CN116817315B - Concave cavity flame stabilizer with front concave cavity slope heightening fuel jet - Google Patents
Concave cavity flame stabilizer with front concave cavity slope heightening fuel jet Download PDFInfo
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- CN116817315B CN116817315B CN202310276699.3A CN202310276699A CN116817315B CN 116817315 B CN116817315 B CN 116817315B CN 202310276699 A CN202310276699 A CN 202310276699A CN 116817315 B CN116817315 B CN 116817315B
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Abstract
本发明涉及一种凹腔前斜坡垫高燃料射流的凹腔火焰稳定器，凹腔火焰稳定器由后向台阶和前向台阶组成，在凹腔火焰稳定器前缘进行斜切，并在斜切面上对应每对燃料射流孔布置1对斜坡。本发明的优点和取得的有益结果为：超燃冲压燃烧室采用该凹腔前斜坡垫高燃料射流的凹腔火焰稳定器，能增加燃料穿透深度，促进燃料‑空气混合，提高燃烧效率。
The present invention relates to a concave cavity flame stabilizer with a front slope of the concave cavity to raise the fuel jet, the concave cavity flame stabilizer is composed of a rearward step and a forward step, the front edge of the concave cavity flame stabilizer is beveled, and a pair of slopes are arranged on the beveled surface corresponding to each pair of fuel jet holes. The advantages and beneficial results of the present invention are: the concave cavity flame stabilizer with a front slope of the concave cavity to raise the fuel jet can increase the fuel penetration depth, promote fuel-air mixing, and improve combustion efficiency.
Description
Technical Field
The invention relates to a concave cavity flame stabilizer with a concave cavity front slope heightening fuel jet, which can be used for a combustion chamber of a scramjet engine and belongs to the technical field of aviation.
Background
The scramjet engine is an ideal power device for hypersonic aircrafts. The air flow in the combustion chamber of the scramjet engine flows at supersonic speed, and the residence time of fuel in the combustion chamber is only in the order of milliseconds. By establishing a recirculation zone in the combustion chamber using a flame stabilizing device, the flow rate in the recirculation zone is reduced and the residence time of the fuel-air mixture in the combustion chamber is increased. So that the flame can reside in the recirculation zone as a source of fire to maintain the sustained presence and propagation of the flame throughout the combustion chamber.
As the most commonly used flame stabilizing devices at present, the performance of recessed flame holders has been widely accepted, being structurally composed of a forward step and a rearward step. In the combustion chamber, a recirculation zone is formed within the cavity flame holder as the high velocity air flow passes through the cavity flame holder, and a free shear layer is formed between the main flow and the recirculation zone due to the lower flow rate within the cavity flame holder. The air flow structure in the recessed flame holder also induces acoustic perturbations that act in concert with the large scale structure of the falling-off of the recessed flame holder trailing edge to enhance fuel-air mixing. Although the cavity flame stabilizer does not have a physically intrusive structure, it is prone to fuel accumulation in the wall shear layer, resulting in greater wall heat flow.
Disclosure of Invention
The invention aims to provide a concave cavity flame stabilizer with a concave cavity front slope heightening fuel jet, wherein the front edge of the concave cavity is beveled, and a slope is arranged on a bevel surface so as to improve the penetration depth of fuel, shorten the complete combustion distance of a combustion chamber, enlarge the downstream combustion area of the combustion chamber, obviously increase the combustion efficiency and reduce the total pressure loss.
The invention is realized by the following technical scheme.
A recessed flame stabilizer for raising fuel jet by a recessed front slope is characterized in that the front edge of the recessed flame stabilizer is beveled, and 1 pair of slopes are arranged corresponding to each pair of fuel nozzles on the bevel.
Further, the cavity flame stabilizer is connected with the lower wall surface of the stamping combustion chamber at the front edge and the rear edge, the width is determined by a specific engine, the cavity flame stabilizer mainly comprises a front step and a rear step, the cavity flame stabilizer can be divided into a front edge, a front wall, a bottom wall, a rear edge and fuel nozzles, the front wall is perpendicular to the bottom wall, the front wall is 35-65 mm high, the bottom wall is 140-180 mm long, the rear wall is 20-50 mm high, the included angle between the rear wall and the bottom wall is 30-70 degrees, the fuel nozzles are arranged at the upstream of the front edge, the diameter of each fuel nozzle is 2-5 mm, the distance between each fuel nozzle and the front edge is 5-50 mm, and the distance between every two adjacent fuel nozzles is 10-40 mm.
Further, the front edge of the concave flame stabilizer is beveled, the distance between the beveled starting position and the front edge is 10-50 mm, and the beveled angle is 10-30 degrees.
Further, the slope is a trapezoid wedge block, the slope front edge coincides with the inclined cutting starting position, the slope front edge is 15-28 mm wide, the slope tail plane coincides with the plane where the front wall is located, the slope tail is 4-15 mm wide, the slope tail is 10-25 mm high, the included angle between each pair of slope inner sides and the slope front edge is 75-85 degrees, the included angle between each pair of slope outer sides and the slope front edge is 65-80 degrees, and the distance between each pair of slope front edges is 0-10 mm.
Compared with the prior art, the invention has the advantages that:
First, the fuel penetration depth is increased. Firstly, the slope plays a role in heightening the fuel nozzle, secondly, the front edge of the concave cavity is beveled, so that the scale of trapped vortex in the concave cavity is reduced, the entrainment induction effect of the trapped vortex on the fuel jet is weakened, the penetration depth of the fuel jet is increased, and the penetration depth of the fuel is increased by superposition of the two.
Second, fuel-air mixing is promoted. The penetration depth of the fuel is increased, so that the fuel jet is positioned in the middle of the combustion chamber and is far away from the wall surface, the fuel is not rolled into the concave cavity to form aggregation, the fuel jet can be mixed with enough air from the periphery, and the flow direction vortex generated after the slope is beneficial to strengthening the fuel-air mixing, so that the front edge of the concave cavity is beveled and the slope is arranged to heighten the fuel nozzle, and the fuel-air mixing can be effectively promoted.
Third, combustion efficiency is improved. The front edge of the concave cavity is beveled and is provided with a slope heightening fuel nozzle, so that the penetration depth of fuel is increased, the fuel-air mixing is promoted, and the combustion efficiency of the scramjet combustion chamber can be remarkably improved.
Drawings
Fig. 1 is an isometric view of a conventional re-entrant flame holder.
FIG. 2 is an isometric view of a bowl flame holder of the present invention with a pre-bowl ramp up fuel jet.
FIG. 3 is a side view of a bowl flame holder of the present invention with a pre-bowl ramp up fuel jet.
FIG. 4 is a top view of a bowl flame holder of the present invention with a pre-bowl ramp up fuel jet.
FIG. 5 is a front view of a bowl flame holder of the present invention with a bowl front ramp up fuel jet.
FIG. 6 is a rear view of a bowl flame holder of the present invention with a front bowl ramp up fuel jet.
FIG. 7 is a cross-sectional C 2H4 component distribution of a combustion chamber of a re-entrant flame holder with re-entrant front ramp-up fuel jet of the present invention.
FIG. 8 is a temperature profile of a combustion chamber of a re-entrant flame holder with a re-entrant front ramp up fuel jet of the present invention.
FIG. 9 is a transverse cross-sectional C 2H4 component distribution of a combustion chamber with a conventional re-entrant flame holder in accordance with the present invention.
FIG. 10 is a temperature distribution of a transverse cross-section of a combustion chamber with a conventional re-entrant flame holder in accordance with the invention.
FIG. 11 is a flow chart of a portion of a combustion chamber of a re-entrant flame holder with re-entrant front ramp up fuel jet of the present invention.
In the drawings, 1 is a front edge, 2 is a front wall, 3 is a bottom wall, 4 is a rear wall, 5 is a rear edge, 6 is a slope, 7 is a fuel nozzle, and 8 is a lower wall surface of the stamping combustion chamber.
Wherein L1 is the bottom wall length, L2 is the cavity flame stabilizer width, L3 is the distance between the fuel nozzle and the front edge, L4 is the distance between adjacent fuel nozzles, H1 is the front wall height, H2 is the back wall height, H3 is the slope tail height, alpha 1 is the included angle between the back wall and the bottom wall, alpha 2 is the inclined angle, alpha 3 is the included angle between the inner side surface of the slope and the slope front edge, alpha 4 is the included angle between the outer side surface of the slope and the slope front edge, D is the diameter of the fuel nozzle, S1 is the distance between the inclined starting position and the front edge, S2 is the slope front edge width, S3 is the slope tail width, and S4 is the distance between the slope and the front edge.
Detailed Description
The invention will be described in further detail with reference to fig. 1 to 6 and examples.
The front slope of the concave cavity is used for heightening the concave cavity flame stabilizer of the fuel jet, the front edge 1 of the concave cavity flame stabilizer is beveled, and 1 pair of slopes 6 are arranged corresponding to each pair of fuel nozzles 7 on the bevel.
As a further improvement of the embodiment of the invention, the cavity flame stabilizer is characterized in that the front edge 1 and the rear edge 5 are connected with the lower wall surface 8 of the stamping combustion chamber, the width L2 is determined by a specific engine, the embodiment is specifically 75mm, the cavity flame stabilizer mainly comprises a front step and a rear step, the cavity flame stabilizer can be subdivided into the front edge 1, the front wall 2, the bottom wall 3, the rear wall 4, the rear edge 5 and the fuel nozzle 7, the front wall 2 is perpendicular to the bottom wall 3, the height H1 of the front wall 2 is 35-65 mm, the embodiment is specifically 50.5mm, the length L1 of the bottom wall 3 is 140-180 mm, the embodiment is 163.2mm, the height H2 of the rear wall 4 is 20-50 mm, the embodiment is 34mm, the included angle alpha 1 between the rear wall 4 and the bottom wall 3 is 30-70 degrees, the embodiment is specifically 45 degrees, the diameter D of the fuel nozzle 7 is 2-5 mm, the embodiment is specifically 3.4mm, the distance L3 between the fuel nozzle 7 and the front edge 1 is 5-50 mm, the embodiment is specifically 10mm, the distance L3 between the fuel nozzle 7 and the front edge 1 is 40-50 mm, the embodiment is specifically 10mm, and the distance between the adjacent fuel nozzle 7 and the embodiment is 40mm is 10 mm.
As a further improvement of the embodiment of the invention, the front edge of the concave flame stabilizer is beveled, the distance S1 between the beveled initial position and the front edge 1 is 10-50 mm, the beveled angle alpha 2 is 10-30 degrees, and the beveled angle alpha 2 is 15 degrees.
As a further improvement of the embodiment of the invention, the slope 6 is a trapezoid wedge-shaped block, the front edge of the slope 6 coincides with the inclined cutting starting position, the front edge width S2 of the slope 6 is 15-28 mm, the embodiment is 17.5mm, the tail plane of the slope 6 coincides with the plane where the front wall 2 is, the tail width S3 of the slope 6 is 4-15 mm, the embodiment is 11.3mm, the tail height H3 of the slope 6 is 10-25mm, the embodiment is 18mm, 1 pair of slopes 6 are arranged corresponding to 1 pair of fuel nozzles 7, the included angle alpha 3 between the inner side surface of each pair of slopes 6 and the front edge of the slope 6 is 75-85 degrees, the embodiment is 80 degrees, the included angle alpha 4 between the outer side surface of each pair of slopes 6 and the front edge of the slope 6 is 65-80 degrees, the embodiment is 70 degrees, the front edge distance S4 of each pair of slopes 6 is 0-10 mm, and the embodiment is 4mm.
The above described embodiments are only preferred examples of the invention and are not exhaustive of the possible implementations of the invention. Any obvious modifications thereof, which do not depart from the spirit and scope of the present invention, should be deemed to be within the scope and meaning of the appended claims. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (1)
1. A recessed flame stabilizer for heightening fuel jet by a recessed front slope, characterized in that, the front edge (1) of the recessed flame stabilizer is beveled, and 1 pair of slopes (6) are arranged corresponding to each pair of fuel nozzles (7) on the beveled surface;
The width of the cavity flame stabilizer is determined by a specific engine, the cavity flame stabilizer comprises a front edge (1), a front wall (2), a bottom wall (3), a rear wall (4), a rear edge (5) and a fuel nozzle (7), wherein the front edge (1), the front wall (2) and the bottom wall (3) form a forward step, the bottom wall (3), the rear wall (4) and the rear edge (5) form a backward step, the front edge (1) and the rear edge (5) are connected with a lower wall surface (8) of a stamping combustion chamber, the front wall (2) is vertical to the bottom wall (3), the front wall (2) is 35-65 mm high, the bottom wall (3) is 140-180 mm long, the rear wall (4) is 20-50 mm high, an included angle of 30-70 degrees is formed between the rear wall (4) and the bottom wall (3), the fuel nozzle (7) is arranged at the upstream of the front edge (1), the diameter of the fuel nozzle (7) is 2-5 mm, the distance between the fuel nozzle (7) and the front edge (1) is 5-50 mm, and the distance between adjacent fuel nozzle (7) is 10-40 mm;
The front edge of the concave flame stabilizer is beveled, the distance between the beveled starting position and the front edge (1) is 10-50 mm, and the beveled angle is 10-30 degrees;
The slope (6) is a trapezoid wedge block, the front edge of the slope (6) coincides with the inclined cutting starting position, the front edge of the slope (6) is 15-28 mm wide, the plane of the tail of the slope (6) coincides with the plane of the front wall (2), the tail of the slope (6) is 4-15 mm wide, the tail of the slope (6) is 10-25 mm high, the included angle between the inner side surface of each pair of slopes (6) and the front edge of the slope (6) is 75-85 degrees, the included angle between the outer side surface of each pair of slopes (6) and the front edge of the slope (6) is 65-80 degrees, and the distance between the front edges of each pair of slopes (6) is 0-10 mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310276699.3A CN116817315B (en) | 2023-03-21 | 2023-03-21 | Concave cavity flame stabilizer with front concave cavity slope heightening fuel jet |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310276699.3A CN116817315B (en) | 2023-03-21 | 2023-03-21 | Concave cavity flame stabilizer with front concave cavity slope heightening fuel jet |
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| CN116817315A CN116817315A (en) | 2023-09-29 |
| CN116817315B true CN116817315B (en) | 2025-07-08 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116379477B (en) * | 2023-04-20 | 2024-08-27 | 中国人民解放军国防科技大学 | Slope concave cavity combustion chamber and scramjet engine |
| CN118734491B (en) * | 2024-07-19 | 2025-10-10 | 中国人民解放军国防科技大学 | Design method of large-scale cavity flame stabilizer considering scale effect |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101435586A (en) * | 2007-11-15 | 2009-05-20 | 周建兴 | Supersonic speed combustion chamber scheme of step / groove composite injection structure |
| CN104764045A (en) * | 2015-04-21 | 2015-07-08 | 中国人民解放军国防科学技术大学 | Supersonic combustion chamber cavity ignition device and scramjet engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP6788522B2 (en) * | 2017-02-24 | 2020-11-25 | 三菱重工業株式会社 | Scramjet engine |
| CN111649352B (en) * | 2020-06-02 | 2021-08-06 | 中国人民解放军国防科技大学 | A self-sustained fluid oscillator and a rocket-based combined cycle engine |
| CN112747335B (en) * | 2021-01-06 | 2022-05-13 | 中国人民解放军国防科技大学 | A lobe type backward stepped structure, a lobe type concave cavity device and a supplementary combustion chamber |
| CN113623686B (en) * | 2021-08-10 | 2022-07-29 | 中国人民解放军国防科技大学 | Sliding arc cascade discharge concave flame stabilization device for scramjet engine |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101435586A (en) * | 2007-11-15 | 2009-05-20 | 周建兴 | Supersonic speed combustion chamber scheme of step / groove composite injection structure |
| CN104764045A (en) * | 2015-04-21 | 2015-07-08 | 中国人民解放军国防科学技术大学 | Supersonic combustion chamber cavity ignition device and scramjet engine |
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