CN101782231B - Minitype gas turbine burner with secondary air inlet structure - Google Patents
Minitype gas turbine burner with secondary air inlet structure Download PDFInfo
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- CN101782231B CN101782231B CN2010101313147A CN201010131314A CN101782231B CN 101782231 B CN101782231 B CN 101782231B CN 2010101313147 A CN2010101313147 A CN 2010101313147A CN 201010131314 A CN201010131314 A CN 201010131314A CN 101782231 B CN101782231 B CN 101782231B
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Abstract
The invention discloses a minitype gas turbine burner with a secondary air inlet structure, comprising a combustion chamber, a burner outer shell which is surrounded outside the combustion chamber and a gas channel which is communicated with the inner part of the combustion chamber, the wall surface of the combustion chamber comprises a secondary air multi-hole downside wall surface, a combustion chamber lower wall surface, and a gas mixture multi-hole upper wall surface and a gas mixture multi-hole upside wall surface which are connected with each other, a gas mixture distribution chamber is formed among the gas mixture multi-hole upper wall surface, the gas mixture multi-hole upside wall surface and the burner outer shell and is communicated with a fuel/air gas mixture inlet; a secondary air distribution chamber is formed among the secondary air multi-hole downside wall surface, the combustion chamber lower wall surface and the burner outer shell and is communicated with a secondary air inlet; the gas mixture distribution chamber and the secondary air distribution chamber are isolated by the side wall of the burner outer shell, thereby realizing the purposes of adjusting the temperature and the flow rate of working gas and providing the optimal working temperature for a gas turbine blade.
Description
Technical field
The present invention relates to microkinetic system, especially a kind of minitype gas turbine burner with secondary wind structure based on hydrocarbon fuel combustion.
Background technology
Microkinetic system based on hydrocarbon fuel combustion has the energy density height, lasting, stable output can be provided, and continuous can conveniently wait advantage, several watts to tens watts power mechanical or electrical energy outputs can be provided, can be widely used in military affairs, medical treatment, scientific research and the daily life electronic product, have a good application prospect.
The minitype gas turbine system is numerous in one of burning microkinetic system, trace carbon hydrogen fuel (hydrogen or hydrocarbon) and oxidant (being generally air) are in miniature combustion chamber internal combustion, the high-temperature flue gas that produces promotes little turbine rotation acting, realizes power output.When little turbine connects microgenerator, can realize the output of electric energy.Micro-burner is the critical component of minitype gas turbine system, because the high surface area/volume ratio of burner under the minute yardstick, the micro-burner heat loss rate causes the micro-burner job insecurity and the thermal efficiency low usually up to more than 50%, thereby has seriously restricted little gas turbine system performance.In addition, be subjected to the little restriction in micro-burner internal combustion space, it is difficult that the efficient burning process organization in the combustion chamber also becomes.For the heat loss that reduces micro-burner with improve combustion stability, existing little gas burner has adopted air inlet backheat passage technology, be that the cold premixing air-flow flows into the combustion chamber again behind the backheat passage, can the recovery section heat, thus the Flammability limits scope of system's heat loss and extension micro-burner reduced.But, adopted the total heat loss rate of little gas turbine burner of backheat passage technology still to be higher than 40%, meanwhile, because the heat recovery effect of backheat passage, the fuel/oxidant gaseous mixture has been realized partly super enthalpy burning in the combustion chamber, and flame temperature rises, and causes burner wall surface temperature and exhaust temperature to raise simultaneously, easily combustion chamber internal face and turbine blade are formed thermal ablation destruction, seriously restrict the job security of minitype gas turbine system.Therefore, it is limited to adopt the mode of heat-insulation and heat-preservation to improve the minitype gas turbine burner impact of performance merely, need solve that heat loss is too high from the rationalization of combustion process, problem such as poor combustion stability and security of system are low.
Utilize porous media material as combustion chamber wall surface and air inlet, when passing the porous media wall, premix gas enters the combustion chamber, can form stable flame front on porous media wall surface, flame and wall are separated by one deck unreacted fuel gas film, can avoid thermal-flame to contact fully with the direct of wall, the chamber wall surface temperature will be lower than several Baidu of flame temperature, thereby guarantee that wall is not ablated.Meanwhile, the good heat exchange effect of cold premixing air-flow when porous wall makes the porous wall temperature further reduce and the efficient preheating of premix gas quilt.Therefore, can effectively reclaim the outside heat radiation of combustion chamber wall surface, also realize super enthalpy burning, make that Flammability limits obtains extending, the final heat loss that effectively reduces micro-burner.But, when combustion chamber wall surface all adopts the porous media wall to be the import of fuel/air premix gas, part of fuel can directly enter exhaust gases passes have neither part nor lot in the burning and overflow, cause the efficiency of combustion of micro-burner to reduce.On the other hand, though porous media wall surface has formed the generation that big flame front has been avoided localized hyperthermia in the combustion chamber, but, the efficient preheating that cold premixing gas enters before the combustion chamber has caused super enthalpy burning, so the flue-gas temperature that produces in this burner is still than higher, particularly under high fuel equivalence ratio and fuel flow rate situation, flue-gas temperature can be higher than the safe working temperature of minitype gas turbine blade.Therefore, need further control and improve the burner combustion process regulates and improves the burner performance.
Summary of the invention
The objective of the invention is to overcome the technical problem that prior art burner efficiency of combustion in combustion process is low, combustion stability is not enough, provide a kind of and can effectively improve the minitype gas turbine burner that the burner performance was regulated and improved to the burner combustion process with secondary air inlet structure.
For realizing above purpose, the present invention has taked following technical scheme: a kind of minitype gas turbine burner of secondary air inlet structure, include the combustion chamber and be enclosed in burner housing outside the combustion chamber, with the exhaust gases passes that communicates in the combustion chamber, the wall of described combustion chamber comprises auxiliary air porous downside wall, the combustion chamber lower wall surface, interconnective gaseous mixture porous upper wall surface and gaseous mixture porous upside wall, between described gaseous mixture porous upper wall surface and gaseous mixture porous upside wall and burner housing, be formed with the gaseous mixture distribution cavity, be communicated with the fuel/air mixture mixed gas inlet with this gaseous mixture distribution cavity; Between described auxiliary air porous downside wall and combustion chamber lower wall surface and described burner housing, be formed with the auxiliary air distribution cavity, be communicated with the auxiliary air air inlet with this auxiliary air distribution cavity; Isolated by the sidewall of described burner housing between described gaseous mixture distribution cavity and the auxiliary air distribution cavity.
The micro combustor wall is made up of three blocks of sintered porous plates in side (being divided into the upper and lower part) and upper surface and combustion chamber lower wall surface, the porous plate that the fuel/air mixture gaseous mixture passes gaseous mixture porous upper wall surface and gaseous mixture porous upper wall surface part evenly enters the combustion chamber, forms the flame of pressing close to the porous wall surface.This flame organizational form has the advantage that keeps low chamber wall surface temperature and low-heat loss.
The auxiliary air air inlet is the latter half of micro combustor porous media side wall surface, and the size of secondary wind can be adjusted, and realizes by changing the shared whole combustion chamber side wall height certain proportion of auxiliary air porous downside wall.Auxiliary air passes the exhaust gases passes that this porous media wall enters the combustor exit place, because the formation of burning interior flame is stabilized in the porous media wall surface that the fuel/air mixture gaseous mixture is advanced in side wall surface top and upper surface, therefore, the adding of secondary cold air is little near the flow field influence flame front, thereby can not cause big influence to the stability of burning interior flame.
The secondary wind inlet that enters from auxiliary air porous downside wall is arranged in combustor exit, substituted the fuel/air mixture gaseous mixture that this part wall is flowed into, avoided this position directly to overflow as the part of fuel that combi inlet port causes, the imperfect combustion degree be can reduce, thereby the efficiency of combustion and the thermal efficiency improved.Auxiliary air spray into directly cooling down high-temperature flue gas, therefore, under the flame flameholding operating mode of porous media surface, promptly under the immovable situation of fuel/air premix gas, only need to regulate the auxiliary air amount and control flue-gas temperature and flow, help keeping efficient, stable combustion process.Simultaneously, an amount of cold air adds can effectively control the flue-gas temperature of supplying with the combustion gas turbine acting, and more high temperature acting flue gas also can be provided, and is convenient to optimize the turbine operating temperature range and improves system dynamic output.
Upper end, axis at described burner housing is provided with the tail gas outlet, and described exhaust gases passes is communicated with this tail gas outlet.
Described auxiliary air porous downside wall, gaseous mixture porous upper wall surface and gaseous mixture porous upside wall are made by porous media material of the same race.
Described auxiliary air porous downside wall, gaseous mixture porous upper wall surface and gaseous mixture porous upside wall are made by different porous media materials.
The porous media material of described auxiliary air porous downside wall and gaseous mixture porous upside wall is formed by the copper powders may sintering.
The porous media material of described gaseous mixture porous upper wall surface is formed by the powder of stainless steel sintering.
Be provided with the turbine base that communicates with exhaust gases passes in the bottom of described burner housing axis, described burner housing is provided with heat insulation axle sleeve with the part that the tail gas outlet contacts with the turbine base.In burner high temperature parts (as the tail gas outlet) and burner housing contact site, heat insulation axle sleeve realizes further reducing the temperature and the burner heat loss of wall to reduce the solid interior heat conduction of burner wall.
The present invention compared with prior art, have following advantage: burner structure of the present invention is the short cylindrical type, combustion chamber wall surface adopts the porous media wall, cylinder porous media wall the latter half (near combustor exit place side) enters the mouth as secondary wind (cold air), secondary wind directly sprays into the high-temperature flue gas passage at combustor exit place, when cold air mixes with high-temperature flue gas, realize regulating the purpose of acting flue-gas temperature and flow, the optimum operating temperature of combustion gas turbine blade is provided.
Description of drawings
Fig. 1 is a burner structure cutaway view of the present invention;
Description of reference numerals: 1-fuel/air mixture mixed gas inlet, 2-burner housing, 3-gaseous mixture distribution cavity, 4-gaseous mixture porous upper wall surface, 5-flame front, 6-combustion chamber, 7-auxiliary air porous downside wall, 8-auxiliary air distribution cavity, 9-auxiliary air air inlet, the 10-exhaust gases passes, 11-turbine base, the heat insulation axle sleeve of 12-, 13-combustion chamber lower wall surface, the 14-ignition, 15-tail gas outlet, 16-gaseous mixture porous upside wall.
The specific embodiment
Below in conjunction with the drawings and specific embodiments content of the present invention is described in further details.
Embodiment:
See also shown in Figure 1, a kind of minitype gas turbine burner of secondary air inlet structure, the short cylindrical type burner that this burner integral body is made by temperature-resistant materials such as metals, include combustion chamber 6 and be enclosed in combustion chamber 6 burner housing 2 outward, with the exhaust gases passes 10 that communicates in the combustion chamber 6, the wall of combustion chamber 6 comprises auxiliary air porous downside wall 7, combustion chamber lower wall surface 13, interconnective gaseous mixture porous upper wall surface 4 and gaseous mixture porous upside wall 16, between gaseous mixture porous upper wall surface 4 and gaseous mixture porous upside wall 16 and burner housing 2, be formed with gaseous mixture distribution cavity 3, fuel/air mixture can evenly distribute, be communicated with fuel/air mixture mixed gas inlet 1 with this gaseous mixture distribution cavity 3, fuel/air mixture enters into combustion chamber 6 from gaseous mixture porous upper wall surface 4 and gaseous mixture porous upside wall 16; Between auxiliary air porous downside wall 7 and combustion chamber lower wall surface 13 and described burner housing 2, be formed with auxiliary air distribution cavity 8, the auxiliary air that can evenly distribute, be communicated with this auxiliary air distribution cavity 8 and with fuel/air mixture mixed gas inlet 1 symmetrically arranged auxiliary air air inlet 9; The sidewall of burned device shell 2 is isolated between gaseous mixture distribution cavity 3 and the auxiliary air distribution cavity 8, makes fuel/air mixture and secondary wind be spaced in passage, prevents that two strands of gases from mixing mutually.
Also including an end is inserted in the combustion chamber 6, the other end stretches out the ignition 14 of burner housing 2, fuel/air mixture is lighted by ignition 14 in combustion chamber 6, the flame 5 of its formation is pressed close to gaseous mixture porous upper wall surface 4 and gaseous mixture porous upside wall 16, the flame front size is long-pending near air inlet porous wall surface sections, big flame front can form low uniform flame surface temperature, and flame front can be away from porous wall, and the assurance combustion reaction is finished near wall.
After the secondary cold air enters into auxiliary air distribution cavity 8 by auxiliary air air inlet 9, enter in the combustion chamber 6 from auxiliary air porous downside wall 7 again, mix the turbine blade that flows on the turbine base 11 by exhaust gases passes 10 with high-temperature flue gas and do work; The secondary cold air that sprays into is away from flame front, and is little to the combustion reaction influence, and entering of cold air can effectively reduce flue-gas temperature and increase the acting flue gas flow, improves the turbine system effectiveness.Flue gas after the acting is discharged by tail gas outlet 15.For further reducing the micro-burner heat loss, periphery, axis, burner housing 2 at burner are provided with heat insulation axle sleeve 12 with tail gas outlet 15 and turbine base 11 contacted positions, can effectively reduce the heat conduction in the burner wall, further reduce wall surface temperature and reduce heat loss.
Present embodiment burner external diameter is 34.5mm, height is 14.5mm, combustion chamber 6 internal diameters are 25.5mm, high 4.2mm, burner is by the stainless steel manufacturing is arranged, the porous media material of auxiliary air porous downside wall 7 and gaseous mixture porous upside wall 16 is formed by the copper powders may sintering, and the porous media material of gaseous mixture porous upper wall surface 4 is formed by the powder of stainless steel sintering.
In the experiment condition, adopt methane/air to organize premixed combustion, the auxiliary air amount is 1/3 o'clock of total air, and smooth combustion equivalent proportion scope is between 0.55～1.0; During equivalent proportion 0.6, high heat load surpasses 150W; Flame temperature is 1100 ℃, and combustion chamber 6 wall surface temperatures are lower than 350 ℃, burner heat loss rate 20～30% has the conventional wall micro-burner (heat loss is 40～80%) of backheat passage far below same size, and combustor exit high temperature acting flue-gas temperature is 400～650 ℃.Secondary air flow can total air 0～1/3 between regulate, and combustion process stability is not had a negative impact, flue-gas temperature and burner wall surface temperature reduce with the increase of air mass flow.
Above-listed detailed description is at the specifying of possible embodiments of the present invention, and this embodiment is not in order to limiting claim of the present invention, and the equivalence that all the present invention of disengaging do is implemented or change, all should be contained in the claim of this case.
Claims (8)
1. the minitype gas turbine burner of a secondary air inlet structure, include combustion chamber (6) and be enclosed in the outer burner housing (2) in combustion chamber (6), with the exhaust gases passes (10) that communicates in combustion chamber (6), it is characterized in that: the wall of described combustion chamber (6) comprises auxiliary air porous downside wall (7), combustion chamber lower wall surface (13), interconnective gaseous mixture porous upper wall surface (4) and gaseous mixture porous upside wall (16), between described gaseous mixture porous upper wall surface (4) and gaseous mixture porous upside wall (16) and burner housing (2), be formed with gaseous mixture distribution cavity (3), be communicated with fuel/air mixture mixed gas inlet (1) with this gaseous mixture distribution cavity (3); Between described auxiliary air porous downside wall (7) and combustion chamber lower wall surface (13) and described burner housing (2), be formed with auxiliary air distribution cavity (8), be communicated with auxiliary air air inlet (9) with this auxiliary air distribution cavity (8); Isolated by the sidewall of described burner housing (2) between described gaseous mixture distribution cavity (3) and the auxiliary air distribution cavity (8).
2. the minitype gas turbine burner of secondary air inlet structure as claimed in claim 1 is characterized in that: the upper end, axis at described burner housing (2) is provided with tail gas outlet (15), and described exhaust gases passes (10) is communicated with this tail gas outlet (15).
3. the minitype gas turbine burner of secondary air inlet structure as claimed in claim 1, it is characterized in that: described auxiliary air porous downside wall (7), gaseous mixture porous upper wall surface (4) and gaseous mixture porous upside wall (16) are made by porous media material of the same race.
4. the minitype gas turbine burner of secondary air inlet structure as claimed in claim 1, it is characterized in that: described auxiliary air porous downside wall (7), gaseous mixture porous upper wall surface (4) and gaseous mixture porous upside wall (16) are made by different porous media materials.
5. as the minitype gas turbine burner of claim 3 or 4 described secondary air inlet structures, it is characterized in that: the porous media material of described auxiliary air porous downside wall (7) and gaseous mixture porous upside wall (16) is formed by the copper powders may sintering.
6. as the minitype gas turbine burner of claim 3 or 4 described secondary air inlet structures, it is characterized in that: the porous media material of described gaseous mixture porous upper wall surface (4) is formed by the powder of stainless steel sintering.
7. the minitype gas turbine burner of secondary air inlet structure as claimed in claim 2, it is characterized in that: the bottom in described burner housing (2) axis is provided with turbine base (11), exhaust gases passes (10) is formed between combustion chamber lower wall surface (13) and the turbine base (11), and described burner housing (2) is provided with heat insulation axle sleeve (12) with the part that tail gas outlet (15) contacts with turbine base (11).
8. the minitype gas turbine burner of secondary air inlet structure as claimed in claim 1, it is characterized in that: also include an end and be inserted in the described combustion chamber (6), the other end stretches out the ignition (14) of burner housing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101313147A CN101782231B (en) | 2010-03-22 | 2010-03-22 | Minitype gas turbine burner with secondary air inlet structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101313147A CN101782231B (en) | 2010-03-22 | 2010-03-22 | Minitype gas turbine burner with secondary air inlet structure |
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| CN101782231A CN101782231A (en) | 2010-07-21 |
| CN101782231B true CN101782231B (en) | 2011-06-08 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102174338B (en) * | 2010-12-31 | 2013-08-07 | 中国航天科技集团公司第六研究院第十一研究所 | Low-flow, high-mixing ratio and stepless regulation gas-liquid mixing gas generator |
| CN102135272A (en) * | 2011-03-09 | 2011-07-27 | 华中科技大学 | Micro diffusion combustor |
| CN103836629A (en) * | 2012-11-26 | 2014-06-04 | 江苏华东炉业有限公司 | Energy saving burner |
| CN103743571B (en) * | 2013-12-16 | 2016-01-13 | 中国科学院力学研究所 | For the air heating apparatus of long-time supersonic combustion |
| CN105066174A (en) * | 2015-07-24 | 2015-11-18 | 北京航空航天大学 | Super-micro turbojet engine combustor with inverted-L-shaped head |
| CN107702146B (en) * | 2017-10-12 | 2019-10-18 | 四川航天中天动力装备有限责任公司 | For the indoor porous evaporator medium pipe of micro gas turbine engine burning |
| CN113882949B (en) * | 2021-09-29 | 2023-11-10 | 中国人民解放军战略支援部队航天工程大学 | Powder rotary detonation space engine |
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