CN104949152A - LNG and aviation kerosene dual fuel combustor of aero-gas turbine - Google Patents
LNG and aviation kerosene dual fuel combustor of aero-gas turbine Download PDFInfo
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- CN104949152A CN104949152A CN201510270803.3A CN201510270803A CN104949152A CN 104949152 A CN104949152 A CN 104949152A CN 201510270803 A CN201510270803 A CN 201510270803A CN 104949152 A CN104949152 A CN 104949152A
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Abstract
An LNG and aviation kerosene dual fuel combustor of an aero-gas turbine comprises a combustion area which comprises a precombustion area and a main combustion area, the outer boundary of the combustion area is provided with an inner flame tube wall, the inner boundary of the combustion area is provided with an outer flame tube wall, the front of the combustion area is provided with a combustor head, and the combustor head is connected with the inner flame tube wall through a head end wall. The LNG and aviation kerosene dual fuel combustor of the aero-gas turbine has the advantages that a center staged combustion concept is adopted, two kinds of fuel can be applied simultaneously, a precombustion level which adopts gas fuel provides a stable ignition source and reduces pollutant emissions, low pollution combustion is achieved through a main combustion level, pollutant emission is reduced, and the stability of the aero-gas turbine combustor can be guaranteed simultaneously; a double-ring cavity combustor structure is adopted, air used for combustion is all fed from the head, a flame tube is only provided with a dilution hole and a necessary cooling hole, the modularization feature is achieved, the combustion structure is simplified, and a premixed pre-evaporation loop structure is simpler and easy to process.
Description
Technical field
The present invention relates to a kind of aero-gas turbine combustion chamber, particularly relate to and can use LNG/ aviation kerosine dual-fuel aero-gas turbine combustion chamber.
Background technology
Along with developing rapidly of global military aviation and Civil Aviation Industry, the beginning of this century, America and Europe waited national consciousness to self undue dependence to petroleum base aviation fuel, left hidden trouble to national defence and economic security.Simultaneously, Global climate change also proposes new requirement to air-transport industry, in order to meet, future aircraft aero-gas turbine is more economical, the requirement of more environmental protection, the problem of environmental pollution that Ge great aircraft industry big country causes for aero-gas turbine, conducts extensive research the control of pollutant as emphasis problem in aero-gas turbine research.Reach the emission reduction targets that International Air Transport Association proposes, under existing fuel oil mechanism, only rely on airborne vehicle lightweight and high-efficiency environment friendly aviation power technology to be inadequate, also need to rely on the aviation alternative fuel of environmental protection more.In following 30 ~ 50 years, aviation alternative fuel is by based on " instant " fuel that can not have an impact to aircraft and engine hardware.
Liquefied natural gas (LNG) is by after natural gas via super-dry depickling process, is liquefied as liquid a kind of liquid fuel at low temperatures, and main component is the cryogenic liquid of methane (more than 90%), ethane, nitrogen and a small amount of C3 ~ C5 alkane.Liquidus density is 0.42 ~ 0.46t/m
3(3# density of aviation kerosene is 0.78t/m
3), liquid calorific value 50MJ/kg (aviation kerosine is about 42.5MJ/kg).Colourless, tasteless, the nontoxic and non-corrosiveness of LNG, its volume weight is only about 45% of consubstantiality ponding.Compared with aviation kerosine, LNG has that density is low, cost is low, high (in LNG, hydrogen-carbon ratio is 4 to calorific value, Jet A aviation kerosine hydrogen-carbon ratio is that 1.8, LNG is higher by 16% than Jet A aviation kerosine calorific value) feature, the pollutant (CO lower than aviation kerosine produced after simultaneously LNG burning
2low by 20%).Development LNG engine technology, making LNG become the alternative fuel of aviation kerosine by being the effective way solving aviation kerosine exhaustion and environmental problem, having vital effect for civil aviation and science and techniques of defence.
The research taking LNG as the aircraft fuel system of fuel has been carried out for realizing the application GE company of LNG on aero-gas turbine, and applied for multinomial international monopoly: WO2012/173651A1, WO2014/105328A1, these patents as needing during aero-gas turbine fuel to control the temperature of fuel system, LNG and cooperation control between LNG and aviation kerosine is studied, but do not relate to LNG and how aviation kerosine effectively burns in combustion chamber mainly for LNG.
For reducing the discharge of aero-gas turbine burning pollutant, GE company proposes the dicyclo premixed swirl combustion chamber (TAPS) of center classification, and is applied in the GEnx engine of Boeing 787 aircraft for TAPS by I.GE company have developed the fuel nozzle of multiple employing premix and pre-evaporation mode, and applied for multinomial United States Patent (USP): 0178732,6354072,6363726,6381964,6389815,6418726 and 6453660 etc., these patents are all the low emissions for realizing combustion chamber when taking aviation kerosine as fuel by reducing primary zone oil-gas ratio, do not relate to dual-fuel and use.
Summary of the invention
In order to realize the application of LNG on aero-gas turbine, the invention provides one and can apply LNG and aviation kerosine dual-fuel center classification low emission combustor, this technical scheme while guarantee aero-gas turbine uses aviation kerosine, can adopt LNG and the stable operation of aviation kerosine dual-fuel; In addition, this technical scheme can reduce aero-gas turbine fuel system weight, extends aircraft course continuation mileage, reduce aero-gas turbine exhaust emissions.
The present invention is achieved by the following technical solutions: a kind of aero-gas turbine LNG/ aviation kerosine dual-fuel combustor, comprise combustion zone, combustion zone comprises preignition zone and primary zone, the external boundary of combustion zone is provided with flame barrel, inner boundary is provided with outer flame tube wall, outer flame tube wall arranged outside has outer casing, flame barrel arranged outside has interior casing, blending hole in flame tube wall surface is installed, outer burner inner liner wall installs outer blending hole, inside and outside burner inner liner wall is provided with Cooling Holes, front portion, combustion zone is provided with head of combustion chamber, head of combustion chamber is connected with flame tube wall surface by head end wall.
Described outer flame tube wall and flame barrel are annular, and in annular radial distribution between casing and outer casing.
Described head of combustion chamber comprises pre-combustion grade and main combustion stage, and pre-combustion grade and main combustion stage are arranged together according to concentric mode, and pre-combustion grade is at center, and main combustion stage is arranged in pre-combustion grade periphery.Head of combustion chamber is evenly arranged along aero-gas turbine LNG/ aviation kerosine dual-fuel combustor circumference, number 10 ~ 60, its air capacity accounts for 20% ~ 80% of combustion chamber total air, and wherein main combustion stage accounts for 60% ~ 90% of head air capacity, and pre-combustion grade accounts for 10% ~ 40% of head air capacity.
Described pre-combustion grade, comprise central nozzle, one-level cyclone, second cyclone, LNG petroleum pipeline and Venturi tube, LNG petroleum pipeline front end is provided with central nozzle, is disposed with one-level cyclone and second cyclone outside central nozzle, and on central nozzle, cover is embedded with Venturi tube.
Described central nozzle adopts simple nozzle.
Described main combustion stage, comprise annular oil trap, three swirler device, spray-hole, kerosene through petroleum pipeline and main mixed zone, be uniformly distributed circumferentially spray-hole outside annular oil trap, oil groove upper end is provided with kerosene through petroleum pipeline, and spray-hole front end is provided with main mixed zone and three swirler device.
Circumferentially being evenly arranged 8 ~ 24 diameters outside described annular oil trap is 0.3 ~ 0.5mm spray-hole.
Beneficial effect of the present invention: (1) the present invention adopts center fractional combustion concept, apply while realizing two kinds of fuel, the pre-combustion grade of gaseous fuel is adopted to also reduce pollutant emission while providing steady burning things which may cause a fire disaster, main combustion stage realizes combustion with reduced pollutants, can guarantee the stability of aero-gas turbine combustion chamber while reducing disposal of pollutants;
(2) the present invention adopts dicyclo cavity combustion chamber structure, and combustion air is all fed by head, burner inner liner only has blending hole and necessary Cooling Holes, there is modular characteristics, simplify chamber structure, premix and pre-evaporation endless tube structure is also comparatively simple, is easy to processing.
Accompanying drawing illustrates:
Fig. 1 is the aero-gas turbine schematic diagram with center classification low emission dual-fuel combustor provided by the invention;
Fig. 2 is center classification low emission dual-fuel combustor structural representation provided by the invention;
Fig. 3 is center classification low emission dual-fuel combustor head schematic diagram provided by the invention;
Fig. 4 is pre-combustion grade schematic diagram in classification low emission dual-fuel combustor in center provided by the invention;
Fig. 5 is main combustion stage schematic diagram in classification low emission dual-fuel combustor in center provided by the invention;
In figure: 1 low-pressure shaft, 2 high-pressure shaft, 3 fans, 4 low-pressure compressors, 5 high-pressure compressors, 6 aero-gas turbine LNG/ aviation kerosine dual-fuel combustors, 7 high-pressure turbines, 8 low-pressure turbines, 9 preignition zones, 10 primary zones, 11 flame barrels, 12 outer flame tube walls, casing in 13, 14 outer casings, blending hole in 15, 16 outer blending hole, 17 Cooling Holes, 18 head of combustion chamber, 19 head end wall, 20 pre-combustion grade, 21 main combustion stages, 22 central nozzles, 23 one-level cyclones, 24 second cyclones, 25LNG petroleum pipeline, 26 Venturi tubes, 27 annular oil traps, 28 three swirler devices, 29 spray-holes, 30 kerosene are through petroleum pipeline, 31 main mixed zones.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention will be further described with enforcement.
As shown in Figure 1, be the structural representation of the two-axis aero-gas turbine with center classification low emission dual-fuel combustor.Be fan 3 and low-pressure compressor 4 in the front end of low-pressure shaft, rear end is the low-pressure turbine 8 for driving low-pressure shaft.Fan 3, low-pressure compressor 4, low-pressure turbine 8 are connected with low-pressure shaft 1 by connectors such as bearings, before fan 3 is positioned at low-pressure compressor 4, after low-pressure turbine is positioned at high-pressure turbine 7.Be high-pressure compressor 5 in the front end of high-pressure shaft 2, rear end is high-pressure turbine 7, high-pressure compressor 5, high-pressure turbine 7 are connected with high-pressure shaft 2 by bearing, after high-pressure compressor is positioned at low-pressure compressor, before aero-gas turbine LNG/ aviation kerosine dual-fuel combustor 6, after high-pressure turbine 7 is positioned at aero-gas turbine LNG/ aviation kerosine dual-fuel combustor 6, before low-pressure turbine 8.During gas turbine work, air after fan 3, low compressor 4 supercharging, then enters high pressure mechanism of qi 5, and the pressure-air after high-pressure compressor 5 compresses enters in aero-gas turbine LNG/ aviation kerosine dual-fuel combustor 6 and burns.Fuel injection system, to oil spout in high pressure draught, effectively burns in aero-gas turbine LNG/ aviation kerosine dual-fuel combustor 6, and the high-pressure gas formed after burning enters into high-pressure turbine 7 and low-pressure turbine 8 promotes turbine acting.
As shown in Figure 2, aero-gas turbine LNG/ aviation kerosine dual-fuel combustor 6, comprise combustion zone, combustion zone comprises preignition zone 9 and primary zone 10, the external boundary of combustion zone is provided with flame barrel 11, and inner boundary is provided with outer flame tube wall 12, and outer flame tube wall 12 arranged outside has outer casing 14, flame barrel 11 arranged outside has interior casing 13, the outer flame tube wall 12 of annular and flame barrel 11 radial distribution between casing 13 and outer casing 14 in annular.Blending hole 15 in flame barrel 11 is installed, outer flame tube wall 12 is upper installs outer blending hole 16, for adjusting combustor exit temperature distribution, inside and outside flame tube wall 11 is provided with Cooling Holes 17, for cooling flame tube wall surface, ensure the life-span of combustion chamber.Front portion, combustion zone is provided with head of combustion chamber 18, and head of combustion chamber 18 is connected with flame barrel 11 by head end wall 19.
As shown in Figure 3, described head of combustion chamber 18 comprises pre-combustion grade 20 and main combustion stage 21, and pre-combustion grade 20 and main combustion stage 21 are arranged together according to concentric mode, and pre-combustion grade 20 is at center, and it is peripheral that main combustion stage 21 is arranged in pre-combustion grade 20.Head of combustion chamber 18 is evenly arranged along aero-gas turbine LNG/ aviation kerosine dual-fuel combustor 6 circumference, number 10 ~ 60, its air capacity accounts for 20% ~ 80% of combustion chamber total air, wherein main combustion stage accounts for 60% ~ 90% of head air capacity, and pre-combustion grade accounts for 10% ~ 40% of head air capacity.
The described whole fuel oils of fuel nozzle supply needed for combustion chamber, comprise pre-combustion grade nozzle and main combustion stage atomizer, wherein the number of main combustion stage atomizer is 6 ~ 30, and the ratio that main combustion stage fuel oil accounts for total amount of fuel is 50% ~ 90%;
Combustion process completes in the combustion zone of burner inner liner; Pre-combustion grade 20 and main combustion stage 21 form two coaxial ring rotation jets in combustion zone, and the fuel of pre-combustion grade 20 and main combustion stage 21 completes in the precombustion district and outside main combustion zone that are positioned at inside, combustion zone respectively; The function of preignition zone 9 improves the fuel-oil atmozation quality of starting and under low-power operating mode, obtains and meet the flow field needed for designing requirement such as igniting, starting, poor oil firing's stability and efficiency of combustion; The function in primary zone 10 forms equally distributed pre-dark gas, for taking off, climb and cruising;
In burner inner liner, air divides three strands to enter combustion chamber, first strand of air needed for cooling combustion room head and burner inner liner, second strand of air flows through pre-combustion grade cyclone and main blender enters burner inner liner combustion zone, 3rd strand of air enters combustion chamber by the blending hole of combustion chamber, makes combustor exit temperature meet turbine inlet requirement;
As shown in Figure 4, described pre-combustion grade 20, comprise central nozzle 22, one-level cyclone 23, second cyclone 24, LNG petroleum pipeline 25 and Venturi tube 26, LNG petroleum pipeline 25 front end is provided with central nozzle 22, be disposed with one-level 23 and second cyclone 24 outside central nozzle 22, on central nozzle 22, cover is embedded with Venturi tube 26.
Pre-combustion grade 20 is realized by first, second double cyclone of same rotation direction of inner side and the coupling of direct-injection type natural gas nozzle; Wherein, first order cyclone is axial swirler, has 6 ~ 16 swirl vanes; The sheathed nozzle overcoat of nozzle and periphery combines and is installed on first order cyclone 23 entrance center; Second level cyclone 24 is positioned at outside first order cyclone 23, is cyclone in the same way with first order cyclone 23; Venturi tube 26 is connect after second level cyclone 24, first strand of rotational flow air enters Venturi tube 26 through first order cyclone 23, second strand of rotational flow air from second level cyclone 24 import after the passage of the blade of second level axial swirler produces cyclonic action, burner inner liner head is entered from second level cyclone 24 outlet, natural gas cone forms mixture under two bursts of rotational flow air effects, with diffusion combustion mode generation chemical reaction in district on duty;
Central nozzle 22 adopts simple nozzle, it is the spray-hole of 0.3-0.5mm that beam hanger scarf is circumferentially evenly arranged 3-7 diameter, LNG after gasification enters central nozzle 22 through LNG petroleum pipeline 25, burns in the natural gas via one-level cyclone 23 that nozzle sprays, second cyclone 24 and Venturi tube 26 enter into combustion chamber again combustion zone after mixing.
As shown in Figure 5, described main combustion stage 21, comprise annular oil trap 27, three swirler device 28, spray-hole 29, kerosene through petroleum pipeline 30 and main mixed zone 31, spray-hole 29 is uniformly distributed circumferentially outside annular oil trap 27, oil groove 27 upper end is provided with kerosene through petroleum pipeline 30, and spray-hole 29 front end is provided with main mixed zone 31 and three swirler device 28.
Main combustion stage 21 with liquid aviation kerosine for fuel, main combustion stage fuel oil described in it ejects through the flat mouth spray-hole that main combustion stage fuel oil supply nozzle, oil storage tank, multiple circumference are uniform, form the mist of oil cone with cone angle, being directly injected into through multiple flat mouth spray-hole becomes owner of in the cavity of blender, burner inner liner head is entered after fuel oil and the even blending of air of coming in from third level cyclone inlets in cavity, form uniform premix gas mixture to burn in side reflux district outside, form the primary zone of poor premix;
Circumferentially being evenly arranged 8 ~ 24 diameters outside described annular oil trap 27 is 0.3 ~ 0.5mm spray-hole 29, and concrete number depends on the number N of third level swirler blades, and nozzle number equals blade number N, or is the half of N.Aviation kerosine enters annular oil trap 27 through petroleum pipeline 30, main mixed zone 31 is injected again through spray-hole 29, in main mixed zone 31, fuel oil mixes with three swirler device 28 outlet air, realize the premix and pre-evaporation of fuel oil and air, the gas mixture mixed enters primary zone 10 and burns.
The third level cyclone 28 of described main combustion stage 21 is radial swirler, and its blade is camber blades; Blade angle is 47 ° ~ 67 °, and angle depends on required swirl strength; Blade number is 8 ~ 24, and be even number, concrete number is determined by the flow area of cyclone;
The air participating in burning all enters burner inner liner from the combination unit of head three swirler device 28, the air of burning accounts for 80% ~ 90% of whole air capacity, the air of residue 10% ~ 20% cools burner inner liner wall as air film, meets turbine-entry temperature requirement as dilution air.
Principle of the present invention is as follows: by the dual-fuel combustor adopting the center classification of fuel staging to realize LNG and aviation kerosine, reaches by the equivalent proportion and the uniformity controlling aeroengine combustor buring Indoor Combustion district the object reducing disposal of pollutants.Adopt the center fractional combustion scheme of fuel oil classification, LNG enters combustion chamber by pre-combustion grade nozzle after being converted into gaseous state by gasification installation, diffusion combustion is adopted to ensure the combustion stability of whole combustion chamber, guarantee that main combustion stage 21 is complete in wide equivalence ratio range combustion, and aviation kerosine enters primary zone by the fuel nozzle of main combustion stage 21, utilize in primary zone 10 premix and pre-evaporation endless tube by liquid fuel evaporation and with air blending, even flammable mixed gas is provided to combustion chamber, thus control equivalent proportion and the uniformity of whole combustion zone, realize the low emission of combustion chamber.In the startup combustor stage, be that first the pre-combustion grade of fuel starts with LNG, start main combustion stage 21 at higher load condition, under full load and cruising condition, pre-combustion grade 20 and main combustion stage 21 work simultaneously.Because natural gas has the advantages such as Flammability limits is wide, atomization good, pollutant emission is low, the effect adopt the pre-combustion grade of LNG also to have while realizing aero-engine bifuel system and expand combustion chamber Flammability limits, reducing combustion chamber pollutant emission.Under low operating mode, pre-combustion grade 20 local equivalent proportion is higher, has good stability, although combustion chamber overall equivalent ratio is very low at that time, can ensure combustion chamber steady operation.Under large operating mode, main combustion stage 21 and pre-combustion grade 20 work simultaneously, and the oily flow of main combustion stage 21 accounts for major part, and the evenly mixed gas premixed combustion that this part adopts, make the equivalent proportion of combustion zone in the scope that disposal of pollutants is lower, thus control the disposal of pollutants under large operating mode.Therefore, the disposal of pollutants of combustion chamber mainly controls by main combustion stage, and stable operation range mainly controls by pre-combustion grade, ensure that aero-engine has low pollution emission in wide working range, has good stability in low operating mode with turning in level process simultaneously.
A kind of employing center classification low emission dual-fuel combustor of the present invention, uses, have employed fuel oil classification method of supplying while realizing LNG and aviation kerosine.LNG after gasification and aviation kerosine are divided into two-way and enter combustion chamber, wherein the first via be gasification after LNG fuel enter combustion chamber from center pre-combustion grade nozzle 22, under the effect of one-level cyclone 23, second cyclone 24 and Venturi tube 26, evaporate after-combustion, pre-combustion grade adopts diffusion combustion.Be at engine march into the arena, the Smaller load state such as slow train time only pre-combustion grade work independently, and adopt fuel-rich combustion, combustion chamber can work efficiently and stably, effectively can reduce the discharge of pollutant owing to have employed fuel gas while expanding Flammability limits scope simultaneously.
Second tunnel adopts aviation kerosine as fuel, fuel oil enters annular oil trap 27 by aviation kerosine petroleum pipeline 30, it is the aperture of 0.3 ~ 0.5mm that annular oil trap 27 side has multiple circumferentially uniform diameter, fuel oil is directly laterally injected in the cavity of main mixed zone 31 by aperture, burner inner liner head is entered after fuel oil and the even blending of air of coming in from three swirler device 28 import in cavity, form uniform premix gas mixture to burn in side reflux district outside, form the primary zone of poor premix.Primary zone design equivalent proportion is the poor oil firing of 0.6 ~ 0.8, it has the two-fold advantage of lean premixed preevaporated (LPP) and oil-poor direct injection (LDI) concurrently simultaneously, the temperature of comprehensive reduction main combustion stage, primary zone ignition temperature controls, at below 1800K, effectively to suppress NO
xespecially thermal NO
xgeneration.
When above large load of marching into the arena is as taken off and climbing, pre-combustion grade and main combustion stage cooperation, the diffusion combustion of preignition zone provides stable incendiary source to primary zone, both ensure that low emission requirement, fully take into account combustion stability, efficiency of combustion etc. again, meet the Essential Performance Requirements of combustion chamber comprehensively.
Claims (7)
1. an aero-gas turbine LNG/ aviation kerosine dual-fuel combustor, it is characterized in that: comprise combustion zone, combustion zone comprises preignition zone and primary zone, the external boundary of combustion zone is provided with flame barrel, inner boundary is provided with outer flame tube wall, outer flame tube wall arranged outside has outer casing, flame barrel arranged outside has interior casing, blending hole in flame tube wall surface is installed, outer burner inner liner wall installs outer blending hole, inside and outside burner inner liner wall is provided with Cooling Holes, front portion, combustion zone is provided with head of combustion chamber, head of combustion chamber is connected with flame tube wall surface by head end wall.
2. aero-gas turbine LNG/ aviation kerosine dual-fuel combustor according to claim 1, is characterized in that: described outer flame tube wall and flame barrel are annular, and in annular radial distribution between casing and outer casing.
3. aero-gas turbine LNG/ aviation kerosine dual-fuel combustor according to claim 1, it is characterized in that: described head of combustion chamber comprises pre-combustion grade and main combustion stage, pre-combustion grade and main combustion stage are arranged together according to concentric mode, pre-combustion grade is at center, and main combustion stage is arranged in pre-combustion grade periphery.
4. aero-gas turbine LNG/ aviation kerosine dual-fuel combustor according to claim 3, it is characterized in that: described pre-combustion grade, comprise central nozzle, one-level cyclone, second cyclone, LNG petroleum pipeline and Venturi tube, LNG petroleum pipeline front end is provided with central nozzle, be disposed with one-level cyclone and second cyclone outside central nozzle, on central nozzle, cover is embedded with Venturi tube.
5. aero-gas turbine LNG/ aviation kerosine dual-fuel combustor according to claim 4, is characterized in that: described central nozzle adopts simple nozzle.
6. aero-gas turbine LNG/ aviation kerosine dual-fuel combustor according to claim 3, it is characterized in that: described main combustion stage, comprise annular oil trap, three swirler device, spray-hole, kerosene through petroleum pipeline and main mixed zone, spray-hole is uniformly distributed circumferentially outside annular oil trap, oil groove upper end is provided with kerosene through petroleum pipeline, and spray-hole front end is provided with main mixed zone and three swirler device.
7. aero-gas turbine LNG/ aviation kerosine dual-fuel combustor according to claim 6, is characterized in that: being circumferentially evenly arranged 8 ~ 24 diameters outside described annular oil trap is 0.3 ~ 0.5mm spray-hole.
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| CN106838986A (en) * | 2017-02-16 | 2017-06-13 | 中国航发沈阳发动机研究所 | A kind of combustion chamber |
| CN107525097A (en) * | 2017-09-26 | 2017-12-29 | 大连派思透平动力科技有限公司 | Vertical cylinder dual fuel burner |
| CN107575891A (en) * | 2017-07-25 | 2018-01-12 | 西北工业大学 | A kind of dual-fuel gas turbine low pollution combustor head construction |
| CN107906560A (en) * | 2017-11-09 | 2018-04-13 | 四川达宇特种车辆制造厂 | A kind of standing vortex declines type gas turbine combustors |
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| CN107525097A (en) * | 2017-09-26 | 2017-12-29 | 大连派思透平动力科技有限公司 | Vertical cylinder dual fuel burner |
| CN107906560A (en) * | 2017-11-09 | 2018-04-13 | 四川达宇特种车辆制造厂 | A kind of standing vortex declines type gas turbine combustors |
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| CN104949152B (en) | 2017-05-10 |
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