CN115111603B - Combustion chamber flame tube with cooling structure for miniature gas turbine and double-layer wall structure - Google Patents
Combustion chamber flame tube with cooling structure for miniature gas turbine and double-layer wall structure Download PDFInfo
- Publication number
- CN115111603B CN115111603B CN202210613774.6A CN202210613774A CN115111603B CN 115111603 B CN115111603 B CN 115111603B CN 202210613774 A CN202210613774 A CN 202210613774A CN 115111603 B CN115111603 B CN 115111603B
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- Prior art keywords
- combustion chamber
- flame tube
- double
- heat exchange
- chamber flame
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Classifications
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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
- F23R3/52—Toroidal combustion chambers
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention aims to provide a combustion chamber flame tube with a cooling structure and a double-wall structure of a miniature gas turbine, which comprises a combustion chamber flame tube with a double-wall structure, wherein a centrifugal compressor is arranged at the top of the combustion chamber flame tube with the double-wall structure, a centripetal turbine is arranged at the tail part of the combustion chamber flame tube with the double-wall structure, a mounting hole is arranged at the top of the combustion chamber flame tube with the double-wall structure, a dual-fuel efficient nozzle is mounted through the mounting hole, reinforced heat exchange wall surfaces are mounted on two layers of walls on the low-temperature side of the combustion chamber flame tube with the double-wall structure, and cooling holes are formed on the reinforced heat exchange wall surfaces. The cooling mode designed by the invention greatly improves the heat exchange area and the heat exchange strength, ensures the volume of the micro gas turbine, and improves the working range, the stability and the service life of the combustion chamber of the micro gas turbine.
Description
Technical Field
The invention relates to a gas turbine, in particular to a combustor flame tube of the gas turbine.
Background
The combustion chamber is used as a gas combustion part connected with the compressor and the turbine, chemical energy is converted into heat energy, hot air is introduced into the turbine to do work, the working environment temperature is highest, and fuel and the entering air are combusted in the combustion chamber, wherein the combustion temperature can reach more than 2000 ℃. With the development of gas turbine technology, the combustion temperatures in the combustion chamber are also increasing, and the materials are subject to thermal strains, creep and even damage under certain temperature conditions, the maximum allowable temperature of hot gas being limited by the operating temperature limits of the metal components in contact with such hot gas and depending on the ability to cool these components below the hot gas temperature. The thermodynamic efficiency that a heat engine may achieve, depending on the maximum temperature of its working fluid, requires that combustion stability be ensured while not reducing the combustion temperature in order to ensure combustion efficiency and higher gas turbine power, so it is necessary to design efficient and good heat exchange structures to quickly remove heat to reduce the combustion chamber temperature.
The maximum temperature allowed in the combustion chamber of a gas turbine determines the efficiency of the gas turbine, and the temperature is limited by materials, and the cooling task of the combustor basket of an advanced gas turbine is difficult. At present, a part of cold air is mostly introduced into the flame tube from the outer ring cavity of the combustion chamber, and an air film is formed on the inner wall of the flame tube, so that the flame tube wall is cooled on one hand, and hot gas is isolated on the other hand.
Disclosure of Invention
The invention aims to provide a combustion chamber flame tube with a cooling structure for a micro gas turbine, which can realize stronger heat exchange effect in a small volume, improve the working range and the stability of the combustion chamber of the micro gas turbine and prolong the service life of the combustion chamber.
The purpose of the invention is realized in the following way:
the invention relates to a combustion chamber flame tube with a cooling structure and a double-layer wall structure of a miniature gas turbine, which is characterized in that: the dual-fuel high-efficiency nozzle comprises a dual-layer structure combustion chamber flame tube, wherein a centrifugal compressor is arranged at the top of the dual-layer structure combustion chamber flame tube, a centripetal turbine is arranged at the tail of the dual-layer structure combustion chamber flame tube, mounting holes are formed in the top of the dual-layer structure combustion chamber flame tube, the dual-fuel high-efficiency nozzle is mounted through the mounting holes, reinforced heat exchange wall surfaces are mounted on two layers of walls of the low-temperature side of the dual-layer structure combustion chamber flame tube, and cooling holes are formed in the reinforced heat exchange wall surfaces.
The invention may further include:
1. the reinforced heat exchange wall surface is connected with the wall of the corresponding double-layer structure combustion chamber flame tube through the cylindrical rib and is used for cooling and heat exchange.
2. The cylindrical ribs are in a solid and hollow spaced form, the solid cylindrical ribs are connected with the corresponding reinforced heat exchange wall surface and the wall of the double-layer structure combustion chamber flame tube, and the hollow cylindrical ribs take away gas heat.
3. The number of solid cylindrical ribs is greater than the number of hollow cylindrical ribs.
4. The structure formed by the two layers of walls of the double-layer combustion chamber flame tube is in a structure form of inner side and outer side air inlet matched with the centrifugal compressor.
The invention has the advantages that: the invention designs a combustion chamber flame tube with a cooling structure of a miniature gas turbine, which is characterized in that a new cooling structure is added on the combustion chamber flame tube with the double-layer structure, the reinforced heat exchange wall surface with the cooling structure is mainly measured at low temperature by the combustion chamber flame tube with the double-layer structure, and the reinforced heat exchange wall surface is connected with the flame tube wall surface through a solid-hollow cylindrical rib to carry out reinforced heat exchange, and for the self-saving structure of the miniature gas turbine, a stronger heat exchange effect is realized in a small volume.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a combustion chamber nozzle configuration;
FIG. 3 is an air intake mode;
FIG. 4 is a diagram of the connection between the enhanced heat exchange wall and the combustion chamber wall.
Detailed Description
The invention is described in more detail below, by way of example, with reference to the accompanying drawings:
1-4, the present invention is a dual wall structured combustor basket for a micro gas turbine with a cooling structure, comprising: the centrifugal compressor 1, the compressor outlet guide vane 2, the combustion chamber nozzle 3, the combustion chamber wall 4, the centripetal turbine 5, the combustion chamber nozzle adapting hole 6, the hollow cylindrical rib 7, the solid cylindrical rib 8, the reinforced heat exchange wall 9 and the reinforced heat exchange wall cooling hole 10.
The combustion chamber nozzle 3 is used for introducing combustible gas into the combustion chamber with the double-layer structure through the combustion chamber nozzle adapting hole 6, the combustion chamber wall surface 4 and the reinforced heat exchange wall surface 9 are connected and fixed through the hollow cylindrical rib 7 and the solid cylindrical rib 8 to perform reinforced heat exchange, and meanwhile, the reinforced heat exchange wall surface 9 is provided with the reinforced heat exchange wall surface cooling hole 10 to further strengthen the heat exchange. The top of the double-layer wall structure combustion chamber flame tube is provided with a mounting hole of the dual-fuel high-efficiency nozzle 3 and a structural form of inner side and outer side air inlet matched with the centrifugal compressor 1. The reinforced heat exchange wall surface 9 is arranged on the low temperature side of the flame tube of the double-layer structure combustion chamber, and meanwhile, the cooling holes 10 are added on the reinforced heat exchange wall surface 9, so that the air from the air compressor 1 passes through the cooling holes 10 of the reinforced heat exchange wall surface 9 and forms a cooling air film on the wall surface 4 of the double-layer structure combustion chamber flame tube so as to take away heat on the high temperature wall surface. The reinforced heat exchange wall surface 9 is connected with the flame tube of the combustion chamber with the double-layer structure through the solid cylindrical ribs 7 and 8, the solid cylindrical ribs 8 play a main role in connection and fixation, and the number of the solid cylindrical ribs 8 is more than that of the hollow cylindrical ribs 7 so as to ensure the stability of the structural form. After the gas entering between the reinforced heat exchange wall surface 9 and the flame tube wall surface 4 of the combustion chamber with the double-layer structure passes through the cylindrical ribs 7 and 8, vortex is formed between the cylindrical ribs 7 and 8, the heat exchange strength of the reinforced heat exchange wall surface 9 and the flame tube wall surface 4 of the combustion chamber with the double-layer structure can be enhanced, the solid cylindrical rib 8 enables the temperature of the high-temperature end to be rapidly transferred to the reinforced heat exchange wall surface 9, the heat exchange area is equivalent to being increased, and heat near the hollow cylindrical rib can be taken away after the hollow cylindrical rib 7 passes through the gas of the gas compressor, so that heat exchange is further enhanced.
The working process is as follows: air is further pressurized through the centrifugal compressor 1 and then through the compressor outlet guide vanes 2, the high-pressure gas is divided into a plurality of strands and enters the combustion chamber, air is respectively introduced into the space between the combustion chamber wall surface 4 and the reinforced heat exchange wall surface 9, air is introduced into the combustion chamber from the reinforced heat exchange wall surface cooling holes 10 on the reinforced heat exchange wall surface 9 and air inlet holes such as the inside of the combustion chamber on the combustion chamber wall surface 4, and air is introduced from the internal channel of the hollow cylindrical rib 7. The gas entering through the cooling holes 10 on the reinforced heat exchange wall surface 9 forms a cooling gas film on the wall surface of the combustion chamber, the gas entering from the space between the wall surface 4 of the combustion chamber and the reinforced heat exchange wall surface 9 forms vortex after passing through the solid cylindrical rib 7 and the hollow cylindrical rib to take away the heat on the reinforced heat exchange wall surface 9 and the wall surface 4 of the combustion chamber, the cooling gas passing through the hollow cylindrical rib 7 takes away the heat near the hollow cylindrical rib to strengthen the heat exchange efficiency, and the existence of the solid cylindrical rib further diffuses the heat on the wall surface 4 of the combustion chamber to the upper surface of the reinforced heat exchange wall surface 9 while strengthening the flow heat exchange between the wall surface 4 of the combustion chamber and the reinforced heat exchange wall surface 9, which is equivalent to increasing the heat exchange area of the wall surface 4 of the combustion chamber.
Claims (2)
1. The utility model provides a miniature gas turbine double-deck wall structure combustor flame tube with cooling structure which characterized by: the dual-fuel high-efficiency nozzle is installed through the installation holes, the reinforced heat exchange wall surfaces are installed on two layers of walls on the low-temperature side of the dual-layer structure combustion chamber flame tube, and the reinforced heat exchange wall surfaces are all provided with cooling holes;
the reinforced heat exchange wall surface is connected with the wall of the corresponding double-layer structure combustion chamber flame tube through the cylindrical rib and is used for cooling and heat exchange;
the cylindrical ribs are in a solid and hollow interval form, the solid cylindrical ribs are connected with the corresponding reinforced heat exchange wall surface and the wall of the double-layer structure combustion chamber flame tube, and the hollow cylindrical ribs take away gas heat;
the number of solid cylindrical ribs is greater than the number of hollow cylindrical ribs.
2. The combustor basket with cooling structure of a double-walled structure of a micro gas turbine of claim 1, wherein: the structure formed by the two layers of walls of the double-layer combustion chamber flame tube is in a structure form of inner side and outer side air inlet matched with the centrifugal compressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210613774.6A CN115111603B (en) | 2022-05-31 | 2022-05-31 | Combustion chamber flame tube with cooling structure for miniature gas turbine and double-layer wall structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210613774.6A CN115111603B (en) | 2022-05-31 | 2022-05-31 | Combustion chamber flame tube with cooling structure for miniature gas turbine and double-layer wall structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115111603A CN115111603A (en) | 2022-09-27 |
| CN115111603B true CN115111603B (en) | 2023-09-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210613774.6A Active CN115111603B (en) | 2022-05-31 | 2022-05-31 | Combustion chamber flame tube with cooling structure for miniature gas turbine and double-layer wall structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN115111603B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3835922A (en) * | 1972-03-30 | 1974-09-17 | Lindt & Spruengli Schokolade | Heat exchanger for fluent masses |
| US5378132A (en) * | 1990-04-26 | 1995-01-03 | Kaiser; Herbert | Apparatus for producing granules or pastilles from flowable material |
| CN104033927A (en) * | 2014-06-12 | 2014-09-10 | 中国航空动力机械研究所 | Combustion chamber based on RQL principle and aircraft engine with same |
| CN104357018A (en) * | 2014-10-10 | 2015-02-18 | 中关村人居环境工程与材料研究院 | Environment-friendly composite phase change material and phase change energy storage device |
| CN204176685U (en) * | 2014-09-26 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner |
| CN106247403A (en) * | 2016-08-02 | 2016-12-21 | 北京航空航天大学 | A kind of miniature gas turbine combustion chamber of double-wall structure |
| CN111520747A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Soft gas turbine combustion chamber |
| CN111520764A (en) * | 2020-03-25 | 2020-08-11 | 西北工业大学 | Combustion chamber with tail cooling structure |
| CN113217949A (en) * | 2021-05-20 | 2021-08-06 | 西安航天动力研究所 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
-
2022
- 2022-05-31 CN CN202210613774.6A patent/CN115111603B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3835922A (en) * | 1972-03-30 | 1974-09-17 | Lindt & Spruengli Schokolade | Heat exchanger for fluent masses |
| US5378132A (en) * | 1990-04-26 | 1995-01-03 | Kaiser; Herbert | Apparatus for producing granules or pastilles from flowable material |
| CN104033927A (en) * | 2014-06-12 | 2014-09-10 | 中国航空动力机械研究所 | Combustion chamber based on RQL principle and aircraft engine with same |
| CN204176685U (en) * | 2014-09-26 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner |
| CN104357018A (en) * | 2014-10-10 | 2015-02-18 | 中关村人居环境工程与材料研究院 | Environment-friendly composite phase change material and phase change energy storage device |
| CN106247403A (en) * | 2016-08-02 | 2016-12-21 | 北京航空航天大学 | A kind of miniature gas turbine combustion chamber of double-wall structure |
| CN111520747A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Soft gas turbine combustion chamber |
| CN111520764A (en) * | 2020-03-25 | 2020-08-11 | 西北工业大学 | Combustion chamber with tail cooling structure |
| CN113217949A (en) * | 2021-05-20 | 2021-08-06 | 西安航天动力研究所 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
Non-Patent Citations (1)
| Title |
|---|
| 某型斜流驻涡燃烧室火焰筒冷却结构优化研究;张净玉;工程热物理学报;43(4);1013-1020 * |
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| Publication number | Publication date |
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| CN115111603A (en) | 2022-09-27 |
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