CN113779730B - Method for designing opening of flame tube of gas turbine - Google Patents
Method for designing opening of flame tube of gas turbine Download PDFInfo
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- CN113779730B CN113779730B CN202111088741.6A CN202111088741A CN113779730B CN 113779730 B CN113779730 B CN 113779730B CN 202111088741 A CN202111088741 A CN 202111088741A CN 113779730 B CN113779730 B CN 113779730B
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- flame tube
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- gas turbine
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Mathematical Analysis (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Computational Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gas Burners (AREA)
Abstract
The application discloses a design method of the opening of a flame tube of a gas turbine, which comprises the following steps: 1) Determining the axial length L of the flame tube according to the volume flow of the combustion chamber and the residence time of the mixed gas in the flame tube within the limit range of the overall size of the gas turbine f And inner diameter/lumen height D f The method comprises the steps of carrying out a first treatment on the surface of the 2) According to the size of the flame tube, calculating the optimal opening of the flame tube: 3) Calculating the optimal total open area of the flame tube according to the optimal opening of the flame tube: 4) And opening design of each combustion zone of the flame tube is completed according to the optimal total opening area of the flame tube. The method of the application can greatly shorten the research and development period and save the research and development cost.
Description
Technical Field
The application relates to the technical field of development of flame tubes of gas turbines, in particular to a method for designing the opening degree of the flame tube of the gas turbine.
Background
The opening degree of the flame tube of the gas turbine refers to the ratio of the total opening area of the flame tube to the flow cross section area of the flame tube, and the ratio determines the turbulence level of oil-gas mixture in the flame tube, and directly influences the flow loss, combustion efficiency, outlet temperature field, lean extinction and lean ignition performance in a combustion chamber. The opening of the flame tube is small, the turbulence level of the oil-gas mixture in the flame tube is strong, the combustion completeness and the uniformity of the outlet temperature of the combustion chamber are facilitated, the flow loss in the combustion chamber is increased, and the lean blowout and lean ignition boundary of the combustion chamber can be reduced. Therefore, when the flame tube is designed, reasonable opening degree is required to meet the comprehensive performance of the combustion chamber.
In the design of the flame tube, it is difficult to determine whether the opening of the flame tube can meet the requirement of the comprehensive performance of the combustion chamber, a large number of comprehensive performance tests of the combustion chamber are required, and the opening size of the flame tube is continuously corrected to coordinate the contradiction between various performances of the combustion chamber, so that the design of the flame tube meeting the performance requirement can be obtained. Long time and high cost for research and development.
Disclosure of Invention
In view of the above-mentioned drawbacks or shortcomings in the prior art, it is desirable to provide a design method for opening of a gas turbine combustor which can greatly shorten the development period and save the development costs.
The application provides a design method of the opening of a flame tube of a gas turbine, which comprises the following steps:
1) Determining the axial length L of the flame tube according to the volume flow of the combustion chamber and the residence time of the mixed gas in the flame tube within the limit range of the overall size of the gas turbine f And inner diameter/lumen height D f ；
2) According to the size of the flame tube, calculating the optimal opening of the flame tube:
A 0 ＝∑F 0 /F f ＝0.065e 0 . 6Lf/Df ；
wherein ΣF 0 Is the optimal total open area of the flame tube;
F f is the flow cross section of the flame tube;
L f is the axial length of the flame tube;
D f is the inner diameter/channel height of the flame tube;
3) Calculating the optimal total open area of the flame tube according to the optimal opening of the flame tube:
∑F 0 ＝A 0 *F f ；
4) And opening design of each combustion zone of the flame tube is completed according to the optimal total opening area of the flame tube.
Further, the step 4) includes:
41 Preliminary design of openings is carried out on each combustion area of the flame tube, and the total opening area of the design is obtained;
42 Calculating the design opening of the flame tube:
A x ＝∑F x /F f ；
wherein ΣF x The total open area is designed for the flame tube;
F f is the flow cross section of the flame tube;
43 Comparison A) x And A 0 The design of the holes of each combustion zone is corrected to lead A x Equal to A 0 。
Compared with the prior art, the application has the beneficial effects that:
according to the design method, through analysis and related test verification of the comprehensive performance of the combustion chamber, the optimal opening of the flame tube with various sizes is obtained, the flame tube coordinates various performances of the combustion chamber under the opening, the flame tube is designed by matching the opening, and through a follow-up test of the comprehensive performance of the combustion chamber, the opening of the flame tube meeting the performance requirement can be obtained in a shorter time, the research and development time of the flame tube is greatly shortened, and the research and development cost is saved.
It should be understood that the description in this summary is not intended to limit the critical or essential features of the embodiments of the application, nor is it intended to limit the scope of the application. Other features of the present application will become apparent from the description that follows.
Detailed Description
The following examples illustrate the application in further detail. It is to be understood that the specific embodiments described herein are merely illustrative of the application and are not limiting of the application. It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The present application will be described in detail by way of examples.
The embodiment of the application provides a design method of the opening degree of a flame tube of a gas turbine, which comprises the following steps:
1) Determining the axial length L of the flame tube according to the volume flow of the combustion chamber and the residence time of the mixed gas in the flame tube within the limit range of the overall size of the gas turbine f And inner diameter/lumen height D f ；
2) According to the size of the flame tube, calculating the optimal opening of the flame tube:
A 0 ＝∑F 0 /F f ＝0.065e 0 . 6Lf/Df ；
wherein ΣF 0 Is the optimal total open area of the flame tube;
F f is the flow cross section of the flame tube;
L f is the axial length of the flame tube;
D f is the inner diameter/channel height of the flame tube;
3) Calculating the optimal total open area of the flame tube according to the optimal opening of the flame tube:
∑F 0 ＝A 0 *F f ；
4) Completing the opening design of each combustion zone of the flame tube according to the optimal total opening area of the flame tube;
41 Preliminary design of openings is carried out on each combustion area of the flame tube, and the total opening area of the design is obtained;
42 Calculating the design opening of the flame tube:
A x ＝∑F x /F f ；
wherein ΣF x The total open area is designed for the flame tube;
F f is the flow cross section of the flame tube;
43 Comparison A) x And A 0 The design of the holes of each combustion zone is corrected to lead A x Equal to A 0 。
In the present embodiment, the optimum opening value A of the flame tube 0 Is a function of the size (aspect ratio) of the flame tube. When the design of the combustion chamber is carried out, after the outline size of the flame tube is determined according to the volume flow of the combustion chamber and the residence time of the mixed gas in the flame tube within the limit range of the overall size of the engine, the design of the holes of each combustion zone of the flame tube is needed. The design of the opening of the flame tube is influenced by the structure of the flame tube, so that the primary opening design of the flame tube is required to be completed according to the specific structure of the flame tube.
Optimum opening A of flame tube according to the patent 0 Can preliminarily judge the design opening A of the flame tube x If the deviation is reasonable, immediately correcting the deviation to ensure that the opening design of the flame tube meets the optimal opening A 0 . And after the corrected flame tube opening design is carried out, a subsequent comprehensive performance verification test is carried out, and the opening degree of the flame tube meeting the performance requirement can be quickly reached. And a large amount of test adjustment workload is saved, the research and development cost of the combustion chamber is saved, and meanwhile, the accuracy of the design of the flame tube opening is greatly improved.
In the description of the present specification, the description of the term "embodiment" and the like means that a specific feature described in connection with the embodiment is included in an example of the present application. The above is only a preferred embodiment of the present application, and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (2)
1. The method for designing the opening of the flame tube of the gas turbine is characterized by comprising the following steps of:
1) Determining the axial length L of the flame tube according to the volume flow of the combustion chamber and the residence time of the mixed gas in the flame tube within the limit range of the overall size of the gas turbine f And inner diameter/lumen height D f ；
2) According to the size of the flame tube, calculating the optimal opening of the flame tube:
A 0 ＝∑F 0 /F f ＝0.065e 0.6Lf/Df ；
wherein ΣF 0 Is the optimal total open area of the flame tube;
F f is the flow cross section of the flame tube;
L f is the axial length of the flame tube;
D f is the inner diameter/channel height of the flame tube;
3) Calculating the optimal total open area of the flame tube according to the optimal opening of the flame tube:
∑F 0 ＝A 0 *F f ；
4) And opening design of each combustion zone of the flame tube is completed according to the optimal total opening area of the flame tube.
2. The method for designing the opening degree of a combustor basket of a gas turbine according to claim 1, wherein the step 4) includes:
41 Preliminary design of openings is carried out on each combustion area of the flame tube, and the total opening area of the design is obtained;
42 Calculating the design opening of the flame tube:
A x ＝∑F x /F f ；
wherein ΣF x The total open area is designed for the flame tube;
F f is the flow cross section of the flame tube;
43 Comparison A) x And A 0 The design of the holes of each combustion zone is corrected to lead A x Equal to A 0 。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111088741.6A CN113779730B (en) | 2021-09-16 | 2021-09-16 | Method for designing opening of flame tube of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111088741.6A CN113779730B (en) | 2021-09-16 | 2021-09-16 | Method for designing opening of flame tube of gas turbine |
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| Publication Number | Publication Date |
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| CN113779730A CN113779730A (en) | 2021-12-10 |
| CN113779730B true CN113779730B (en) | 2023-10-17 |
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| CN202111088741.6A Active CN113779730B (en) | 2021-09-16 | 2021-09-16 | Method for designing opening of flame tube of gas turbine |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6467505A (en) * | 1987-09-08 | 1989-03-14 | Matsushita Electric Ind Co Ltd | Combustion equipment |
| CN109990309A (en) * | 2019-03-05 | 2019-07-09 | 南京航空航天大学 | A kind of compound cooling structure of combustion chamber wall surface and turboshaft engine reverse flow type combustor |
| CN112696710A (en) * | 2020-12-29 | 2021-04-23 | 中国航发沈阳发动机研究所 | Method and system for determining size of mixing hole of flame tube with funnel |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20210209274A1 (en) * | 2020-01-02 | 2021-07-08 | Viettel Group | Method of designing the spiral vortex chambers of fuel mist atomizing device in gas turbine engines |
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2021
- 2021-09-16 CN CN202111088741.6A patent/CN113779730B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6467505A (en) * | 1987-09-08 | 1989-03-14 | Matsushita Electric Ind Co Ltd | Combustion equipment |
| CN109990309A (en) * | 2019-03-05 | 2019-07-09 | 南京航空航天大学 | A kind of compound cooling structure of combustion chamber wall surface and turboshaft engine reverse flow type combustor |
| CN112696710A (en) * | 2020-12-29 | 2021-04-23 | 中国航发沈阳发动机研究所 | Method and system for determining size of mixing hole of flame tube with funnel |
Non-Patent Citations (2)
| Title |
|---|
| 中国工程热物理学会编.中国工程热物理学会 燃烧学学术会议论文集.燃气轮机合成气燃烧室改造技术-燃烧室设计,2004,第671-675页. * |
| 结构参数对喷嘴性能影响的数值研究;刘国庆等;航空发动机;第41卷(第5期);第28-32页 * |
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| CN113779730A (en) | 2021-12-10 |
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