CN111306577B - Direct-injection fan-shaped nozzle applied to afterburner concave cavity structure - Google Patents
Direct-injection fan-shaped nozzle applied to afterburner concave cavity structure Download PDFInfo
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- CN111306577B CN111306577B CN202010106368.1A CN202010106368A CN111306577B CN 111306577 B CN111306577 B CN 111306577B CN 202010106368 A CN202010106368 A CN 202010106368A CN 111306577 B CN111306577 B CN 111306577B
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- 238000002347 injection Methods 0.000 title claims abstract description 84
- 239000007924 injection Substances 0.000 title claims abstract description 84
- 239000007921 spray Substances 0.000 claims abstract description 100
- 239000003921 oil Substances 0.000 claims abstract description 78
- 239000003595 mist Substances 0.000 claims abstract description 38
- 238000002485 combustion reaction Methods 0.000 claims abstract description 23
- 238000000889 atomisation Methods 0.000 claims abstract description 17
- 239000000295 fuel oil Substances 0.000 claims abstract description 15
- 239000000446 fuel Substances 0.000 claims description 32
- 238000009792 diffusion process Methods 0.000 claims description 6
- 239000003381 stabilizer Substances 0.000 claims description 4
- KWIUHFFTVRNATP-UHFFFAOYSA-N glycine betaine Chemical compound C[N+](C)(C)CC([O-])=O KWIUHFFTVRNATP-UHFFFAOYSA-N 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 9
- 230000008878 coupling Effects 0.000 abstract description 5
- 238000010168 coupling process Methods 0.000 abstract description 5
- 238000005859 coupling reaction Methods 0.000 abstract description 5
- 230000002708 enhancing effect Effects 0.000 abstract description 2
- 230000000087 stabilizing effect Effects 0.000 abstract description 2
- 238000012545 processing Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 241000282461 Canis lupus Species 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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Classifications
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention discloses a direct-injection fan-shaped nozzle applied to a cavity structure of an afterburner, relates to a direct-injection fan-shaped nozzle which is arranged in a cavity of an afterburner and used for enhancing the flame stabilizing performance and the flame coupling performance, and belongs to the field of aircraft engines. The bottom end of each oil spray rod is provided with a plurality of direct injection type spray holes in a certain arrangement shape, fuel oil is sprayed to the concave cavity structure in the afterburner, the shape of each spray hole enables the fuel oil to be sprayed and atomized to be in a fan-shaped oil mist ring surface shape, the fan-shaped oil mist surfaces of two adjacent oil spray rods are crossed, and an oil mist ring concentric with the engine case is formed in the concave cavity structure, so that the fuel oil atomization effect is enhanced, the circumferential flame connection performance is enhanced, and the combustion efficiency is improved.
Description
Technical Field
The invention belongs to the field of fuel atomization of aircraft engines, and relates to a direct-injection fan-shaped nozzle which is simple in structure, convenient to process, installed in a cavity of an afterburner and capable of enhancing the flame stabilizing and coupling capabilities, in particular to a direct-injection fan-shaped nozzle applied to the cavity structure of the afterburner.
Background
The invention relates to a nozzle structure, which is an atomization structure for converting certain liquid into fog drops. The atomization mechanism can be divided into pressure atomization and air atomization nozzles; the spray type may be divided into a direct spray type, a conical spray type, and a fan spray type. In the field of aero-engines, in order to organize the efficient combustion of aviation kerosene in a small space and a short time, a centrifugal nozzle (belonging to a pressure atomizing nozzle) is usually coupled with an air swirler, a fuel-air mixed gas is formed in a main combustion area of a combustion chamber for combustion, while a direct injection type nozzle is generally adopted in an afterburner of a traditional aero-engine, and the nozzles have the main defects of concentrated fuel concentration distribution, small contact area with air, poor combustion efficiency, high oil consumption and the like.
The fan-shaped nozzle is widely studied in the afterburner field in recent years due to the characteristics of stable operation, uniform concentration of formed oil mist field, wide oil drop space distribution and the like, and the research results show that the nozzle is suitable for the application of the patent application in the filed of afterburners (patent application No.: although two fan-shaped nozzles developed in CN201810219294.5 and CN201810219559.1] can obtain fan-shaped oil mist distribution, the structure is relatively complex, in order to obtain the required atomization effect, the first planar fan-shaped nozzle needs to process a V-shaped side nozzle, and the second circular fan-shaped nozzle needs to process a direct injection type spray hole 16 and two circular fan-shaped jet flow surfaces, which increases the difficulty in the processing process and hardly ensures the processing precision, and due to the viscous action of the solid wall on the fuel, the outlet fuel accumulates and drips in the actual work, thereby affecting the downstream fuel atomization effect.
Disclosure of Invention
The invention provides a novel direct-injection fan-shaped nozzle applied to a cavity structure of an afterburner, aiming at the defects of a direct-injection nozzle and a fan-shaped nozzle in an afterburner in the prior art, and combining the advantages of the atomization effect of the fan-shaped nozzle and the simplicity in processing of the direct-injection nozzle.
The invention is realized by the following steps:
a direct injection fan-shaped nozzle applied to a cavity structure of an afterburner is characterized in that the afterburner sequentially comprises a fan, a gas compressor, a combustion chamber and a turbine along the direction of the central axis of a gas turbine; the turbine is a afterburning chamber, a boosting inner cone is arranged in the afterburning chamber in a measuring way, the boosting inner cone is reduced along a downstream direction to form a boosting inner cone gradually-expanded ring surface, a plurality of support plates are arranged between the boosting inner cone gradually-expanded ring surface and the side wall of the afterburning chamber, and the root parts of the support plates are positioned at the initial position of the boosting inner cone gradually-expanded ring surface and are uniformly arranged in the circumferential direction; the support plate can fix the stressing inner cone.
The support plate internally mounted have oil spray pole, should spout oil spray pole side go out oil position and offer a plurality of direct injection formula orifices. The bottom end of the fuel injection rod is provided with the plurality of direct injection type spray holes according to the specific spatial position, and the fuel originally sprayed from one spray hole is sprayed out from the plurality of spray holes, so that the atomization effect of the nozzle is greatly improved, the particle size of the atomized fuel is reduced, and the combustion efficiency is improved.
The direct injection type spray holes are distributed in an arc shape on the surface of the oil spray rod, and the central axis direction of the direct injection type spray holes is mutually vertical to and intersected with the central axis direction of the oil spray rod but not intersected at one point; the oil mist of two adjacent direct injection holes are mutually crossed, a plurality of strands of fuel oil sprayed by the direct injection holes form fan-shaped oil mist arc surfaces, and the oil mist arc surface formed by all the fan-shaped oil mist arc surfaces is an arc surface concentric with the case. The direct injection type fan-shaped nozzle enables fuel oil to be injected into the afterburner in the shape of a fan-shaped ring surface, combustion performances such as combustion stability, ignition success rate and combustion efficiency are greatly improved compared with those of the traditional afterburner, oil mist fan-shaped surfaces of adjacent direct injection type fan-shaped nozzles are mutually intersected, and circumferential flame coupling performance of the afterburner is greatly improved.
The direct injection type fan-shaped nozzle is directly provided with the direct injection type spray holes at the bottom end of the oil spray rod, the central axes of all the spray holes are perpendicular to the central axis of the oil spray rod but not in the same plane, the whole spray hole is radial from the center of the shape of a wolf tooth rod to the periphery, fuel oil is sprayed into the concave cavity in a fan-shaped mode, atomized fuel oil between adjacent direct injection type fan-shaped nozzles is mutually crossed, and the circumferential flame connection performance of the afterburner is enhanced.
Furthermore, the central axes of the spray holes on the spray rod are intersected with the central axis of the spray rod and are radial from the center to the periphery, so that a fan-shaped oil mist surface can be realized, the number of the spray holes is 2-12, the included angle of the central axis projection of two adjacent direct-injection spray holes on the plane perpendicular to the central axis of the spray rod is 5-60 degrees, different oil mist fan-shaped angles can be obtained by processing different spray hole numbers and adjacent spray hole included angles, and the formed oil mist fan-shaped angle is defined as:
in which theta is the oil mist fan angle, beta1Is the central axis of the first spray hole and the central axis of the spray rodThe included angle between the component plane and the plane formed by the central axis of the second spray hole and the central axis of the oil spray rod is analogized by betaiNot necessarily the same. n is the number of orifices. The jet holes formed in the surface of the fuel injection rod have certain radian, so that fuel oil is sprayed out from the jet holes to form curved oil mist, and the fan-shaped oil mist at a certain position downstream from the fuel injection rod is mutually converged to form an oil mist ring concentric with the central axis of the afterburner. In addition, the direct injection type nozzle is composed of a plurality of direct injection holes, the hole opening direction of the injection holes is perpendicular to the side surface of the oil spray rod, and the processing difficulty is greatly reduced compared with the existing fan-shaped nozzle.
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 support plates which are uniformly arranged in the circumferential direction and the stress application inner cone gradually-expanding ring surface form a concave cavity structure.
Furthermore, an igniter and a flame stabilizer are also arranged in the support plate.
Furthermore, the oil spray rod is connected with an oil circuit inlet, the bottom end of the oil spray rod is provided with a fuel outlet, the direct injection type spray hole formed in the bottom end is exposed in the support plate and the stress application inner cone gradually-expanding ring surface to form a concave cavity structure, the concave cavity structure is filled with fuel when the direct injection type spray hole works, and an igniter arranged on the downstream of the oil spray rod is positioned in a secondary fuel atomization area.
The beneficial effects of the invention and the prior art are as follows:
1) the direct injection type fan-shaped nozzle is applied to an afterburner with a concave cavity structure, the direct injection type nozzle is provided with a plurality of direct injection type spray holes 16 at the bottom end of a fuel injection rod, fuel originally sprayed from one spray hole is sprayed out through a plurality of spray holes, the atomization characteristic of the nozzle is greatly improved, the particle size of the atomized fuel is small, the combustion stability, the ignition success rate, the combustion efficiency and other combustion performances of the atomized fuel are greatly improved compared with those of the traditional afterburner, and the afterburner can burn more fully.
2) The sprayed fuel surface is a fan-shaped curved surface, the fuel sprayed by adjacent fuel spray bars at a certain distance from the fuel spray bars can be mutually intersected, and the circumferential cross-flame performance of an afterburner equipped with the nozzle is greatly improved compared with that of an active single-point spraying direct injection type nozzle.
3) Aiming at the problems of high processing difficulty and difficulty in control of processing precision of the conventional afterburner fan-shaped nozzle patent technology, the direct-injection fan-shaped nozzle is directly provided with the spray hole at the bottom end of the oil spray rod, the hole opening direction is vertical to the side surface of the oil spray rod, the spray hole is radial from the center to the periphery, the processing is convenient, and the processing precision is easy to control; because the bottom end of the fuel injection rod is provided with the plurality of fan-shaped curved surface spray holes, fuel is sprayed in a multi-strand mode, and in order to guarantee the oil-gas ratio, the diameter of each spray hole is relatively small, so that the nozzle is good in atomization effect, easy to ignite and capable of improving combustion efficiency.
4) The fan-shaped angle of the fan-shaped oil mist curved surface of the nozzle is determined by the angle of the adjacent spray holes and the quantity of the spray holes, compared with the existing fan-shaped nozzle, the fuel oil in the range of the fan-shaped curved surface of the oil mist is uniformly distributed, the expansion angle of the nozzle is easy to control, and the direct injection type fan-shaped nozzle with different fan-shaped angles and different types can be conveniently changed and processed according to the matched afterburner; in addition, the aperture of the spray hole is small, the fuel flow sprayed out from one spray hole is sprayed out by a plurality of holes, the fuel atomization quality is improved, and the combustion efficiency of the afterburner is greatly improved; the spatial positions of the spray holes are arranged according to a certain arc curved surface, the nozzles are circumferentially and completely arranged in the afterburner, the annular surfaces of the fan-shaped oil mist sprayed by the nozzles are mutually crossed and contacted to form an oil mist annular surface concentric with the afterburner casing, and the circumferential flame coupling performance and the circumferential temperature distribution uniformity of the afterburner can be improved.
5) The bottom end spray holes of the direct injection type nozzle are not in the same plane but are arc surfaces, the central axes of all the spray holes are perpendicular to the central axis of the fuel injection rod, the whole fuel injection nozzle is shaped like a wolf tooth rod, the spray holes in the surface of the fuel injection rod have certain radian, so that fuel oil forms an oil mist ring surface concentric with the casing at a certain downstream position, and the circumferential temperature uniformity of the afterburner is greatly improved due to the atomization effect.
Drawings
FIG. 1 is a block diagram of a turbofan aircraft engine employing a straight fan nozzle and afterburner with a bowl configuration in accordance with the present invention;
FIG. 2 is a partially exploded view of a support plate and bowl structure for an afterburner employing direct injection fan nozzles and a bowl structure of the present invention;
FIG. 3 is a schematic view of a spray bar of a fan nozzle of the present invention employing direct spray orifices;
FIG. 4 is a schematic view of the nozzle space of the direct fan nozzle of the present invention;
FIG. 5 is a schematic view of the injection of the direct injection fan nozzle of the present invention in an afterburner;
the fuel injection device comprises a fan 1, a compressor 2, a combustion chamber 3, a turbine 4, a blender 5, a diffusion section 6, a support plate 7, an internal stressing cone 8, a cavity structure 9, a gradually expanding ring surface of the internal stressing cone 10, an igniter 11, a flame stabilizer 12, a cavity base 13, an oil injection rod 14, an afterburner 15, a fan-shaped nozzle 16, a fan-shaped oil mist arc surface 17, an air incoming flow direction 100, a gas turbine central axis 500, a straight-type spray hole central axis direction 600 and an oil injection rod central axis direction 700.
Detailed Description
In order to make the objects and effects of the present invention more clear, the present invention will be described in further detail below with reference to the accompanying drawings. It should be noted that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring now to FIG. 1, there is shown a block diagram of a turbofan aircraft engine employing a straight fan nozzle and a re-entrant afterburner configuration in accordance with the present invention. A fan 1 and a compressor 2 are sequentially arranged along the air inflow direction 100, namely the central axis 500 of the gas turbine, and air flows into a combustion chamber 3 after passing through the compressor; a turbine 4 behind the combustion chamber is connected with a compressor, a blender 5 is arranged between the turbine 4 and the side wall of an afterburner 15, and a diffusion section 6 is formed between the blender 5 and a support plate 7.
The structures behind the turbine 4 belong to afterburner parts and comprise a support plate 7 and an afterburner cone 8; the support plate is connected with the stressing inner cone 7 and the casing and is used for fixedly supporting the stressing inner cone 7; the stressing inner cone 8 tapers in the downstream direction to form a stressing inner cone diverging annulus 10.
As shown in fig. 2, the inside of the support plate 7 not only functions as a support for the inner cone 7, but also functions as a flame stabilizer 12 of the afterburner at the tail part; meanwhile, an igniter 11 and an oil spray rod 14 are fixedly arranged in the support plate 7, and a direct-injection fan-shaped nozzle 16 is arranged on the side wall surface of the radial bottom end of the oil spray rod 14; the direct-injection fan-shaped nozzle is characterized in that cylindrical direct-injection spray holes 16 with specific diameters, injection directions and N numbers are formed in the bottom end of an oil injection rod, the direct-injection spray holes 16 are connected with the bottom end of an oil injection rod 14, the central axis direction 600 of each direct-injection spray hole is mutually perpendicular to the central axis 700 of the oil injection rod and does not intersect at one point, the direct-injection fan-shaped nozzle is similar to a shape that a wolf tooth rod emits from the center to the periphery, the direction of fuel oil injected from the spray holes is the same as the vector direction of the central axis of the spray holes, as shown in figure 4, the purpose is to obtain the expanded oil mist space distribution in the shape of a fan-shaped oil mist arc surface 17 with a certain fan-shaped angle, and the expansion angle is determined according to the included angle of two adjacent spray holes and the total quantity of the spray holes, namely:
In the above formula, theta is the oil mist fan angle, beta1The included angle between the plane formed by the central axis of the first spray hole and the central axis of the spray rod and the plane formed by the central axis of the second spray hole and the central axis of the spray rod is as follows, betaiN is the number of orifices, not necessarily the same. It should be noted that the physical radian of the spray hole on the surface of the spray rod and the radian of the oil mist arc surface after the single fan-shaped nozzle is atomized are not the same.
The hole opening direction of the spray holes of the direct injection type fan-shaped nozzle is not only required, but also the hole opening position is required, all the spray holes are not positioned on a plane but have a certain radian, the appearance shape is shown in figure 3, the aim is to enable atomized fuel oil to present a fan-shaped cambered surface rather than a plane, when a plurality of direct injection type fan-shaped nozzles are arranged in the circumferential direction of the afterburner, oil mist can be mutually staggered at a certain position away from an oil injection rod to form annular oil mist space distribution, the injection effect diagram is shown in figure 5, and the design can enhance the circumferential flame coupling performance of the afterburner and enable circumferential temperature distribution of the afterburner to be more uniform.
The working process of the invention is as follows:
in the invention, the air flow mode is almost the same as that of a common engine, and after passing through the fan 1, the air is divided into two parts: one part of the gas enters an outer culvert flow channel, the other part of the gas enters a combustion chamber 3 after passing through a high-pressure compressor 2, the combusted gas pushes a turbine 4 to do work, outer culvert gas flow is mixed with the gas which just passes through the turbine 4 to do work after passing through a blender 5, and the gas flows to an oil spray rod 14 after passing through a diffusion section 6 of an afterburner. The fuel oil is sprayed through the direct injection spray holes to form primary atomization in the concave cavity, the fuel oil is further broken into fine oil mist drops under the combined action of inertia force and air power, the fan-shaped oil mist ring surfaces generated by the nozzles and the adjacent nozzles form fan-shaped oil mist ring surfaces to be mutually intersected in the process of further forward movement, high-temperature mixed gas formed by mixing of the mixer enters the concave cavity structure 9, and the mixed gas flow forms backflow in the concave cavity structure 9. After the ignition of the igniter 11, flame is stabilized in the concave cavity in a diffusion combustion mode, stable and reliable ignition and flame linkage of the afterburner under various working conditions are realized, and stable combustion in the afterburner is guaranteed.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the present invention, and these modifications should also be construed as the protection scope of the present invention.
Claims (5)
1. A direct injection fan-shaped nozzle applied to a cavity structure of an afterburner is characterized in that the afterburner sequentially comprises a fan (1), a compressor (2), a combustion chamber (3) and a turbine (4) along the direction of a central axis (500) of a gas turbine; the back side of the turbine (4) is provided with a afterburning chamber (15), the inner side of the afterburning chamber (15) is provided with an afterburning inner cone (8), the afterburning inner cone (8) is gradually reduced along the downstream direction to form an afterburning inner cone gradually-expanded ring surface (10), a plurality of support plates (7) are arranged between the afterburning inner cone gradually-expanded ring surface (10) and the side wall of the afterburning chamber (15), and the roots of the support plates (7) are positioned at the initial position of the afterburning inner cone gradually-expanded ring surface (10) and are uniformly arranged in the circumferential direction;
an oil spray rod (14) is arranged in the support plate (7), a plurality of direct injection type spray holes (16) are formed in the oil outlet position of the side surface of the oil spray rod (14), the direct injection type spray holes (16) are distributed in an arc shape on the surface of the oil spray rod (14), and the central axis direction (600) of the direct injection type spray holes is mutually perpendicular to the central axis direction (700) of the oil spray rod and is intersected with one point;
The direct-injection fan-shaped nozzle is directly provided with an orifice at the bottom end of the oil spray rod, and the orifice direction is vertical to the side surface of the oil spray rod and is radial from the center to the periphery;
the oil mist of two adjacent direct injection holes (16) are mutually crossed, a fan-shaped oil mist arc surface (17) is formed by the fuel oil sprayed from a plurality of direct injection holes (16), and the oil mist arc surface formed by all the fan-shaped oil mist arc surfaces (17) is an arc surface concentric with the case; the number of the direct injection type spray holes (16) is 2-12, the included angle of the projection of the central axis of two adjacent direct injection type spray holes (16) on the central axis plane of the vertical oil spray rod is 5-60 degrees, and the formed oil mist fan-shaped angle is defined as:
in which theta is the oil mist fan angle, beta1The included angle between the plane formed by the central axis of the first spray hole and the central axis of the spray rod and the plane formed by the central axis of the second spray hole and the central axis of the spray rod is as follows, betaiN is the number of orifices, not necessarily the same.
2. The direct injection fan nozzle for afterburner bowl structures as claimed in claim 1, wherein a blender (5) is arranged between the turbine (4) and the afterburner (15) side wall; and a diffusion section (6) is formed between the blender (5) and the support plate (7).
3. The direct injection fan nozzle for afterburner bowl structures of claim 1 wherein the bowl structure (9) is formed by circumferentially aligned struts (7) and an afterburner cone diverging annular surface (10).
4. The direct injection fan nozzle for afterburner bowl structures as claimed in claim 1, wherein said brackets (7) further comprise igniters (11) and flame stabilizers (12).
5. The direct injection fan-shaped nozzle applied to the afterburner concave cavity structure is characterized in that an oil injection rod (14) is connected with an oil path inlet, the bottom end of the oil injection rod (14) is a fuel outlet, a direct injection spray hole (16) formed in the bottom end is exposed in a concave cavity structure (9) formed by a support plate (7) and an afterburning inner cone divergent ring surface (10), the concave cavity structure (9) is filled with fuel when the direct injection spray hole (16) works, and an igniter (11) arranged at the downstream of the oil injection rod is positioned in a secondary fuel atomization area.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010106368.1A CN111306577B (en) | 2020-02-21 | 2020-02-21 | Direct-injection fan-shaped nozzle applied to afterburner concave cavity structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010106368.1A CN111306577B (en) | 2020-02-21 | 2020-02-21 | Direct-injection fan-shaped nozzle applied to afterburner concave cavity structure |
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| CN111306577B true CN111306577B (en) | 2021-10-26 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112228908A (en) * | 2020-09-18 | 2021-01-15 | 西北工业大学 | Controllable flow type centrifugal nozzle for strengthening atomization |
| CN113187637B (en) * | 2021-04-06 | 2022-09-23 | 大连理工大学 | Composite hole nozzle with intersection structure |
| CN113190932B (en) * | 2021-05-31 | 2022-04-19 | 中国人民解放军国防科技大学 | Method for improving combustion efficiency of scramjet engine based on pneumatic virtual concave cavity |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6125627A (en) * | 1998-08-11 | 2000-10-03 | Allison Advanced Development Company | Method and apparatus for spraying fuel within a gas turbine engine |
| CN105674332A (en) * | 2016-01-19 | 2016-06-15 | 西北工业大学 | Pre-evaporation type integrated afterburner |
| CN108844094A (en) * | 2018-03-16 | 2018-11-20 | 南京航空航天大学 | A kind of after-burner using flat fan spray nozzle fuel feeding |
| CN108870441A (en) * | 2018-03-16 | 2018-11-23 | 南京航空航天大学 | It is a kind of to use arc-shaped fan nozzle and curved cavity after-burner |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6971239B2 (en) * | 2003-05-13 | 2005-12-06 | United Technologies Corporation | Augmentor pilot nozzle |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6125627A (en) * | 1998-08-11 | 2000-10-03 | Allison Advanced Development Company | Method and apparatus for spraying fuel within a gas turbine engine |
| CN105674332A (en) * | 2016-01-19 | 2016-06-15 | 西北工业大学 | Pre-evaporation type integrated afterburner |
| CN108844094A (en) * | 2018-03-16 | 2018-11-20 | 南京航空航天大学 | A kind of after-burner using flat fan spray nozzle fuel feeding |
| CN108870441A (en) * | 2018-03-16 | 2018-11-23 | 南京航空航天大学 | It is a kind of to use arc-shaped fan nozzle and curved cavity after-burner |
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