) | 2021-06-18 |
Family
ID=76332854
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110287615.7A Pending CN112984558A (en) | 2021-03-17 | 2021-03-17 | Natural gas nozzle of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112984558A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6082113A (en) * | 1998-05-22 | 2000-07-04 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
| CN102242930A (en) * | 2011-07-05 | 2011-11-16 | 清远市精旺环保设备有限公司 | Nozzle of burner |
| CN204478042U (en) * | 2015-01-13 | 2015-07-15 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of heads fuel atomizer |
| US20170045231A1 (en) * | 2014-05-02 | 2017-02-16 | Siemens Aktiengesellschaft | Combustor burner arrangement |
| CN108443912A (en) * | 2018-02-08 | 2018-08-24 | 中国船舶重工集团公司第七0三研究所 | A kind of self-priming air-assisted atomization dual fuel nozzle |
| CN208554675U (en) * | 2018-07-05 | 2019-03-01 | 迈德乐喷雾系统广州有限公司 | A kind of low pressure internal-mixing two-fluid spray nozzle |
-
2021
- 2021-03-17 CN CN202110287615.7A patent/CN112984558A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6082113A (en) * | 1998-05-22 | 2000-07-04 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
| CN102242930A (en) * | 2011-07-05 | 2011-11-16 | 清远市精旺环保设备有限公司 | Nozzle of burner |
| US20170045231A1 (en) * | 2014-05-02 | 2017-02-16 | Siemens Aktiengesellschaft | Combustor burner arrangement |
| CN204478042U (en) * | 2015-01-13 | 2015-07-15 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of heads fuel atomizer |
| CN108443912A (en) * | 2018-02-08 | 2018-08-24 | 中国船舶重工集团公司第七0三研究所 | A kind of self-priming air-assisted atomization dual fuel nozzle |
| CN208554675U (en) * | 2018-07-05 | 2019-03-01 | 迈德乐喷雾系统广州有限公司 | A kind of low pressure internal-mixing two-fluid spray nozzle |
Non-Patent Citations (2)
| Title |
|---|
| 何敏 等: "《不同气体喷嘴的燃气轮机燃烧室性能对比》", 《航空动力学报》 * |
| 何敏 等: "《不同气体喷嘴的燃气轮机燃烧室性能对比》", 《航空动力学报》, 30 June 2018 (2018-06-30), pages 1291 - 1296 * |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210618 |
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| RJ01 | Rejection of invention patent application after publication |