CN102506446B - Fuel and air mixing device for low-pollution burning chamber of gas turbine - Google Patents
Fuel and air mixing device for low-pollution burning chamber of gas turbine Download PDFInfo
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- CN102506446B CN102506446B CN 201110310667 CN201110310667A CN102506446B CN 102506446 B CN102506446 B CN 102506446B CN 201110310667 CN201110310667 CN 201110310667 CN 201110310667 A CN201110310667 A CN 201110310667A CN 102506446 B CN102506446 B CN 102506446B
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Abstract
The invention discloses a fuel and air mixing device for a low-pollution burning chamber of a gas turbine. Fuel comprises a main burning level and a duty burning level; and air is supplied by a three-stage cyclone. The fuel and air mixing device is characterized in that the central duty level adopts diffusive burning, and the peripheral main burning level adopts premixing or semi-premixing burning. The central duty level consists of a centrifugal atomizing nozzle and first-stage cyclone air; and the rotating directions of the first-stage cyclone air and second-stage cyclone air are opposite. The fuel of the main burning level is supplied by a multipoint direct-injection type nozzle, the air is respectively supplied by the second-stage cyclone air and third-stage cyclone air, and the rotating directions of the second-stage cyclone air and third-stage cyclone air are opposite. The central duty level is used when in low working conditions such as starting and slowing and the like, so that the stable burning range can be widened, the burning efficiency can be improved and the emission of CO and UHC is reduced; and when in large working conditions, the duty level and the main burning level work simultaneously, the duty level provides a stable ignition source for the main burning level, a main burning area is in a lean-oil state, and the temperature is far lower than the temperatureof insulated flame, so that the emission of NOx under the large working conditions can be obviously reduced. The fuel and air mixing device can be used for an aerial gas turbine engine or an industrial gas turbine.
Description
Technical field
The present invention relates to a kind of fuel oil and air mixing device of low pollution combustor, relate in particular to a kind of fuel oil and air mixing device that utilizes the fuel oil hierarchy plan to realize the gas turbine low pollution emission.
Background technology
For the oil-fired gas turbine engine, fuel-oil atmozation and mixing have decisive influence to engine combustion performance, efficiency of combustion and pollutant emission, and therefore, fuel-oil atmozation research obtains paying attention to, and this has also promoted the development of fuel atomizer.
International Civil Aviation Organization is more and more stricter to the pollutant emission standard of aero-gas turbine, and particularly to the NOx emission requirement, combustion with reduced pollutants becomes the development trend of modern aeroengine combustion chamber.At present the combustion with reduced pollutants technology that proposes comprises that fuel-rich combustion-temper put out-poor oil firing (RQL), poor premixed combustion (LPP) and oil-poor direct injection burn (LDI).
Fig. 4 is the conventional flame combustion chamber barrel structure of gas turbine cutaway view, outer burner inner liner 4, interior burner inner liner 8 and head of combustion chamber have constituted the combustion zone, can be divided into primary zone, afterburning district and dilution zone in the burner inner liner, primary holes 5, afterburning hole 6 and blending hole 7 are arranged on the burner inner liner.Be in the rich oil state in the primary zone, the air and the high-temperature fuel gas that are entered by afterburning hole 6 further react, and improve efficiency of combustion, and the air that is entered by blending hole 7 further mixes adjusting combustor exit Temperature Distribution with high-temperature fuel gas.Head of combustion chamber is made up of pressure or air atomizer spray nozzle 1, one-level cyclone 2, second cyclone 3 and Venturi tube 9.The fuel atomization device that adopt conventional combustion chamber makes the combustion chamber adopt diffusion combustion when big operating mode, and the local equivalent proportion in combustion zone is near 1, the flame temperature height, and this moment, the discharging of NOx reached maximum.During low operating mode, the primary zone equivalent proportion is low, has that efficiency of combustion is low, CO and a high problem of UHC discharging.
Each big aero-engine GE of company, PW, R-R, Snecma have begun the combustion with reduced pollutants Study on Technology in the world.Recently, GE company has developed TAPS(Twin Annular Premixing Swirler based on oil-poor direct injection combustion technology (LDI) for commercial aviation fanjet Genx of new generation) low pollution combustor, NOx discharges than CAEP2(Committee on Aviation Environmental Protection) discharge standard reduced by 50%.For air and fuel oil well were pre-mixed before the combustion chamber, the multiple fuel nozzle of prewhirling has been researched and developed in the design of GE company, and at the different designs application of TAPS combustion chamber fuel nozzle multinomial United States Patent (USP): 6354072,6453660,6389815,6381964,0178732,6418726 and 6363726 etc., the main combustion stage of these patents is gas mixtures that fuel oil is ejected into the rear portion formation premix and pre-evaporation of main cyclone device, for making the blending of premix barrel outlet gas mixture even, the mixing that this hybrid mode is required and evaporation distance are longer, thereby increase length and the weight of combustion chamber, this radially outside fuel injection mode strikes the outer wall of main cyclone device at jet penetration Gao Shiyi simultaneously, influence atomizing effect, be attached to fuel oil on the wall and easily produce coking or make tempering takes place in the premix barrel, have a strong impact on engine combustion stability.R-R company is that Engine 3E core engine has been researched and developed multiple fractional combustion fuel nozzle based on LDI burning concept, pre-combustion grade adopts air atomizer spray nozzle or centrifugal atomizing nozzle, main combustion stage adopts pre-membrane type air atomizer spray nozzle, and the NOx discharging has reduced by 70% than CAEP2 standard on engine loopful testpieces.The BJ University of Aeronautics ﹠ Astronautics of China has also applied for heterogeneous patent aspect low pollution combustor, application number: 200810104686.3, the scheme that adopts of 200810105061.9,200810105062.3,200810104684.4 premix and pre-evaporation combustion chamber main combustion stage is that the inner or district of turning round sprays into the main combustion stage fuel oil in swirler blades, TAPS head of combustion chamber axial length than GE company has certain shortening, but still when existing the jet degree of depth big, the problem of the easy cyclone opposite side of impinging jet wall.Application number: 201010034141.7 and the low pollution combustor main combustion stage fuel oil of 201010101574.X band premix and pre-evaporation endless tube adopt tangential or axial fuel system, increased the complexity of head of combustion chamber fuel oil and air mixing device.
Summary of the invention
The technical problem to be solved in the present invention is:For overcoming the shortcoming and defect of above-mentioned prior art, the present invention adopts the scheme of fuel oil classification to realize that aero-engine can smooth combustion when different operating mode can effectively reduce the discharging of pollutant again, particularly reduces the NOx discharging under the big operating mode; Simultaneously, can control the fuel jet penetration depth, strengthen air to atomizing and the blending of fuel jet, effectively suppress coking and tempering problem that fuel jet bump swirler passages wall causes.
The technical solution adopted for the present invention to solve the technical problems:
According to an aspect of the present invention, a kind of fuel oil for the gas turbine low pollution combustor and air mixing device are provided, comprise main combustion stage and level on duty, it is characterized in that, level on duty comprises the centrifugal spraying nozzle, primary axis is to air cyclone and taper flameholder, wherein, the centrifugal spraying nozzle is positioned at the center of described device, primary axis is arranged at the outer ring of centrifugal spraying nozzle to air cyclone, the taper flameholder is positioned at the back of centrifugal spraying nozzle, level fuel oil on duty atomizes for the first time through the centrifugal spraying nozzle ejection, secondary-atomizing and blending are carried out in effect with the one-level rotational flow air then, and the flame stabilization of level on duty is realized by the recirculating zone of one-level rotational flow air formation and the taper flameholder of nozzle back; Main combustion stage is positioned at described on duty grade outer ring and coaxial with described level on duty, comprise premix barrel, the multiple spot simple nozzle, secondary axial air cyclone and three grades of radial air cyclones, wherein, the multiple spot simple nozzle is along on the outer wall that circumferentially is evenly arranged in three grades of radial air cyclones and be in the intersection porch of secondary axial air cyclone and three grades of radial air cyclones, secondary axial air cyclone and three grades of radial air cyclones form the axial rotational flow air of secondary and three grades of radial vortex air, and the rotation direction of secondary and three swirler air is opposite, secondary and three swirler air enter premix barrel, fuel is ejected in the premix barrel by the multiple spot simple nozzle, and fuel and air enter the combustion chamber forms homogeneous before in premix barrel mixture.
Preferably, described multiple spot simple nozzle diameter is 0.3～0.5mm, number is 8～24, fuel injected inwardly and behind the axial angle at 45 radially, fuel jet and two, three swirler air interact, jet path bending under the effect of aerodynamic force, and disturbance takes place in the jet surface, jet crushing forms little fragment, and fractionlet is out of shape under capillary effect and becomes droplet.
Preferably, described secondary axial air cyclone and three grades of radial air cyclones are respectively axial blade formula and radial blade formula, and the number of blade is 8～24.
Preferably, described taper flameholder is provided with three row's cooling holes, avoids flameholder to be burnt out by high-temperature fuel gas.
Preferably, the bottom of described taper flameholder is provided with air admission hole, and high-temperature flue gas that can inhibiting value class enters main combustion stage premix section, avoids the generation of tempering.
Preferably, primary axis adopts axial blade to air cyclone, is made up of 18 to 24 blades, and established angle is 30～60 degree.
Preferably, described device also comprises fuel pipe connecting hole and the oil trap on the outer wall that is arranged on three grades of radial air cyclones, and simple nozzle and oil trap communicate, and the fuel pipe connecting hole is circumferentially evenly being arranged 2.
According to a further aspect in the invention, a kind of burner inner liner for the gas turbine low pollution combustor is provided, described burner inner liner comprises outer burner inner liner, interior burner inner liner, and fuel oil of the present invention and air mixing device, be provided with blending hole on the wall of outer burner inner liner and interior burner inner liner, combustion air all enters from fuel oil and air mixing device, combustion air accounts for 80～90% of whole air capacities, 10～20% cooling air enters burner inner liner with further adjusting combustor exit Temperature Distribution from blending hole, makes Temperature Distribution satisfy the requirement of turbine inlet guide vane heat intensity.
The characteristics of main combustion stage of the present invention are that secondary is opposite with three swirler air rotation direction, at this moment can make the main combustion stage gas mixture that from premix barrel, comes out have weak eddy flow, in addition, this structural design can be strengthened the interaction of rotational flow air and fuel jet, shear action is strengthened, be conducive to atomizing and blending, in relatively shorter space, realize fuel oil and the even blending of air.
The fuel oil of low pollution combustor of the present invention and air mixing device are at engine and start and during low operating mode such as slow train, have only level work on duty; When load increases, taking off, cruising or climb mode, main combustion stage is started working, at this moment level on duty plays the effect of point of safes burning things which may cause a fire disaster to main combustion stage, homogeneous fuel oil and the air mixture equivalent proportion of coming out from premix barrel are 0.3～0.8, and the part high-temperature flue gas of main combustion stage gas mixture and level on duty mixes, and the main combustion stage gas mixture takes fire, can make the ignition temperature control of primary zone, combustion chamber below 1800K because main combustion stage is in oil-poor state, the NOx growing amount is few.The NOx growing amount depends primarily on ignition temperature and the time of staying, and exponentially rises with the increase of temperature.The generating rate of NOx and ignition temperature are with the variation of air-fuel ratio as shown in Figure 3, during near stoichiometric ratio, reaction temperature is the highest, in oil-poor and rich range, reaction temperature is lower, and the generating rate of NOx increases with the rising exponentially of temperature, therefore, oil-poor and fuel-rich combustion becomes the means that reduce the NOx discharging, and wherein poor oil firing is used widely in the becate shape combustion chamber of research and development recently.When the big operating mode of engine, the control primary zone is in oil-poor state, and at this moment equivalent proportion controls the primary zone temperature below 1800K in 0.3～0.8 scope, can guarantee that efficiency of combustion is high and pollutant (NOx, CO and UHC) discharging is low.
Principle of the present invention:Fuel oil and air mixing device adopt the mode of classification fuel feeding, when hanging down operating mode, level on duty works independently, district on duty adopts diffusion combustion, fuel oil by controlling district on duty and air equivalent ratio are near stoichiometric ratio, cooperate flame stabilizer to guarantee combustion stability, therefore the efficiency of combustion in the time of can widening the smooth combustion scope under the low operating mode and improve low operating mode effectively reduces the discharging of CO and UHC; During big operating mode, level on duty and main combustion stage are worked simultaneously, by the equivalent proportion in primary zone in the control combustion chamber in 0.3～0.8 scope, simultaneously, assurance primary zone fuel oil and air mix and make the primary zone is the diffusion combustion that there is not stoichiometric ratio in premixed combustion, make the primary zone ignition temperature be lower than 1800K, reach the purpose that reduces pollutant emission, particularly NOx discharging.At this moment, combustion air all enters from head of combustion chamber, combustion stability and efficiency of combustion when level on duty adopts diffusion combustion to be used for guaranteeing to hang down operating mode, when big operating mode, level on duty is as the incendiary source of main combustion stage, for the uniform main combustion stage gas mixture of blending provides high-temperature fuel gas, main combustion stage can fully be burnt and temperature can be too not high, main combustion stage is for reducing NOx discharging under the big operating mode.The main combustion stage fuel oil is ejected into the intersection porch of secondary axial swirler and three grades of radial swirlers, and secondary and three swirler device rotation direction can strengthen the shear action of rotational flow air and fuel jet on the contrary, atomizing particle size is diminished, be conducive in short distance, drop evaporation and fuel oil and air be mixed, for the primary zone provides uniform gas mixture, make the primary zone realize poor premix and pre-evaporation burning, therefore adiabatic flame temperature when guaranteeing the primary zone ignition temperature far below stoichiometric ratio can reduce the NOx discharging.Main combustion stage adopts multiple spot simple nozzle fuel injected in the main combustion stage rotational flow air, fuel jet radial velocity component direction is opposite with the centrifugal force direction, can suppress coking and the tempering problem that impinging jet causes to the opposite side wall when fuel jet speed increases.
The advantage that the present invention compared with prior art has:
(1) main combustion stage of the present invention realizes the good atomizing of fuel oil by secondary axial swirler, three grades of radial swirlers and multiple spot jet nozzle, secondary and three swirler device air rotation direction have been strengthened the interaction of air and drop on the contrary, atomizing particle size is diminished, be conducive in short geometry, realize fuel oil rapid evaporation and blending, make real poor premixed combustion, realization low pollution emission when guaranteeing efficiency of combustion realized in primary zone.
(2) main combustion stage is radially inwardly sprayed with axially at 45 backward, fuel jet and air shaft increase to relative velocity, strengthened the interaction of air and jet, be conducive to jet crushing and form the little drop of particle diameter, the jet radial direction is opposite with rotational flow air centrifugal force, the coking and the tempering problem that cause in the time of can effectively suppressing to clash into the opposite side wall when fuel jet speed increases.
(3) level nozzle on duty in the speed increase that jet expansion closes up and realizes air, is strengthened the interaction of air and primary atomization drop, to improve atomizing effect, combustion stability when rotational flow air and flameholder guarantee unskilled labourer's condition by the rotational flow air passage.
(4) the present invention adopts the fuel oil hierarchical concept, level on duty works independently when hanging down operating mode, widen the engine stable operation range, during big operating mode, level on duty and main combustion stage are worked simultaneously, combustion zone on duty provides stable incendiary source for the primary zone, and the primary zone is that poor premixed combustion can effectively reduce the pollutant emission under the big operating mode.
Description of drawings
Fig. 1 is the fuel oil for the gas turbine low pollution combustor of the present invention and air mixing device structure cutaway view;
Fig. 2 is gas turbine low pollution combustor burner inner liner structure cutaway view of the present invention;
Fig. 3 is that temperature and NOx generating rate and air-fuel ratio concern schematic diagram in the gas-turbine combustion chamber;
Fig. 4 is the conventional flame combustion chamber barrel structure of gas turbine cutaway view.
Wherein 1 is pressure or air atomizer spray nozzle, the 2nd, and one-level cyclone, the 3rd, second cyclone, the 4th, burner inner liner outside the conventional combustion chamber, the 5th, primary holes, the 6th, afterburning hole, the 7th, blending hole, the 8th, interior burner inner liner, the 9th, Venturi tube, the 10th, centrifugal spraying nozzle, the 11st, one-level cyclone inwall, the 12nd, one-level cyclone, the 13rd, one-level cyclone outer wall, the 14th, second cyclone, the 15th, second cyclone outer wall or three swirler device antetheca, the 16th, three swirler device, the 17th, main combustion stage simple nozzle, the 18th, fuel passage connecting hole, the 19th, the main combustion stage oil trap, the 20th, outer burner inner liner, 21 blending hole, the 22nd, combustor exit, the 23rd, interior burner inner liner, the 24th, district on duty, the 25th, primary zone, the 26th, classification fuel nozzle and burner inner liner connecting portion, the 27th, air admission hole, the 28th, flameholder, the 29th, cooling hole, the 30th, premix barrel.
The specific embodiment
For making purpose of the present invention, technical scheme and advantage clearer, below with reference to the accompanying drawing embodiment that develops simultaneously, inventing type is further described.
Fig. 1 is the fuel oil for the gas turbine low pollution combustor of the present invention and air mixing device structure cutaway view, adopt the scheme of classification fuel feeding, comprise main combustion stage and level on duty, level on duty comprises centrifugal spraying nozzle 10, primary axis is to air cyclone 12 and taper flameholder 28, wherein, centrifugal spraying nozzle 10 is positioned at the center of described device, primary axis is arranged at the outer ring of centrifugal spraying nozzle 10 to air cyclone 12, taper flameholder 28 is positioned at the back of centrifugal spraying nozzle 10, level fuel oil on duty sprays through centrifugal spraying nozzle 10 and atomizes for the first time, secondary-atomizing and blending are carried out in effect with the one-level rotational flow air then, and the flame stabilization of level on duty is realized by the recirculating zone of one-level rotational flow air formation and the taper flameholder 28 of nozzle back; Main combustion stage is positioned at described on duty grade outer ring and coaxial with described level on duty, comprise premix barrel 30, multiple spot simple nozzle 17, secondary axial air cyclone 14 and three grades of radial air cyclones 16, wherein, multiple spot simple nozzle 17 is along on the outer wall that circumferentially is evenly arranged in three grades of radial air cyclones 16 and be in the intersection porch of secondary axial air cyclone 14 and three grades of radial air cyclones 16, secondary axial air cyclone 14 and three grades of radial air cyclones 16 form the axial rotational flow air of secondary and three grades of radial vortex air, and the rotation direction of secondary and three swirler air is opposite, secondary and three swirler air enter premix barrel 30, fuel is ejected in the premix barrel 30 by multiple spot simple nozzle 17, and fuel and air enter the combustion chamber forms homogeneous before in premix barrel 30 mixture.
One-level cyclone 12 adopts axial blade, is made up of 18 to 24 blades, and established angle is 30～60 °.
In addition, the fuel oil direction that simple nozzle 17 sprays is opposite with the centrifugal force of rotational flow air, on the one hand, the relative velocity of air and fuel oil can increase, atomizing and blending have been improved, on the other hand, can suppress to strike cyclone opposite side wall when fuel jet speed is big, solve jet in the prior art and easily be rebuffed and cause the problem of coking in the premix barrel 30 or tempering.Realized even blending from fuel oil and air mixture that the main combustion stage cyclone comes out, mix with the high-temperature fuel gas of level on duty, realize poor premixed combustion, the primary zone ignition temperature is lower than 1800K, can fully burn and pollutant emission few, particularly NOx discharging is effectively controlled.Air admission hole 27 can inhibiting value class high-temperature flue gas enter main combustion stage premix section, avoid the generation of tempering.Therefore, this fuel oil and air mixing device can be realized widening the combustion stability under the low operating mode of gas-turbine combustion chamber and improve efficiency of combustion, the pollutant emission when reducing big operating mode, particularly NOx discharging.
Fig. 2 is gas turbine low pollution combustor burner inner liner structure cutaway view of the present invention, described burner inner liner comprises outer burner inner liner 20, interior burner inner liner 23, and fuel oil and air mixing device, the fuel oil here and air mixing device adopt structure as shown in Figure 1, be provided with blending hole 21 on the wall of outer burner inner liner 20 and interior burner inner liner 23, combustion air all enters from fuel oil and air mixing device, combustion air accounts for 80～90% of whole air capacities, 10～20% cooling air enters burner inner liner with further adjusting combustor exit Temperature Distribution from blending hole 21, makes Temperature Distribution satisfy the requirement of turbine inlet guide vane heat intensity.
The above only is preferred embodiment of the present invention, and is in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of making, is equal to replacement, improvement etc., all should be included within the scope of the present invention.
Claims (10)
1. fuel oil and air mixing device that is used for the gas turbine low pollution combustor, comprise main combustion stage and level on duty, it is characterized in that, level on duty comprises centrifugal spraying nozzle (10), primary axis is to air cyclone (12) and taper flameholder (28), wherein, centrifugal spraying nozzle (10) is positioned at the center of described device, primary axis is arranged at the outer ring of centrifugal spraying nozzle (10) to air cyclone (12), taper flameholder (28) is positioned at the back of centrifugal spraying nozzle (10), level fuel oil on duty sprays through centrifugal spraying nozzle (10) and atomizes for the first time, secondary-atomizing and blending are carried out in effect with the one-level rotational flow air then, and the flame stabilization of level on duty is realized by the recirculating zone of one-level rotational flow air formation and the taper flameholder (28) of nozzle back; Main combustion stage is positioned at described on duty grade outer ring and coaxial with described level on duty, comprise premix barrel (30), multiple spot simple nozzle (17), secondary axial air cyclone (14) and three grades of radial air cyclones (16), wherein, multiple spot simple nozzle (17) is along on the outer wall that circumferentially is evenly arranged in three grades of radial air cyclones (16) and be in the intersection porch of secondary axial air cyclone (14) and three grades of radial air cyclones (16), secondary axial air cyclone (14) and three grades of radial air cyclones (16) form the axial rotational flow air of secondary and three grades of radial vortex air, and the rotation direction of secondary and three swirler air is opposite, secondary and three swirler air enter premix barrel (30), fuel is ejected in the premix barrel (30) by multiple spot simple nozzle (17), and fuel and air enter the combustion chamber forms homogeneous before in premix barrel (30) mixture.
2. fuel oil and air mixing device for the gas turbine low pollution combustor according to claim 1, it is characterized in that, described device also comprises fuel pipe connecting hole (18) and the oil trap (19) on the outer wall that is arranged on three grades of radial air cyclones (16), described simple nozzle (17) and oil trap (19) communicate, and fuel pipe connecting hole (18) is circumferentially evenly arranged 2 at three grades of radial air cyclones (16).
3. fuel oil and air mixing device for the gas turbine low pollution combustor according to claim 1 is characterized in that, described taper flameholder (28) is provided with three row's cooling holes (29), in order to cool off flameholder (28).
4. fuel oil and air mixing device for the gas turbine low pollution combustor according to claim 1, it is characterized in that, the bottom of described taper flameholder (28) is provided with air admission hole (27), high-temperature flue gas in order to inhibiting value class enters main combustion stage premix section, avoids the generation of tempering.
5. according to claim 1 to 4 each described fuel oil and air mixing device for the gas turbine low pollution combustor, it is characterized in that, described multiple spot simple nozzle (17) diameter is 0.3～0.5mm, and number is 8～24, radially fuel injected inwardly and behind the axial angle at 45.
6. according to claim 1 to 4 each described fuel oil and air mixing device for the gas turbine low pollution combustor, it is characterized in that, described secondary axial air cyclone (14) and three grades of radial air cyclones (16) are respectively axial--flow blading and radial vane, and the number of blade is 8～24.
7. according to claim 1 to 4 each described fuel oil and air mixing device for the gas turbine low pollution combustor, it is characterized in that, described primary axis adopts axial blade to air cyclone (12), is made up of 18 to 24 blades, and established angle is 30～60 °.
8. according to claim 1 to 4 each described fuel oil and air mixing device for the gas turbine low pollution combustor, it is characterized in that described gas turbine is aero-gas turbine engine or industry gas turbine.
9. according to claim 1 to 4 each described fuel oil and air mixing device for the gas turbine low pollution combustor, it is characterized in that homogeneous fuel oil and the air mixture equivalent proportion of coming out from described premix barrel (30) are 0.3～0.8.
10. burner inner liner that is used for the gas turbine low pollution combustor, comprise outer burner inner liner (20), interior burner inner liner (23), and claim 1 to 9 each described fuel oil and air mixing device for the gas turbine low pollution combustor, be provided with blending hole (21) on the wall of outer burner inner liner (20) and interior burner inner liner (23), combustion air all enters from fuel oil and air mixing device, combustion air accounts for 80～90% of whole air capacities, 10～20% cooling air enters burner inner liner with further adjusting combustor exit (22) Temperature Distribution from blending hole (21), makes Temperature Distribution satisfy the requirement of turbine inlet guide vane heat intensity.
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| CN202303463U (en) * | 2011-10-13 | 2012-07-04 | 中国科学院工程热物理研究所 | Fuel oil and air mixing device for low-pollution combustion chamber |
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| JPH0668374B2 (en) * | 1987-07-28 | 1994-08-31 | 石川島播磨重工業株式会社 | Fuel injector |
| JPH1033421A (en) * | 1996-07-25 | 1998-02-10 | Tec Corp | Nozzle structure for vacuum cleaner |
| US6862889B2 (en) * | 2002-12-03 | 2005-03-08 | General Electric Company | Method and apparatus to decrease combustor emissions |
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| GB2134243A (en) * | 1983-01-27 | 1984-08-08 | Rolls Royce | Combustion equipment for a gas turbine engine |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| CN102200291A (en) * | 2011-03-29 | 2011-09-28 | 北京航空航天大学 | Pneumatic primary level graded low-pollution combustion chamber |
| CN202303463U (en) * | 2011-10-13 | 2012-07-04 | 中国科学院工程热物理研究所 | Fuel oil and air mixing device for low-pollution combustion chamber |
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