CN108870441B - Afterburner adopting circular arc fan-shaped nozzle and concave cavity structure - Google Patents
Afterburner adopting circular arc fan-shaped nozzle and concave cavity structure Download PDFInfo
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- CN108870441B CN108870441B CN201810219294.5A CN201810219294A CN108870441B CN 108870441 B CN108870441 B CN 108870441B CN 201810219294 A CN201810219294 A CN 201810219294A CN 108870441 B CN108870441 B CN 108870441B
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 26
- 239000003921 oil Substances 0.000 claims description 42
- 239000007921 spray Substances 0.000 claims description 39
- 239000000295 fuel oil Substances 0.000 claims description 18
- 238000002347 injection Methods 0.000 claims description 17
- 239000007924 injection Substances 0.000 claims description 17
- 239000003381 stabilizer Substances 0.000 claims description 6
- 239000003344 environmental pollutant Substances 0.000 abstract description 2
- 231100000719 pollutant Toxicity 0.000 abstract description 2
- 238000011084 recovery Methods 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 description 13
- 238000000889 atomisation Methods 0.000 description 6
- 238000009792 diffusion process Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000003595 mist Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
Abstract
The invention discloses a afterburner adopting an arc-shaped fan-shaped nozzle and a concave cavity structure, belonging to the field of aircraft engines. The invention can ensure that the afterburner can be smoothly ignited under various complex working conditions, and flame propagation is realized along the concave cavity in the circumferential direction of the afterburner cone, so that the combustion stability in the afterburner is effectively improved, the length of the afterburner is shortened, the total pressure recovery coefficient is improved, the flow loss is reduced, the combustion efficiency is increased, the generation of pollutants such as NOx, CO and the like is effectively reduced, and the overall performance of the engine is improved.
Description
Technical Field
The invention belongs to the field of aeroengines, and particularly relates to an afterburner adopting an arc-shaped fan-shaped nozzle and a concave cavity structure.
Background
Jet engines have gained more and more widespread use in the aeronautical field since the beginning of the last century. In order to improve the operational performance and flight envelope of military fighters, afterburner technology has begun to be widely used in aviation power plants. The afterburner can greatly improve the unit thrust and thrust-weight ratio of the engine and effectively improve the operational efficiency of military aircraft, so the afterburner plays an important role in the development of military aircraft.
At present, a common turbofan engine afterburner is composed of an internal and external culvert mixing diffuser, a direct injection type fuel nozzle, a flame stabilizer, a vibration-proof heat shield, a cylinder body and other parts. When the engine is started to apply force, the gas exhausted by the low-pressure turbine and the air entering from the outer duct are mixed by the mixer and then enter the afterburner, are subjected to speed reduction and pressure expansion in the diffuser, and then are mixed with the fuel oil sprayed by the direct injection nozzle to form mixed gas, and the mixed gas is ignited under the action of the igniter to organize combustion. However, with the development of the aviation technology, the performance requirements of modern advanced warplanes on aircraft engines are higher and higher, the traditional afterburner usually adopts a bluff body flame stabilizer arranged in a gas flow path to stabilize flame, an oil spray rod usually adopts a direct injection type nozzle to carry out fuel oil atomization, and the spray expansion angle is small, so that the main flow is blocked, obvious total pressure loss is caused, especially flow resistance loss when no force is applied, and the cylindrical fuel oil jet sprayed by the direct injection type nozzle is too narrow in contact area with the gas flow, so that the fuel oil atomization effect is insufficient, the afterburner is difficult to ignite under complex working conditions, the combustion stability is poor, the engine oil consumption rate is higher, and the overall performance of the military aircraft is influenced. At present, the afterburner of the military aircraft engine which is researched usually adopts a method for improving the structural design of the afterburner and improving the fuel atomization effect, but the methods do not fundamentally solve the defects of unsatisfactory fuel atomization effect, difficult ignition of the afterburner under a complex working condition, poor combustion stability and high fuel consumption rate of the engine.
Disclosure of Invention
Aiming at the problems in the prior art, the invention discloses an afterburner with an arc-shaped fan-shaped nozzle and a concave cavity structure, the ignition stability of the afterburner is improved by optimizing the structural design of the afterburner, the ignition stability of the afterburner is improved by adopting the concave cavity structure, the fuel space atomizing cone angle is enlarged by adopting the arc-shaped fan-shaped fuel nozzle, the contact area of fuel and air is increased, and the fuel atomizing effect is enhanced, so that the combustion efficiency of the afterburner is improved, the overall performance of an engine is improved, and the defects in the prior art are overcome.
The invention is realized by the following steps:
an afterburner adopting an arc-shaped fan-shaped nozzle and a concave cavity structure comprises an afterburner, wherein a turbine is arranged on the central axis of a gas turbine in the afterburner along the incoming air flow direction, and an afterburning inner cone is arranged behind the turbine; the boosting inner cone is positioned in the center of the flow channel in the flowing direction of the airflow, and is reduced along the downstream direction to form an arc-shaped ring surface at a gradually expanding end, and the arc-shaped ring surface is a gradually expanding ring surface of the boosting inner cone; a support plate is arranged between the circumferential direction of the radial upper end of the outer conical surface of the boosting inner cone and the circumference of the side wall of the boosting combustion chamber, and the support plate is positioned at the front end of the gradually expanding annular surface of the boosting inner cone; an oil spray rod is fixedly arranged in the support plate. The wall surface of the radial lower end side of the oil injection rod is provided with an arc-shaped fan-shaped nozzle, and the design of the arc-shaped fan-shaped nozzle can increase the fuel oil spraying expansion angle in the circumferential direction of the stressing inner cone, so that the fuel oil space distribution in the circumferential direction is more uniform; the support plate and the boosting inner cone gradually expand the ring surface to form a concave cavity structure. The arc oil mist cones of each nozzle are mutually overlapped, so that the cross flame in the circumferential direction of the stress application inner cone concave cavity (9) is facilitated.
Further, the arc-shaped fan-shaped nozzle is arc-shaped fan-shaped, and an oil injection hole is formed in the middle of the arc-shaped fan-shaped nozzle; the oil spray rod is provided with an inlet and an outlet. The inlet of the oil spray rod is connected with the fuel oil pipeline, and the oil spray hole is communicated with the outlet of the oil spray rod; the two end faces of the oil spray hole are respectively a first arc-shaped fan-shaped jet flow face and a second arc-shaped fan-shaped jet flow face by taking the oil spray hole as a boundary.
Furthermore, the included angle between the first arc-shaped fan-shaped jet flow surface and the second arc-shaped fan-shaped jet flow surface of the arc-shaped fan-shaped nozzle is theta, and the theta range is 30-150 degrees.
Furthermore, the number of the oil injection rods is set to be 1-30; the angle between the oil spray rod and the central axis of the gas turbine is 10-90 degrees.
Furthermore, an igniter and a flame stabilizer are fixedly arranged in the support plate, and the igniter is positioned at the downstream of the oil injection rod; the oil spray rod and the igniter are sequentially arranged along the air inflow direction. The support plate, the igniter and the oil injection rod all have inclination angles with the central axis of the gas turbine. The opening of the igniter points to the center line of the fan-shaped fuel fog surface.
Furthermore, a blender is arranged between the turbine and the side wall of the afterburner, and a diffusion section is formed between the blender and the support plate.
Furthermore, the boosting inner cone gradually-expanding ring surface of the boosting inner cone outer conical surface is the front wall surface of the concave cavity structure, and the longitudinal surface of the boosting inner cone gradually-expanding ring surface of the boosting inner cone, which extends backwards, forms the concave cavity base of the concave cavity structure.
Furthermore, two arc-shaped fan-shaped jet flow surfaces of the arc-shaped fan-shaped nozzle are in the opening direction of the nozzle, the opening direction of the nozzle points to the plane of the base of the concave cavity, the central line of the arc-shaped fan-shaped jet flow surface and the central axis of the gas turbine form an angle of 10-90 degrees, arc-shaped fan-shaped fuel oil sprays are mutually overlapped, and the number of the arc-shaped fan-shaped nozzles is set to be 1-30.
Furthermore, the radian of the stress application inner cone gradually-expanding ring surface is 10-90 degrees.
Furthermore, the inlet of the afterburner along the air inflow direction is also sequentially provided with a low-pressure compressor, a high-pressure compressor and a main combustion chamber connected with the high-pressure compressor; the primary combustion chamber is connected to the turbine.
Compared with the prior art, the invention has the beneficial effects that:
1) the afterburner has a combustion mode of stabilizing flame by adopting a cavity structure and strengthening afterburner inner cone circumferential direction space fuel atomization by adopting the arc-shaped fan-shaped nozzle, can ensure that the afterburner can be smoothly ignited under various complex working conditions, and can realize flame propagation along the cavity in the afterburner inner cone circumferential direction, so that the combustion stability in the afterburner is effectively improved, meanwhile, the length of the afterburner is shortened, the total pressure recovery coefficient is improved, the flow loss is reduced, the circular arc-shaped fan-shaped nozzle can strengthen afterburner inner cone circumferential direction fuel atomization effect, the combustion efficiency is increased, the generation of pollutants such as NOx, CO and the like is effectively reduced, and the overall performance of an engine is improved;
2) the arc-shaped fan-shaped nozzle is arranged along the circumferential direction, the expansion angle of the generated spray is large (the fan angle is 30-150 degrees and is far larger than the spray cone angle of the direct-injection nozzle), and meanwhile, as the arc-shaped fan-shaped nozzle is adopted, the spray is arc-shaped and is matched with the stress application inner cone gradually-expanded ring surface of the concave cavity structure, and the flame connection in the circumferential direction in the concave cavity is convenient. The diffusion combustion is adopted in the concave cavity structure, so that stable ignition can be realized under various complex working conditions, and stable and efficient combustion of the afterburner is ensured;
3) the oil spray rod adopts the arc-shaped fan-shaped nozzle, so that the number of the nozzles can be greatly reduced on the premise of ensuring that fuel oil is uniformly distributed along the inner circumference space of the concave cavity and flame is reliably and stably connected; the arc-shaped sprays of the arc-shaped fan-shaped nozzles are mutually overlapped, so that reliable and stable flame connection is realized in the inner circumference direction of the concave cavity structure, and stable ignition is facilitated under various working conditions;
4) compared with a direct injection type nozzle, the circular arc-shaped fan-shaped nozzle on the wall surface of the radially lower end side of the oil injection rod has a larger spray expansion angle in the circumferential direction, so that the fuel oil in the cavity structure is fully atomized, and the problem of nozzle blockage is effectively reduced;
5) the concave cavity structure greatly shortens the length of the afterburner, reduces the additional mass of the combustor and reduces the flow resistance loss in the afterburner;
6) the gradual expansion section formed by the stress application inner cone gradual expansion ring surface can effectively prevent the problems of tempering, nozzle carbon deposition and the like in lean oil premixed and pre-evaporated combustion; the downstream end of the afterburning inner cone is designed to be a pointed cone, and the wall surface of the inner cone is subjected to air film cooling, so that the infrared radiation of an afterburner can be effectively reduced, and the stealth performance of the military aircraft is improved.
Drawings
FIG. 1 is a block diagram of a turbofan aircraft engine employing an afterburner with a circular arc sector nozzle and bowl configuration in accordance with the present invention;
FIG. 2 is a partially exploded view of a plate and bowl configuration of an afterburner of the present invention employing a circular arc sector nozzle and bowl configuration;
FIG. 3 is a schematic view of a circular sector nozzle of the afterburner of the present invention employing a circular sector nozzle and a bowl configuration;
FIG. 4 is a schematic diagram of the distribution of the boosting inner cone divergent ring surface circumferential direction fan-shaped nozzles of the boosting combustor adopting the circular arc fan-shaped nozzles and the concave cavity structure;
the gas turbine comprises a low-pressure gas compressor 1, a high-pressure gas compressor 2, a main combustion chamber 3, a turbine 4, a blender 5, a diffusion section 6, a support plate 7, an internal stress cone 8, a cavity structure 9, a gradual expansion ring surface 10, an igniter 11, a flame stabilizer 12, a first circular arc fan-shaped jet surface 126, an oil spray hole 127, a second circular arc fan-shaped jet surface 128, a cavity base 13, an oil spray rod 14, an afterburner 15, an air inflow direction 100, a gas turbine central axis 500 and a circular arc fan-shaped nozzle 001.
Detailed Description
In order to make the objects, technical solutions and effects of the present invention clearer, the present invention is further described in detail below with reference to the accompanying drawings and examples. It should be noted that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1, a low-pressure compressor 1, a high-pressure compressor 2, and a main combustion chamber 3 connected to the high-pressure compressor 2 are sequentially disposed on a central axis 500 of the gas turbine along an air inflow direction 100 in the afterburner of the present invention; the main combustion chamber 3 is connected with a turbine 4, a blender 5 is arranged between the turbine 4 and the side wall of the afterburner 15, and a diffusion section 6 is formed between the blender 5 and a support plate 7.
A boosting inner cone 8 is arranged behind the turbine 4; the boosting inner cone 8 is reduced along the downstream direction to form an arc-shaped ring surface at a gradually expanding end, the arc-shaped ring surface is a boosting inner cone gradually expanding ring surface 10, and the radian of the boosting inner cone gradually expanding ring surface 10 is 10-90 degrees; a support plate 7 is arranged between the circumferential direction of the radial upper end of the outer conical surface of the boosting inner cone 8 and the circumference of the side wall of the boosting combustion chamber 15, and the support plate 7 is positioned at the front end of the boosting inner cone divergent ring surface 10.
As shown in fig. 2 to 3, an igniter 11, a flame stabilizer 12 and an oil spray rod 14 are fixedly arranged inside the support plate 7, and a circular arc fan-shaped nozzle 001 is arranged on the side wall surface of the radial lower end of the oil spray rod 14; the arc-shaped fan-shaped nozzle 001 is in an arc-shaped fan shape, and the middle part of the arc-shaped fan-shaped nozzle 001 is provided with an oil injection hole 127; the oil spray hole 127 is communicated with the outlet of the oil spray rod 14; the two end surfaces of the oil spray hole 127 are respectively a first circular arc sector jet surface 126 and a second circular arc sector jet surface 128 by taking the oil spray hole 127 as a boundary. The concave cavity structure 9 is formed by the support plate 7 and the boosting inner cone divergent ring surface 10. The boosting inner cone gradually-expanding ring surface 10 of the outer conical surface of the boosting inner cone 8 is the front wall surface of the concave cavity structure 9, and the longitudinal surface of the boosting inner cone gradually-expanding ring surface 10 of the boosting inner cone 8, which extends backwards, forms a concave cavity base 13 of the concave cavity structure. The two arc-shaped fan-shaped jet flow surfaces of the arc-shaped fan-shaped nozzle 001 are in the nozzle opening direction, the nozzle opening direction points to the concave cavity base portion plane 13, the center line of the arc-shaped fan-shaped jet flow surface and the central axis of the gas turbine form an angle of 10-90 degrees, arc-shaped fan-shaped fuel oil sprays are mutually overlapped, the number of the arc-shaped fan-shaped nozzles is set to be 1-30, and the nozzles are selected according to the number of the support plates. The overall shape of the oil spray bar 14 can be realized by casting, and the circular arc-shaped fan-shaped nozzle 001 can be processed by laser drilling, drilling or surface milling.
As shown in fig. 4, fig. 4 is a schematic diagram of the distribution of the boosting cone divergent torus circumferential direction fan-shaped nozzles of the boosting combustor adopting the circular arc fan-shaped nozzles and the cavity structure, wherein the circular arc fan-shaped nozzles 001 are distributed in the circumferential direction of the boosting cone 8, and the fuel sprays of the circular arc fan-shaped nozzles 001 are overlapped with each other to facilitate flame coupling in the inner circumferential direction of the cavity.
The working process of the invention is as follows:
after passing through the low-pressure compressor 1, the air is divided into two parts: one part enters an outer culvert flow channel, the other part enters a main combustion chamber 3 after passing through a high-pressure compressor 2, the combusted gas pushes a turbine 4 to do work,
the outer culvert air flow is mixed with the gas which does work through the turbine 4 through the blender 5, and flows to the oil spray rod 14 after passing through the diffusion section 6 of the afterburner. The fuel oil is atomized by the arc-shaped fan-shaped nozzle 001 in the initial arc-shaped fan-shaped mode, the fuel oil is crushed and further atomized under the action of the incoming flow pneumatic acting force, the fuel oil sprayed by the arc-shaped fan-shaped nozzle 001 in the concave cavity is sprayed out on a fan-shaped fuel oil surface under the action of arc-shaped fan-shaped extrusion to form an arc-shaped fan-shaped oil mist cone, the arc-shaped fan-shaped fuel oil cones in the direction of the stress application inner cone gradually-expanding ring surface 10 are overlapped with each other and are connected in the direction of the stress application inner cone gradually-expanding ring surface 10, and the flame connection. The mixture is mixed to form an oil-gas mixture which enters the cavity structure 9, and the mixed gas flow forms a backflow in the cavity structure 9. After the ignition of the igniter 11, the diffusion combustion is realized, a stable high-temperature ignition source is formed, flame is radially transmitted along the direction of the boosting inner cone gradually-expanding ring surface 10 and the support plate 7, and fuel oil sprayed from a nozzle at the radial upper end of the fuel spray rod 14 is continuously ignited, so that the stable combustion can be realized in the afterburner 15, the stable and reliable ignition and flame linkage of the afterburner under various working conditions are realized, and the stable combustion in the afterburner is ensured.
Claims (9)
1. An afterburner adopting an arc-shaped fan-shaped nozzle and a concave cavity structure comprises an afterburner (15), wherein a turbine (4) is arranged on a central axis (500) of a gas turbine in the afterburner (15) along the incoming air flow direction (100), and is characterized in that an afterburner inner cone (8) is arranged behind the turbine (4); the boosting inner cone (8) is reduced along the downstream direction to form an arc-shaped ring surface at a gradually expanding end, and the arc-shaped ring surface is a boosting inner cone gradually expanding ring surface (10); a support plate (7) is arranged between the circumferential direction of the radial upper end of the outer conical surface of the boosting inner cone (8) and the circumference of the side wall of the boosting combustion chamber (15), and the support plate (7) is positioned at the front end of the boosting inner cone gradually-expanding ring surface (10); an oil spray rod (14) is fixedly arranged in the support plate (7), and a circular arc fan-shaped nozzle (001) is arranged on the side wall surface of the radial lower end of the oil spray rod (14); a concave cavity structure (9) is formed behind the support plate (7) and the stress application inner cone gradually-expanding ring surface (10); the arc-shaped fan-shaped nozzle (001) is arc-shaped fan-shaped, and an oil spray hole (127) is formed in the middle of the arc-shaped fan-shaped nozzle (001); the oil injection hole (127) is communicated with the outlet of the oil injection rod (14); the two end surfaces of the oil spray hole (127) are respectively a first circular arc sector jet flow surface (126) and a second circular arc sector jet flow surface (128) by taking the oil spray hole (127) as a boundary.
2. The afterburner with the circular arc sector nozzle and the cavity structure as claimed in claim 1, wherein the included angle between the first circular arc sector jet surface (126) and the second circular arc sector jet surface (128) of the circular arc sector nozzle (001) is theta, and the theta is in the range of 30-150 degrees.
3. The afterburner adopting the circular arc-shaped fan-shaped nozzle and the concave cavity structure is characterized in that the number of the oil injection rods (14) is 1-30; the angle between the oil injection rod (14) and the central axis (500) of the gas turbine is 10-90 degrees.
4. The afterburner with the circular arc-shaped fan-shaped nozzle and the cavity structure is characterized in that an igniter (11) and a flame stabilizer (12) are fixedly arranged in the support plate (7), and the igniter (11) is positioned at the downstream of the oil spray rod (14); the oil spray rod (14) and the igniter (11) are sequentially arranged along the air inflow direction.
5. The afterburner with the circular arc sector nozzle and cavity structure is characterized in that a blender (5) is arranged between the turbine (4) and the side wall of the afterburner (15), and a diffuser section (6) is formed between the blender (5) and the support plate (7).
6. The afterburner with circular arc sector nozzles and cavity structures as claimed in claim 1, wherein the stress application inner cone divergent ring surface (10) of the stress application inner cone (8) outer cone surface is the front wall surface of the cavity structure (9), and the longitudinal surface of the stress application inner cone divergent ring surface (10) of the stress application inner cone (8) extending backwards forms the cavity base (13) of the cavity structure.
7. The afterburner with the structure of the circular arc fan-shaped nozzle and the cavity is characterized in that two circular arc fan-shaped jet flow surfaces of the circular arc fan-shaped nozzle (001) are in the nozzle opening direction, the nozzle opening direction is directed to the cavity base (13), the central line of each circular arc fan-shaped jet flow surface and the central axis of the gas turbine form a 10-90 degrees angle, circular arc fan-shaped fuel oil sprays are mutually overlapped, and the number of the circular arc fan-shaped nozzles is set to be 1-30.
8. The afterburner with circular arc sector nozzle and cavity structure as claimed in claim 1, wherein the radian of the afterburner inner cone divergent ring surface (10) is 10-90 °.
9. The afterburner with the circular arc-shaped fan-shaped nozzle and the cavity structure is characterized in that a low-pressure compressor (1), a high-pressure compressor (2) and a main combustion chamber (3) connected with the high-pressure compressor (2) are sequentially arranged at an inlet of the afterburner (15) along the air inflow direction; the main combustion chamber (3) is connected with a turbine (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810219294.5A CN108870441B (en) | 2018-03-16 | 2018-03-16 | Afterburner adopting circular arc fan-shaped nozzle and concave cavity structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810219294.5A CN108870441B (en) | 2018-03-16 | 2018-03-16 | Afterburner adopting circular arc fan-shaped nozzle and concave cavity structure |
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| Publication Number | Publication Date |
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| CN108870441A CN108870441A (en) | 2018-11-23 |
| CN108870441B true CN108870441B (en) | 2020-03-17 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111306577B (en) * | 2020-02-21 | 2021-10-26 | 南京航空航天大学 | Direct-injection fan-shaped nozzle applied to afterburner concave cavity structure |
| CN113606610B (en) * | 2021-07-27 | 2022-10-21 | 南京航空航天大学 | Pneumatic auxiliary atomization direct injection type nozzle applied to afterburner |
| CN115200045B (en) * | 2022-07-21 | 2023-08-04 | 中国航发沈阳发动机研究所 | External culvert ignition afterburner |
| CN115183273A (en) * | 2022-07-21 | 2022-10-14 | 中国航发沈阳发动机研究所 | Afterburning engine combustion chamber |
Citations (5)
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| CN101275750A (en) * | 2008-04-25 | 2008-10-01 | 北京航空航天大学 | Radial swirler turning zone direct injection premixing and prevapourising low pollution burning chamber |
| WO2011040892A1 (en) * | 2009-10-01 | 2011-04-07 | Albayrak, Muzaffer | Combustion chamber of an internal combustion diesel engine |
| CN102538010A (en) * | 2012-02-12 | 2012-07-04 | 北京航空航天大学 | Afterburner integrated with stabilizer and worm wheel rear rectification support plate |
| CN103196155A (en) * | 2012-01-04 | 2013-07-10 | 通用电气公司 | System comprising fuel nozzles for injecting fuel in a gas turbine combustor |
| CN106678873A (en) * | 2016-11-16 | 2017-05-17 | 西北工业大学 | Integrated afterburner of supporting plate tail dual oil channels |
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2018
- 2018-03-16 CN CN201810219294.5A patent/CN108870441B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101275750A (en) * | 2008-04-25 | 2008-10-01 | 北京航空航天大学 | Radial swirler turning zone direct injection premixing and prevapourising low pollution burning chamber |
| WO2011040892A1 (en) * | 2009-10-01 | 2011-04-07 | Albayrak, Muzaffer | Combustion chamber of an internal combustion diesel engine |
| CN103196155A (en) * | 2012-01-04 | 2013-07-10 | 通用电气公司 | System comprising fuel nozzles for injecting fuel in a gas turbine combustor |
| CN102538010A (en) * | 2012-02-12 | 2012-07-04 | 北京航空航天大学 | Afterburner integrated with stabilizer and worm wheel rear rectification support plate |
| CN106678873A (en) * | 2016-11-16 | 2017-05-17 | 西北工业大学 | Integrated afterburner of supporting plate tail dual oil channels |
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