CN105020744A - Inclined-flow trapped-vortex combustor - Google Patents
Inclined-flow trapped-vortex combustor Download PDFInfo
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- CN105020744A CN105020744A CN201510392306.0A CN201510392306A CN105020744A CN 105020744 A CN105020744 A CN 105020744A CN 201510392306 A CN201510392306 A CN 201510392306A CN 105020744 A CN105020744 A CN 105020744A
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Abstract
The embodiment of the invention discloses an inclined-flow trapped-vortex combustor, and relates to the technical field of combustion gas turbines. The inclined-flow trapped-vortex combustor can reduce dead load and volume while increasing a power to weight ratio of the combustion gas turbines. The inclined-flow trapped-vortex combustor comprises a combustion chamber which is a totally ring-shaped structure, wherein a flame barrel wall cooling hole is formed in the wall surface of a flame barrel; the wall surface of the flame barrel is enclosed to form a concave cavity and a primary combustion-level combustion region; the wall surface of the concave cavity formed by enclosing comprises a concave cavity front wall, a concave cavity rear wall and a concave cavity outer wall; a concave cavity front wall gas inlet is formed in the concave cavity front wall; a concave cavity rear wall gas inlet is formed in the concave cavity rear wall; the wall surface of the primary combustion-level combustion region formed by enclosing comprises a first arc-shaped wall surface and a second arc-shaped wall surface; the concave cavity rear wall is connected with the second arc-shaped wall surface of the primary combustion-level combustion region formed by enclosing; a primary combustion hole is formed in the first arc-shaped wall surface; a mixing hole is formed in the second arc-shaped wall surface; and the first arc-shaped wall surface and the second arc-shaped wall surface are gradually converged at one side far from a flame plate to form an outlet of the combustion chamber. The inclined-flow trapped-vortex combustor is suitable for the combustion gas turbines.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of oblique flow standing vortex burning chamber.
Background technology
At present, axle combustion chamber, whirlpool mainly reverse flow type combustor and the throughflow combustor on aero gas turbine engine and ground industrial gas turbine is applied to.But, along with the raising of engine power to weight ratio, this two classes combustion chamber mainly contains following shortcoming: due to the raising of power to weight ratio, reverse flow type combustor is difficult to meet cooling when running and thermal capacitance needs, often need to increase extra structure and solve cooling and thermal capacitance problem, the S elbow structure that such as volume is larger, if be applied on small aircraft, can improve the deadweight of aircraft; In order to ensure efficiency of combustion while raising power to weight ratio, need the burner inner liner of throughflow combustor to design longer, axle system distance extends, and rotor is mated more difficult, cause the volume of throughflow combustor to become large and structure is too fat to move, be also difficult to be applied on small aircraft.
In sum, existing engine chamber design, is difficult to while the power to weight ratio improving gas turbine, reduce engine deadweight and volume, small aircraft power performance is restricted.
Summary of the invention
Embodiments of the invention provide a kind of oblique flow standing vortex burning chamber, can reduce deadweight and volume while the power to weight ratio improving gas turbine.
For achieving the above object, embodiments of the invention adopt following technical scheme: embodiments of the invention provide a kind of oblique flow standing vortex burning chamber 1, it is characterized in that, comprise: outer casing 2, interior casing 3, diffuser 4, high-energy spark plug 5, main combustion stage fuel manifold import 6, level fuel manifold on duty import 7, main combustion stage fuel manifold 8, level fuel manifold 9 on duty, burner inner liner 10, flame tube wall Cooling Holes 11, cavity antetheca air inlet 12, cavity rear wall air inlet 13, main flow import 14, connection flame plate 15, for oil baffle 16, main combustion stage oil and gas import 17, primary holes 18, blending hole 19, cavity 20, main combustion stage fuel manifold outlet 21, level fuel nozzle 22 on duty and main combustion stage combustion zone 23,
Described oblique flow standing vortex burning chamber is full loop configuration;
Described diffuser 4 enters described oblique flow standing vortex burning chamber after described diffuser for air, arrives the head of described burner inner liner 10 after described air is carried out deceleration supercharging;
The wall of described burner inner liner 10 arranges described flame tube wall Cooling Holes 11;
The wall of described burner inner liner 10 is around the described cavity 20 of formation and described main combustion stage combustion zone 23, cavity antetheca, cavity rear wall and cavity outer wall is comprised around the wall forming described cavity 20, described cavity antetheca is arranged described cavity antetheca air inlet 12, described cavity rear wall is arranged described cavity rear wall air inlet 13;
The first curved wall and the second curved wall is comprised around the wall forming described main combustion stage combustion zone 23, described cavity rear wall is connected with around the second curved wall forming described main combustion stage combustion zone 23, described first curved wall arranges described primary holes 18, described second curved wall arranges described blending hole 19, and described first curved wall and described second curved wall are restraining away from described flame plate 15 side the outlet forming described oblique flow standing vortex burning chamber gradually;
The both sides of described flame plate 15 are connected with described first curved wall and described cavity antetheca respectively.
The oblique flow standing vortex burning chamber that embodiments of the invention provide, using main combustion stage combustion zone 23 be integrated in a concave volume structure as the cavity 20 of level combustion zone on duty, and different whirlpools can be formed in same concave volume structure, ensure that main combustion stage and level on duty can independently be burnt, can burn together again, thus improve power to weight ratio.And relative to reflow type combustion chamber, do not need the element using large and small S type bend pipe equal-volume larger; And relative to once-through type combustion chamber, solve the problem that distance between axles is longer, therefore the present invention also reduces deadweight and the volume of engine while the power to weight ratio improving gas turbine.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the embodiment of the present invention, be briefly described to the accompanying drawing used required in embodiment below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the perspective view of oblique flow standing vortex burning chamber provided by the invention;
Fig. 2 is the partial sectional view of oblique flow standing vortex burning chamber provided by the invention;
Fig. 3 is the flame tube structure partial sectional view in oblique flow standing vortex burning chamber provided by the invention;
Fig. 4 is the oil supply system schematic diagram in oblique flow standing vortex burning chamber provided by the invention;
Fig. 5 is the fuel manifold structural representation in oblique flow standing vortex burning chamber provided by the invention;
Fig. 6 is oblique flow standing vortex burning chamber provided by the invention connection flame plate cross section combustion process schematic diagram;
Fig. 7 is oblique flow standing vortex burning chamber main flow cross section provided by the invention combustion process schematic diagram;
Label in each figure represents: 1-oblique flow standing vortex burning chamber, the outer casing of 2-, casing in 3-, 4-diffuser, 5-high-energy spark plug, the import of 6-main combustion stage fuel manifold, the import of 7-level fuel manifold on duty, 8-main combustion stage fuel manifold, 9-level fuel manifold on duty, 10-burner inner liner, 11-flame tube wall Cooling Holes, 12-cavity antetheca air inlet, 13-cavity rear wall air inlet, the import of 14-main flow, 15-joins flame plate, 16-is for oil baffle, 17-main combustion stage oil and gas import, 18-primary holes, 19-blending hole, 20-cavity, 21-main combustion stage fuel manifold exports, 22-level fuel nozzle on duty, 23-main combustion stage combustion zone, the main whirlpool of 24-cavity, the secondary whirlpool of 25-cavity.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be clearly and completely described the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making other embodiments all obtained under creative work prerequisite, belong to the scope of protection of the invention.
The embodiment of the present invention provides a kind of oblique flow standing vortex burning chamber as shown in Figure 1, be mainly used in aero gas turbine engine, and centrifugal compressor and axial-flow turbine, be especially applied in small-sized manned vehicle, unmanned plane, paraglider etc. and possess on the small aircraft of the features such as compact conformation, deadweight be lower.Also can be used for ground industrial gas turbine.
Oblique flow standing vortex burning chamber 1 comprises: outer casing 2, interior casing 3, diffuser 4, high-energy spark plug 5, fuel pipe import 6, level fuel manifold on duty import 7, main combustion stage fuel manifold 8, level fuel manifold 9 on duty, burner inner liner 10, flame tube wall Cooling Holes 11, cavity antetheca air inlet 12, cavity rear wall air inlet 13, main flow import 14, connection flame plate 15, for oil baffle 16, main combustion stage oil and gas import 17, primary holes 18, blending hole 19, cavity 20, main combustion stage fuel manifold outlet 21, level fuel nozzle 22 on duty and main combustion stage combustion zone 23.
In the present embodiment, as depicted in figs. 1 and 2, described oblique flow standing vortex burning chamber 1 is full loop configuration.
In a preferred approach, as shown in Figure 3, the wall of burner inner liner 10 adopts effusion wall mode to cool.Optionally, burner inner liner 10 also can use other types of cooling, such as: impinging cooling, impact air film etc.The wall of described burner inner liner 10 arranges described flame tube wall Cooling Holes 11, the wall of described burner inner liner 10 is around the described cavity 20 of formation and described main combustion stage combustion zone 23, cavity antetheca, cavity rear wall and cavity outer wall is comprised around the wall forming described cavity 20, described cavity antetheca is arranged described cavity antetheca air inlet 12, described cavity rear wall is arranged described cavity rear wall air inlet 13.
The first curved wall and the second curved wall is comprised around the wall forming described main combustion stage combustion zone 23, described cavity rear wall is connected with around the second curved wall forming described main combustion stage combustion zone 23, described first curved wall arranges described primary holes 18, described second curved wall arranges described blending hole 19.
The both sides of described flame plate 15 are connected with described first curved wall and described cavity antetheca respectively.
Described oblique flow standing vortex burning chamber 1 also includes the main combustion stage oil supply system be connected with main combustion stage fuel manifold 8 and the level oil supply system on duty be connected with level fuel manifold 9 on duty.Described main combustion stage oil supply system comprises for oil baffle 16, main combustion stage oil and gas import 17, main combustion stage fuel manifold outlet 21.Described antetheca cracks near diffuser 4 side air inlet, and described rear wall to crack air inlet away from diffuser side.Air enters oblique flow standing vortex burning chamber 1 from diffuser intake, to slow down supercharging through diffuser 4, so that the tissue of burning.The wall distribution of burner inner liner 10 arranges a large amount of Cooling Holes 11, with satisfied cooling needs.
Suppose that oblique flow standing vortex burning chamber length provided by the invention is about about 30mm, to reach close power to weight ratio:
Be designed to example with reflow type, the chamber length of backflow standing vortex burning chamber is about about 100mm; And the arc length that oblique flow standing vortex burning chamber is obtained by computation model, the arc length obtained by computation model with backflow standing vortex burning chamber is basically identical, at about 70mm.When width is consistent, the area ratio of oblique flow standing vortex burning chamber is 0.58, reduces more than 30% relative to the combustion chamber area of reflow type.
Be designed to example with once-through type, then the chamber length that direct current standing vortex burning chamber is obtained by computation model is about about 100mm, and therefore the distance between axles of oblique flow standing vortex burning chamber reduces more than 50% relative to the distance between axles of the combustion chamber of once-through type.Therefore the present invention also reduces deadweight and the volume of engine while the power to weight ratio improving gas turbine.
Further, as shown in Figure 3, described first curved wall is provided with row's primary holes 18 near interior casing 3 side, for be entered in oblique flow standing vortex burning chamber 1 by primary holes 18 by air and block flame.Air is entered in oblique flow standing vortex burning chamber 1 by primary holes 18, plays and blocks flame, controls the effect of the length of flame, thus extenuates the calcination of flame for oblique flow trapped vortex combustion cell structure, improves the service life of oblique flow standing vortex burning chamber.As shown in Figure 3, described first curved wall and described second curved wall are respectively provided with row's blending hole 19 respectively near the position of described outlet, for air is entered also cooling down high-temperature combustion gas in oblique flow standing vortex burning chamber 1 by the blending hole 19 of both sides, so that air enters in 19 oblique flow standing vortex burning chambers 1 by blending hole, play cooling down high-temperature combustion gas, improve the effect of Exit temperature distribution, thus extenuate the calcination of high-temperature fuel gas for oblique flow trapped vortex combustion cell structure, improve the service life of oblique flow standing vortex burning chamber.
Wherein, the sectional view that the oil supply system structure at connection flame plate 15 place is as shown in Figure 4 shown, the effect of transmitting flame and stabilizing the flame born by connection flame plate 15, the effect of main flow incendiary source can be played simultaneously, thus do not need the igniter that main flow is additionally set again, simplify the structure of oblique flow standing vortex burning chamber 1, cut down finished cost.
After applying the gas-turbine unit igniting of oblique flow standing vortex burning chamber 1 of the present invention, fuel oil sprays along fuel manifold 8 from fuel outlet 21, to beat after fuel oil ejection on confession oil baffle 16 and to be moved along baffle surface current by air driven, after premix, entering main combustion stage combustion zone 23 for main combustion stage from oil and gas import 17 fuel oil is provided.Level fuel manifold 9 on duty and fuel nozzle 22 provide fuel oil for cavity 20.Air enters provided with internal duct and external duct and main flow respectively.Inside and outside air-flow of containing enters burner inner liner from cavity antetheca air inlet 12 and cavity rear wall air inlet 13 respectively, and remaining air enters burner inner liner 10 from flame tube wall Cooling Holes 11, primary holes 18, blending hole 19 respectively.Primary air enters burner inner liner 10 from the gap between connection flame plate 15.
In the present embodiment, oblique flow standing vortex burning chamber 1 also comprises main combustion stage oil supply system, and described main combustion stage oil supply system is Multi-point jetting type oil supply system.Concrete, described main combustion stage oil supply system comprises: the described main combustion stage fuel manifold 8 be connected with described main combustion stage oil supply system, described main combustion stage fuel manifold 8 is arranged main combustion stage fuel manifold outlet 21, described main combustion stage fuel manifold outlet 21 supplies oil baffle 16 towards described, so that fuel oil is from described main combustion stage fuel manifold outlet 21 ejection, get to described on oil baffle 16.Such as: the fuel manifold structure of oil supply system as shown in Figure 4 and oblique flow standing vortex burning chamber 1 as shown in Figure 5, oil supply system is divided into main combustion stage oil supply system and level oil supply system on duty.Wherein, main combustion stage oil supply system comprises main combustion stage fuel manifold 8, for oil baffle 16, main combustion stage oil and gas import 17, main combustion stage fuel manifold outlet 21.In Fuel injection system, fuel oil sprays along fuel manifold 8 from fuel outlet 21, beats for oil baffle 16 is moved along baffle surface current by air driven, enters main combustion stage combustion zone 23 for main combustion stage provide fuel oil after premix from oil and gas import 17.Level oil supply system on duty comprises level fuel manifold 9 on duty, fuel nozzle 22 is swirl atomizer, is arranged on cavity 20 nose air intake 12, enters cavity 20 and burn together with air.
Further, described oblique flow standing vortex burning chamber 1 also includes the level fuel nozzle 22 on duty be connected with described level fuel manifold 9 on duty, and level fuel nozzle 22 on duty is installed on described cavity antetheca air inlet 12 place.
In the present embodiment, distance between described cavity antetheca air inlet 12 and described cavity outer wall is less than the distance between described cavity rear wall air inlet 13 and described cavity outer wall, so that described cavity antetheca air inlet 12 is in different radial positions from described cavity rear wall air inlet 13.
In the present embodiment, in conjunction with the structure of oblique flow standing vortex burning chamber 1 as Figure 1-5, the course of work of the cavity 20 of oblique flow standing vortex burning chamber 1 is: cavity 20 is as the level combustion chamber on duty of whole oblique flow standing vortex burning chamber 1, and air and fuel oil enter cavity 20 and burn.After compressed air enters oblique flow standing vortex burning chamber 1, enter main flow and oblique flow standing vortex burning chamber 1 provided with internal duct and external duct respectively.The inside and outside air-flow of containing of oblique flow standing vortex burning chamber 1 enters burner inner liner from cavity antetheca air inlet 12 and cavity rear wall air inlet 13 respectively.Simultaneously, because the distance between described cavity antetheca air inlet 12 and described cavity outer wall is less than the distance between described cavity rear wall air inlet 13 and described cavity outer wall, make described cavity antetheca air inlet 12 be in different radial positions from described cavity rear wall air inlet 13, thus form stable double vortex structure in burner inner liner combustion zone.
Concrete, as shown in Figure 6, fuel nozzle 22 is arranged on cavity antetheca air inlet 12 place, and fuel oil enters in burner inner liner together with the air of burner inner liner antetheca, and moves in the single whirlpool formed in combustion zone with air, formation combustion mixture.When ignition system is connected, two electrode voltages of high-energy spark plug 5 exceed air breakdown threshold values, send electric spark, form the high-temperature plasma district of a similar diffusion flame shape, light the combustion mixture near sparking plug, form core fire group.This core fire group, while surrounding propagating flame, moves with air-flow, makes flame propagation arrive in the recirculating zone in the main whirlpool 24 of cavity, form point of safes burning things which may cause a fire disaster.After incoming mixture enters cavity 20, carry out heating and being lighted under the effect of this point of safes burning things which may cause a fire disaster.The circumference of flame is propagated, and will light adjacent head, and be lighted by whole cavity 20 further, thus light a fire successfully.
Concrete, as shown in Figure 7, the main combustion stage course of work of oblique flow standing vortex burning chamber 1 is: main flow carries out premix and pre-evaporation burning, as the main combustion stage of oblique flow standing vortex burning chamber 1.Double vortex structure is formed, level fuel oil on duty burning in the main whirlpool 24 of cavity and the secondary whirlpool 25 of cavity in cavity 20.At the secondary whirlpool 25 of cavity and the intersection of main flow, there is speed difference between the two, thus form shear layer.Because in shear layer, turbulivity is high, and there is a large amount of whirlpools, make fluidal texture be conducive to the mass exchange of cavity 20 high-temperature fuel gas and the non-burning mixt of main flow, thus light main flow mixture.Further, in the cross section of connection flame plate 15 as shown in Figure 6, in cavity 20, Some gases flows in the following wake of connection flame plate 15 under pressure differential, thus in the formation high-temperature region, tail district of connection flame plate 15, main flow also can be lighted herein.Achieve connection flame plate 15 and not only play the effect of biography flame, also can play the effect of main flow incendiary source.Flame propagation is to main flow center, and the gaseous mixture entering main flow evaporates mixing in advance in upstream, formed more uniform premix gas laggard enter primary zone 23.
The oblique flow standing vortex burning chamber that embodiments of the invention provide, using main combustion stage combustion zone 23 be integrated in a concave volume structure as the cavity 20 of level combustion zone on duty, and different whirlpools can be formed in same concave volume structure, ensure that main combustion stage and level on duty can independently be burnt, can burn together again, thus improve power to weight ratio.And relative to reflow type combustion chamber, do not need the element using large and small S type bend pipe equal-volume larger; And relative to once-through type combustion chamber, solve the problem that distance between axles is longer, therefore the present invention also reduces deadweight and the volume of engine while the power to weight ratio improving gas turbine.Each embodiment in this description all adopts the mode of going forward one by one to describe, between each embodiment identical similar part mutually see, what each embodiment stressed is the difference with other embodiments.Especially, for apparatus embodiments, because it is substantially similar to embodiment of the method, so describe fairly simple, relevant part illustrates see the part of embodiment of the method.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claim.
Claims (6)
1. an oblique flow standing vortex burning chamber, it is characterized in that, comprise: outer casing (2), interior casing (3), diffuser (4), high-energy spark plug (5), main combustion stage fuel manifold import (6), level fuel manifold on duty import (7), main combustion stage fuel manifold (8), level fuel manifold (9) on duty, burner inner liner (10), flame tube wall Cooling Holes (11), cavity antetheca air inlet (12), cavity rear wall air inlet (13), main flow import (14), connection flame plate (15), for oil baffle (16), main combustion stage oil and gas import (17), primary holes (18), blending hole (19), cavity (20), main combustion stage fuel manifold outlet (21), level fuel nozzle (22) on duty and main combustion stage combustion zone (23),
Described oblique flow standing vortex burning chamber is full loop configuration;
Described diffuser (4) enters described oblique flow standing vortex burning chamber after described diffuser for air, arrives the head of described burner inner liner (10) after described air is carried out deceleration supercharging;
The wall of described burner inner liner (10) is arranged described flame tube wall Cooling Holes (11);
The wall of described burner inner liner (10) is around the described cavity of formation (20) and described main combustion stage combustion zone (23), cavity antetheca, cavity rear wall and cavity outer wall is comprised around the wall forming described cavity (20), described cavity antetheca is arranged described cavity antetheca air inlet (12), described cavity rear wall is arranged described cavity rear wall air inlet (13);
The first curved wall and the second curved wall is comprised around the wall forming described main combustion stage combustion zone (23), described cavity rear wall is connected with around the second curved wall forming described main combustion stage combustion zone (23), described first curved wall is arranged described primary holes (18), described second curved wall is arranged described blending hole (19), described first curved wall and described second curved wall are restraining away from described flame plate (15) side the outlet forming described oblique flow standing vortex burning chamber gradually;
The both sides of described flame plate (15) are connected with described first curved wall and described cavity antetheca respectively.
2. oblique flow standing vortex burning chamber according to claim 1, is characterized in that, described oblique flow standing vortex burning chamber also comprises main combustion stage oil supply system, and described main combustion stage oil supply system is Multi-point jetting type oil supply system;
Described main combustion stage oil supply system comprises: the described main combustion stage fuel manifold (8) be connected with described main combustion stage oil supply system, described main combustion stage fuel manifold (8) is arranged main combustion stage fuel manifold outlet (21), described main combustion stage fuel manifold outlet (21) supplies oil baffle (16) towards described, so that fuel oil exports (21) ejection from described main combustion stage fuel manifold, get to described on oil baffle (16).
3. oblique flow standing vortex burning chamber according to claim 1, is characterized in that, described oblique flow standing vortex burning chamber also includes the level fuel nozzle (22) on duty be connected with described level fuel manifold (9) on duty;
Described level fuel nozzle (22) on duty is installed on described cavity antetheca air inlet (12) place.
4. oblique flow standing vortex burning chamber according to claim 1, it is characterized in that, distance between described cavity antetheca air inlet (12) and described cavity outer wall is less than the distance between described cavity rear wall air inlet (13) and described cavity outer wall, so that described cavity antetheca air inlet (12) is in different radial positions from described cavity rear wall air inlet (13).
5. oblique flow standing vortex burning chamber according to claim 1, it is characterized in that, described first curved wall is provided with row's primary holes (18) near interior casing (3) side, for air being entered oblique flow trapped vortex combustion indoor by primary holes (18) and blocking flame.
6. oblique flow standing vortex burning chamber according to claim 5, it is characterized in that, described first curved wall and described second curved wall are respectively provided with row's blending hole (19) respectively near the position of described outlet, for air is entered the indoor also cooling down high-temperature combustion gas of oblique flow trapped vortex combustion by the blending hole (19) of both sides.
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| CN201510392306.0A CN105020744A (en) | 2015-07-06 | 2015-07-06 | Inclined-flow trapped-vortex combustor |
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Cited By (5)
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| CN106907742A (en) * | 2017-02-08 | 2017-06-30 | 南京航空航天大学 | A kind of integrated standing vortex burning chamber head device of fuel feeding blending and its method of work |
| CN111706879A (en) * | 2020-06-10 | 2020-09-25 | 中国空气动力研究与发展中心 | Standing vortex combustion chamber class flame stabilizing concave cavity and oil gas matching device |
| CN113685844A (en) * | 2021-08-24 | 2021-11-23 | 中国航发湖南动力机械研究所 | Little return bend assembly fixture of combustion chamber full ring test spare |
| CN115076721A (en) * | 2022-06-01 | 2022-09-20 | 南京航空航天大学 | Pre-evaporation standing vortex on-duty flame stabilizer and working method thereof |
| CN115143489A (en) * | 2022-06-15 | 2022-10-04 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale cyclone air intake |
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| CN115143489A (en) * | 2022-06-15 | 2022-10-04 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale cyclone air intake |
| CN115143489B (en) * | 2022-06-15 | 2023-08-11 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale rotational flow air intake |
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Application publication date: 20151104 |