CN110925798A - Combustion chamber with spiral-flow type flame tube - Google Patents
Combustion chamber with spiral-flow type flame tube Download PDFInfo
- Publication number
- CN110925798A CN110925798A CN201911074777.1A CN201911074777A CN110925798A CN 110925798 A CN110925798 A CN 110925798A CN 201911074777 A CN201911074777 A CN 201911074777A CN 110925798 A CN110925798 A CN 110925798A
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- Prior art keywords
- swirl
- holes
- area
- hole
- flame tube
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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
- F23R3/56—Combustion chambers having rotary flame tubes
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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
- F23R3/28—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
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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
- F23R3/28—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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention provides a combustion chamber with a spiral-flow type flame tube, and relates to the field of combustion chambers of aero-engines. Based on the different functions of the main combustion hole, the middle hole and the mixing hole of the flame tube of the original combustion chamber, the spiral-flow type airflow holes are added at three different positions on the wall surface of the flame tube. The swirling flow gas entering the main combustion area is mixed with mixed fuel gas sprayed out of the vicinity of the swirler, and the area of a backflow area is increased. And then, the fuel gas flow after full combustion in the main combustion area flows into the middle area, and further fully combusts with the rotational flow entering from the middle hole, so that unburned fuel gas and intermediate combustion products can be effectively and completely combusted. Finally, the generated incomplete combustion products and residual fuel oil pass through the blending area and lean-burn with the swirling flow gas entering from the blending holes by the tail of the flame sprayed from the main combustion area, so that extremely low emission of pollutants is realized. The invention can be applied to low-pollution aircraft engines.
Description
Technical Field
The invention belongs to the field of aero-engine combustors, and particularly relates to a combustor with a spiral-flow type flame tube.
Background
With the development of civilization of human being more and more rapid, the international aviation industry is getting stronger, which brings great convenience to the global economic development and communication, but also causes a plurality of problems in the aspect of environment. According to effective data, in 1999, the greenhouse gas emitted to the atmosphere by the aviation industry accounts for 3.5% of all human activities, which means that the development of the aviation industry also seriously affects the atmospheric environment, and therefore, the emission requirements for the aviation engine are higher and higher. The investigation shows that the emission requirement of the aeroengine on nitrogen oxide (NOx) is reduced by 45-60% compared with the emission standard specified by the international civil aviation organization. In addition to nitrogen oxides (NOx), other pollutants (carbon monoxide, unburned hydrocarbons, smoke, etc.) emitted by aircraft engines are also in need of further reduction in their emissions.
The important problem to be solved on the combustion chamber of the aircraft engine is nitrogen oxide, and the key point for controlling the emission of the nitrogen oxide is to control the combustion reaction temperature in the combustion chamber. At present, a low-pollution combustor reduces the generation of nitrogen oxides by adopting a lean oil premixing and pre-evaporation technology to control flame temperature, and reduces the emission of pollutants by adopting a staged combustion technology, but both methods can cause automatic ignition or backfire at a high inlet temperature, and the combustor runs near the lean oil flameout limit at the same time, so that the operation of the combustor is greatly influenced by the structure of the combustor, and the reduction of the emission of pollutants is also limited.
The flame tube structure of the combustion chamber of the aircraft engine is improved, so that spontaneous combustion and backfire can be effectively prevented, the swirling flow gas entering the main combustion area is mixed with the mixed gas sprayed by the swirler, the area of a backflow area is increased, the combustion of the main combustion area is more sufficient, and the generation amount of pollution gas in the main combustion area is reduced. The gas enters the middle area after entering, and at the moment, the gas coming from the main combustion area and the rotating airflow entering from the swirling holes of the middle area form a second swirling area, so that the unburned gas and the intermediate combustion products can be effectively and completely combusted. And finally, the gas flow entering the mixing region is influenced by the rotating air flow entering the swirl holes to form a low-speed backflow region, the backflow temperature can be controlled by the swirl direction under the action of the tail flame, and the emission of pollutants such as nitrogen oxides and the like is further reduced by lean oil combustion, so that extremely low emission of the pollutants is realized.
Disclosure of Invention
The invention aims to solve the technical problem of providing a combustion chamber with a flame tube with a rotational flow characteristic. Compared with the existing combustion chamber structure, the invention has the advantage that the wall surface of the flame tube is reasonably changed on the basis of the original flame tube structure. Part of the main combustion holes are reformed into swirl holes on the wall surface of the main combustion area, which are called as main combustion area swirl holes, so that the area of a backflow area is increased, the combustion of the main combustion area is more sufficient, and the generation amount of pollution gas in the main combustion area is reduced; part of the middle holes are reformed into swirl holes on the wall surface of the middle area, which are called as middle area swirl holes, so that unburned gas and middle combustion products are effectively and completely combusted; part of the mixing holes are reformed into swirl holes on the wall surface of the mixing region, which are called swirl holes in the mixing region, the reflux temperature is controlled, the lean oil combustion is utilized to further reduce the discharge amount of pollutants such as nitrogen oxides and the like, and the combustion efficiency is improved.
Technical scheme
The invention aims to provide a combustor with a swirl type flame tube.
The technical scheme of the invention is as follows:
a combustor with a swirl-type flame tube comprises a basic combustor structure (a shell, a swirler, a nozzle and the like) and a flame tube wall surface with swirl characteristics. The method is characterized in that: based on the different functions of the main combustion hole, the middle hole and the mixing hole of the flame tube of the original combustion chamber, the spiral-flow type airflow holes are added at three different positions on the wall surface of the flame tube and are in spaced fit with the main combustion hole, the middle hole and the mixing hole. The air flow entering from the main combustion hole is fully mixed with the fuel oil at the edge of the rotational flow area, then the fuel gas flow fully combusted in the main combustion area flows into the middle area, the fuel gas flow is further fully combusted with the rotational flow entering from the middle hole, incomplete combustion is reduced, finally generated incomplete combustion products and residual fuel oil pass through the mixing area, lean oxygen combustion is carried out on the incomplete combustion products and the rotational flow gas entering from the mixing hole by means of the tail part of the flame sprayed out of the main combustion area, and then the combustion products and air which does not participate in reaction are discharged out of the flame tube.
The flame tube wall swirl hole is characterized in that: the swirl hole is similar to a swirler at the front end of the flame tube in shape, the swirl angle and swirl characteristics of the swirl hole are similar to those of the swirler, and the swirl hole plays a strengthening role rather than a restraining role in comparison with the swirl caused by the original main combustion area. The ranges of the swirl hole areas on the wall surfaces of the main combustion area, the middle area and the mixing area are determined according to the distribution range of the main combustion holes, the middle holes and the mixing holes on the wall surface of the original flame tube, and the number of rows of swirl holes is about 1-5 rows, 1-5 rows and 1-3 rows. When the number of rows of swirl holes formed in the three areas on the wall surface of the flame tube exceeds one row, the swirl holes can be arranged in an inserting or sequential manner, and the sizes of the swirl holes in the distribution areas of the main combustion holes, the intermediate holes and the mixing holes are 1-10 times of the sizes of the swirl holes.
The flame tube main combustion area is characterized in that: based on the position and size arrangement of the original flame tube main combustion holes, the designed swirl holes are about 5-7 mm in size and are designed between the main combustion holes, the spacing included angle of each main combustion area swirl hole is about 30 degrees, and the swirl holes are circumferentially arranged.
The flame tube middle area is characterized in that: based on the position and size arrangement of the middle holes of the original flame tube, the swirl holes are designed to be about 4-6 mm in size and are designed to be about 30 degrees at intervals between the middle holes, and the swirl holes are circumferentially arranged.
The flame tube mixing area is characterized in that: based on the position and the size arrangement of the mixing holes of the original flame tube, the size of the designed swirl holes is about 3-5 mm, the swirl holes in each mixing area are designed between the mixing holes, the interval included angle between the swirl holes in each mixing area is about 30 degrees, and the swirl holes are circumferentially arranged.
The invention has the following beneficial effects:
the combustor with the spiral-flow type flame tube has the advantages that the wall surface of the flame tube is reasonably changed on the basis of the original flame tube structure, the trend of the airflow inside the flame tube can be reasonably improved without changing the internal structure of the combustor, the combustion efficiency can be effectively improved, fuel can be completely combusted to the maximum extent, and the emission of pollutants is reduced. And the structural design is relatively simple, the feasibility is high, and the method has a good application prospect.
Drawings
FIG. 1: schematic view of combustor with swirl type flame tube
FIG. 2: wall surface expansion diagram of combustion chamber with swirl type flame tube
FIG. 3: swirl hole schematic
In the drawing 1, a flame tube front end device 2, an outer wall surface main combustion hole 3, an outer wall surface main combustion area swirl hole 4, an outer wall surface middle hole 5, an outer wall surface middle area swirl hole 6, an outer wall surface mixing area 7, an outer wall surface mixing area swirl hole 8, an inner wall surface main combustion hole 9, an inner wall surface main combustion area swirl hole 10, an inner wall surface middle hole 11, an inner wall surface middle area swirl hole 12, an inner wall surface mixing area 13, an inner wall surface mixing area swirl hole
In figure 2, 1-main combustion hole 2-main combustion area swirl hole 3-middle hole 4-middle area swirl hole 5-mixing area 6-mixing area swirl hole 7-main combustion hole and middle hole transition area 8-middle hole and mixing hole transition area
FIG. 3 1-hub 2-guide blade 3-outer ring
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
referring to fig. 1, 2 and 3, the present invention is a combustor with a swirl liner. FIG. 1 is a schematic view of a combustor with a swirl liner, FIG. 2 is a wall expansion view of the combustor with a swirl liner, and FIG. 3 is a schematic view of swirl holes.
In order to make the fuel oil fully heated and combusted in the flame tube of the combustion chamber, a swirl hole is added on the wall surface of the flame tube to form a novel swirl flame tube. The fuel is sprayed out through the central nozzle and is fully mixed with the rotating air entering from the front swirler 1 to form a return area of the main combustion area. However, the flame spraying range in the backflow zone is small, and the combustion range cannot reach the whole area in the main combustion zone, so that the problem of incomplete combustion inevitably exists, and therefore, swirl holes 3 and 9 are arranged in rows (in rows) at the main combustion holes on the inner wall surface and the outer wall surface of the main combustion zone, so that an auxiliary swirl zone is formed at the peripheral part of the main backflow zone, the outer ring part of the fuel in the swirl zone is fully mixed with the rotating airflow entering the main combustion zone, and the flame is also effectively combusted along with the swirl direction and the main combustion zone. Through rich oil combustion in the main combustion area, a large amount of intermediate products generated by combustion in the main combustion area and a small amount of unburned fuel exist in the air flow entering the middle area, and therefore swirl holes 5 and 11 are arranged in parallel (in an inserted manner) on the wall surface of the middle area, the purpose is to mix the fuel gas flow with the air flow entering the middle area to generate a new swirl area, and the mixed oil gas and unburned products in the middle area are ignited through upstream flame, so that the combustion effect is better and more sufficient compared with the original combustion effect in the middle area, complete combustion can be almost realized, and the generation of pollutants is reduced. A large amount of combustion products after being combusted in the middle area can not be combusted again, but still few intermediate products are extruded by the wall surface of the flame tube or have temperature limit, so that the intermediate products have to flow to the mixing area for reaction, and swirl holes 7 and 13 are added in the mixing area, on one hand, the swirl holes are fully mixed with hot gas flow, the temperature of the gas flow can be effectively reduced, the temperature of the gas in front of a turbine is prevented from exceeding the temperature limit, on the other hand, the combustible gas in the gas flow is further completely combusted, the condition that the gas flow at the outlet of the combustion chamber is free of pollutants is ensured, and the design of the combustion chamber is optimized. Can effectively improve the combustion efficiency, reduce the pollutant discharge and fully reduce the outlet temperature.
Claims (7)
1. A combustor with a swirl-type flame tube comprises a basic combustor structure (a shell, a swirler, a nozzle and the like) and a flame tube wall surface with swirl characteristics. The method is characterized in that: based on the different functions of the main combustion hole, the middle hole and the mixing hole of the flame tube of the original combustion chamber, the spiral-flow type airflow holes are added at three different positions on the wall surface of the flame tube and are in spaced fit with the main combustion hole, the middle hole and the mixing hole. The air flow entering from the main combustion hole is fully mixed with the fuel oil at the edge of the rotational flow area, then the fuel gas flow fully combusted in the main combustion area flows into the middle area, the fuel gas flow is further fully combusted with the rotational flow entering from the middle hole, the incomplete combustion amount is reduced, finally the generated incomplete combustion products and residual fuel oil pass through the mixing area, lean oxygen combustion is carried out on the incomplete combustion products and the rotational flow gas entering from the mixing hole by the tail part of the flame sprayed out from the main combustion area, and then the combustion products and air which does not participate in reaction are discharged out of the flame tube.
2. The combustor with swirl liner of claim 1, wherein: the swirl hole is similar to a swirler at the front end of the flame tube in shape, the swirl angle and swirl characteristics of the swirl hole are similar to those of the swirler, and the swirl hole plays a strengthening role rather than a restraining role in comparison with the swirl caused by the original main combustion area.
3. The combustor with swirl liner of claim 1, wherein: based on the position and size arrangement of the original flame tube main combustion holes, the designed swirl holes are about 5-7 mm in size and are designed between the main combustion holes, the spacing included angle of each main combustion area swirl hole is about 30 degrees, and the swirl holes are circumferentially arranged.
4. The combustor with swirl liner of claim 1, wherein: based on the position and size arrangement of the middle holes of the original flame tube, the swirl holes are designed to be about 4-6 mm in size and are designed to be about 30 degrees at intervals between the middle holes, and the swirl holes are circumferentially arranged.
5. The combustor with swirl liner of claim 1, wherein: based on the position and the size arrangement of the mixing holes of the original flame tube, the size of the designed swirl holes is about 3-5 mm, the swirl holes in each mixing area are designed between the mixing holes, the interval included angle between the swirl holes in each mixing area is about 30 degrees, and the swirl holes are circumferentially arranged.
6. The combustor with swirl liner of claim 1, wherein: the ranges of the swirl hole areas on the wall surfaces of the main combustion area, the middle area and the mixing area are determined according to the distribution range of the main combustion holes, the middle holes and the mixing holes on the wall surface of the original flame tube, and the number of rows of swirl holes is about 1-5 rows, 1-5 rows and 1-3 rows.
7. The combustor with swirl liner of claim 1, wherein: when the number of rows of swirl holes formed in the three areas on the wall surface of the flame tube exceeds one row, the swirl holes can be arranged in an inserting or sequential manner, and the sizes of the swirl holes in the distribution areas of the main combustion holes, the intermediate holes and the mixing holes are 1-10 times of the sizes of the swirl holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911074777.1A CN110925798A (en) | 2019-11-06 | 2019-11-06 | Combustion chamber with spiral-flow type flame tube |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911074777.1A CN110925798A (en) | 2019-11-06 | 2019-11-06 | Combustion chamber with spiral-flow type flame tube |
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| Publication Number | Publication Date |
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| CN110925798A true CN110925798A (en) | 2020-03-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911074777.1A Pending CN110925798A (en) | 2019-11-06 | 2019-11-06 | Combustion chamber with spiral-flow type flame tube |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112963864A (en) * | 2021-03-26 | 2021-06-15 | 西北工业大学 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
| CN114484500A (en) * | 2022-01-27 | 2022-05-13 | 北京航空航天大学 | Uniform flow sleeve and combustion chamber head structure |
| CN115355538A (en) * | 2022-08-15 | 2022-11-18 | 中国航发沈阳发动机研究所 | Hydrogen fuel non-premixed combustion chamber with variable mixing hole area |
| CN116045309A (en) * | 2023-01-29 | 2023-05-02 | 中国航发沈阳发动机研究所 | Radial swirl mixing reinforced flame tube |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201059603Y (en) * | 2007-07-04 | 2008-05-14 | 中国船舶重工集团公司第七O三研究所 | Long-term durability gas turbine flame barrel |
| CN101818910A (en) * | 2010-03-24 | 2010-09-01 | 北京航空航天大学 | Miniature gas turbine combustion chamber |
| CN202709181U (en) * | 2012-06-27 | 2013-01-30 | 中国航空动力机械研究所 | Flame tube of short-ring reflow combustion chamber |
| CN104197373A (en) * | 2014-08-26 | 2014-12-10 | 南京航空航天大学 | Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used |
| CN107525095A (en) * | 2017-07-24 | 2017-12-29 | 西北工业大学 | A kind of axially staged can burner of gas turbine |
| CN107796017A (en) * | 2017-11-23 | 2018-03-13 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
| CN108954391A (en) * | 2018-05-25 | 2018-12-07 | 中国航发商用航空发动机有限责任公司 | It is put out based on fuel-rich, temper, the low emission burner inner liner of lean-burn topologies |
| US20180356099A1 (en) * | 2017-06-09 | 2018-12-13 | General Electric Company | Bulk swirl rotating detonation propulsion system |
-
2019
- 2019-11-06 CN CN201911074777.1A patent/CN110925798A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201059603Y (en) * | 2007-07-04 | 2008-05-14 | 中国船舶重工集团公司第七O三研究所 | Long-term durability gas turbine flame barrel |
| CN101818910A (en) * | 2010-03-24 | 2010-09-01 | 北京航空航天大学 | Miniature gas turbine combustion chamber |
| CN202709181U (en) * | 2012-06-27 | 2013-01-30 | 中国航空动力机械研究所 | Flame tube of short-ring reflow combustion chamber |
| CN104197373A (en) * | 2014-08-26 | 2014-12-10 | 南京航空航天大学 | Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used |
| US20180356099A1 (en) * | 2017-06-09 | 2018-12-13 | General Electric Company | Bulk swirl rotating detonation propulsion system |
| CN107525095A (en) * | 2017-07-24 | 2017-12-29 | 西北工业大学 | A kind of axially staged can burner of gas turbine |
| CN107796017A (en) * | 2017-11-23 | 2018-03-13 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
| CN108954391A (en) * | 2018-05-25 | 2018-12-07 | 中国航发商用航空发动机有限责任公司 | It is put out based on fuel-rich, temper, the low emission burner inner liner of lean-burn topologies |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112963864A (en) * | 2021-03-26 | 2021-06-15 | 西北工业大学 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
| CN112963864B (en) * | 2021-03-26 | 2022-07-12 | 西北工业大学 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
| CN114484500A (en) * | 2022-01-27 | 2022-05-13 | 北京航空航天大学 | Uniform flow sleeve and combustion chamber head structure |
| CN114484500B (en) * | 2022-01-27 | 2022-12-20 | 北京航空航天大学 | Uniform flow sleeve and combustion chamber head structure |
| CN115355538A (en) * | 2022-08-15 | 2022-11-18 | 中国航发沈阳发动机研究所 | Hydrogen fuel non-premixed combustion chamber with variable mixing hole area |
| CN115355538B (en) * | 2022-08-15 | 2023-06-20 | 中国航发沈阳发动机研究所 | Hydrogen fuel non-premixed combustion chamber with variable mixing hole area |
| CN116045309A (en) * | 2023-01-29 | 2023-05-02 | 中国航发沈阳发动机研究所 | Radial swirl mixing reinforced flame tube |
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Application publication date: 20200327 |